HOST payload for STS-95 being moved into SSPF

NASA Technical Reports Server (NTRS)

1998-01-01

The Hubble Space Telescope Orbiting Systems Test (HOST)is being raised to a workstand by technicians in the Space Shuttle Processing Facility. One of the payloads on the STS-95 mission, the HOST platform is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process.

HOST payload for STS-95 being moved into SSPF

NASA Technical Reports Server (NTRS)

1998-01-01

Workers watch as the Hubble Space Telescope Orbiting Systems Test (HOST)is lowered onto a workstand in the Space Shuttle Processing Facility. To the right can be seen the Rack Insertion Device and Leonardo, a Multi-Purpose Logistics Module. The HOST platform, one of the payloads on the STS-95 mission, is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process.

LWS/SET End-to-End Data System

NASA Technical Reports Server (NTRS)

Giffin, Geoff; Sherman, Barry; Colon, Gilberto (Technical Monitor)

2002-01-01

This paper describes the concept for the End-to-End Data System that will support NASA's Living With a Star Space Environment Testbed missions. NASA has initiated the Living With a Star (LWS) Program to develop a better scientific understanding to address the aspects of the connected Sun-Earth system that affect life and society. A principal goal of the program is to bridge the gap.between science, engineering, and user application communities. The Space Environment Testbed (SET) Project is one element of LWS. The Project will enable future science, operational, and commercial objectives in space and atmospheric environments by improving engineering approaches to the accommodation and/or mitigation of the effects of solar variability on technological systems. The End-to-end data system allows investigators to access the SET control center, command their experiments, and receive data from their experiments back at their home facility, using the Internet. The logical functioning of major components of the end-to-end data system are described, including the GSFC Payload Operations Control Center (POCC), SET Payloads, the GSFC SET Simulation Lab, SET Experiment PI Facilities, and Host Systems. Host Spacecraft Operations Control Centers (SOCC) and the Host Spacecraft are essential links in the end-to-end data system, but are not directly under the control of the SET Project. Formal interfaces will be established between these entities and elements of the SET Project. The paper describes data flow through the system, from PI facilities connecting to the SET operations center via the Internet, communications to SET carriers and experiments via host systems, to telemetry returns to investigators from their flight experiments. It also outlines the techniques that will be used to meet mission requirements, while holding development and operational costs to a minimum. Additional information is included in the original extended abstract.

Commercial Biomedical Experiments

NASA Technical Reports Server (NTRS)

2003-01-01

Experiments to seek solutions for a range of biomedical issues are at the heart of several investigations that will be hosted by the Commercial Instrumentation Technology Associates (ITA), Inc. Biomedical Experiments (CIBX-2) payload. CIBX-2 is unique, encompassing more than 20 separate experiments including cancer research, commercial experiments, and student hands-on experiments from 10 schools as part of ITA's ongoing University Among the Stars program. Valerie Cassanto of ITA checks the Canadian Protein Crystallization Experiment (CAPE) carried by STS-86 to Mir in 1997. The experiments are sponsored by NASA's Space Product Development Program (SPD).

Commercial Instrumentation Technology Associates, Biomedical Experiments

NASA Technical Reports Server (NTRS)

2003-01-01

Experiments to seek solutions for a range of biomedical issues are at the heart of several investigations that will be hosted by the Commercial Instrumentation Technology Associates (ITA), Inc. Biomedical Experiments (CIBX-2) payload. CIBX-2 is unique, encompassing more than 20 separate experiments including cancer research, commercial experiments, and student hands-on experiments from 10 schools as part of ITA's ongoing University Among the Stars program. A number of Liquids Mixing Apparatus (LMA) syringes like this one will be used in the experiments. The experiments are sponsored by NASA's Space Product Development Program (SPD).

Space Product Development (SPD)

NASA Image and Video Library

2003-01-12

Experiments to seek solutions for a range of biomedical issues are at the heart of several investigations that will be hosted by the Commercial Instrumentation Technology Associates (ITA), Inc. Biomedical Experiments (CIBX-2) payload. CIBX-2 is unique, encompassing more than 20 separate experiments including cancer research, commercial experiments, and student hands-on experiments from 10 schools as part of ITA's ongoing University Among the Stars program. Valerie Cassanto of ITA checks the Canadian Protein Crystallization Experiment (CAPE) carried by STS-86 to Mir in 1997. The experiments are sponsored by NASA's Space Product Development Program (SPD).

Host computer software specifications for a zero-g payload manhandling simulator

NASA Technical Reports Server (NTRS)

Wilson, S. W.

1986-01-01

The HP PASCAL source code was developed for the Mission Planning and Analysis Division (MPAD) of NASA/JSC, and takes the place of detailed flow charts defining the host computer software specifications for MANHANDLE, a digital/graphical simulator that can be used to analyze the dynamics of onorbit (zero-g) payload manhandling operations. Input and output data for representative test cases are contained.

STS-47 Payload Specialist Mohri adjusts life vest during Homestead training

NASA Technical Reports Server (NTRS)

1990-01-01

STS-47 Endeavour, Orbiter Vehicle (OV) 105, Payload Specialist Mamoru Mohri adjusts his life jacket with a training instructor's assistance as backup (alternate) payload specialist Takao Doi looks on. The STS-47 prime and alternate payload specialists are participating in a special water survival training course hosted by Homestead Air Force Base in Florida. Mohri and Doi represent the National Space Development Agency of Japan (NASDA).

Materials processing in space: Future technology trends

NASA Technical Reports Server (NTRS)

Barter, N. J.

1980-01-01

NASA's materials processing in space- (MPS) program involves both ground and space-based research and looks to frequent and cost effective access to the space environment for necessary progress. The first generation payloads for research are under active design and development. They will be hosted by the Space Shuttle/Spacelab on Earth orbital flights in the early 1980's. hese missions will focus on the acquisition of materials behavior research data, the potential enhancement of Earth based technology, and the implementation of space based processing for specialized, high value materials. Some materials to be studied in these payloads may provide future breakthroughs for stronger alloys, ultrapure glasses, superior electronic components, and new or better chemicals. An operational 25 kW power system is expected to be operational to support sustained, systematic space processing activity beyond shuttle capability for second generation payload systems for SPACELAB and free flyer missions to study solidification and crystal growth and to process metal/alloys, glasses/ceramics, and chemicals and biologicals.

Payload Crew Training Complex (PCTC) utilization and training plan

NASA Technical Reports Server (NTRS)

Self, M. R.

1980-01-01

The physical facilities that comprise the payload crew training complex (PCTC) are described including the host simulator; experiment simulators; Spacelab aft flight deck, experiment pallet, and experiment rack mockups; the simulation director's console; payload operations control center; classrooms; and supporting soft- and hardware. The parameters of a training philosophy for payload crew training at the PCTC are established. Finally the development of the training plan is addressed including discussions of preassessment, and evaluation options.

Astronaut William Gregory activates Liquids Mixing Apparatus

NASA Technical Reports Server (NTRS)

2003-01-01

Experiments to seek solutions for a range of biomedical issues are at the heart of several investigations that will be hosted by the Commercial Instrumentation Technology Associates (ITA), Inc. Biomedical Experiments (CIBX-2) payload. CIBX-2 is unique, encompassing more than 20 separate experiments including cancer research, commercial experiments, and student hands-on experiments from 10 schools as part of ITA's ongoing University Among the Stars program. Astronaut William G. Gregory activates Liquids Mixing Apparatus (LMA) vials during STS-67. Other LMAs hang at top on the face of the middeck locker array. The experiments are sponsored under NASA's Space Product Development Program (SPD).

Space Product Development (SPD)

NASA Image and Video Library

2003-01-12

Experiments to seek solutions for a range of biomedical issues are at the heart of several investigations that will be hosted by the Commercial Instrumentation Technology Associates (ITA), Inc. Biomedical Experiments (CIBX-2) payload. CIBX-2 is unique, encompassing more than 20 separate experiments including cancer research, commercial experiments, and student hands-on experiments from 10 schools as part of ITA's ongoing University Among the Stars program. Astronaut William G. Gregory activates Liquids Mixing Apparatus (LMA) vials during STS-67. Other LMAs hang at top on the face of the middeck locker array. The experiments are sponsored under NASA's Space Product Development Program (SPD).

KSC-98pc1139

NASA Image and Video Library

1998-09-23

KENNEDY SPACE CENTER, FLA. -- The Hubble Space Telescope Orbiting Systems Test (HOST), one of the payloads on the STS-95 mission, is placed inside its payload canister in the Space Station Processing Facility. The canister is 65 feet long, 18 feet wide and 18 feet, 7 inches high. The HOST platform is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry other payloads such as the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker (IEH-3), and the SPACEHAB single module with experiments on space flight and the aging process

KSC-98pc1138

NASA Image and Video Library

1998-09-23

KENNEDY SPACE CENTER, FLA. -- The Hubble Space Telescope Orbiting Systems Test (HOST), one of the payloads on the STS-95 mission, is suspended above its payload canister in the Space Station Processing Facility. The canister is 65 feet long, 18 feet wide and 18 feet, 7 inches high. The HOST platform is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry other payloads such as the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker (IEH-3), and the SPACEHAB single module with experiments on space flight and the aging process

KSC-98pc1136

NASA Image and Video Library

1998-09-23

KENNEDY SPACE CENTER, FLA. -- The Hubble Space Telescope Orbiting Systems Test Platform (HOST) is lifted off its work stand in the Space Station Processing Facility before moving it to its payload canister. One of the payloads on the STS-95 mission, the HOST platform is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry other payloads such as the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker (IEH-3), and the SPACEHAB single module with experiments on space flight and the aging process

Hosting the first EDRS payload

NASA Astrophysics Data System (ADS)

Poncet, D.; Glynn, S.; Heine, F.

2017-11-01

The European Data Relay System (EDRS) will provide optical and microwave data relay services between Low Earth Orbit (LEO) satellites at altitudes up to 2000 km and the ground through geostationary (GEO) satellite nodes. Currently, two such nodes have been procured as part of a Public Private Partnership (PPP) between Astrium (now Airbus Defence and Space) and ESA. The first node (EDRS-A) is a hosted payload embarked upon the Eutelsat 9B satellite and scheduled for launch in early 2015.

Strawman payload data for science and applications space platforms

NASA Technical Reports Server (NTRS)

1980-01-01

The need for a free flying science and applications space platform to host compatible long duration experiment groupings in Earth orbit is discussed. Experiment level information on strawman payload models is presented which serves to identify and quantify the requirements for the space platform system. A description data base on the strawman payload model is presented along with experiment level and group level summaries. Payloads identified in the strawman model include the disciplines of resources observations and environmental observations.

Houston, We Have a Podcast. Episode 41 The Space Launch System Part.1

NASA Image and Video Library

2018-04-20

Production Transcript for Ep41 The Space Launch System Part.1.mp3 Gary Jordan (Host): Houston, we have a podcast. Welcome to the official podcast of the NASA Johnson Space Center Episode 41, the Space Launch System part one. I'm Gary Jordan, and I'll be your host today. On this podcast, we bring in the experts, NASA scientists, engineers, astronauts, all to let you know the coolest information right here at NASA. So, today, we're talking about the most powerful rocket since the Saturn V moon rocket. It's called NASA's Space Launch System. So, we've got two guests from Marshall Space Flight Center in Huntsville, Alabama here with us today to tell us a little bit about the rocket, the payloads it will carry. Don't worry. We'll define what a payload is. And then, where it's going to go. Spoiler alert, it will bring people big stuff and little stuff all farther than we've ever gone before. Wait. Why did I do that? That totally ruins the, oh wait. Never mind. It doesn't ruin anything. This is a really good topic, jam packed with information. So much information that we're going to do this in two parts. This is part one. So, with us today are David Smith and Paul Bookout. David is the Vice President for Advanced Programs at Victory Solutions in Huntsville, Alabama. He has a long career in aerospace engineering and is a Subject Matter Expert on rocket architecture and how payloads fit inside the rocket. He wrote the SLS mission planner's guide which gives payload developers a general idea of the capabilities of the rocket and some technical specifications, so they can determine how their payloads might fit inside of it. He looks after some of the big payloads. Our other guest is Dr. Paul Bookout, EM-1 Secondary Payloads Integration Manager who manages integration of five CubeSats in the giant rocket as well as the avionics that will control deployment of the 13 small satellite payloads on the first mission of SLS and Orion called Exploration Mission-1, EM-1. He spends his time managing the little payloads, not much bigger than a shoebox, that goes inside of a skyscraper-sized rocket. So, we're going to be talking about just how powerful this monster rocket is, its unique capabilities, and what it will be used for, where it is in its development, its first mission with the Orion crew vehicle, and then look ahead to the future to missions to the moon, to Mars, and throughout the solar system. So, we are go for launch with Mr. David Smith and Dr. Paul Bookout for the Space Launch System Program. T minus five, four, three, two, one, zero, and liftoff of Episode 41 of Houston, We Have a Podcast. Always wanted to do that. Feel like I just ruined it. You know what? Let's just start. [ Music ] Host: T minus five second and counting. Mark. [ Music ] Host: There she goes. Host: Houston, we have a podcast. [ Music ] Host: All right. Paul and David, thanks so much for coming on the podcast today. We talked about Orion on a few episodes so far but really haven't had the privilege to talk about he giant rocket that Orion is going to be on, the SLS. And, we have you guys here from Marshall to actually talk to us about this rocket. So, thank you very much for coming on. David Smith: Sure. David Smith: Thank you for having us. Host: Our pleasure. Host: All right. Just to sort of back up, we have Paul Bookout and David Smith, so you guys want to talk a little bit about each one, so we can identify your voices. Paul Bookout: David, go ahead. David Smith: Well, sure. I'm just an engineer. My associate Dr. Bookout is a doctor. Host: Okay. David Smith: But, we both work together on trying to find innovative ways to associate payloads with the capability of SLS which is going to be the world's largest rocket. So, I kind of look at the larger payloads, and Dr. Bookout looks at maybe some of the other kind, smaller payloads that can fit in the niches that are left over. Paul Bookout: Well, thank you Vice President David. David Smith: Yes. Paul Bookout: I appreciate you talking about introducing myself. So, what we have is secondary payloads. Again, we're just trying to understand the whole utilization of SLS since it's going to be the most powerful rocket built since the Saturn V. It's going to have a lot more capability, so we want to utilize it to its fullest. Host: Okay. So, you said there's going to be, basically, we're going to utilize the rocket to its maximum potential. We got this big rocket, and we're going to test it. But, while we test it, let's put some cool stuff on it. Paul Bookout: Exactly. Host: So, let's back up and talk about just SLS. What is SLS? What is this giant rocket that we're talking about? Paul Bookout: SLS is America's rocket. It's the next NASA's launch vehicle that's going to be able to put humans back to the moon and further out into deep space. Of course, a lot of it's built on shuttle hardware heritage. The SLS rocket's made up of the solar rocket boosters, a main core, an upper stage, and then the crew Orion spacecraft with a co-manifest payload or a primary payload. And, David will talk a little bit more about that later. So, of course, this is NASA's first exploration class launch vehicle since Saturn V, so we're going to be putting humans back to the moon, out to deep space, and eventually, you know, to Mars systems. It has a very large mass lift capability and also volume, so some of these larger probes that are satellites or probes that are going to outer planets that they'll be able to arrive at their destination in just a few years instead of maybe eight to ten years. [00:05:24] You're cutting that trip down to one or two years. So, it's a lot of savings there. Host: So, that's a really important part to kind of hone in on is just the versatility of this rocket. You're talking about a giant rocket that can take people, giant payloads, faster, farther. That's pretty much the whole summary of the SLS, right? Paul Bookout: Yes. Definitely. Host: So, what's, what does it take to be human rated? So, I guess the difference between something that's not a rocket and something that is. Paul Bookout: Of course, it goes through the whole development process, starts at the beginning. You have to have safety emission assurances involved from the very beginning. Just an overview, you have to have, like redundant systems. If something goes wrong with one system, there's another system to kick in to back up to still make the vehicle safe. There's safety reviews throughout the whole process. We do additional testing, a lot more testing than other commercial launch vehicles do just to make sure that the vehicle is safe for humans. Host: That's really the main thing, right? Paul Bookout: Yeah. [00:06:33] Host: The safety. But, then, also the redundancy because I guess redundancy is cost. Redundancy is weight. So, you have to factor that into a rocket where you can just say, "Oh, if it fails, you know, with the primary systems, it fails." But, at least the only thing we lose is this piece of hardware. And, not to say that that's not a bad thing, but. Paul Bookout: Right. Host: It's very different from human life. So, I guess, absolutely, you need to be considerate of that. Paul Bookout: Right. And, there is a tradeoff, as you was saying. Additional systems, more mass, and that's mass that is being taken away from your primary payloads. Host: Yeah. Paul Bookout: And lift capability, but we need that to be safe. Host: You know what? I actually always wanted to ask this question, but you said primary payloads. I get this question all the time from folks not in NASA, and it's just, we use this term all the time, but what, to you, is a payload? [00:07:22] Paul Bookout: A payload is anything that goes up on top of the rocket that's lifted into space. It can be a satellite. I can be probes. Of course, the Orion spacecraft, once it's on the rocket, it can have its own second co-manifested payload along with it. So, just anything, really, that's launched into space. Host: Does a person count as a payload. Paul Bookout: We don't like to refer to. [ Laughter ] Host: It doesn't humanize it as much, right? Paul Bookout: No, it doesn't. No. Host: So, I guess, for example, going back to that co-manifest thing, the Orion. The Orion would be the payload. That would be the primary thing that you want to bring into orbit. Paul Bookout: Correct. Host: But, then, there's something that is, something called co-manifested which means it's not the primary thing, but it's also part of the part that you want to lift the mission. Paul Bookout: Correct. Host: Okay. Paul Bookout: For example, on the second generation of the SLS rocket, it will have capability of launching a co-manifest payload along with Orion, and it could be anywhere from additional probe going out into the moon, or it can be call separation bus, propulsion system that's launched. And, then, when a habitat is launched, then they can be combined and go to the moon. So, it's, allows us to build capabilities out in space, too, with co-manifested payloads. Host: Okay. Paul Bookout: Along with Orion. Host: Is that one of the things you're working on? Or, you're working on, I guess, secondary payload? Paul Bookout: Yes. I'm mainly focused in on secondary payloads. Host: So, what's secondary payloads? Paul Bookout: Okay. Secondary payloads, or they call auxiliary payloads. Host: Okay. Paul Bookout: They're payloads that do not drive the primary mission of the, of that launch. For example, on EM-1, we have secondary payloads on that. That's EM-1, Exploration Mission-1. Host: Okay. Paul Bookout: First launch of SLS rocket. David Smith: Yeah. Paul Bookout: We have 13 payloads on that, and I'll talk a little bit more about that later. But, the primary requirements they have is for secondary payloads in general is do no harm to the vehicle and minimal impact. So, the do no harm aspect is that we have to fly safe. The whole system, deployment system and everything, is designed to be safe. Like, all the CubeSats are turned off during launch. They have to have, like, redundant systems, as in two separation switches that allow them to turn on. Because, if one fails while we're being launched, it could turn on the systems. So, we have two there. Host: Oh, okay. Paul Bookout: To back that up, to keep it safe. And then, minimal requirements, of course, if the rocket is ready to launch and the secondary payload's not ready yet, it's going to launch. Because it does not affect the primary mission of the payload, of the launch. Host: Right. Paul Bookout: Of that. Host: Well, that puts a lot of constraints on you, then, huh? Paul Bookout: Yes, yes it does. Host: Because, not only do you have to worry about these, and I guess we can kind of hone in on the CubeSats a little bit later. But, you have to worry about the CubeSats, but now you have to add something else to it. Now, you have to add these redundant systems. And then, there's no guarantee that if you're not ready, that's okay. We're going to go without you. Paul Bookout: Right. Exactly. SLS is, the first rocket's not going to be the only configuration of SLS. And, of course, SLS is Space Launch System. We, the first launch is going to be called Block 1. Then, we're going to be stepping up to Block 1B which means we're going to be adding a different upper stage. Right now, we're utilizing an existing Boeing ULA upper stage to use on this mission, mainly to save initial money so we can develop the core stage. And, once the core stage has been developed, then we can have additional funds to start developing the new upper stage or exploration upper stage. Host: Okay. Paul Bookout: Okay? And, that's going to be the Block 1B configuration. And, Block 1B will have actually two configurations. It'll be a crew which was, as we talked about before, the Orion spacecraft with a co-manifested payload. The other configuration will be the Block 1B cargo where that would be your primary payloads. So, the only payload will be that major payload. Host: Okay. So, when you say "Block", you're looking at the entire rocket configuration. Paul Bookout: Correct. Host: And, Block 1 is this configuration with the ULE booster, right? Paul Bookout: Right. Host: Okay. And then, Block 1B has the NASA booster on top. Paul Bookout: Correct. Host: Instead of the ULA, but then you can do crew or cargo on that one. Paul Bookout: Exactly. Host: Whereas, EM-1 you don't, and EM-1, we can get into this later, is, you're not going to have crew on it, right? That's not part of the test. That's for one of the later missions. Paul Bookout: Correct. Host: I see. So, really, the blocks are kind of the stages of developing the rocket into its full capability of. Paul Bookout: Right. Host: Of this eventual Mars lander. That's awesome. So, now, you're using these commercial elements. You're using ULA in Block 1 and the leftover solid rocket boosters until, eventually, 1B, 1B crew, you get to Block 2. Now, you have the configuration. New boosters. You got the NASA upper stage. You got all of these configurations, and now you can go to, where can you go? David Smith: Well. Host: Is it just to Mars? David Smith: Well, you really need Block 2, ultimately, to fulfill a human settlement on the lunar surface as well. Host: Really? David Smith: You need a kind of lift capability. But, if you want to assemble an architecture, because it'll take multiple flights of a Block 2 to assemble a human architecture capable of transiting to Mars, you'll need four to five Block 2 flights at a time to assemble that stack that can go to Mars. Host: So, what's, I guess, how much more power does Block 2 provide you that, I guess, Block 1B would not? David Smith: Well, it nominally, you're talking another 25 tons or so. So, it could bring a second Orion vehicle in comparison because Orion weighs about 25 tons. So, it, really, from a lift standpoint, is maybe a fifth more powerful than the Block 1B, and it gives you that extra diameter, potentially for the payload ferrying that would allow, you know, the smaller the diameter of the ferrying, the taller a lander needs to be. And, think about a lander on the surface of the moon or Mars, if it's three or four stories, that's a lot of vertical height an astronaut has to overcome every time they're taking stuff back and forth. Host: That's right. David Smith: So, we're, the larger the diameter, the shorter can be the squatter, can be the easier it is to manipulate items on and off a lander. Whether it's on the moon or Mars. Host: Okay. Wow. So, then, you're talking about once this Block 2 configuration is done with the new solid rocket boosters, you can actually have a wider payload go on top of the rocket. David Smith: Right. Well, there's a nuclear thermal propulsion that's out there that has the potential of getting people to Mars a lot sooner. It needs a much larger diameter because it used hydrogen as a fuel. Hydrogen is very bulky because it isn't very dense. And so, if we were ever to use a new kind of propulsion that would lower the time to get to Mars, you need a Block 2 vehicle. A smaller rocket will never allow you to do nuclear thermal propulsion. Host: Okay. Let's go back to some of these other configurations. I kind of want to get a sense of the look and feel of this rocket. We sort of talked about it, but to just sort of go into detail. If I was looking at let's just say the Block 1 configuration, the one that's actually going to go for EM-1, what does that look like? How tall is it? What's the weight of it? How much power? David Smith: Right. So, roughly Block 1 and 1B are somewhat similar. Host: Okay. David Smith: They're going to be about the same height as the Saturn V. Host: Oh. David Smith: Which means it's a big rocket, but part of that's because we can't really exceed the vehicle assembly building limitations that are at the Cape. So, you want to make it as big as you can, so you can put as much fuel in it as you can. Basically, the thrust of the Block 1 vehicle which is similar to the Block 1B for the solid rocket motors is about 3.6 million pounds each. Those only fly for about two minutes. Then, you have the core engines. There's four space shuttle era type SSMEs that each have about 512,000 pounds of thrust. You multiply that by four. They operate for about eight minutes. Together, you get about a total thrust of about 8.8 million pounds which gives you an escape velocity of over 22,000 miles an hour. The core stage itself is about 2/3 the length of a football field which is pretty tremendous. One single stage of this vehicle's about 2/3 of a football stadium. And, which is around 212 feet, and the Block 1B ferrying that we talked about, the 8.4-meter diameter ferrying, could accommodate up to three school buses inside its volume. So, that's pretty incredible when you think about the size of what can be lofted in a single vehicle like that. In comparison, the Block 1 vehicle, you know, can throw 70 tons to lower earth orbit where the shuttle can only do 28 tons to low earth orbit. So, it's about three times more powerful than the shuttle. Host: Wow. So, you're talking, you're comparing it to the Saturn V in terms of its size but talking about these efficient engines. What makes, what is it about the engines that's more efficient that's giving you this extra power? David Smith: Well, they, you know, the shuttle engines were rated at 100% thrust originally, and I think they got them up to 109%. So, they actually got them to work 9% more efficiently at the end of the shuttle program. We're taking these up to 11% more thrust, and maybe even 13% more thrust. So, you're really pushing these engines to their limit, and the, it's really coupling their efficiency now at 113% thrust with the reliability of the shuttle system. Host: Unbelievable. The engine itself is called an RS25, right? Paul Bookout: Yes. Host: That's what it's called. And, these are the engines that were on the shuttle. Now, you're pretty much just putting it on the SLS, but it sounds like there's a good reason for that. It's because you've flown the shuttle so many times, improved the capability of it past its, like, total 100% thrust ratio. Now, you're going, you're going past the 100%. So, basically, is like why would we, why would we do something else? We worked so hard on this one. This one is, like, extremely efficient. Why would we, and we can make it even more efficient. That's the logic behind it? Paul Bookout: Well, right. Initially, of course, we have about, I believe, 16 space shuttle main engines or these RS25s left over from the shuttle program. So, we're utilizing the existing hardware to save cost while we're developing the core stage. You know, the first part of the SLS. Host: Yeah. Paul Bookout: And, as you mentioned, we are updating the engines, getting more capability out of them. So, to that point, we can do four per, so we can do about four launches, four rocket, or four engines on each launch. So, we can do about four launches with the current RS25s. Host: Okay. And, that, is that for one of the later configurations? Paul Bookout: That's correct. Host: Okay. Paul Bookout: Yeah. Host: Is it the Block 2? Paul Bookout: The Block 2. Host: Block 2? Paul Bookout: Block 2 and beyond. Host: Oh, okay. I see. I see where the whole idea of staging this whole thing comes from, right? Paul Bookout: Correct. Host: You've got, you're using the leftover solid rocket boosters, and you're using this commercial upper stage. And, it's just basically getting to this point where you're going to maximize the efficiency of the rocket. Paul Bookout: Right. Host: Unbelievable. So, three school buses inside of the 1B configuration, right? That's, is it about the weight of three school buses? Is like taking three school buses to space? David Smith: No, it would be, it would be more than that. Host: More than that? David Smith: I mean, nominally, if you went to the moon, we're going to take, the Block 1B could take roughly 40 tons to lunar vicinity which is, which is pretty incredible. Host: Wow, and just in terms of not only, like, quantity, you're talking three school buses. But, also size. David Smith: Yeah, and mass. Host: Also weight. David Smith: Right. Host: You know, you got all of these, all these different components. So, I guess we can kind of focus in on now that we kind of understand the rocket and the evolution of the rocket, let's go to that first, that first test flight, EM-1. We've talked about EM-1 on the podcast before, especially from testing Orion and that. But, really haven't focused in on what is it about, what is it about EM-1 that we're testing SLS for? So, let's start with that. What are we going to test, and I guess we can kind of start with the overview of EM-1 for those who haven't listened to it before. Paul Bookout: Right. So, EM-1 is, of course, going to be the first launch of the SLS rocket. Its primary segments are, of course, solid rocket motors which are a heritage from shuttle hardware. Shuttle had four segments, where EM-1 is going to have five segment motors. Then, of course, the core stage which is heritage off the shuttle external tank but made longer for additional capability of fuel. And, we're also using the main engines from the shuttle program with updated technology and ratings to get more power out of those four rockets on there. So, that makes up the primary lift capability of the SLS rocket. On top of that, we have an interim cryogenic propulsion stage, which, or second stage, upper stage, that we're utilizing from Boeing, existing hardware for EM-1 mission. And then, of course, in addition to adaptors, then there will be the Orion spacecraft, which is the primary mission of EM-1 is to test out the SLS rocket. Then, also, to test out the Orion spacecraft with its trajectory and telemetries and communications. It's going to be on about a 25 1/2 day mission to distant retrograde orbit. That really means just go way past the moon and come back. Host: Yeah. Paul Bookout: You know, a 25 1/2 day trip. Of course, and, you know, we're doing all this because, again, for the safety aspects. We want to test the vehicle out and Orion spacecraft before we put humans in it. Host: Right. Paul Bookout: So, we want to make sure it's safe, make sure everything works. And, that's that safety aspect, that human rated part of a launch vehicle. Host: So, the human rated part is the Orion can go to 25.5 days, or is this going past what it's expected to possibly operate at? David Smith: I think that's a nominal timeframe for the Orion with crew. So, this is pretty much, I think, its extreme capability. Host: Yeah. David Smith: But, you know, part of it is testing just the systems period. You always, for human rating, you always want to test it far in, you know, far from what the humans will actually experience so that you have a safety factor that's sufficient for human use. Host: Oh, yeah. Because if you're going to be operating on, say, 16 day missions, you don't really want to, okay. Well, let's just test 16. Paul Bookout: Exactly. Host: You really want to go kind of further out and see, all right. Let's see how far this puppy can go. David Smith: And, I think part of this mission's objective is to bring it in at a lunar return velocity to test that heat shield. Host: Yeah. David Smith: You can't do it from low earth orbit. You got to kind of go out and bring it in fast, so. Host: So, what's the difference with EFT-1? That was one of the first test flights we did where we didn't go all the way out to the moon, but we did kind of a, this large apogee so that we can get up to, I think it was some, like 25,000 miles. Or, maybe it was a little slower than that. The difference is between EFT-1 and EM-1. David Smith: I think, I think it was very close to what they would experience in a lunar return, but it's not the actual lunar return. Host: I see. David Smith: Right, so you want to be able to stage it. You want to go out in orbit. You want to test the time that you're out in orbit. That was a very short mission, maybe five or six hours. Now, we're talking 25 days. Well, all the equipment still work when it's, you know, soaked in a cold temperature, hot temperature, all those days. And, now, you're coming in. Will it all work when it comes to the right moment. So, this really puts the pedal to the metal. Host: That's right. So, what is it? I guess the relationship between what are you guys looking at for SLS versus Orion on this particular mission, EM-1? Paul Bookout: So, for SLS, again, we want to test all the systems, make sure they're fully functional. We'll be checking out redundant systems indirectly, of course. And, communications with the vehicle, since it's the first time the vehicle's being launched. We're all, we're talking with the vehicle all the way up. Host: Yeah. Paul Bookout: So, we want to make sure all those ground systems are ready to support, actually, human flight mission. So, it's just not the vehicle. It's the overall architecture of everything that goes into supporting a launch that we want to verify and check out. Host: Oh, that's right. Now, we're preparing to go into fly deep space missions. So, not only is it, all right, let's test the hardware, but let's test to operational aspect. Paul Bookout: Exactly. Host: Let's test what it's going to take to actually do these missions from the broadest perspective possible. David Smith: And, that includes, even, just bringing the, you know, the pieces are being built all over the place. Host: Yeah. David Smith: And, tested all over the place. So, just bringing them together at the cape and making sure they can be integrated in a safe and timely fashion for launch. That, in itself, is a really important objective. We're talking about such a large rocket. Paul Bookout: Yeah, so this is the first time all those components going to be coming together, and there's going to be hiccups along the way. And, we just need to understand how this vehicle goes together and make sure we do it correctly. Host: So, you say the vehicle's going to be talking to you guys throughout its flight. What is it going to be telling you? What kinds of data are you really looking for that's really going to tell you that this thing is working how we're expecting it to work? David Smith: Well, remember, you're talking to payload guys, so, you know, we're more interested in seeing what the payload's going to experience. Host: Yeah. David Smith: But, think about this. When it launches on the pad, it has an incredible noise issue coming off that mobile launch platform. That's why, if you remember, they had these things called rainbirds, the big sprinklers that start spraying as soon as the engines go to try to mitigate that noise. Host: Right. David Smith: The payload is particularly sensitive to it. Obviously, the vehicle itself is sensitive to that noise as well. So, acoustic mitigation is one of the most important things at launch. Then, we have a thermal issue, right? We go up to max Q, max dynamic pressure. We have a certain heating that is, occurs on the outside of the vehicle. And, before, we got to get through all that heating before we can make sure that the crew is going to be safe, that we can take the shielding off the Orion and so forth. So, we're going to be testing all those environmental concerns as we go forward, and of course, the jettisoning of, you know, the SRBs off the core stage. Then, the ICPS in Orion off the core stage. And then, of course, then, the Orion off the ICPS. All these jettison events, and there's quite a few of them, are extremely important, and we need to test those. Each one has its associated thermal and acoustic issues. So, we're going to test each one of those as it goes forward. Paul Bookout: Since this is the first launch of SLS rocket, we don't really understand the full environments that it's going to be launched in. As David mentioned, the thermal, interior thermal, acoustic, vibration. It's the first time we're going to launch it. So, what we're also have is a lot of instrumentation on this vehicle to be able to measure the actual vibration levels and everything else. So, we can, once we go back to designing and looking at what we call safety factors, reducing those so we can have more margin on the vehicle and means that goes into more mass lift capabilities. So, we're trying to understand the overall characteristics of the vehicle itself. So, in addition, for secondary payload, or payloads in general, we can give them more of an accurate environment that they will see during launch. As in, how much vibration they'll feel, how much thermal environments that they'll see. So, when they start designing their payloads for, to run the ride on this vehicle, they can have more of an accurate environment. And, maybe not have, make it a lot more efficient design. Host: Okay. So, then, what data are you going off of now based on, you guess you haven't launched the SLS. So, what are you assuming, or where are you getting the data from? David Smith: We have, we started off with assuming, at least for the payloads, that we would provide an ELV, and expendable launch vehicle class environment. Host: Okay. David Smith: So, if you've flown on Atlas or Delta, you should expect nothing worse than that. Host: Okay. David Smith: That's our starting point. Host: Oh, okay. David Smith: Now, what Paul's going into is we're going to try to characterize is that really true? So, the first flight's important. Are we in? Are we out? What do we have to do? Is there more foam that you got to put in the payload section to mitigate the noise? That's what we're trying to figure out. But, we should be within an ELV class is what we're projecting right now. Host: Okay. So, then, I'm assuming you're going to have some actual science on board EM-1, right? Because you're testing, you're testing the structure of EM-1. You're testing the rocket. But then, you have this mission. Why not take advantage of it? Is there anything else going on the EM-1? Paul Bookout: Oh, definitely. Host: Okay, good. Paul Bookout: Yes. We have, we'll have 13 secondary payloads that we're going to be launching on EM-1. Host: Wow. Paul Bookout: That'll, that is located in the Orion stage adapter. That's the segment that connects the SLS rocket to the Orion spacecraft. So, it's a small ring about five feet high. About 18 or so feet in diameter. And, along the inner circumference of that is where we are mounting these 13 secondary payloads. Host: Oh, so I guess they have to be kind of small, right? That's not a lot of space compared to the, what's in the ferrying. Paul Bookout: Correct. So, on EM-1, we have 13 CubeSats. CubeSats are defined as a, we call a 1U, which is about ten by ten by ten-centimeter cube. Host: Okay. Paul Bookout: So, what we're having on EM-1 is allowing them to go up to what we call a 6U. So, it's a CubeSat that's about the, a little bit larger than the size of a shoebox, a large shoebox. Host: Okay. Paul Bookout: And, that's kind of the dimensions of these 6U CubeSats that we're having on EM-1. David Smith: Which is the most common CubeSat, really, today, right? Paul Bookout: Correct. Exactly. So, we have multiple missions that these payloads are going to be doing. So, we've got one destination is to the moon. We have Lunar Flashlight which is out of Jet Propulsion Laboratory, and their primary mission is to search for ice deposits and resources on the moon using a laser. Host: Ooh. Paul Bookout: Okay. And, the second one is Lunar IceCube which is Morehead State University up in Kentucky. And, they're going to also be searching for water of all forms and volatiles on the moon using infrared spectrometer. These are some big words that I can't even define, so. [ Laughter ] LunaH-Map is from Arizona State University, and they're going to be creating high fidelity map of near surface hydrogen in craters on the moon. Lunar IR is from Lockheed Martin in Colorado, and they're going to be performing advanced infrared imagery of lunar surface. We've got one that's going to the sun facility, and it's called CuSP. It's from Southwest Research Institute here in Texas, and it's going to be measuring particles and magnetic fields of space weather between us and the sun. We have one that's going around the Earth. It's called EQUULEUS. It's a Japanese payload, and we actually have three international payloads on this mission. And, I'll touch on those others. Host: Awesome. Paul Bookout: So, again, EQUULEUS is from JAXA. It's the University of Tokyo supporting that. I mean, it's imaging the Earth's plasma sphere for a better understanding of Earth radiation environment. And also, it's going to be initially on the far side of the moon and detecting any meteor crater flashes that may impact the far side of the moon. Host: Wow. Paul Bookout: So, they'll be out there for about two months or so and just hopefully they'll be able to catch something. Some of the other missions are BioSentinel. It's from Ames Research Center, and they're going to be using baker's yeast to see the effects of radiation on actual live items, you know, live yeast. And, then, ArgoMoon, which is the European Space Agency, is built in Italy. It's going to be observing the interim cryogenic propulsion stage. That's upper stage is going to be deployed. Look at that upper stage, and then it's going to go on some additional missions. And, it's going to look at the upper stage to see what kind of effects the environment has during liftoff on the upper stage. Because, until now, we, once the upper stage is launched, we usually don't get a chance to look the conditions of that. This will give us some feedback and see what the upper stage has went through, if there's any damage or anything. Host: It sounds like these CubeSats are all over the place. Paul Bookout: Yes. Yeah. I've got a couple more here. Host: Oh, really. Paul Bookout: I haven't got to my two favorite yet. So. Host: Oh, we're standing by. Paul Bookout: Okay. Centennial Challenge. That was a challenge that NASA set up called Cube Quest, and it's to help develop communications for these smaller CubeSats. There's two challenges. One was a lunar challenge to around the lunar surface and for longevity. And, the other one was a deep space mission which was a CubeSat, as it says, going out into deep space to see how far and long and what burst rates and clarity that you can have in your signals. So, there's total prizes for everything through all the development and final missions. It's up to $5 million. Host: Wow. Paul Bookout: So, that's a lot of money. Host: Yeah. Paul Bookout: Spread out over those. So, you did, you asked what my two favorite payloads are. Host: Oh, yeah. Paul Bookout: Let me tell you. One of them is NEA Scout. That's developed at Marshall Spaceflight Center. What's unique about that is NEA Scout means Near Earth Asteroid. So, they're going to be going to a near earth asteroid. But, the exciting thing about it is that they're going to be using solar cell to get there for their propulsion system. So, this is the first time a solar cell will be used to, for propulsion out into deep space. There have been other missions in low earth orbit to check out the technology and feasibility of solar cells, but this is the first time going out to deep space. And, for a CubeSat that's a little bit larger than a shoebox, it will be deploying the cell that will be 40 by 40 feet. Host: Whoa. Paul Bookout: So, that's huge. Host: Wait, and a little CubeSat. Paul Bookout: In a little CubeSat. Host: And, it deploys a 40 foot. Paul Bookout: Yes. Host: Oh, wow. Paul Bookout: Yeah, so that solar cell is very thin material. Host: Yeah. It must be to fold up into, like, this ten-centimeter cube thing. Paul Bookout: Exactly. Host: So, so, the solar. Paul Bookout: You said ten centimeters. 6U CubeSat is 10 by 20 by 30. Host: Oh, because this is 6U. Paul Bookout: 6U, correct. Host: Oh, okay. Okay. Okay. So, solar sails, though, this is, it basically unfurls this 40-foot sail, and is it the one where the high-power laser that pushes it? Paul Bookout: No. Paul Bookout: That's different. Paul Bookout: This is going to ride the solar winds. Paul Bookout: Ride the solar winds. Paul Bookout: Solar particles will be pushing it along. It'll do actually a fly by the near-earth asteroid as it comes up. It'll be taking images all the way around as it passes. Host: Okay. Wow. Paul Bookout: So, and my ultimate favorite one is. Host: Yeah, we didn't get the last one. Paul Bookout: Is actually the one that I'm the Secondary Payload Integration Manager for. Host: Oh. Paul Bookout: So, it's one of my CubeSats. Host: So, it's an unbiased favorite, then. Paul Bookout: Yes. Host: Okay. Paul Bookout: Yeah, still. It's called OMOTENASHI. It's another Japanese CubeSat. Host: Okay. Paul Bookout: And, their mission is to land on the moon. Host: Oh. Paul Bookout: Can you imagine a small little CubeSat, you know, a little bit larger than a shoebox, land on the moon? Of course, and the big thing about it is that they're going to be using a solid rocket motor to slow down to be able to land on the moon. So, that's one of the things on EM-1 that we're offering that previous commercial launch vehicles and that don't offer propulsion systems for secondary payload to be able to utilize that. That's one thing EM-1 and SLS is allowing. So, that's a huge deal. Host: Yeah. Paul Bookout: For those. So, if OMOTENASHI is successful at landing on the moon, they'll be the fourth nation in the world to have actually land and do some science on the moon. Host: Wow. Paul Bookout: You know. Host: So, what kind of science? Paul Bookout: Well, because, again, they're still a small payload, so they can't get large science instruments to the moon, when they land, actually land on the moon, all that will be left is about the size of a sandwich box. Because they have to get rid of all the extra weight to be able to slow down enough to be able to land. And, they'll probably so some soil impact measurements, as in how soft vibration, shock, as it's landing on the moon. And, I, so, and they're only going to be able to do it for about 30 minutes or so. Again, because of the size, what we're limiting them to. Host: Yeah. Paul Bookout: They can't get the mechanics, orbital mechanics and velocities and everything. I'm sorry. Host: So, it's, it's kind of general on where you can land, then? It's just like, it's just going to land. It's not going to land in a targeted spot, I guess? Paul Bookout: Correct. They know the general vicinity where it's going to land. Host: Okay. Paul Bookout: But, they can't have ultimate control, like any of the other landers that have larger systems, propulsion systems, to slow them down. So, they would be actually, once the solar motor fires, they'll still be traveling at about 60 miles an hour when they impact the moon. So, they're going to inflate these impact balloons to actually bounce, similar to what they've done on Mars, some of the Mars Rovers. Host: Okay. Paul Bookout: So, it'll come and impact moon and bounce and then finally rest on the moon. Host: Okay. Paul Bookout: And, do about 30 minutes of impact soil measurements. Host: Wow. How would that be, though? I'm imagining, I mean, landing at 60 miles an hour. That's, you know. Paul Bookout: Well. Host: That's not slow, but at the same time, it's the moon, right? It's. Paul Bookout: Right. Yes, but then again, you're not going directly into it. You know, you're coming in at an angle, too. Host: At an angle. Paul Bookout: So, it's not a fully impact. Host: Okay. Great. Paul Bookout: Direct impact, so. Host: So, you got all these CubeSats going around the Earth, around the upper stage, around the moon, on the moon, to deep space. Where do you deploy, how does that work? Where do you deploy everything? It's not just like you just let everything go at all. It has to be pretty controlled because each one has a very specific mission. Paul Bookout: Right. We've created what we call bus stops. Host: Oh. Paul Bookout: They're basically different aspects of the trajectory of the upper stage. So, the first bus stop is when you're in between the two radiation belts or Van Allen belts. Bus stop two is when you've passed all the radiation belts. Bus stop three is half way between the Earth and the moon. Bus stop four is the closest proximity to the moon, and bus stop five is when you're going into a heliosynchronous or sun orbit. And, that's where the upper stage will be disposed into the sun orbit. So, when a payload says, "Hey, I want to get off at 200,000 miles away from the Earth." Well, okay, where is that exactly? So, that's why we kind of created these bus stops. Host: I see. Paul Bookout: They can get off anywhere they want to, but it helps us relate to the areas where they want off. So, most of them are wanting off at stop one. About seven or eight of them. Because they need to get out and start changing their trajectory as soon as possible. Again, we're offering propulsion systems, but they're not large enough to have really change their directions further on. So, a little change at first makes a big change later. Host: Yeah. Paul Bookout: So, they want to get off to be able to do that, make those little changes. Most of the payloads that are going to lunar orbit, what they're wanting to do is slow down because the ICPS, you know, is launching Orion into this distant retrograde orbit. And, you know, way past the moon. Host: Yeah. Paul Bookout: So, it has a lot of velocity heading that way, and if the payloads don't slow down, they'll just go flying past the moon. The moon can't, doesn't have enough gravity to pull them back into an orbit. And, some of them, even though they are going to the moon, they'll actually fly past the moon, and it may take a month or so for them to come back, to slow down enough to come back and get hooked into the moon's gravity and start orbiting the moon. Host: Oh, wow. Paul Bookout: So, it's not a direct flight into the moon orbit, just because they don't have the propulsion systems large enough to be able to do that. Host: So, is it fair to say they're all going to be in a very similar orbit, or are they all going to kind of go their respective directions? Paul Bookout: They're going to do their respective ways. Host: Okay. Paul Bookout: Some of them wants to do in the crater, so they're going to be going to the pole system, up to the poles to look see if there's ice up in there. And, some of them will just be doing a regular geosynchronous type of orbit. Host: Okay. Paul Bookout: Type thing. Host: All right. Paul Bookout: We talked about where these, what the payloads are and where they're going to want to get off. To be able to allow them to get off, again, we have to have a deployment system where, again, some of the primary requirements for EM-1 was or SLS is to do no harm and to have minimal impact to the vehicle. Host: Yes. Paul Bookout: Well, to do that latter one, what we've come up with a system is that we will receive an energy, the avionics unit for deploying the secondary payloads will receive an energy pulse for, from Orion. Or, I'm sorry. Will receive an energy pulse from the upper stage once Orion has already left and the upper stage has gone through its disposal maneuvers. That means burning off extra fuel and everything making it safe. Right before it shuts down, it will turn on the avionics unit for deploying the secondary payloads. Then, the upper stage turns off. So, we wake up, and we've got our own internal battery system. And, each payload is inside of a dispenser, and so, the dispenser operates as the, has a spring-loaded lid. And, the payloads inside are installed by compressing the spring. So, when the, when it's time for that particular payload to be deployed, we get an energy pulse from the avionics unit sent to the dispenser to open the door. The door flings open, and then the secondary payload is pushed out by springs. So, that's how they're deployed. Host: Okay. So, like a, so, like an SLS jack in the box. [laughter] Paul Bookout: If you will. Host: That's what I'm imagining. Obviously, it's going to shoot out. Paul Bookout: We have pulled those analogies before, but I'll let you state it. Host: And then, I guess there's, you get this power pulse that's going to, I guess, be directed to whatever seven is going to be part of bus stop one, and whatever the next ones for bus stop two. Paul Bookout: Correct. Host: Okay. Paul Bookout: And, they'll be deployed, if there's multiple at a particular bus stop, they'll be deployed a minute or two away from each other, after each other because we don't want to be able to deploy one and then deploy another one right behind it. Host: Yeah. Paul Bookout: And then, they have recontact. Host: So, I'm trying to imagine the way everything is situated in my head, and at this part of the flight when you're starting to deploy these secondary payloads, what does, what does the rocket, I guess, or what does the piece that's actually flying, what does it look like? I guess you have Orion and then there's this deployment system, and then there's, is it the upper stage behind it? Paul Bookout: Okay. So, once we've launched. Host: Yeah. Paul Bookout: After about two minutes, the solar rocket motors are. David Smith: Jettisoned. Paul Bookout: Jettisoned. And then, the core stage lifts the rest of the vehicle up into orbit. And, after that time, when the core stage is spent, then it'll be jettisoned. And then, you'll have your upper stage and your Orion spacecraft which of course the secondary payloads are still in part of that. And then, then, it'll go into what they call a translunar injection that's basically the upper stage will ignite and put Orion into its mission profile going past the moon. Host: So, at this point, right before it ignites, it's still in, I guess, Earth orbit, and the translunar injection gets it to the moon. Paul Bookout: Correct. Host: Okay. Paul Bookout: Okay. So, once the upper stage has spent its fuel, the Orion spacecraft will separate, okay? From the upper stage. So, it'll go through on to its mission. And then, about 30 minutes later, 20, 30 minutes later, the secondary payloads will start their deployment. Host: I see. Okay. Paul Bookout: So, Orion is well away and actually speeding faster away from the upper stage. Host: Yeah. Paul Bookout: The upper stage, once it goes through its disposal maneuver, is actually flying kind of, you would say, backwards, engine first, towards the moon. Host: Oh. Paul Bookout: So, the secondary payloads will be ejected out the other direction. So. Host: Okay. So, so. Paul Bookout: So, when they're deployed, the ICPS won't run back into them. Host: That's right. Paul Bookout: Okay. So, they'll be deployed in the other direction. Host: But, now, Orion is going in, it's doing its own thing. Paul Bookout: Correct. Host: Because it did its job. It delivered Orion. That's the primary payload. Now, it's off. But, the secondary payloads are still part of this upper stage. They haven't gone with Orion. They're totally separate. Paul Bookout: Correct. They have their own. Host: So, it's like, they're kind of doing, they're going. Paul Bookout: Yeah. Host: Different ways. Interesting. Paul Bookout: Yeah, they have their own mission profiles going in all different directions. Host: Okay. Okay. I don't know why that wasn't clear to me before but thank you. All right. So, I guess kind of backing up from there, you're talking about the solid rocket boosters are disposed. The core stage is disposed. Where are all these pieces going? Paul Bookout: Okay. Depending on their mission profile, all the secondary payloads are going to end of missions at different places. Some of them will be actually crashing into the moon, and that's common where the other countries and their lunar missions depositing on the moon. Some will, one or two will burn up in Earth's atmosphere as it comes back. Some of the other ones that are going out into deep space, of course, just keep going. The CuSP, which is going to solar. I'm sorry. CuSP, which is going to the sun's vicinity will just stay out there and eventually be pulled into the sun. Host: Okay. Host: So, that's all the secondary payloads. Paul Bookout: Correct. And, for each mission, each payload that's launched on U.S. rockets, they all have to have an end of mission plan. What are they going to do to end their mission, not just to be left out there as space junk. Because that's, we're having, sorry. We're starting to have a lot of problems with, as you know, there's a lot of space junk around Earth. Host: Oh, yeah. Paul Bookout: And, you don't want that same situation around other planets, too. Host: That's fair. That's fair. And, that's why, that's part of the, I mean, this is going back, but Cassini, right? That was the whole. It did its thing, and instead of just letting it be. It had a controlled entry into Saturn so that it didn't contaminate any other. Paul Bookout: Exactly. Yes. Host: Any other bodies. Yes, yes, of course. Paul Bookout: And, it doesn't matter what size you are. Host: Yeah. Paul Bookout: Even these small CubeSats have to have an end of mission. Host: Have to have an end of mission. Paul Bookout: Yes. Host: Awesome. But, I did want to go back to some of the earlier parts of the mission, right after launch. You know, you're talking about solid rocket boosters separating being. David Smith: Those go into the ocean. Host: Ocean? Okay. David Smith: Still, but they're not recovered this time. Host: Oh, okay. David Smith: You know, for shuttle, they were recovered. This time, it's too difficult. They're too large. So, they're just going to sink. Host: Okay. [00:48:19] David Smith: The external tank is, it can't go into orbit, so it's kind of lofted in such a way that it'll break up over the Indian Ocean safely. Host: Ah. David Smith: So, it's a very large tank. You know, this is much larger than the external tank of shuttle, so it's very important that it break up safely. So, that's, that's why you need the upper stage to actually bring the payload up into a circular orbit around the Earth. Otherwise, the payload would go down with the core module as well. Host: Okay. Okay. And, what about the, I guess, the upper stage. You said it's going to be doing this deployment, but then, after it deploys [inaudible]. David Smith: It's heliocentric. It goes into a sun, heliocentric disposal. Host: Sun heliocentric disposal. David Smith: So, it kind of goes away, and we should, hopefully, not see it again. Host: Okay. All right. That's a very nice summary of EM-1, and I feel like there's so much more to talk about. I kind of wanted to get into, you know, where are we now with SLS, all the history of it. So, I think we should take a break and just sort of let this one be Episode 41. We'll come back, and we'll do Episode 42 and just sort of get into the process behind building the SLS and then the journeys of where it's going to go and beyond. So, guys, thank you so much for coming on. We'll take a break. I'll see you in a few minutes. And, for everyone else, I guess we'll see you for the next episode. David Smith: All right. David Smith: Great, thank you. Look forward to it. Paul Bookout: Thank you. [ Music ] Houston, go ahead. [ Inaudible Comment ] [inaudible] for all mankind. Not because they are easy, but because they are hard. Welcome to space [echo]. Host: Hey, thanks for sticking around. So, the best places to follow development and delivery of the rocket as we test the major components and deliver it piece by piece to the Kennedy Space Center are on the social media channels on the web for the Space Launch System. So, first the website. You can go to www.nasa.gov/ guess what? SLS. That's where you can get the latest, the greatest on the Space Launch System. On Twitter, it's @nasa underscore SLS. On Facebook, it's NASASLS, that's one word. Or, this is one of the things that actually David Smith wrote. You can actually search SLS Mission Planner's Guide. And, it's a document that you can find on the web. You can download it, and it actually has a lot of great information on just the whole scope of the Space Launch System. We're really looking forward to the first launch of SLS and Orion from the Kennedy in a couple years. Sounds like we're well on our way to the pad, and we'll be launching astronauts back to the moon in just a few short years. If you have questions on SLS and its development, use the hashtag asknasa on your favorite platform. Just go to the Johnson accounts. Those are the ones we look at. The NASA Johnson Space Center accounts on Facebook, Twitter, and Instagram. You can send an idea or a question, and we'll make sure to mention it's for, or just make sure to mention it's for Houston, We Have a Podcast, and we'll bring it up in a later episode. Or, maybe address it in an entire episode. The whole episode will be dedicated to the question. Who knows? So, this podcast was recorded on March 20, 2018. Thanks to Alex Perryman, Rachel Craft, Laura Reshawn [assumed spelling], Kelly Humphries, Pat Ryan, Tyler Martin, Bev Perry, and all the folks at the Marshall Spaceflight Center for coming on to help to put this together. Thanks again to Dr. Paul Bookout and Mr. David Smith for coming on the show. We'll be back next week with part two.

Why Major Programs Need Innovation Support Labs: An Example from the Space Shuttle Launch Program at KSC

NASA Technical Reports Server (NTRS)

Youngquist, Robert C.; Starr, Stanley O.; Stevenson, G.; Rivera, Jorge E.; Sullivan, Steven J.

2011-01-01

For over 30 years the Kennedy Space Center (KSC) has processed the Space Shuttle; handling all hands-on aspects from receiving the Orbiter, External Tanks, Solid Rocket Booster Segments, and Payloads, through certification, check-out, and assembly, and ending with fueling, count-down, and launch. A team of thousands have worked this highly complicated, yet supremely organized, process and have, as a consequence, generated an exceptional amount of technology to solve a host of problems. This paper describes the contributions of one team that formed with the express purpose to help solve some of these diverse Shuttle ground processing problems.

Design guide for low cost standardized payloads, volume 1

NASA Technical Reports Server (NTRS)

1972-01-01

Concept point designs of low cost and refurbishable spacecraft, subsystems, and modules revealed payload program savings up to 50 percent. The general relationship of payload approaches to program costs; cost reductions from low cost standardized payloads; cost effective application of payload reliability, MMD, repair, and refurbishment; and implementation of standardization for future spacecraft are discussed. Shuttle interfaces and support equipment for future payloads are also considered

Students Compete in NASA's Student Launch Competition

NASA Image and Video Library

2018-03-30

NASA's Student Launch competition challenges middle school, high school and college teams to design, build, test and fly a high-powered, reusable rocket to an altitude of one mile above ground level while carrying a payload. During the eight-month process, the selected teams will go through a series of design, test and readiness reviews that resemble the real-world process of rocket development. In addition to building and preparing their rocket and payload, the teams must also create and execute an education and outreach program that will share their work with their communities and help inspire the next generation of scientists, engineers and explorers. Student Launch is hosted by NASA's Marshall Space Flight Center in Huntsville, Alabama, and is managed by Marshall's Academic Affairs Office to further NASA’s major education goal of attracting and encouraging students to pursue degrees and careers in the STEM fields of science, technology, engineering and mathematics.

Integrated operations/payloads/fleet analysis. Volume 2: Payloads

NASA Technical Reports Server (NTRS)

1971-01-01

The payloads for NASA and non-NASA missions of the integrated fleet are analyzed to generate payload data for the capture and cost analyses for the period 1979 to 1990. Most of the effort is on earth satellites, probes, and planetary missions because of the space shuttle's ability to retrieve payloads for repair, overhaul, and maintenance. Four types of payloads are considered: current expendable payload; current reusable payload; low cost expendable payload, (satellite to be used with expendable launch vehicles); and low cost reusable payload (satellite to be used with the space shuttle/space tug system). Payload weight analysis, structural sizing analysis, and the influence of mean mission duration on program cost are also discussed. The payload data were computerized, and printouts of the data for payloads for each program or mission are included.

Payload training methodology study

NASA Technical Reports Server (NTRS)

1990-01-01

The results of the Payload Training Methodology Study (PTMS) are documented. Methods and procedures are defined for the development of payload training programs to be conducted at the Marshall Space Flight Center Payload Training Complex (PCT) for the Space Station Freedom program. The study outlines the overall training program concept as well as the six methodologies associated with the program implementation. The program concept outlines the entire payload training program from initial identification of training requirements to the development of detailed design specifications for simulators and instructional material. The following six methodologies are defined: (1) The Training and Simulation Needs Assessment Methodology; (2) The Simulation Approach Methodology; (3) The Simulation Definition Analysis Methodology; (4) The Simulator Requirements Standardization Methodology; (5) The Simulator Development Verification Methodology; and (6) The Simulator Validation Methodology.

Approaches to environmental verification of STS free-flier and pallet payloads

NASA Technical Reports Server (NTRS)

Keegan, W. B.

1982-01-01

This paper presents an overview of the environmental verification programs followed on an STS-launched free-flier payload, using the Tracking and Data Relay Satellite (TDRS) as an example, and a pallet payload, using the Office of Space Sciences-1 (OSS-1) as an example. Differences are assessed and rationale given as to why the differing programs were used on the two example payloads. It is concluded that the differences between the programs are due to inherent differences in the payload configuration, their respective mission performance objectives and their operational scenarios rather than to any generic distinctions that differentiate between a free-flier and a pallet payload.

KSC-98pc1039

NASA Image and Video Library

1998-09-04

Workers watch as the Hubble Space Telescope Orbiting Systems Test (HOST)is moved inside the Space Shuttle Processing Facility. The HOST platform, one of the payloads on the STS-95 mission, is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process

KSC-98pc1037

NASA Image and Video Library

1998-09-04

The Hubble Space Telescope Orbiting Systems Test (HOST)is being raised to a workstand by technicians in the Space Shuttle Processing Facility. One of the payloads on the STS-95 mission, the HOST platform is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process

KSC-98pc1137

NASA Image and Video Library

1998-09-23

KENNEDY SPACE CENTER, FLA. -- The Hubble Space Telescope Orbiting Systems Test (HOST) is suspended above its work stand in the Space Station Processing Facility before moving it to its payload canister. The HOST platform is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry other payloads such as the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker (IEH-3), and the SPACEHAB single module with experiments on space flight and the aging process

KSC-98pc1036

NASA Image and Video Library

1998-09-04

KENNEDY SPACE CENTER, FLA. -- The Hubble Space Telescope Orbiting Systems Test (HOST) is checked out by technicians in the Space Shuttle Processing Facility. One of the payloads on the STS-95 mission, the HOST platform is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process

Applications of Payload Directed Flight

NASA Technical Reports Server (NTRS)

Ippolito, Corey; Fladeland, Matthew M.; Yeh, Yoo Hsiu

2009-01-01

Next generation aviation flight control concepts require autonomous and intelligent control system architectures that close control loops directly around payload sensors in manner more integrated and cohesive that in traditional autopilot designs. Research into payload directed flight control at NASA Ames Research Center is investigating new and novel architectures that can satisfy the requirements for next generation control and automation concepts for aviation. Tighter integration between sensor and machine requires definition of specific sensor-directed control modes to tie the sensor data directly into a vehicle control structures throughout the entire control architecture, from low-level stability- and control loops, to higher level mission planning and scheduling reasoning systems. Payload directed flight systems can thus provide guidance, navigation, and control for vehicle platforms hosting a suite of onboard payload sensors. This paper outlines related research into the field of payload directed flight; and outlines requirements and operating concepts for payload directed flight systems based on identified needs from the scientific literature.'

Payload accommodations. Avionics payload support architecture

NASA Technical Reports Server (NTRS)

Creasy, Susan L.; Levy, C. D.

1990-01-01

Concepts for vehicle and payload avionics architectures for future NASA programs, including the Assured Shuttle Access program, Space Station Freedom (SSF), Shuttle-C, Advanced Manned Launch System (AMLS), and the Lunar/Mars programs are discussed. Emphasis is on the potential available to increase payload services which will be required in the future, while decreasing the operational cost/complexity by utilizing state of the art advanced avionics systems and a distributed processing architecture. Also addressed are the trade studies required to determine the optimal degree of vehicle (NASA) to payload (customer) separation and the ramifications of these decisions.

STS-47 Payload Specialist Mohri parasails during Homestead AFB water training

NASA Technical Reports Server (NTRS)

1990-01-01

STS-47 Endeavour, Orbiter Vehicle (OV) 105, Payload Specialist Mamoru Mohri parasails during a special survival training course hosted by Homestead Air Force Base (AFB) in Florida. Mohri simulates a paraglide into water. The exercise was part of an overall course on water survival, attended by the STS-47 prime and alternate (backup) payload specialists shortly after they were announced for the scheduled summer of 1992 Spacelab Japan (SLJ) mission. Mohri represents the National Space Development Agency of Japan (NASDA).

TMA Chemical Release Payloads for Stratospheric Wind Measurements Auroral E Program and Related Programs

DTIC Science & Technology

1982-03-15

this work was to provide a piston tank filled with trimethyl aluminum for release as a trail in the upper atmosphere. This payload was launched from the...trail payloads. II. PAYLOAD DESCRIPTION The payload consists of a programmer section with plumbing and a piston tank section. The outer shell of the...payload is the wall of the piston tank . The liquid side of the piston tank is filled with 20 pounds of tri- methyl- aluminum (TMA). After filling the

KSC-98pc1185

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- Inside the Payload Changeout Room (PCR) in the Rotating Service Structure (RSS) at Launch Pad 39-B, technicians in clean suits move the payloads for mission STS-95 to the payload bay of Space Shuttle Discovery. At the top of the RSS is the Spacehab module; below it are the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and the International Extreme Ultraviolet Hitchhiker (IEH-3). The PCR is an environmentally controlled facility with seals around the mating surface that fit against the orbiter or payload canister and permit the payload bay or canister doors to be opened and cargo removed without exposing it to outside air and contaminants. Payloads are installed vertically in the orbiter using the extendable payload ground handling mechanism. Fixed and extendable work platforms provide work access in the PCR. The SPACEHAB single module involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Mission STS-95 is scheduled to launch Oct. 29, 1998

NH11B-1726: FrankenRaven: A New Platform for Remote Sensing

NASA Technical Reports Server (NTRS)

Dahlgren, Robert; Fladeland, Matthew M.; Pinsker, Ethan A.; Jasionowicz, John P.; Jones, Lowell L.; Pscheid, Matthew J.

2016-01-01

Small, modular aircraft are an emerging technology with a goal to maximize flexibility and enable multi-mission support. This reports the progress of an unmanned aerial system (UAS) project conducted at the NASA Ames Research Center (ARC) in 2016. This interdisciplinary effort builds upon the success of the 2014 FrankenEye project to apply rapid prototyping techniques to UAS, to develop a variety of platforms to host remote sensing instruments. In 2016, ARC received AeroVironment RQ-11A and RQ-11B Raven UAS from the US Department of the Interior, Office of Aviation Services. These aircraft have electric propulsion, a wingspan of roughly 1.3m, and have demonstrated reliability in challenging environments. The Raven airframe is an ideal foundation to construct more complex aircraft, and student interns using 3D printing were able to graft multiple Raven wings and fuselages into FrankenRaven aircraft. Aeronautical analysis shows that the new configuration has enhanced flight time, payload capacity, and distance compared to the original Raven. The FrankenRaven avionics architecture replaces the mil-spec avionics with COTS technology based upon the 3DR Pixhawk PX4 autopilot with a safety multiplexer for failsafe handoff to 2.4 GHz RC control and 915 MHz telemetry. This project demonstrates how design reuse, rapid prototyping, and modular subcomponents can be leveraged into flexible airborne platforms that can host a variety of remote sensing payloads and even multiple payloads. Modularity advances a new paradigm: mass-customization of aircraft around given payload(s). Multi-fuselage designs are currently under development to host a wide variety of payloads including a zenith-pointing spectrometer, a magnetometer, a multi-spectral camera, and a RGB camera. After airworthiness certification, flight readiness review, and test flights are performed at Crows Landing airfield in central California, field data will be taken at Kilauea volcano in Hawaii and other locations.

FrankenRaven: A New Platform for Remote Sensing

NASA Astrophysics Data System (ADS)

Dahlgren, R. P.; Fladeland, M. M.; Pinsker, E. A.; Jasionowicz, J. P.; Jones, L. L.; Mosser, C. D.; Pscheid, M. J.; Weidow, N. L.; Kelly, P. J.; Kern, C.; Werner, C. A.; Johnson, M. S.

2016-12-01

Small, modular aircraft are an emerging technology with a goal to maximize flexibility and enable multi-mission support. This reports the progress of an unmanned aerial system (UAS) project conducted at the NASA Ames Research Center (ARC) in 2016. This interdisciplinary effort builds upon the success of the 2014 FrankenEye project to apply rapid prototyping techniques to UAS, to develop a variety of platforms to host remote sensing instruments. In 2016, ARC received AeroVironment RQ-11A and RQ-11B Raven UAS from the US Department of the Interior, Office of Aviation Services. These aircraft have electric propulsion, a wingspan of roughly 1.3m, and have demonstrated reliability in challenging environments. The Raven airframe is an ideal foundation to construct more complex aircraft, and student interns using 3D printing were able to graft multiple Raven wings and fuselages into "FrankenRaven" aircraft. Aeronautical analysis shows that the new configuration has enhanced flight time, payload capacity, and distance compared to the original Raven. The FrankenRaven avionics architecture replaces the mil-spec avionics with COTS technology based upon the 3DR Pixhawk PX4 autopilot with a safety multiplexer for failsafe handoff to 2.4 GHz RC control and 915 MHz telemetry. This project demonstrates how design reuse, rapid prototyping, and modular subcomponents can be leveraged into flexible airborne platforms that can host a variety of remote sensing payloads and even multiple payloads. Modularity advances a new paradigm: mass-customization of aircraft around given payload(s). Multi-fuselage designs are currently under development to host a wide variety of payloads including a zenith-pointing spectrometer, a magnetometer, a multi-spectral camera, and a RGB camera. After airworthiness certification, flight readiness review, and test flights are performed at Crows Landing airfield in central California, field data will be taken at Kilauea volcano in Hawaii and other locations.

Scheduling Algorithm for Mission Planning and Logistics Evaluation (SAMPLE). Volume 2: Mission payloads subsystem description

NASA Technical Reports Server (NTRS)

Dupnick, E.; Wiggins, D.

1980-01-01

The scheduling algorithm for mission planning and logistics evaluation (SAMPLE) is presented. Two major subsystems are included: The mission payloads program; and the set covering program. Formats and parameter definitions for the payload data set (payload model), feasible combination file, and traffic model are documented.

Ares V: Shifting the Payload Design Paradigm

NASA Technical Reports Server (NTRS)

Sumrall, Phil; Creech, Steve; Cockrell, Charles E.

2009-01-01

NASA is designing the Ares V heavy-lift cargo launch vehicle to send more crew and cargo to more places on the lunar surface than the 1960s-era Saturn V and to provide ongoing support for a permanent lunar outpost. This uncrewed cargo vehicle is designed to operate together with the Ares I crew vehicle (Figure 1). In addition to this role, however, its unmatched mass and volume capability represent a national asset for exploration, science, and commerce. The Ares V also enables or significantly enhances a large class of space missions not thought possible by scientists and engineers since the Saturn V program ended over 30 years ago. Compared to current systems, it will offer approximately five times the mass and volume to most orbits and locations. This should allow prospective mission planners to build robust payloads with margins that are three to five times the industry norm. The space inside the planned payload shroud has enough usable volume to launch the volumetric equivalent of approximately 10 Apollo Lunar Modules or approximately five equivalent Hubble Space Telescopes. This mass and volume capability to low-Earth orbit (LEO) enables a host of new scientific and observation platforms, such as telescopes, satellites, planetary and solar missions, as well as being able to provide the lift for future large in-space infrastructure missions, such as space based solar power and mining, Earth asteroid defense, propellant depots, etc. In addition, payload designers may also have the option of simplifying their designs or employing Ares V s payload as dumb mass to reduce technical and operational risk. The Ares V team is engaging the potential payload community now, two to three years before System Requirements Review (SRR), in order to better understand the additional requirements from the payload community that could be accommodated in the Ares V design in its conceptual phase. This paper will discuss the Ares V reference mission and capability, as well as its potential to perform other missions in the future.

Space program payload costs and their possible reduction

NASA Technical Reports Server (NTRS)

Vanvleck, E. M.; Deerwester, J. M.; Norman, S. M.; Alton, L. R.

1973-01-01

The possible ways by which NASA payload costs might be reduced in the future were studied. The major historical reasons for payload costs being as they were, and if there are technologies (hard and soft), or criteria for technology advances, that could significantly reduce total costs of payloads were examined. Payload costs are placed in historical context. Some historical cost breakdowns for unmanned NASA payloads are presented to suggest where future cost reductions could be most significant. Space programs of NOAA, DoD and COMSAT are then examined to ascertain if payload reductions have been brought about by the operational (as opposed to developmental) nature of such programs, economies of scale, the ability to rely on previously developed technology, or by differing management structures and attitudes. The potential impact was investigated of NASA aircraft-type management on spacecraft program costs, and some examples relating previous costs associated with aircraft costs on the one hand and manned and unmanned costs on the other are included.

The ARIEL Instrument Control Unit design - For the M4 Mission Selection Review of the ESA's Cosmic Vision Program

NASA Astrophysics Data System (ADS)

Focardi, M.; Pace, E.; Farina, M.; Di Giorgio, A. M.; Ferrer, J. Colomé; Ribas, I.; Roig, C. Sierra; Bote, L. Gesa; Morales, J. C.; Amiaux, J.; Cara, C.; Augurés, J. L.; Pascale, E.; Morgante, G.; Da Deppo, V.; Pancrazzi, M.; Noce, V.; Pezzuto, S.; Frericks, M.; Zwart, F.; Bishop, G.; Middleton, K.; Eccleston, P.; Micela, G.; Tinetti, G.

2017-11-01

The Atmospheric Remote-sensing Infrared Exoplanet Large-survey mission (ARIEL) (Tinetti et al. 2017) is one of the three present candidates for the ESA M4 (the fourth medium mission) launch opportunity. The proposed Payload (Eccleston et al. 2017; Morgante et al. 2017; Da Deppo et al. 2017) will perform a large unbiased spectroscopic survey from space concerning the nature of exoplanets atmospheres and their interiors to determine the key factors affecting the formation and evolution of planetary systems. ARIEL will observe a large number (> 500) of warm and hot transiting gas giants, Neptunes and super-Earths around a wide range of host star types, targeting planets hotter than 600 K to take advantage of their well-mixed atmospheres. It will exploit primary and secondary transits spectroscopy in the 1.2 - 8μ m spectral range and broad-band photometry in the optical and Near IR (NIR). The main instrument of the ARIEL Payload is the IR Spectrometer (AIRS) (Amiaux et al. 2017) providing low-resolution spectroscopy in two IR channels: C h a n n e l 0 (C H 0) for the 1.95 - 3.90μ m band and C h a n n e l 1 (C H 1) for the 3.90 - 7.80μ m range. It is located at the intermediate focal plane of the telescope (Da Deppo et al. 2016, 2017, 2017) and common optical system and it hosts two IR sensors and two cold front-end electronics (CFEE) for detectors readout, a well defined process calibrated for the selected target brightness and driven by the Payload's Instrument Control Unit (ICU).

Concepts for Cost-Effective Enhanced Cryosat Continuity: Opportunity in the Iridium PRIME Context

NASA Astrophysics Data System (ADS)

Le Roy, Y.; Caubet, E.; Silverstrin, P.; Legrand, C.

2016-08-01

The Iridium-PRIME offer, recently initiated by the Iridium company, consists in hosting payloads on customized low cost Iridium-NEXT platforms on which the main telecom mission antenna (L-band) is removed. This leaves significant resources in terms of mass, volume and power consumption to host up to three payloads on these customized platforms. The Iridium-PRIME satellites will be inserted in the Iridium-NEXT constellation to take benefit of the low cost operation service (command, control and data telemetry through the life time of the Iridium-PRIME mission). Given the synergy between schedules of the Iridium-PRIME program (launches starting around 2020) and of a possible CryoSat Follow-On (FO) mission (launch around 2022) and the adequacy of the available on-board resources for such a mission, ESA tasked Thales Alenia Space, as responsible for the SIRAL radar instrument of the currently in-orbit CryoSat mission, to study the feasibility of a concept for enhanced continuity of CryoSat on an Iridium- PRIME satellite as potential low-cost fast-track solution. The study aimed to define a cost-effective topographic payload including not only the SIRAL radar but also the necessary sub-systems to retrieve the SIRAL antenna baseline attitude (star trackers) with high accuracy and to perform a Precise Orbit Determination (POD). All these aspects are presented in this paper. In addition, possible evolutions/improvements of the Ku-band radar instrument were analysed and are presented: adding a Ka-band nadir measurement capability and a Ku-band or Ka-band wide swath mode measurement capability. The transmission issue for the SIRAL science data is also discussed in the paper.

Space Shuttle utilization characteristics with special emphasis on payload design, economy of operation and effective space exploitation

NASA Technical Reports Server (NTRS)

Turner, D. N.

1981-01-01

The reusable manned Space Shuttle has made new and innovative payload planning a reality and opened the door to a variety of payload concepts formerly unavailable in routine space operations. In order to define the payload characteristics and program strategies, current Shuttle-oriented programs are presented: NASA's Space Telescope, the Long Duration Exposure Facility, the West German Shuttle Pallet Satellite, and the Goddard Space Flight Center's Multimission Modular Spacecraft. Commonality of spacecraft design and adaptation for specific mission roles minimizes payload program development and STS integration costs. Commonality of airborne support equipment assures the possibility of multiple program space operations with the Shuttle. On-orbit maintenance and repair was suggested for the module and system levels. Program savings from 13 to over 50% were found obtainable by the Shuttle over expendable launch systems, and savings from 17 to 45% were achievable by introducing reuse into the Shuttle-oriented programs.

Scheduling Algorithm for Mission Planning and Logistics Evaluation (SAMPLE). Volume 3: The GREEDY algorithm

NASA Technical Reports Server (NTRS)

Dupnick, E.; Wiggins, D.

1980-01-01

The functional specifications, functional design and flow, and the program logic of the GREEDY computer program are described. The GREEDY program is a submodule of the Scheduling Algorithm for Mission Planning and Logistics Evaluation (SAMPLE) program and has been designed as a continuation of the shuttle Mission Payloads (MPLS) program. The MPLS uses input payload data to form a set of feasible payload combinations; from these, GREEDY selects a subset of combinations (a traffic model) so all payloads can be included without redundancy. The program also provides the user a tutorial option so that he can choose an alternate traffic model in case a particular traffic model is unacceptable.

Operations analysis (study 2.1). Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Wolfe, R. R.

1975-01-01

Subjects related to future STS operations concepts were investigated. The majority of effort was directed at assessing the benefits of automated space servicing concepts as related to improvements in payload procurement and shuttle utilization. Another subject was directed at understanding shuttle upper stage software development and recurring costs relative to total program projections. Space serving of automated payloads is addressed by examining the broad spectrum of payload applications with the belief that shared logistic operations will be a major contributor to reduction of future program costs. However, there are certain requirements for support of payload operations, such as availability of the payload, that may place demands upon the shuttle fleet. Because future projections of the NASA Mission Model are only representative of the payload traffic, it is important to recognize that it is the general character of operations that is significant rather than service to any single payload program.

System cost performance analysis (study 2.3). Volume 1: Executive summary. [unmanned automated payload programs and program planning

NASA Technical Reports Server (NTRS)

Campbell, B. H.

1974-01-01

A study is described which was initiated to identify and quantify the interrelationships between and within the performance, safety, cost, and schedule parameters for unmanned, automated payload programs. The result of the investigation was a systems cost/performance model which was implemented as a digital computer program and could be used to perform initial program planning, cost/performance tradeoffs, and sensitivity analyses for mission model and advanced payload studies. Program objectives and results are described briefly.

KSC-98pc1183

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER, FLA. -- Inside the Payload Changeout Room (PCR) in the Rotating Service Structure (RSS) at Launch Pad 39-B, technicians in clean suits and tethers prepare to move the payloads for mission STS-95 through the open doors of the payload bay (right) of Space Shuttle Discovery. At the top of the RSS is the Spacehab module; below it are the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and International Extreme Ultraviolet Hitchhiker (IEH-3). The PCR is an environmentally controlled facility with seals around the mating surface that fit against the orbiter or payload canister and permit the payload bay or canister doors to be opened and cargo removed without exposing it to outside air and contaminants. Payloads are installed vertically in the orbiter using the extendable payload ground handling mechanism. Fixed and extendable work platforms provide work access in the PCR. The SPACEHAB single module involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Mission STS-95 is scheduled to launch Oct. 29, 1998

KSC-98pc1184

NASA Image and Video Library

1998-09-30

KENNEDY SPACE CENTER,FLA. -- Inside the Payload Changeout Room (PCR) in the Rotating Service Structure (RSS) at Launch Pad 39-B, technicians in clean suits and tethers prepare to move the payloads for mission STS-95 through the open doors of the payload bay (left) of Space Shuttle Discovery. At the top of the RSS is the Spacehab module; below it are the Spartan solar-observing deployable spacecraft, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and the International Extreme Ultraviolet Hitchhiker (IEH-3). The PCR is an environmentally controlled facility with seals around the mating surface that fit against the orbiter or payload canister and permit the payload bay or canister doors to be opened and cargo removed without exposing it to outside air and contaminants. Payloads are installed vertically in the orbiter using the extendable payload ground handling mechanism. Fixed and extendable work platforms provide work access in the PCR. The SPACEHAB single module involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Mission STS-95 is scheduled to launch Oct. 29, 1998

Commercial Instrumentation Technology Associates Inc. Biomedical Experiments Payload (CIBX-2)

NASA Technical Reports Server (NTRS)

Morrison, Dennis; Edmundson, Allen; Robinson, Keith (Technical Monitor)

2002-01-01

Experiments to find solutions for a range of biomedical issues are being hosted by the Commercial Instrumentation Technology Associates Inc. (ITA) Biomedical Experiments (CIBX-2) payload. This research encompasses more than 20 separate experiments including cancer research, commercial experiments and hands-on student experiments from 10 schools as part of ITA's ongoing University Among the Stars program. Protein crystal growth experiments will address the structure of urokinase - a protein that has been identified as a key enzyme in the spread of brain, lung, colon, prostate and breast cancers. Crystals of Bence Jones, a protein associated with bone cancer, will also be grown. Understanding their structures may help scientists develop treatments. In a related area, the Microencapsulation of Drugs (MEPS) is an anti-cancer drug delivery system, based on a 10-year partnership with NASA's Johnson Space Center. On this mission, the co-encapsulation of antibodies and immune stimulants will be made in submicron microcapsules to target pulmonary and bacterial infections.

Using Distributed Operations to Enable Science Research on the International Space Station

NASA Technical Reports Server (NTRS)

Bathew, Ann S.; Dudley, Stephanie R. B.; Lochmaier, Geoff D.; Rodriquez, Rick C.; Simpson, Donna

2011-01-01

In the early days of the International Space Station (ISS) program, and as the organization structure was being internationally agreed upon and documented, one of the principal tenets of the science program was to allow customer-friendly operations. One important aspect of this was to allow payload developers and principle investigators the flexibility to operate their experiments from either their home sites or distributed telescience centers. This telescience concept was developed such that investigators had several options for ISS utilization support. They could operate from their home site, the closest telescience center, or use the payload operations facilities at the Marshall Space Flight Center in Huntsville, Alabama. The Payload Operations Integration Center (POIC) processes and structures were put into place to allow these different options to its customers, while at the same time maintain its centralized authority over NASA payload operations and integration. For a long duration space program with many scientists, researchers, and universities expected to participate, it was imperative that the program structure be in place to successfully facilitate this concept of telescience support. From a payload control center perspective, payload science operations require two major elements in order to make telescience successful within the scope of the ISS program. The first element is decentralized control which allows the remote participants the freedom and flexibility to operate their payloads within their scope of authority. The second element is a strong ground infrastructure, which includes voice communications, video, telemetry, and commanding between the POIC and the payload remote site. Both of these elements are important to telescience success, and both must be balanced by the ISS program s documented requirements for POIC to maintain its authority as an integration and control center. This paper describes both elements of distributed payload operations and discusses the benefits and drawbacks.

Enhancing the NASA Expendable Launch Vehicle Payload Safety Review Process Through Program Activities

NASA Technical Reports Server (NTRS)

Palo, Thomas E.

2007-01-01

The safety review process for NASA spacecraft flown on Expendable Launch Vehicles (ELVs) has been guided by NASA-STD 8719.8, Expendable Launch Vehicle Payload Safety Review Process Standard. The standard focused primarily on the safety approval required to begin pre-launch processing at the launch site. Subsequent changes in the contractual, technical, and operational aspects of payload processing, combined with lessons-learned supported a need for the reassessment of the standard. This has resulted in the formation of a NASA ELV Payload Safety Program. This program has been working to address the programmatic issues that will enhance and supplement the existing process, while continuing to ensure the safety of ELV payload activities.

Detecting Payload Attacks on Programmable Logic Controllers (PLCs)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Yang, Huan

Programmable logic controllers (PLCs) play critical roles in industrial control systems (ICS). Providing hardware peripherals and firmware support for control programs (i.e., a PLC’s “payload”) written in languages such as ladder logic, PLCs directly receive sensor readings and control ICS physical processes. An attacker with access to PLC development software (e.g., by compromising an engineering workstation) can modify the payload program and cause severe physical damages to the ICS. To protect critical ICS infrastructure, we propose to model runtime behaviors of legitimate PLC payload program and use runtime behavior monitoring in PLC firmware to detect payload attacks. By monitoring themore » I/O access patterns, network access patterns, as well as payload program timing characteristics, our proposed firmware-level detection mechanism can detect abnormal runtime behaviors of malicious PLC payload. Using our proof-of-concept implementation, we evaluate the memory and execution time overhead of implementing our proposed method and find that it is feasible to incorporate our method into existing PLC firmware. In addition, our evaluation results show that a wide variety of payload attacks can be effectively detected by our proposed approach. The proposed firmware-level payload attack detection scheme complements existing bumpin- the-wire solutions (e.g., external temporal-logic-based model checkers) in that it can detect payload attacks that violate realtime requirements of ICS operations and does not require any additional apparatus.« less

NASA ELV Payload Safety Program Information Exchange

NASA Technical Reports Server (NTRS)

Staubus, Cal; Palo, Tom; Dook, Mike; Donovan, Shawn

2007-01-01

This presentation details the Expendable Launch Vehicle (ELV) Payload Safety Program in its development and plan for implementation. It is an overview of the program's policies, process and requirements.

KSC-98pc1038

NASA Image and Video Library

1998-09-04

Workers watch as the Hubble Space Telescope Orbiting Systems Test (HOST)is lowered onto a workstand in the Space Shuttle Processing Facility. To the right can be seen the Rack Insertion Device and Leonardo, a Multi-Purpose Logistics Module. The HOST platform, one of the payloads on the STS-95 mission, is carrying four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an earth orbiting environment. The STS-95 mission is scheduled to launch Oct. 29. It will carry three other payloads: the Spartan solar-observing deployable spacecraft, the International Extreme Ultraviolet Hitchhiker, and the SPACEHAB single module with experiments on space flight and the aging process

The post Challenger era Get Away Special program January 1992

NASA Technical Reports Server (NTRS)

Prouty, Clarke

1992-01-01

The Get Away Special (GAS) program is described in terms of the changes that have taken place in both NASA and the GAS itself. Attention is given to the relationships developed between NASA and GAS customers in the context of programmatic and technical issues. The background of the GAS program is outlined with reference given to policy publications, the design of the Flight Verification Payload, and the first GAS payload launched. A review process is described that facilitates the management of the payloads through flight certification. The GAS Bridge was developed to carry up to 12 payloads simultaneously, and the recent period of GAS inactivity is explained. A price increase is introduced for future GAS payloads with negotiable access to optional services, and the ease and accessibility of the GAS programs for private experiments is emphasized.

A review of Spacelab mission management approach

NASA Technical Reports Server (NTRS)

Craft, H. G., Jr.

1979-01-01

The Spacelab development program is a joint undertaking of the NASA and ESA. The paper addresses the initial concept of Spacelab payload mission management, the lessons learned, and modifications made as a result of the actual implementation of Spacelab Mission 1. The discussion covers mission management responsibilities, program control, science management, payload definition and interfaces, integrated payload mission planning, integration requirements, payload specialist training, payload and launch site integration, payload flight/mission operations, and postmission activities. After 3.5 years the outlined overall mission manager approach has proven to be most successful. The approach does allow the mission manager to maintain the lowest overall mission cost.

Design guide for space shuttle low-cost payloads

NASA Technical Reports Server (NTRS)

1971-01-01

A handbook is presented which delineates the principles of the new low-cost design methodology for designers of unmanned payloads to be carried by the space shuttle. The basic relationships between payload designs and program cost effects are discussed, and some concepts for designing low-cost payloads and implementing low-cost programs are given. The data are summarized from a payloads effects study of three unmanned earth satellites (OAO, a syneq orbiter, and a small research satellite), and the earth satellite design is emphasized. Brief summaries of space shuttle and space tug performance, environmental, and interface data pertinent to low-cost payload concepts are included.

Hosting a Fourier Transform Spectrometer (FTS) on CubeSat Spacecraft Platforms for Global Measurements of Three-Dimensional Winds

NASA Astrophysics Data System (ADS)

Scott, D. K.; Neilsen, T. L.; Weston, C.; Frazier, C.; Smith, T.; Shumway, A.

2015-12-01

Global measurements of vertically-resolved atmospheric wind profiles offer the potential for improved weather forecasts and superior predictions of atmospheric wind patterns. A small-satellite constellation that uses a Fourier Transform Spectrometer (FTS) instrument onboard 12U CubeSats can provide measurements of global tropospheric wind profiles from space at a very low cost. These small satellites are called FTS CubeSats. This presentation will describe a spacecraft concept that provides a stable, robust platform to host the FTS payload. Of importance to the payload are power, data, station keeping, thermal, and accommodations that enable high spectral measurements to be made from a LEO orbit. The spacecraft concept draws on Space Dynamics Laboratory (SDL) heritage and the recent success of the Dynamic Ionosphere Cubesat Experiment (DICE) and HyperAngular Rainbow Polarimeter (HARP) missions. Working with team members, SDL built a prototype observatory (spacecraft and payload) for testing and proof of concept.

Software for Remote Monitoring of Space-Station Payloads

NASA Technical Reports Server (NTRS)

Schneider, Michelle; Lippincott, Jeff; Chubb, Steve; Whitaker, Jimmy; Gillis, Robert; Sellers, Donna; Sims, Chris; Rice, James

2003-01-01

Telescience Resource Kit (TReK) is a suite of application programs that enable geographically dispersed users to monitor scientific payloads aboard the International Space Station (ISS). TReK provides local ground support services that can simultaneously receive, process, record, playback, and display data from multiple sources. TReK also provides interfaces to use the remote services provided by the Payload Operations Integration Center which manages all ISS payloads. An application programming interface (API) allows for payload users to gain access to all data processed by TReK and allows payload-specific tools and programs to be built or integrated with TReK. Used in conjunction with other ISS-provided tools, TReK provides the ability to integrate payloads with the operational ground system early in the lifecycle. This reduces the potential for operational problems and provides "cradle-to-grave" end-to-end operations. TReK contains user guides and self-paced tutorials along with training applications to allow the user to become familiar with the system.

The 1973 NASA payload model: Space opportunities 1973 - 1991. [characteristics of payloads and requirements of user community

NASA Technical Reports Server (NTRS)

1973-01-01

The tables of schedules and descriptions which portray the 1973 NASA Payload Model are presented. The schedules cover all NASA programs and the anticipated requirements of the user community, not including the Department of Defense, for the 1973 to 1991 period. The descriptions give an indication of what the payload is expected to accomplish, its characteristics, and where it is going. The payload flight schedules shown for each of the discipline areas indicate the time frame in which individual payloads will be launched, serviced, or retrieved. These do not necessarily constitute shuttle flights, however, since more than one payload can be flown on a single shuttle flight depending on size, weight, orbital destination, and the suitability of combining them. The weight, dimension, and destination data represent approximations of the payload characteristics as estimated by the Program Offices. Payload codes are provided for easy correlation between the schedules and descriptions of the Payload Model and subsequent documentation which may reference this model.

STS-107 payload arrangement

NASA Technical Reports Server (NTRS)

2001-01-01

Thisdiagram shows the general arrangement of the payloads to be carried by the multidisciplinary STS-107 Research-1 Space Shuttle mission in 2002. The Spacehab module will host experiments that require direct operation by the flight crew. Others with special requirements will be on the GAS Bridge Assembly sparning the payload bay. The Extended Duration Orbiter kit carries additional oxygen and hydrogen for the electricity-producing fuel cells. Research-1 experiments will cover space biology, life science, microgravity research, and commercial space product development, research sponsored by NASA's Office of Biological and Physical Research. An alternative view with callouts is available at 0101764.

STS-107 payload arrangement

NASA Technical Reports Server (NTRS)

2001-01-01

This diagram shows the general arrangement of the payloads to be carried by the multidisciplinary STS-107 Research-1 Space Shuttle mission in 2002. The Spacehab module will host experiments that require direct operation by the flight crew. Others with special requirements will be on the GAS Bridge Assembly sparning the payload bay. The Extended Duration Orbiter kit carries additional oxygen and hydrogen for the electricity-producing fuel cells. Research-1 experiments will cover space biology, life science, microgravity research, and commercial space product development, research sponsored by NASA's Office of Biological and Physical Research. An alternative view without callouts is available at 0101765.

Innovative approach for low-cost quick-access small payload missions

NASA Astrophysics Data System (ADS)

Friis, Jan W., Jr.

2000-11-01

A significant part of the burgeoning commercial space industry is placing an unprecedented number of satellites into low earth orbit for a variety of new applications and services. By some estimates the commercial space industry now exceeds that of government space activities. Yet the two markets remain largely separate, with each deploying dedicated satellites and infrastructure for their respective missions. One commercial space firm, Final Analysis, has created a new program wherein either government, scientific or new technology payloads can be integrated on a commercial spacecraft on commercial satellites for a variety of mission scenarios at a fraction of the cost of a dedicated mission. NASA has recognized the advantage of this approach, and has awarded the Quick Ride program to provide frequent, low cost flight opportunities for small independent payloads aboard the Final Analysis constellation, and investigators are rapidly developing science programs that conform to the proposed payload accommodations envelope. Missions that were not feasible using dedicated launches are now receiving approval under the lower cost Quick Ride approach. Final Analysis has dedicated ten out of its thirty-eight satellites in support of the Quick Ride efforts. The benefit of this type of space access extend beyond NASA science programs. Commercial space firms can now gain valuable flight heritage for new technology and satellite product offerings. Further, emerging international space programs can now place a payload in orbit enabling the country to allocate its resources against the payload and mission requirements rather htan increased launch costs of a dedicated spacecraft. Finally, the low cost nature provides University-based research educational opportunities previously out of the reach of most space-related budgets. This paper will describe the motivation, benefits, technical features, and program costs of the Final Analysis secondary payload program. Payloads can be accommodated on up to thirty-eight separate satellites. Since the secondary payloads will fly on satellites designed for global wireless data services, each user can utilize low cost communication system already in place for sending and retrieving digital information from its payload.

Space Product Development (SPD)

NASA Image and Video Library

2003-01-12

Experiments to seek solutions for a range of biomedical issues are at the heart of several investigations that will be hosted by the Commercial Instrumentation Technology Associates (ITA), Inc. Biomedical Experiments (CIBX-2) payload. CIBX-2 is unique, encompassing more than 20 separate experiments including cancer research, commercial experiments, and student hands-on experiments from 10 schools as part of ITA's ongoing University Among the Stars program. This drawing depicts a cross-section of a set of Dual-Materials Dispersion Apparatus (DMDA) specimen wells, one of which can include a reverse osmosis membrane to dewater a protein solution and thus cause crystallization. Depending on individual needs, two or three wells may be used, the membrane may be absent, or other proprietary enhancements may be present. The experiments are sponsored by NASA's Space Product Development Program (SPD).

Dual-Materials Dispersion Apparatus

NASA Technical Reports Server (NTRS)

2003-01-01

Experiments to seek solutions for a range of biomedical issues are at the heart of several investigations that will be hosted by the Commercial Instrumentation Technology Associates (ITA), Inc. Biomedical Experiments (CIBX-2) payload. CIBX-2 is unique, encompassing more than 20 separate experiments including cancer research, commercial experiments, and student hands-on experiments from 10 schools as part of ITA's ongoing University Among the Stars program. This drawing depicts a cross-section of a set of Dual-Materials Dispersion Apparatus (DMDA) specimen wells, one of which can include a reverse osmosis membrane to dewater a protein solution and thus cause crystallization. Depending on individual needs, two or three wells may be used, the membrane may be absent, or other proprietary enhancements may be present. The experiments are sponsored by NASA's Space Product Development Program (SPD).

Some aerodynamic discoveries and related NACA/NASA research programs following World War 2

NASA Technical Reports Server (NTRS)

Spearman, M. L.

1984-01-01

The World War 2 time period ushered in a new era in aeronautical research and development. The air conflict during the war highlighted the need of aircraft with agility, high speed, long range, large payload capability, and in addition, introduced a new concept in air warfare through the use of guided missiles. Following the war, the influx of foreign technology, primarily German, led to rapid advances in jet propulsion and speed, and a host of new problem areas associated with high-speed flight designs were revealed. The resolution of these problems led to a rash of new design concepts and many of the lessons learned, in principle, are still effective today. In addition to the technical lessons learned related to aircraft development programs, it might also be noted that some lessons involving the political and philosophical nature of aircraft development programs are worth attention.

STS-73 Flight Day 15

NASA Technical Reports Server (NTRS)

1995-01-01

On this fifteenth day of the STS-73 sixteen day mission, the crew Cmdr. Kenneth Bowersox, Pilot Kent Rominger, Payload Specialists Albert Sacco and Fred Leslie, and Mission Specialists Kathryn Thornton, Catherine 'Cady' Coleman, and Michael Lopez-Alegria are shown hosting an in-orbit interview with various newspaper reporters from Johnson Space Center, Kennedy Space Center, and Marshall Space Flight Center via satellite hookup. The astronauts were asked questions regarding the status of the United States Microgravity Lab-2 (USML-2) experiments, their personal goals regarding their involvement in the mission, their future in the space program, and general questions about living in space. Earth views included cloud cover and a tropical storm.

Accommodations for earth-viewing payloads on the international space station

NASA Astrophysics Data System (ADS)

Park, B.; Eppler, D. B.

The design of the International Space Station (ISS) includes payload locations that are external to the pressurized environment. These external or attached payload accommodation locations will allow direct access to the space environment at the ISS orbit and direct viewing of the earth and space. NASA sponsored payloads will have access to several different types of standard external locations; the S3 Truss Sites, the Columbus External Payload Facility (EPF), and the Japanese Experiment Module Exposed Facility (JEM-EF). As the ISS Program develops, it may also be possible to locate external payloads at the P3 Truss Sites or at non-standard locations similar to the handrail-attached payloads that were flown during the MIR Program. Earth-viewing payloads may also be located within the pressurized volume of the US Lab in the Window Observational Research Facility (WORF). Payload accommodations at each of the locations will be described, as well as transport to and retrieval from the site.

ISS Payload Operations: The Need for and Benefit of Responsive Planning

NASA Technical Reports Server (NTRS)

Nahay, Ed; Boster, Mandee

2000-01-01

International Space Station (ISS) payload operations are controlled through implementation of a payload operations plan. This plan, which represents the defined approach to payload operations in general, can vary in terms of level of definition. The detailed plan provides the specific sequence and timing of each component of a payload's operations. Such an approach to planning was implemented in the Spacelab program. The responsive plan provides a flexible approach to payload operations through generalization. A responsive approach to planning was implemented in the NASA/Mir Phase 1 program, and was identified as a need during the Skylab program. The current approach to ISS payload operations planning and control tends toward detailed planning, rather than responsive planning. The use of detailed plans provides for the efficient use of limited resources onboard the ISS. It restricts flexibility in payload operations, which is inconsistent with the dynamic nature of the ISS science program, and it restricts crew desires for flexibility and autonomy. Also, detailed planning is manpower intensive. The development and implementation of a responsive plan provides for a more dynamic, more accommodating, and less manpower intensive approach to planning. The science program becomes more dynamic and responsive as the plan provides flexibility to accommodate real-time science accomplishments. Communications limitations and the crew desire for flexibility and autonomy in plan implementation are readily accommodated with responsive planning. Manpower efficiencies are accomplished through a reduction in requirements collection and coordination, plan development, and maintenance. Through examples and assessments, this paper identifies the need to transition from detailed to responsive plans for ISS payload operations. Examples depict specific characteristics of the plans. Assessments identify the following: the means by which responsive plans accommodate the dynamic nature of science programs and the crew desire for flexibility; the means by which responsive plans readily accommodate ISS communications constraints; manpower efficiencies to be achieved through use of responsive plans; and the implications of responsive planning relative to resource utilization efficiency.

Fast Kalman Filtering for Relative Spacecraft Position and Attitude Estimation for the Raven ISS Hosted Payload

NASA Technical Reports Server (NTRS)

Galante, Joseph M.; Van Eepoel, John; D'Souza, Chris; Patrick, Bryan

2016-01-01

The Raven ISS Hosted Payload will feature several pose measurement sensors on a pan/tilt gimbal which will be used to autonomously track resupply vehicles as they approach and depart the International Space Station. This paper discusses the derivation of a Relative Navigation Filter (RNF) to fuse measurements from the different pose measurement sensors to produce relative position and attitude estimates. The RNF relies on relative translation and orientation kinematics and careful pose sensor modeling to eliminate dependence on orbital position information and associated orbital dynamics models. The filter state is augmented with sensor biases to provide a mechanism for the filter to estimate and mitigate the offset between the measurements from different pose sensors

Fast Kalman Filtering for Relative Spacecraft Position and Attitude Estimation for the Raven ISS Hosted Payload

NASA Technical Reports Server (NTRS)

Galante, Joseph M.; Van Eepoel, John; D' Souza, Chris; Patrick, Bryan

2016-01-01

The Raven ISS Hosted Payload will feature several pose measurement sensors on a pan/tilt gimbal which will be used to autonomously track resupply vehicles as they approach and depart the International Space Station. This paper discusses the derivation of a Relative Navigation Filter (RNF) to fuse measurements from the different pose measurement sensors to produce relative position and attitude estimates. The RNF relies on relative translation and orientation kinematics and careful pose sensor modeling to eliminate dependence on orbital position information and associated orbital dynamics models. The filter state is augmented with sensor biases to provide a mechanism for the filter to estimate and mitigate the offset between the measurements from different pose sensors.

Rapid prototyping and AI programming environments applied to payload modeling

NASA Technical Reports Server (NTRS)

Carnahan, Richard S., Jr.; Mendler, Andrew P.

1987-01-01

This effort focused on using artificial intelligence (AI) programming environments and rapid prototyping to aid in both space flight manned and unmanned payload simulation and training. Significant problems addressed are the large amount of development time required to design and implement just one of these payload simulations and the relative inflexibility of the resulting model to accepting future modification. Results of this effort have suggested that both rapid prototyping and AI programming environments can significantly reduce development time and cost when applied to the domain of payload modeling for crew training. The techniques employed are applicable to a variety of domains where models or simulations are required.

Payload Documentation Enhancement Project

NASA Technical Reports Server (NTRS)

Brown, Betty G.

1999-01-01

In late 1998, the Space Shuttle Program recognized a need to revitalize its payload accommodations documentation. As a result a payload documentation enhancement project was initiated to review and update payload documentation and improve the accessibility to that documentation by the Space Shuttle user community.

Orbiter/payload contamination control assessment support

NASA Technical Reports Server (NTRS)

Rantanen, R. O.; Strange, D. A.; Hetrick, M. A.

1978-01-01

The development and integration of 16 payload bay liner filters into the existing shuttle/payload contamination evaluation (SPACE) computer program is discussed as well as an initial mission profile model. As part of the mission profile model, a thermal conversion program, a temperature cycling routine, a flexible plot routine and a mission simulation of orbital flight test 3 are presented.

Small Payload Integration and Testing Project Development

NASA Technical Reports Server (NTRS)

Sorenson, Tait R.

2014-01-01

The National Aeronautics and Space Administration's (NASA) Kennedy Space Center (KSC) has mainly focused on large payloads for space flight beginning with the Apollo program to the assembly and resupply of the International Space Station using the Space Shuttle. NASA KSC is currently working on contracting manned Low Earth Orbit (LEO) to commercial providers, developing Space Launch System, the Orion program, deep space manned programs which could reach Mars, and providing technical expertise for the Launch Services Program for science mission payloads/satellites. KSC has always supported secondary payloads and smaller satellites as the launch provider; however, they are beginning to take a more active role in integrating and testing secondary payloads into future flight opportunities. A new line of business, the Small Payload Integration and Testing Services (SPLITS), has been established to provide a one stop shop that can integrate and test payloads. SPLITS will assist high schools, universities, companies and consortiums interested in testing or launching small payloads. The goal of SPLITS is to simplify and facilitate access to KSC's expertise and capabilities for small payloads integration and testing and to help grow the space industry. An effort exists at Kennedy Space Center to improve the external KSC website. External services has partnered with SPLITS as a content test bed for attracting prospective customers. SPLITS is an emerging effort that coincides with the relaunch of the website and has a goal of attracting external partnerships. This website will be a "front door" access point for all potential partners as it will contain an overview of KSC's services, expertise and includes the pertinent contact information.

Materials experiment carrier concepts definition study. Volume 2: Technical report, part 2

NASA Technical Reports Server (NTRS)

1981-01-01

A materials experiment carrier (MEC) that provides effective accommodation of the given baseline materials processing in space (MPS) payloads and demonstration of the MPS platform concept for high priority materials processing science, multidiscipline MPS investigations, host carrier for commercial MPS payloads, and system economy of orbital operations is defined. The study flow of task work is shown. Study tasks featured analysis and trades to identify the MEC system concept options.

OPEX: (Olympus Propagation EXperiment)

NASA Technical Reports Server (NTRS)

Brussaard, Gert

1988-01-01

The Olympus-1 satellite carries four distinct payloads for experimental utilization and research in the field of satellite communications: (1) the Direct Broadcasting Service (DBS) payload; (2) the Specialized Services Payload; (3) the 20/30 GHz Advanced Communications Payload; and (4) the Propagation Payload. Experimental utilization of the first three payloads involves ground transmissions to the satellite and hence sharing of available satellite time among experimenters. This is coordinated through the Olympus Utilization Program.

Predicting the payload capability of cable logging systems including the effect of partial suspension

Treesearch

Gary D. Falk

1981-01-01

A systematic procedure for predicting the payload capability of running, live, and standing skylines is presented. Three hand-held calculator programs are used to predict payload capability that includes the effect of partial suspension. The programs allow for predictions for downhill yarding and for yarding away from the yarder. The equations and basic principles...

HP-9810A calculator programs for plotting the 2-dimensional motion of cyclindrical payloads relative to the shuttle orbiter

NASA Technical Reports Server (NTRS)

Wilson, S. W.

1976-01-01

The HP-9810A calculator programs described provide the capability to generate HP-9862A plotter displays which depict the apparent motion of a free-flying cyclindrical payload relative to the shuttle orbiter body axes by projecting the payload geometry into the orbiter plane of symmetry at regular time intervals.

Data base architecture for instrument characteristics critical to spacecraft conceptual design

NASA Technical Reports Server (NTRS)

Rowell, Lawrence F.; Allen, Cheryl L.

1990-01-01

Spacecraft designs are driven by the payloads and mission requirements that they support. Many of the payload characteristics, such as mass, power requirements, communication requirements, moving parts, and so forth directly affect the choices for the spacecraft structural configuration and its subsystem design and component selection. The conceptual design process, which translates mission requirements into early spacecraft concepts, must be tolerant of frequent changes in the payload complement and resource requirements. A computer data base was designed and implemented for the purposes of containing the payload characteristics pertinent for spacecraft conceptual design, tracking the evolution of these payloads over time, and enabling the integration of the payload data with engineering analysis programs for improving the efficiency in producing spacecraft designs. In-house tools were used for constructing the data base and for performing the actual integration with an existing program for optimizing payload mass locations on the spacecraft.

Hubble Space Telescope Program on STS-95 Supported by Space Acceleration Measurement System for Free Flyers

NASA Technical Reports Server (NTRS)

Kacpura, Thomas J.

2000-01-01

John Glenn's historic return to space was a primary focus of the STS 95 space shuttle mission; however, the 83 science payloads aboard were the focus of the flight activities. One of the payloads, the Hubble Space Telescope Orbital System Test (HOST), was flown in the cargo bay by the NASA Goddard Space Flight Center. It served as a space flight test of upgrade components for the telescope before they are installed in the shuttle for the next Hubble Space Telescope servicing mission. One of the upgrade components is a cryogenic cooling system for the Near Infrared Camera and Multi-Object Spectrometer (NICMOS). The cooling is required for low noise in the receiver's sensitive electronic instrumentation. Originally, a passive system using dry ice cooled NICMOS, but the ice leaked away and must be replaced. The active cryogenic cooler can provide the cold temperatures required for the NICMOS, but there was a concern that it would create vibrations that would affect the fine pointing accuracy of the Hubble platform.

Payload crew training scheduler (PACTS) user's manual

NASA Technical Reports Server (NTRS)

Shipman, D. L.

1980-01-01

The operation of the payload specialist training scheduler (PACTS) is discussed in this user's manual which is used to schedule payload specialists for mission training on the Spacelab experiments. The PACTS program is a fully automated interactive, computerized scheduling program equipped with tutorial displays. The tutorial displays are sufficiently detailed for use by a program analyst having no computer experience. The PACTS program is designed to operate on the UNIVAC 1108 computer system, and has the capability to load output into a PDP 11/45 Interactive Graphics Display System for printing schedules. The program has the capacity to handle up to three overlapping Spacelab missions.

Manned Systems Utilization Analysis. Study 2.1: Space Servicing Pilot Program Study. [for automated payloads

NASA Technical Reports Server (NTRS)

Wolfe, R. R.

1975-01-01

Space servicing automated payloads was studied for potential cost benefits for future payload operations. Background information is provided on space servicing in general, and on a pilot flight test program in particular. An fight test is recommended to demonstrate space servicing. An overall program plan is provided which builds upon the pilot program through an interim servicing capability. A multipayload servicing concept for the time when the full capability tug becomes operational is presented. The space test program is specifically designed to provide low-cost booster vehicles and a flight test platform for several experiments on a single flight.

Lessons learned from evaluating launch-site processing problems of Space Shuttle payloads

NASA Technical Reports Server (NTRS)

Flores, Carlos A.; Heuser, Robert E.; Sales, Johnny R.; Smith, Anthony M.

1992-01-01

The authors discuss a trend analysis program that is being conducted on the problem reports written during the processing of Space Shuttle payloads at Kennedy Space Center. The program is aimed at developing lessons learned that can both improve the effectiveness of the current payload processing cycles as well as help to guide the processing strategies for Space Station Freedom. The payload processing reports from STS 26R and STS 41 are used. A two-tier evaluation activity is described, and some typical results from the tier one analyses are presented.

Quo Vadis Payload Safety?

NASA Technical Reports Server (NTRS)

Fodroci, Michael P.; Schwartz, MaryBeth

2008-01-01

As we complete the preparations for the fourth Hubble Space Telescope (HST) servicing mission, we note an anniversary approaching: it was 30 years ago in July that the first HST payload safety review panel meeting was held. This, in turn, was just over a year after the very first payload safety review, a Phase 0 review for the Tracking and Data Relay Satellite and its Inertial Upper Stage, held in June of 1977. In adapting a process that had been used in the review and certification of earlier Skylab payloads, National Aeronautics and Space Administration (NASA) engineers sought to preserve the lessons learned in the development of technical payload safety requirements, while creating a new process that would serve the very different needs of the new space shuttle program. Their success in this undertaking is substantiated by the fact that this process and these requirements have proven to be remarkably robust, flexible, and adaptable. Furthermore, the payload safety process has, to date, served us well in the critical mission of safeguarding our astronauts, cosmonauts, and spaceflight participants. Both the technical requirements and their interpretation, as well as the associated process requirements have grown, evolved, been streamlined, and have been adapted to fit multiple programs, including the International Space Station (ISS) program, the Shuttle/Mir program, and most recently the United States Constellation program. From its earliest days, it was anticipated that the payload safety process would be international in scope, and so it has been. European Space Agency (ESA), Japan Aerospace Exploration Agency (JAXA), German Space Agency (DLR), Canadian Space Agency (CSA), Russian Space Agency (RSA), and many additional countries have flown payloads on both the space shuttle and on the ISS. Our close cooperation and long-term working relationships have culminated in the franchising of the payload safety review process itself to our partners in ESA, which in turn will serve as a roadmap for extending the franchise to other Partners.

Space station payload operations scheduling with ESP2

NASA Technical Reports Server (NTRS)

Stacy, Kenneth L.; Jaap, John P.

1988-01-01

The Mission Analysis Division of the Systems Analysis and Integration Laboratory at the Marshall Space Flight Center is developing a system of programs to handle all aspects of scheduling payload operations for Space Station. The Expert Scheduling Program (ESP2) is the heart of this system. The task of payload operations scheduling can be simply stated as positioning the payload activities in a mission so that they collect their desired data without interfering with other activities or violating mission constraints. ESP2 is an advanced version of the Experiment Scheduling Program (ESP) which was developed by the Mission Integration Branch beginning in 1979 to schedule Spacelab payload activities. The automatic scheduler in ESP2 is an expert system that embodies the rules that expert planners would use to schedule payload operations by hand. This scheduler uses depth-first searching, backtracking, and forward chaining techniques to place an activity so that constraints (such as crew, resources, and orbit opportunities) are not violated. It has an explanation facility to show why an activity was or was not scheduled at a certain time. The ESP2 user can also place the activities in the schedule manually. The program offers graphical assistance to the user and will advise when constraints are being violated. ESP2 also has an option to identify conflict introduced into an existing schedule by changes to payload requirements, mission constraints, and orbit opportunities.

Study to evaluate the effect of EVA on payload systems. Volume 1: Executive summary. [project planning of space missions employing extravehicular activity as a means of cost reduction

NASA Technical Reports Server (NTRS)

Patrick, J. W.; Kraly, E. F.

1975-01-01

Programmatic benefits to payloads are examined which can result from the routine use of extravehicular activity (EVA) during space missions. Design and operations costs were compared for 13 representative baseline payloads to the costs of those payloads adapted for EVA operations. The EVA-oriented concepts developed in the study were derived from these baseline concepts and maintained mission and program objectives as well as basic configurations. This permitted isolation of cost saving factors associated specifically with incorporation of EVA in a variety of payload designs and operations. The study results were extrapolated to a total of 74 payload programs. Using appropriate complexity and learning factors, net EVA savings were extrapolated to over $551M for NASA and U.S. civil payloads for routine operations. Adding DOD and ESRO payloads increases the net estimated savings of $776M. Planned maintenance by EVA indicated an estimated $168M savings due to elimination of automated service equipment. Contingency problems of payloads were also analyzed to establish expected failure rates for shuttle payloads. The failure information resulted in an estimated potential for EVA savings of $1.9 B.

An intelligent position-specific training system for mission operations

NASA Technical Reports Server (NTRS)

Schneider, M. P.

1992-01-01

Marshall Space Flight Center's (MSFC's) payload ground controller training program provides very good generic training; however, ground controller position-specific training can be improved by including position-specific training systems in the training program. This report explains why MSFC needs to improve payload ground controller position-specific training. The report describes a generic syllabus for position-specific training systems, a range of system designs for position-specific training systems, and a generic development process for developing position-specific training systems. The report also describes a position-specific training system prototype that was developed for the crew interface coordinator payload operations control center ground controller position. The report concludes that MSFC can improve the payload ground controller training program by incorporating position-specific training systems for each ground controller position; however, MSFC should not develop position-specific training systems unless payload ground controller position experts will be available to participate in the development process.

Payload IVA training and simulation

NASA Technical Reports Server (NTRS)

Monsees, J. H.

1982-01-01

The development of a training program for the intravehicular operation of space shuttle payloads is discussed. The priorities for the program are compliance with established training standards, and accommodating changes. Simulation devices are also reviewed.

14 CFR 1214.807 - Exceptional payloads.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Spacelab Services § 1214.807 Exceptional payloads. Customers whose payloads qualify under the NASA Exceptional Program Selection Process shall reimburse NASA for Spacelab and Shuttle services on the basis indicated in the Shuttle policy. ...

14 CFR 1214.807 - Exceptional payloads.

Code of Federal Regulations, 2010 CFR

2010-01-01

... Spacelab Services § 1214.807 Exceptional payloads. Customers whose payloads qualify under the NASA Exceptional Program Selection Process shall reimburse NASA for Spacelab and Shuttle services on the basis indicated in the Shuttle policy. ...

14 CFR 1214.807 - Exceptional payloads.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Spacelab Services § 1214.807 Exceptional payloads. Customers whose payloads qualify under the NASA Exceptional Program Selection Process shall reimburse NASA for Spacelab and Shuttle services on the basis indicated in the Shuttle policy. ...

14 CFR 1214.807 - Exceptional payloads.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Spacelab Services § 1214.807 Exceptional payloads. Customers whose payloads qualify under the NASA Exceptional Program Selection Process shall reimburse NASA for Spacelab and Shuttle services on the basis indicated in the Shuttle policy. ...

Verification approach for the Shuttle/Payload Contamination Evaluation computer program - Spacelab induced environment

NASA Technical Reports Server (NTRS)

Bareiss, L. E.

1978-01-01

The paper presents a compilation of the results of a systems level Shuttle/payload contamination analysis and related computer modeling activities. The current technical assessment of the contamination problems anticipated during the Spacelab program are discussed and recommendations are presented on contamination abatement designs and operational procedures based on experience gained in the field of contamination analysis and assessment, dating back to the pre-Skylab era. The ultimate test of the Shuttle/Payload Contamination Evaluation program will be through comparison of predictions with measured levels of contamination during actual flight.

14 CFR § 1214.807 - Exceptional payloads.

Code of Federal Regulations, 2014 CFR

2014-01-01

... for Spacelab Services § 1214.807 Exceptional payloads. Customers whose payloads qualify under the NASA Exceptional Program Selection Process shall reimburse NASA for Spacelab and Shuttle services on the basis indicated in the Shuttle policy. ...

The October 1973 NASA mission model analysis and economic assessment

NASA Technical Reports Server (NTRS)

1974-01-01

Results are presented of the 1973 NASA Mission Model Analysis. The purpose was to obtain an economic assessment of using the Shuttle to accommodate the payloads and requirements as identified by the NASA Program Offices and the DoD. The 1973 Payload Model represents a baseline candidate set of future payloads which can be used as a reference base for planning purposes. The cost of implementing these payload programs utilizing the capabilities of the shuttle system is analyzed and compared with the cost of conducting the same payload effort using expendable launch vehicles. There is a net benefit of 14.1 billion dollars as a result of using the shuttle during the 12-year period as compared to using an expendable launch vehicle fleet.

Normal mode analysis of the IUS/TDRS payload in a payload canister/transporter environment

NASA Technical Reports Server (NTRS)

Meyer, K. A.

1980-01-01

Special modeling techniques were developed to simulate an accurate mathematical model of the transporter/canister/payload system during ground transport of the Inertial Upper Stage/Tracking and Data Relay Satellite (IUS/TDRS) payload. The three finite element models - the transporter, the canister, and the IUS/TDRS payload - were merged into one model and used along with the NASTRAN normal mode analysis. Deficiencies were found in the NASTRAN program that make a total analysis using modal transient response impractical. It was also discovered that inaccuracies may exist for NASTRAN rigid body modes on large models when Given's method for eigenvalue extraction is employed. The deficiencies as well as recommendations for improving the NASTRAN program are discussed.

Shuttle payload interface verification equipment study. Volume 2: Technical document, part 1

NASA Technical Reports Server (NTRS)

1976-01-01

The technical analysis is reported that was performed during the shuttle payload interface verification equipment study. It describes: (1) the background and intent of the study; (2) study approach and philosophy covering all facets of shuttle payload/cargo integration; (3)shuttle payload integration requirements; (4) preliminary design of the horizontal IVE; (5) vertical IVE concept; and (6) IVE program development plans, schedule and cost. Also included is a payload integration analysis task to identify potential uses in addition to payload interface verification.

Elliptical orbit performance computer program

NASA Technical Reports Server (NTRS)

Myler, T. R.

1981-01-01

A FORTRAN coded computer program which generates and plots elliptical orbit performance capability of space boosters for presentation purposes is described. Orbital performance capability of space boosters is typically presented as payload weight as a function of perigee and apogee altitudes. The parameters are derived from a parametric computer simulation of the booster flight which yields the payload weight as a function of velocity and altitude at insertion. The process of converting from velocity and altitude to apogee and perigee altitude and plotting the results as a function of payload weight is mechanized with the ELOPE program. The program theory, user instruction, input/output definitions, subroutine descriptions and detailed FORTRAN coding information are included.

Integrated operations payloads/fleet analysis study extension report

NASA Technical Reports Server (NTRS)

1971-01-01

An analysis of the factors affecting the cost effectiveness of space shuttle operations is presented. The subjects discussed are: (1)payload data bank, (2) program risk analysis, (3)navigation satellite program, and (4) reusable launch systems.

Payload test philosophy. [to provide confidence in Shuttle structural math models

NASA Technical Reports Server (NTRS)

Mayhew, D.

1979-01-01

Shuttle payload test philosophy is discussed with reference to testing to provide confidence in Shuttle structural math models. Particular attention is given the Shuttle quarter-scale program and the Mated Vertical Ground Vibration Test Program.

Mission management - Lessons learned from early Spacelab missions

NASA Technical Reports Server (NTRS)

Craft, H. G., Jr.

1980-01-01

The concept and the responsibilities of a mission manager approach are reviewed, and some of the associated problems in implementing Spacelab mission are discussed. Consideration is given to program control, science management, integrated payload mission planning, and integration requirements. Payload specialist training, payload and launch site integration, payload flight/mission operations, and postmission activities are outlined.

Design and Functional Validation of a Mechanism for Dual-Spinning CubeSats

NASA Technical Reports Server (NTRS)

Peters, Eric; Dave, Pratik; Kingsbury, Ryan; Marinan, Anne; Wise, Evan; Pong, Chris; Prinkey, Meghan; Cahoy, Kerri; Miller, David W.; Sklair, Devon

2014-01-01

The mission of the Micro-sized Microwave Atmospheric Satellite (MicroMAS) is to collect useful atmospheric images using a miniature passive microwave radiometer payload hosted on a low-cost CubeSat platform. In order to collect this data, the microwave radiometer payload must rotate to scan the ground-track perpendicular to the satellite's direction of travel. A custom motor assembly was developed to facilitate the rotation of the payload while allowing the spacecraft bus to remained fixed in the local-vertical, local-horizontal (LVLH) frame for increased pointing accuracy. This paper describes the mechanism used to enable this dual-spinning operation for CubeSats, and the lessons learned during the design, fabrication, integration, and testing phases of the mechanism's development lifecycle.

Historical data and analysis for the first five years of KSC STS payload processing

NASA Technical Reports Server (NTRS)

Ragusa, J. M.

1986-01-01

General and specific quantitative and qualitative results were identified from a study of actual operational experience while processing 186 science, applications, and commercial payloads for the first 5 years of Space Transportation System (STS) operations at the National Aeronautics and Space Administration's (NASA) John F. Kennedy Space Center (KSC). All non-Department of Defense payloads from STS-2 through STS-33 were part of the study. Historical data and cumulative program experiences from key personnel were used extensively. Emphasis was placed on various program planning and events that affected KSC processing, payload experiences and improvements, payload hardware condition after arrival, services to customers, and the impact of STS operations and delays. From these initial considerations, operational drivers were identified, data for selected processing parameters collected and analyzed, processing criteria and options determined, and STS payload results and conclusions reached. The study showed a significant reduction in time and effort needed by STS customers and KSC to process a wide variety of payload configurations. Also of significance is the fact that even the simplest payloads required more processing resources than were initially assumed. The success to date of payload integration, testing, and mission operations, however, indicates the soundness of the approach taken and the methods used.

Evaluation philosophy for shuttle launched payloads

NASA Technical Reports Server (NTRS)

Heuser, R. E.

1975-01-01

Some approaches to space-shuttle payload evaluation are examined. Issues considered include subsystem replacement in low-cost modular spacecraft (LCMS), validation of spacelab payloads, the use of standard components in shuttle-era spacecraft, effects of shuttle-induced environments on payloads, and crew safety. The LCMS is described, and goals are discussed for its evaluation program. Concepts regarding how the evaluation should proceed are considered.

The 1993 Shuttle Small Payloads Symposium

NASA Technical Reports Server (NTRS)

Thomas, Lawrence R. (Editor); Mosier, Frances L. (Editor)

1993-01-01

The 1993 Shuttle Small Payloads Symposium is a combined symposia of the Get Away Special (GAS), Hitchhiker, and Complex Autonomous Payloads (CAP) programs, and is proposed to continue as an annual conference. The focus of this conference is to educate potential Space Shuttle Payload Bay users as to the types of carrier systems provided and for current users to share experiment concepts.

Space processing applications payload equipment study. Volume 2B: Payload interface analysis (power/thermal/electromagnetic compatibility)

NASA Technical Reports Server (NTRS)

Hammel, R. L. (Editor); Smith, A. G. (Editor)

1974-01-01

As a part of the task of performing preliminary engineering analysis of modular payload subelement/host vehicle interfaces, a subsystem interface analysis was performed to establish the integrity of the modular approach to the equipment design and integration. Salient areas that were selected for analysis were power and power conditioning, heat rejection and electromagnetic capability (EMC). The equipment and load profiles for twelve representative experiments were identified. Two of the twelve experiments were chosen as being representative of the group and have been described in greater detail to illustrate the evaluations used in the analysis. The shuttle orbiter will provide electrical power from its three fuel cells in support of the orbiter and the Spacelab operations. One of the three shuttle orbiter fuel cells will be dedicated to the Spacelab electrical power requirements during normal shuttle operation. This power supplies the Spacelab subsystems and the excess will be available to the payload. The current Spacelab sybsystem requirements result in a payload allocation of 4.0 to 4.8 kW average (24 hour/day) and 9.0 kW peak for 15 minutes.

International Space Station Payload Training Overview

NASA Technical Reports Server (NTRS)

Underwood, Deborah B.; Noneman, Steven R.; Sanchez, Julie N.

2001-01-01

This paper describes payload crew training-related activities performed by NASA and the U.S. Payload Developer (PD) community for the International Space Station (ISS) Program. It describes how payloads will be trained and the overall training planning and integration process. The overall concept, definition, and template for payload training are described. The roles and responsibilities of individuals, organizations, and groups involved are discussed. The facilities utilized during payload training and the primary processes and activities performed to plan, develop, implement, and administer payload training for ISS crews are briefly described. Areas of improvement to crew training processes that have been achieved or are currently being worked are identified.

A NASA Strategy for Leveraging Emerging Launch Vehicles for Routine, Small Payload Missions

NASA Technical Reports Server (NTRS)

Underwood, Bruce E.

2005-01-01

Orbital flight opportunities for small payloads have always been few and far between, and then on February 1, 2002, the situation got worse. In the wake of the loss of the Columbia during STS- 107, changing NASA missions and priorities led to the termination of the Shuttle Small Payloads Projects, including Get-Away Special, Hitcbker, and Space Experiment Module. In spite of the limited opportunities, long queue, and restrictions associated with flying experiments on a man-rated transportation system; the carriers provided a sustained, high quality experiment services for education, science, and technology payloads, and was one of the few games in town. Attempts to establish routine opportunities aboard existing ELVs have been unsuccessful, as the cost-per-pound on small ELVs and conflicts with primary spacecraft on larger vehicles have proven prohibitive. Ths has led to a backlog of existing NASA-sponsored payloads and no prospects or plans for fbture opportunities within the NASA community. The prospects for breaking out of this paradigm appear promising as a result of NASA s partnership with DARPA in pursuit of low-cost, responsive small ELVs under the Falcon Program. Through this partnership several new small ELVs, providing 1000 lbs. to LEO will be demonstrated in less than two years that promise costs that are reasonable enough that NASA, DoD, and other sponsors can once again invest in small payload opportunities. Within NASA, planning has already begun. NASA will be populating one or more of the Falcon demonstration flights with small payloads that are already under development. To accommodate these experiments, Goddard s Wallops Flight Facility has been tasked to develop a multi-payload ejector (MPE) to accommodate the needs of these payloads. The MPE capabilities and design is described in detail in a separately submitted abstract. Beyond use of the demonstration flights however, Goddard has already begun developing strategies to leverage these new ELVs as elements of a larger system designed to provide routine, low-cost end-to-end services for small science, Exploration, and education payloads. The plan leverages the management approaches of the successful Sounding Rocket Program and Shuttle Small Payloads Projects. The strategy consists of using a systems implementation approach of elements, including 1) Falcon ELVs, 2) advanced launch site technologies and processes, 3) suite of experiment carriers accommodating different mission requirements, 4) streamlined integration and test operations, 5 ) experiment brokering and management, and 6) standardized, distributed payload operations. The envisioned suite of carriers includes the MPE, a standard interface experiment carrier, and potentially a reentry fieeflyer experiment carrier. Key to the success of this strategy is standard experiment interfaces within the carriers to limit mission- unique tasks, establishmg and managing a program of scheduled reoccurring flights rather than discrete missions, and streamlined, centralized implementation of the elements. These individual elements are each under development and Goddard will demonstrate the overall system strategy low-cost small payload missions on the initial Falcon demonstration launches from Wallops. goal is to show that this model should be converted to a sustained NASA program supporting science, technology, and education, with annual flight opportunities. The paper will define in detail the various elements of the overall program, as well as provide status, philosophy, and strategy for the program that will hopefully once-and-for-all provide low-cost, routine access to space for the small payloads community.

NASA Expendable Launch Vehicle (ELV) Payload Safety Review Process

NASA Technical Reports Server (NTRS)

Starbus, Calvert S.; Donovan, Shawn; Dook, Mike; Palo, Tom

2007-01-01

Issues addressed by this program: (1) Complicated roles and responsibilities associated with multi-partner projects (2) Working relationships and communications between all organizations involved in the payload safety process (3) Consistent interpretation and implementation of safety requirements from one project to the rest (4) Consistent implementation of the Tailoring Process (5) Clearly defined NASA decision-making-authority (6) Bring Agency-wide perspective to each ElV payload project. Current process requires a Payload Safety Working Group (PSWG) for eac payload with representatives from all involved organizations.

Considerations in STS payload environmental verification

NASA Technical Reports Server (NTRS)

Keegan, W. B.

1978-01-01

Considerations regarding the Space Transportation System (STS) payload environmental verification are reviewed. It is noted that emphasis is placed on testing at the subassembly level and that the basic objective of structural dynamic payload verification is to ensure reliability in a cost-effective manner. Structural analyses consist of: (1) stress analysis for critical loading conditions, (2) model analysis for launch and orbital configurations, (3) flight loads analysis, (4) test simulation analysis to verify models, (5) kinematic analysis of deployment/retraction sequences, and (6) structural-thermal-optical program analysis. In addition to these approaches, payload verification programs are being developed in the thermal-vacuum area. These include the exposure to extreme temperatures, temperature cycling, thermal-balance testing and thermal-vacuum testing.

Remote Advanced Payload Test Rig (RAPTR) Portable Payload Test System for the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Calvert, John; Freas, George, II

2017-01-01

The RAPTR was developed to test ISS payloads for NASA. RAPTR is a simulation of the Command and Data Handling (C&DH) interfaces of the ISS (MIL-STD 1553B, Ethernet and TAXI) and is designed to facilitate rapid testing and deployment of payload experiments to the ISS. The ISS Program's goal is to reduce the amount of time it takes a payload developer to build, test and fly a payload, including payload software. The RAPTR meets this need with its user oriented, visually rich interface. Additionally, the Analog and Discrete (A&D) signals of the following payload types may be tested with RAPTR: (1) EXPRESS Sub Rack Payloads; (2) ELC payloads; (3) External Columbus payloads; (4) External Japanese Experiment Module (JEM) payloads. The automated payload configuration setup and payload data inspection infrastructure is found nowhere else in ISS payload test systems. Testing can be done with minimal human intervention and setup, as the RAPTR automatically monitors parameters in the data headers that are sent to, and come from the experiment under test.

Office of Aeronautics and Space Technology preliminary requirements for space science and applications platform studies

NASA Technical Reports Server (NTRS)

1979-01-01

Needs and requirements for a free flying space science and applications platform to host groupings of compatible, extended mission experiments in earth orbit are discussed. A payload model which serves to define a typical set of mission requirements in the form of a descriptive data base is presented along with experiment leval and group level data summarizations and flight schedules. The payload descriptions are grouped by technology into the following categories: communications, materials (long term effect upon), materials technology development, power, sensors, and thermal control.

'Secret' Shuttle payloads revealed

NASA Astrophysics Data System (ADS)

Powell, Joel W.

1993-05-01

A secret military payload carried by the orbiter Discovery launched on January 24 1985 is discussed. Secondary payloads on the military Shuttle flights are briefly reviewed. Most of the military middeck experiments were sponsored by the Space Test Program established at the Pentagon to oversee all Defense Department space research projects.

Development of a Remote Sensing and Microgravity Student GAS Payload

NASA Technical Reports Server (NTRS)

Branly, Rolando; Ritter, Joe; Friedfeld, Robert; Ackerman, Eric; Carruthers, Carl; Faranda, Jon

1999-01-01

The G-781 Terrestrial and Atmospheric Multi-Spectral Explorer payload (TAMSE) is the result of an educational partnership between Broward and Brevard Community Colleges with the Association of Small Payload Researchers (ASPR) and the Florida Space Institute, University of Central Florida. The effort focuses on flying nine experiments, including three earth viewing remote sensing experiments, three microgravity experiments involving crystal growth, and three radiation measurement experiments. The G-781 science team, composed of both student and faculty members, has been working on this payload since 1995. The dream of flying the first Florida educational GAS experiment led to the flight of a passive Radiation dosimetry experiment on STS-91 (ASPR-GraDEx-I), which will be reflown as part of TAMSE. This project has lead to the development of a mature space science program within the schools. Many students have been positively touched by direct involvement with NASA and the GAS program as well as with other flight programs e.g. the KC-135 flight program. Several students have changed majors, and selected physics, engineering, and other science career paths as a result of the experience. The importance of interdisciplinary training is fundamental to this payload and to the teaching of the natural sciences. These innovative student oriented projects will payoff not only in new science data, but also in accomplishing training for the next generation of environmental and space scientists. The details the TAMSE payload design are presented in this paper.

The use of tethers for payload orbital transfer. Continuation of investigation of electrodynamic stabilization and control of long orbiting tethers, volume 2

NASA Technical Reports Server (NTRS)

Colombo, G.; Martinez-Sanchez, M.; Arnold, D.

1982-01-01

The SKYHOOK program was used to do simulations of two cases of the use of the tether for payload orbital transfer. The transport of a payload along the tether from a heavy lower platform to an upper launching platform is considered. A numerical example of the Shuttle launching a payload using an orbital tether facility is described.

Future payload technology requirements study

NASA Technical Reports Server (NTRS)

1975-01-01

Technology advances needed for an overall mission model standpoint as well as those for individual shuttle payloads are defined. The technology advances relate to the mission scientific equipment, spacecraft subsystems that functionally support this equipment, and other payload-related equipment, software, and environment necessary to meet broad program objectives. In the interest of obtaining commonality of requirements, the study was structured according to technology categories rather than in terms of individual payloads.

The cyclotron energization through auroral wave experiments (CENTAUR 2B)

NASA Technical Reports Server (NTRS)

Winningham, J. D.

1992-01-01

The CENTAUR 2B mission, a dual payload program, is in many aspects the same as the previous missions from Cape Perry and Norway in 1985. It was planned that these payloads would be launched from Andoya, Norway, Nov. 1989 from the Universal II launcher. The payloads are identical, but would have been launched at different azimuths as far north and as far west as possible. Particle experiments include the angular resolving energy analyzer (AREA), the fast ion mass spectrometer (FIMS), the spectrographic particle images (SPI), and finally, the differential ion flux probe (DIFP). SwRI was responsible for the scientific payload, which includes the power supplies, the power supply interfacing, the manipulating of the data from the instruments to format it for the telemetry system, all mechanical structure and restraint mechanisms, and the payload subskin. The status of the various components of this program is given.

10. PAYLOAD CONTROL CONSOLE NEAR SOUTH WALL OF SLC3W CONTROL ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

10. PAYLOAD CONTROL CONSOLE NEAR SOUTH WALL OF SLC-3W CONTROL ROOM. DECALS ON CONSOLE IN FOREGROUND INDICATE PAYLOAD PROGRAMS LAUNCHED FROM SLC-3W. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

Atmosphere, Magnetosphere and Plasmas in Space (AMPS). Spacelab payload definition study. Volume 7, book 2: AMPS phase C/D analysis and planning document

NASA Technical Reports Server (NTRS)

1976-01-01

The results are presented of the AMPS Phase C/D (Design, Development, and Operations) program analysis and planning effort. Cost and schedule estimates are included. Although the AMPS program has been specifically addressed, these task descriptions are basically adaptable to a broader-based program incorporating additional or different Spacelab/orbiter payloads.

Results from Two Low Mass Cosmic Ray Experiments Flown on the HASP Platform

NASA Astrophysics Data System (ADS)

Fontenot, R. S.; Hollerman, W. A.; Tittsworth, M.; Fountain, W.; Christl, M.; Thibodaux, C.; Broussard, B. M.

2009-03-01

The High Altitude Student Payload (HASP) program is designed to carry twelve student experiments to an altitude of about 123,000 feet (˜37 km). In 2006, students participated in the first HASP launch to measure cosmic ray intensities using traditional film and absorbers. This 10 kg payload flew from Fort Sumner, New Mexico in early September 2006 and was a great success. In 2007, students participated in the second HASP flight to measure the cosmic ray intensity and flux using a traditional film and absorber stack with five layers of optically stimulated luminescent (OSL) dosimeters. Results from both payloads showed that the cosmic ray flux decreases as a function of payload depth. As the cosmic rays go through the stack, they deposit their energy in the payload material. Determining cosmic ray flux is a tedious task. It involves digitizing the film and determining the real cosmic ray density. For the first HASP payload, students used a program known as GlobalLab to count particles. For the second payload, the students decided to use a combination of the GREYCStoration image regularization algorithm, an embossing filter, and a depth-merging filter to reconstruct the paths of the cosmic rays.

Considerations in STS payload environmental verification

NASA Technical Reports Server (NTRS)

Keegan, W. B.

1978-01-01

The current philosophy of the GSFS regarding environmental verification of Shuttle payloads is reviewed. In the structures area, increased emphasis will be placed on the use of analysis for design verification, with selective testing performed as necessary. Furthermore, as a result of recent cost optimization analysis, the multitier test program will presumably give way to a comprehensive test program at the major payload subassembly level after adequate workmanship at the component level has been verified. In the thermal vacuum area, thought is being given to modifying the approaches used for conventional spacecraft.

The Living With a Star Space Environment Testbed Experiments

NASA Technical Reports Server (NTRS)

Xapsos, Michael A.

2014-01-01

The focus of the Living With a Star (LWS) Space Environment Testbed (SET) program is to improve the performance of hardware in the space radiation environment. The program has developed a payload for the Air Force Research Laboratory (AFRL) Demonstration and Science Experiments (DSX) spacecraft that is scheduled for launch in August 2015 on the SpaceX Falcon Heavy rocket. The primary structure of DSX is an Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) ring. DSX will be in a Medium Earth Orbit (MEO). This oral presentation will describe the SET payload.

Sally Ride EarthKAM: 15 Years of STEM Education and Outreach from Aboard the International Space Station

NASA Astrophysics Data System (ADS)

Finley, T.; Griffin, R.; Klug, T.; Harbour, S.; Au, B.; Graves, S. J.

2016-12-01

Sally Ride EarthKAM @ Space Camp is a digital camera payload on board the International Space Station (ISS) that allows students from around the globe to request photos of the Earth from space. Since its launch to the ISS in 2001, approximately 110,000 images have been requested by students from over 90 countries. EarthKAM provides the ultimate platform for STEM engagement in both formal and informal educational settings, as it is currently the only earth observation science payload on station completely controlled by students. Images are requested and accessed through a web portal and can be used by educators in a multitude of ways to promote interest in geosciences, math, physics, and numerous other fields. EarthKAM is currently operated out of the US Space and Rocket Center in Huntsville, Alabama and is incorporated into many Space Camp programs. Space Camp hosts nearly 25,000 students and 500 educators each year, vastly improving EarthKAM exposure. Future concepts currently in development include the ability to collect new data products such as night-time and near-infrared imagery, additional science curricula in the form of focused lesson plans and image applications, and a redesigned graphical user interface for requesting photos. The EarthKAM project, a NASA educational outreach program, is currently managed by the US Space and Rocket Center, the University of Alabama in Huntsville, and Teledyne Brown Engineering, Inc.

Communication Platform Payload Definition (CPPD) study. Volume 2: Technical report

NASA Technical Reports Server (NTRS)

Hunter, E. M.; Driggers, T.; Jorasch, R.

1986-01-01

This is Volume 2 (Technical Report) of the Ford Aerospace & Communications Corporation Final Report for the Communication Platform Payload Definition (CPPD) Study program conducted for NASA Lewis Research Center under contract No. NAS3-24235. This report presents the results of the study effort leading to five potential platform payloads to service CONUS and WARC Region 2 traffic demand as projected to the year 2008. The report addresses establishing the data bases, developing service aggregation scenarios, selecting and developing 5 payload concepts, performing detailed definition of the 5 payloads, costing them, identifying critical technology, and finally comparing the payloads with each other and also with non-aggregated equivalent services.

Communication Platform Payload Definition (CPPD) study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Hunter, E. M.

1986-01-01

This is Volume 1 (Executive Summary) of the Ford Aerospace & Communications Corporation Final Report for the Communication Platform Payload Definition (CPPD) Study program conducted for NASA Lewis Research Center under contract No. NAS3-24235. This report presents the results of the study effort leading to five potential platform payloads to service CONUS and WARC Region 2 traffic demand as projected to the year 2008. The report addresses establishing the data bases, developing service aggregation scenarios, selecting and developing 5 payload concepts, performing detailed definition of the 5 payloads, costing them, identifying critical technology, and finally comparing the payloads with each other and also with non-aggregated equivalent services.

Near Space Environments: Tethering Systems

NASA Technical Reports Server (NTRS)

Lucht, Nolan R.

2013-01-01

Near Space Environments, the Rocket University (Rocket U) program dealing with high altitude balloons carrying payloads into the upper earth atmosphere is the field of my project. The tethering from balloon to payload is the specific system I am responsible for. The tethering system includes, the lines that tie the payload to the balloon, as well as, lines that connect payloads together, if they are needed, as well as how to sever the tether to release payloads from the balloon. My objective is to design a tethering system that will carry a payload to any desired altitude and then sever by command at any given point during flight.

Communication Platform Payload Definition (CPPD) study. Volume 3: Addendum

NASA Technical Reports Server (NTRS)

Hunter, E. M.; Driggers, T.; Jorasch, R.

1986-01-01

This is Volume 3 (Addendum) of the Ford Aerospace & Communications Corporation Final Report for the Communication Platform Payload Definition (CPPD) Study Program conducted for NASA Lewis Research Center under contract No. NAS3-24235. This report presents the results of the study effort leading to five potential platform payloads to service CONUS and WARC Region 2 traffic demand as projected to the year 2008. The report addresses establishing the data bases, developing service aggregation scenarios, selecting and developing 5 payload concepts, performing detailed definition of the 5 payloads, costing them, identifying critical technology, and finally comparing the payloads with each other and also with non-aggregated equivalent services.

Payload Operations Control Center (POCC). [spacelab flight operations

NASA Technical Reports Server (NTRS)

Shipman, D. L.; Noneman, S. R.; Terry, E. S.

1981-01-01

The Spacelab payload operations control center (POCC) timeline analysis program which is used to provide POCC activity and resource information as a function of mission time is described. This program is fully automated and interactive, and is equipped with tutorial displays. The tutorial displays are sufficiently detailed for use by a program analyst having no computer experience. The POCC timeline analysis program is designed to operate on the VAX/VMS version V2.1 computer system.

The Get Away Special Program: Year 2000 and Beyond

NASA Technical Reports Server (NTRS)

Wilcox, David A.

1999-01-01

The Get Away Special (GAS) Program flew its first payload in 1982. Since then, 157 payloads have flown on the STS. As the GAS program approaches the new millennium, interest in flying the low-cost access to space continues. Many changes are in store, or are already underway, that will impact the GAS user community in the coming years. This presentation will briefly outline some of those changes and other external impacts to the GAS Program.

EVAL system concept definition. Partial spacelab payload

NASA Technical Reports Server (NTRS)

1976-01-01

The preliminary design of an earth-viewing spacelab payload, with accommodations shared by both NASA and ESA is addressed. Mission parameters for this flight include a launch date of September 1981, an inclination of 57 deg, and an orbital altitude of 325 km. A seven-day mission is planned. The NASA portion of this payload is assigned to the EVAL (Earth Viewing Applications Laboratory) program. The ESA complement is designed as a multiuser payload.

International utilization and operations

NASA Technical Reports Server (NTRS)

Goldberg, Stanley R.

1989-01-01

The international framework of the Space Station Freedom Program is described. The discussion covers the U.S. space policy, international agreements, international Station elements, overall program management structure, and utilization and operations management. Consideration is also given to Freedom's user community, Freedom's crew, pressurized payload and attached payload accommodations, utilization and operations planning, user integration, and user operations.

STS-34 Cargo Configuration drawing with payload bay location of Galileo/IUS

NASA Technical Reports Server (NTRS)

1989-01-01

Visual aid entitled NATIONAL STS PROGRAM STS-34 CARGO CONFIGURATION is a line drawing of Atlantis, Orbiter Vehicle (OV) 104, orbiting the Earth with its payload bay doors (PLBDs) open. A label identifies the Galileo spacecraft on an inertial upper stage (IUS) and its location in the payload bay (PLB).

Payload analysis for space shuttle applications (study 2.2). Volume 3: Payload system operations analysis (task 2.2.1). [payload system operations analysis for shuttles and space tugs

NASA Technical Reports Server (NTRS)

1972-01-01

The technical and cost analysis that was performed for the payload system operations analysis is presented. The technical analysis consists of the operations for the payload/shuttle and payload/tug, and the spacecraft analysis which includes sortie, automated, and large observatory type payloads. The cost analysis includes the costing tradeoffs of the various payload design concepts and traffic models. The overall objectives of this effort were to identify payload design and operational concepts for the shuttle which will result in low cost design, and to examine the low cost design concepts to identify applicable design guidelines. The operations analysis examined several past and current NASA and DoD satellite programs to establish a shuttle operations model. From this model the analysis examined the payload/shuttle flow and determined facility concepts necessary for effective payload/shuttle ground operations. The study of the payload/tug operations was an examination of the various flight timelines for missions requiring the tug.

Express Payload Project - A new method for rapid access to Space Station Freedom

NASA Technical Reports Server (NTRS)

Uhran, Mark L.; Timm, Marc G.

1993-01-01

The deployment and permanent operation of Space Station Freedom will enable researchers to enter a new era in the 21st century, in which continuous on-orbit experimentation and observation become routine. In support of this objective, the Space Station Freedom Program Office has initiated the Express Payload Project. The fundamental project goal is to reduce the marginal cost associated with small payload development, integration, and operation. This is to be accomplished by developing small payload accommodations hardware and a new streamlined small payload integration process. Standardization of small payload interfaces, certification of small payload containers, and increased payload developer responsibility for mission success are key aspects of the Express Payload Project. As the project progresses, the principles will be applied to both pressurized payloads flown inside the station laboratories and unpressurized payloads attached to the station external structures. The increased access to space afforded by Space Station Freedom and the Express Payload Project has the potential to significantly expand the scope, magnitude, and success of future research in the microgravity environment.

Bantam System Technology Project Ground System Operations Concept and Plan

NASA Technical Reports Server (NTRS)

Moon, Jesse M.; Beveridge, James R.

1997-01-01

The Low Cost Booster Technology Program, also known as the Bantam Booster program, is a NASA sponsored initiative to establish a viable commercial technology to support the market for placing small payloads in low earth orbit. This market is currently served by large boosters which orbit a number of small payloads on a single launch vehicle, or by these payloads taking up available space on major commercial launches. Even by sharing launch costs, the minimum cost to launch one of these small satellites is in the 6 to 8 million dollar range. Additionally, there is a shortage of available launch opportunities which can be shared in this manner. The goal of the Bantam program is to develop two competing launch vehicles, with launch costs in the neighborhood of 1.5 million dollars to launch a 150 kg payload into low earth orbit (200 nautical mile sun synchronous). Not only could the cost of the launch be significantly less than the current situation, but the payload sponsor could expect better service for his expenditure, the ability to specify his own orbit, and a dedicated vehicle. By developing two distinct launch vehicles, market forces are expected to aid in keeping customer costs low.

Catalog of lunar and Mars science payloads

NASA Technical Reports Server (NTRS)

Budden, Nancy Ann (Editor)

1994-01-01

This catalog collects and describes science payloads considered for future robotic and human exploration missions to the Moon and Mars. The science disciplines included are geosciences, meteorology, space physics, astronomy and astrophysics, life sciences, in-situ resource utilization, and robotic science. Science payload data is helpful for mission scientists and engineers developing reference architectures and detailed descriptions of mission organizations. One early step in advanced planning is formulating the science questions for each mission and identifying the instrumentation required to address these questions. The next critical element is to establish and quantify the supporting infrastructure required to deliver, emplace, operate, and maintain the science experiments with human crews or robots. This requires a comprehensive collection of up-to-date science payload information--hence the birth of this catalog. Divided into lunar and Mars sections, the catalog describes the physical characteristics of science instruments in terms of mass, volume, power and data requirements, mode of deployment and operation, maintenance needs, and technological readiness. It includes descriptions of science payloads for specific missions that have been studied in the last two years: the Scout Program, the Artemis Program, the First Lunar Outpost, and the Mars Exploration Program.

Program Manager: Journal of the Defense Management College. Volume 16, Number 4, July-August 1987,

DTIC Science & Technology

1987-08-01

Payload as:Review and flight customer. This sets the stage for the -Annex 1: Payload Physical Data elinked next activity in the Integration process are...REQUIREMENTS is held approximately 10 months Ebefore flight to ensure that the payload(s) selected to make up the *cargo can be physically and...EXECUTIVE outlining physical characteristics of the OFFICE item. Now, the procurement specialist solicits industry and if a satisfactory STAFF offer is

Microgravity

NASA Image and Video Library

2001-05-31

This diagram shows the general arrangement of the payloads to be carried by the multidisciplinary STS-107 Research-1 Space Shuttle mission in 2002. The Spacehab module will host experiments that require direct operation by the flight crew. Others with special requirements will be on the GAS Bridge Assembly sparning the payload bay. The Extended Duration Orbiter kit carries additional oxygen and hydrogen for the electricity-producing fuel cells. Research-1 experiments will cover space biology, life science, microgravity research, and commercial space product development, research sponsored by NASA's Office of Biological and Physical Research. An alternative view without callouts is available at 0101765.

Microgravity

NASA Image and Video Library

2001-05-31

Thisdiagram shows the general arrangement of the payloads to be carried by the multidisciplinary STS-107 Research-1 Space Shuttle mission in 2002. The Spacehab module will host experiments that require direct operation by the flight crew. Others with special requirements will be on the GAS Bridge Assembly sparning the payload bay. The Extended Duration Orbiter kit carries additional oxygen and hydrogen for the electricity-producing fuel cells. Research-1 experiments will cover space biology, life science, microgravity research, and commercial space product development, research sponsored by NASA's Office of Biological and Physical Research. An alternative view with callouts is available at 0101764.

STS-95 Day 05 Highlights

NASA Technical Reports Server (NTRS)

1998-01-01

On this fifth day of the STS-95 mission, the flight crew, Cmdr. Curtis L. Brown, Pilot Steven W. Lindsey, Mission Specialists Scott E. Parazynski, Stephen K. Robinson, and Pedro Duque, and Payload Specialists Chiaki Mukai and John H. Glenn, check the status of components of the Hubble Space Telescope Orbital Systems Test (HOST) payload, which provides an on-orbit test bed for hardware that will be used during the third Hubble servicing mission. Then Parazynski and Pilot Steve Lindsey set up some of the tools that will be used during the rendezvous and subsequent capture and reberthing of the Spartan satellite.

Ribbon cutting opens new ELV offices

NASA Technical Reports Server (NTRS)

2000-01-01

The audience applauds and enjoys the official opening of the E&O Building as the new site of the Expendable Launch Vehicle Program. Home for NASA's unmanned missions since 1964, the building has been renovated to house the ELV Program. Cutting the ribbon for the event were Deputy Manager of the ELV and Payload Carrier Programs, Steve Francois; Director of ELV Launch Services, Michael Benik; Center Director Roy Bridges; Manager of the ELV and Payload Carrier Programs, Bobby Bruckner; and Senior Manager of the Boeing ELV Program Support office, Jim Schofield.

KSC-00pp1668

NASA Image and Video Library

2000-11-08

The audience applauds and enjoys the official opening of the E&O Building as the new site of the Expendable Launch Vehicle Program. Home for NASA’s unmanned missions since 1964, the building has been renovated to house the ELV Program.; Cutting the ribbon for the event were Deputy Manager of the ELV and Payload Carrier Programs, Steve Francois; Director of ELV Launch Services, Michael Benik; Center Director Roy Bridges; Manager of the ELV and Payload Carrier Programs, Bobby Bruckner; and Senior Manager of the Boeing ELV Program Support office, Jim Schofield

International Space Station Payload Operations Integration Center (POIC) Overview

NASA Technical Reports Server (NTRS)

Ijames, Gayleen N.

2012-01-01

Objectives and Goals: Maintain and operate the POIC and support integrated Space Station command and control functions. Provide software and hardware systems to support ISS payloads and Shuttle for the POIF cadre, Payload Developers and International Partners. Provide design, development, independent verification &validation, configuration, operational product/system deliveries and maintenance of those systems for telemetry, commanding, database and planning. Provide Backup Control Center for MCC-H in case of shutdown. Provide certified personnel and systems to support 24x7 facility operations per ISS Program. Payloads CoFR Implementation Plan (SSP 52054) and MSFC Payload Operations CoFR Implementation Plan (POIF-1006).

Study of orbiter/payload interface communications configuration control board directive from an operational perspective

NASA Technical Reports Server (NTRS)

Addis, A. W.; Tatosian, C. G.; Lidsey, J. F.

1974-01-01

Orbiter/payload data and communications interface was examined. It was found that the Configuration Control Board Directive (CCBD) greatly increases the capability of the orbiter to communicate with a wide variety of projected shuttle payloads. Rather than being derived from individual payload communication requirements, the CCBD appears to be based on an operational philosophy that requires the orbiter to duplicate or augment the ground network/payload communication links. It is suggested that the implementation of the CCBD be reviewed and compared with the Level 1 Program Requirements Document, differences reconciled, and interface characteristics defined.

The 1995 Shuttle Small Payloads Symposium

NASA Technical Reports Server (NTRS)

Goldsmith, Frann (Editor); Mosier, Frances L. (Editor)

1995-01-01

The 1995 Shuttle Small Payloads Symposium is a combined symposia of the Get Away Special (GAS) and Hitchhiker programs, and is proposed to continue as an annual conference. The focus of this conference is to educate potential Space Shuttle Payload Bay users as to the types of carrier systems provided and for current users to share experiment concepts.

1999 Shuttle Small Payloads Symposium

NASA Technical Reports Server (NTRS)

Daelemans, Gerard (Editor); Mosier, Frances L. (Editor)

1999-01-01

The 1999 Shuttle Small Payloads Symposium is a combined symposia of the Get Away Special (GAS), Space Experiment Module (SEM), and Hitchhiker programs, and is proposed to continue as an annual conference. The focus of this conference is to educate potential Space Shuttle Payload Bay users as to the types of carrier systems provided and for current users to share experiment concepts.

Advanced space program studies: Overall executive summary

NASA Technical Reports Server (NTRS)

Sitney, L. R.

1974-01-01

Studies were conducted to provide NASA with advanced planning analyses which relate integrated space program goals and options to credible technical capabilities, applications potential, and funding resources. The studies concentrated on the following subjects: (1) upper stage options for the space transportation system based on payload considerations, (2) space servicing and standardization of payloads, (3) payload operations, and (4) space transportation system economic analyses related to user charges and new space applications. A systems cost/performance model was developed to synthesize automated, unmanned spacecraft configurations based on the system requirements and a list of equipments at the assembly level.

STS-39 AFP-675 and STP-1 MPESS in OV-103's payload bay (PLB)

NASA Image and Video Library

1991-05-06

STS039-10-019 (28 April-6 May 1991) --- This 35mm frame, taken from inside the crew cabin, shows some of the cargo in Discovery's payload bay. Seen are the tops of canisters on the STP-1 payload, configured on the STS 39 Hitchhiker carrier; and the Air Force Program (AFP) 675 package. AFP-675 consists of the Cryogenic Infrared Radiance Instrumentation for Shuttle (CIRRIS)-1A; Far Ultraviolet Camera (FAR-UV) Experiment; Horizon Ultraviolet Program (HUP); Quadruple Ion Neutral Mass Spectrometer (QINMS); and the Uniformly Redundant Array (URA).

Integrated payload and mission planning, phase 3. Volume 2: Logic/Methodology for preliminary grouping of spacelab and mixed cargo payloads

NASA Technical Reports Server (NTRS)

Rodgers, T. E.; Johnson, J. F.

1977-01-01

The logic and methodology for a preliminary grouping of Spacelab and mixed-cargo payloads is proposed in a form that can be readily coded into a computer program by NASA. The logic developed for this preliminary cargo grouping analysis is summarized. Principal input data include the NASA Payload Model, payload descriptive data, Orbiter and Spacelab capabilities, and NASA guidelines and constraints. The first step in the process is a launch interval selection in which the time interval for payload grouping is identified. Logic flow steps are then taken to group payloads and define flight configurations based on criteria that includes dedication, volume, area, orbital parameters, pointing, g-level, mass, center of gravity, energy, power, and crew time.

A Simplified Shuttle Payload Thermal Analyzer /SSPTA/ program

NASA Technical Reports Server (NTRS)

Bartoszek, J. T.; Huckins, B.; Coyle, M.

1979-01-01

A simple thermal analysis program for Space Shuttle payloads has been developed to accommodate the user who requires an easily understood but dependable analytical tool. The thermal analysis program includes several thermal subprograms traditionally employed in spacecraft thermal studies, a data management system for data generated by the subprograms, and a master program to coordinate the data files and thermal subprograms. The language and logic used to run the thermal analysis program are designed for the small user. In addition, analytical and storage techniques which conserve computer time and minimize core requirements are incorporated into the program.

NASA LeRC's Acoustic Fill Effect Test Program and Results

NASA Technical Reports Server (NTRS)

Hughes, William O.; Mcnelis, Mark E.; Manning, Jerome E.

1994-01-01

NASA Lewis Research Center, in conjunction with General Dynamics Space Systems Division, has performed a test program to investigate the acoustic fill effect for an unblanketed payload fairing for a variety of payload simulators. This paper will discuss this test program and fill factor test data, and make comparisons with theoretical predictions. This paper will also address the NASA acoustic fill effect standard which was verified from the test data analysis.

STS-59 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-59 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-second flight of the Space Shuttle Program and sixth flight of the Orbiter vehicle Endeavor (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-63; three SSME's which were designated as serial numbers 2028, 2033, and 2018 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-065. The RSRM's that were installed in each SRB were designated as 360W037A (welterweight) for the left SRB, and 360H037B (heavyweight) for the right SRB. This STS-59 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objective of the STS-59 mission was to successfully perform the operations of the Space Radar Laboratory-1 (SRL-1). The secondary objectives of this flight were to perform the operations of the Space Tissue Loss-A (STL-A) and STL-B payloads, the Visual Function Tester-4 (VFT-4) payload, the Shuttle Amateur Radio Experiment-2 (SAREX-2) experiment, the Consortium for Materials Development in Space Complex Autonomous Payload-4 (CONCAP-4), and the three Get-Away Special (GAS) payloads.

Bantam: A Cautionary Tale

NASA Technical Reports Server (NTRS)

McNeal, Curtis I., Jr.

2004-01-01

This viewgraph presentation reviews the history of the Bantam program that was cancelled in 1999 due to the decision that the focus on the small payloads was unsustainable and that there would be no return on investment. The comparison is made between NASA's Bantam program, and DARPA's (Defense Advanced Research Projects Agency) two similar projects (Falcon and Rascal). The Bantam Program was to be a small launch vehicle, aimed at launching small payloads (i.e., of 150-300 kg) into space.

International Cooperation of Payload Operations on the International Space Station

NASA Technical Reports Server (NTRS)

Melton, Tina; Onken, Jay

2003-01-01

One of the primary goals of the International Space Station (ISS) is to provide an orbiting laboratory to be used to conduct scientific research and commercial products utilizing the unique environment of space. The ISS Program has united multiple nations into a coalition with the objective of developing and outfitting this orbiting laboratory and sharing in the utilization of the resources available. The primary objectives of the real- time integration of ISS payload operations are to ensure safe operations of payloads, to avoid mutual interference between payloads and onboard systems, to monitor the use of integrated station resources and to increase the total effectiveness of ISS. The ISS organizational architecture has provided for the distribution of operations planning and execution functions to the organizations with expertise to perform each function. Each IPP is responsible for the integration and operations of their payloads within their resource allocations and the safety requirements defined by the joint program. Another area of international cooperation is the sharing in the development and on- orbit utilization of unique payload facilities. An example of this cooperation is the Microgravity Science Glovebox. The hardware was developed by ESA and provided to NASA as part of a barter arrangement.

Amine Swingbed Payload Project Management

NASA Technical Reports Server (NTRS)

Hayley, Elizabeth; Curley, Su; Walsh, Mary

2011-01-01

The International Space Station (ISS) has been designed as a laboratory for demonstrating technologies in a microgravity environment, benefitting exploration programs by reducing the overall risk of implementing such technologies in new spacecraft. At the beginning of fiscal year 2010, the ISS program manager requested that the amine-based, pressure-swing carbon dioxide and humidity absorption technology (designed by Hamilton Sundstrand, baselined for the ORION Multi-Purpose Crew Vehicle, and tested at the Johnson Space Center in relevant environments, including with humans, since 2005) be developed into a payload for ISS Utilization. In addition to evaluating the amine technology in a flight environment before the first launch of the ORION vehicle, the ISS program wanted to determine the capability of the amine technology to remove carbon dioxide from the ISS cabin environment at the metabolic rate of the full 6-person crew. Because the amine technology vents the absorbed carbon dioxide and water vapor to space vacuum (open loop), additional hardware needed to be developed to minimize the amount of air and water resources lost overboard. Additionally, the payload system would be launched on two separate Space Shuttle flights, with the heart of the payload the swingbed unit itself launching a full year before the remainder of the payload. This paper discusses the project management and challenges of developing the amine swingbed payload in order to accomplish the technology objectives of both the open-loop ORION application as well as the closed-loop ISS application.

Amine Swingbed Payload Project Management

NASA Technical Reports Server (NTRS)

Walsch, Mary; Curley, Su

2013-01-01

The International Space Station (ISS) has been designed as a laboratory for demonstrating technologies in a microgravity environment, benefitting exploration programs by reducing the overall risk of implementing such technologies in new spacecraft. At the beginning of fiscal year 2010, the ISS program manager requested that the amine-based, pressure-swing carbon dioxide and humidity absorption technology (designed by Hamilton Sundstrand, baselined for the Orion Multi-Purpose Crew Vehicle, and tested at the Johnson Space Center in relevant environments, including with humans, since 2005) be developed into a payload for ISS Utilization. In addition to evaluating the amine technology in a flight environment before the first launch of the Orion vehicle, the ISS program wanted to determine the capability of the amine technology to remove carbon dioxide from the ISS cabin environment at the metabolic rate of the full 6 ]person crew. Because the amine technology vents the absorbed carbon dioxide and water vapor to space vacuum (open loop), additional hardware needed to be developed to minimize the amount of air and water resources lost overboard. Additionally, the payload system would be launched on two separate Space Shuttle flights, with the heart of the payload-the swingbed unit itself-launching a full year before the remainder of the payload. This paper discusses the project management and challenges of developing the amine swingbed payload in order to accomplish the technology objectives of both the open -loop Orion application as well as the closed-loop ISS application.

STS-95 Mission Highlights Resources Tape

NASA Technical Reports Server (NTRS)

1999-01-01

The STS-95 flight crew, Commander Curtis L. Brown, Pilot Steven W. Lindsey, Mission Specialists Scott E. Parazynski, Stephen K. Robinson, and Pedro Duque, and Payload Specialists Chiaki Mukai and John H. Glenn present a video overview of their space flight. They are seen performing pre-launch activities such as eating the traditional breakfast, crew suit-up, and the ride out to the launch pad. Also, included are various panoramic views of the shuttle on the pad. The crew is readied in the 'white room' for their mission. After the closing of the hatch and arm retraction, launch activities are shown including countdown, engine ignition, launch, and the separation of the Solid Rocket Boosters. Once on-orbit the primary objectives include conducting a variety of science experiments in the pressurized SPACEHAB module, the deployment and retrieval of the Spartan free-flyer payload, and operations with the Hubble Space Telescope (HST) Orbiting Systems Test (HOST) and the International Extreme Ultraviolet Hitchhiker (IEH) payloads being carried in the payload bay. Throughout the presentation, the astronauts take turns narrating particular aspects of the mission with which they were involved.

Impact of low cost refurbishable and standard spacecraft upon future NASA space programs. Payload effects follow-on study

NASA Technical Reports Server (NTRS)

1972-01-01

The study has concluded that there are very large space program cost savings to be obtained by use of low cost, refurbishable, and standard spacecraft in conjunction with the shuttle transportation system. The range of space program cost savings for three different groups of programs are shown in quantitative terms. The total savings for the 91 programs will range from $13.4 billion to $18.0 billion depending on the degree of hardware standardization. These savings, principally resulting from payload cost reductions, tangibly support the development costs of the shuttle system.

Sounding rocket thermal analysis techniques applied to GAS payloads. [Get Away Special payloads (STS)

NASA Technical Reports Server (NTRS)

Wing, L. D.

1979-01-01

Simplified analytical techniques of sounding rocket programs are suggested as a means of bringing the cost of thermal analysis of the Get Away Special (GAS) payloads within acceptable bounds. Particular attention is given to two methods adapted from sounding rocket technology - a method in which the container and payload are assumed to be divided in half vertically by a thermal plane of symmetry, and a method which considers the container and its payload to be an analogous one-dimensional unit having the real or correct container top surface area for radiative heat transfer and a fictitious mass and geometry which model the average thermal effects.

Payload accommodation and development planning tools - A Desktop Resource Leveling Model (DRLM)

NASA Technical Reports Server (NTRS)

Hilchey, John D.; Ledbetter, Bobby; Williams, Richard C.

1989-01-01

The Desktop Resource Leveling Model (DRLM) has been developed as a tool to rapidly structure and manipulate accommodation, schedule, and funding profiles for any kind of experiments, payloads, facilities, and flight systems or other project hardware. The model creates detailed databases describing 'end item' parameters, such as mass, volume, power requirements or costs and schedules for payload, subsystem, or flight system elements. It automatically spreads costs by calendar quarters and sums costs or accommodation parameters by total project, payload, facility, payload launch, or program phase. Final results can be saved or printed out, automatically documenting all assumptions, inputs, and defaults.

Guidelines for Hosted Payloads Integration Product Overview

DTIC Science & Technology

2014-05-08

nro.mil NRO Hans Koenigsmann hans.koenigsmann@spacex.com SpaceX James Koory james.koory@rocket.com Rocket Brian Kosinski Kosinski.Brian@ssd.loral.com...Milligen fvanmilligen@jdsu.com JDSU Marvin VanderWeg marvin.vanderwag@spacex.com SpaceX Gerrit VanOmmering gerrit.vanommering@sslmda.com SSL Michael

Guidelines for Hosted Payload Integration

DTIC Science & Technology

2014-06-06

Micopac markking@micropac.com Andrew King Boeing andrew.m.king@boeing.com Byron Knight NRO knightby@nro.mil Hans Koenigsmann SpaceX hans.koenigsmann...jdsu.com Marvin VanderWeg SpaceX marvin.vanderwag@spacex.c om Gerrit VanOmmering SSL gerrit.vanommering@sslmda. com Michael Verzuh Ball mverzuh@ball.com

Get away special the low-cost route to orbit

NASA Technical Reports Server (NTRS)

Prouty, C.

1986-01-01

NASA has established the Get Away Special (GAS) program as a means for providing anyone who wishes the opportunity to place a small self-contained experimental payload aboard a Space Shuttle mission for a very low cost. The GAS program is now well established, and has a respectable history with 53 payloads flown to date. The GAS experimenters are a diverse group who have demonstrated that people from all walks of life, and from many nations, are interested in working in space. This paper traces the history of the program from its concept through the development phase to the present time, and takes a brief look at the future. It also addresses the steps involved in making a payload reservation and the programmatic and technical relationships that are established between NASA and GAS customers.

Pegaso: Long durations balloons from polar regions

NASA Astrophysics Data System (ADS)

Romeo, G. R.; di Stefano, G. D. S.; di Felice, F. D. F.; Masi, S. M.; Cardillo, A. C.; Musso, I. M.; Ibba, R. I.; Palangio, P. P.; Caprara, F. C.; Peterzen, S. P.; Pegaso Group

Launched from the Mario Zuccelli Station Baia Terra Nova in Antarctica during the 2005 06 austral summer the PEGASO-D payload lifted into the stratospheric anticyclone over the southern polar region This effort marks the first Long Duration Scientific payload to be launched from this location and is the fourth such payload launched in the polar regions Performing in the framework of the NOBILE AMUNDSEN collaborative LDB development between ASI-ARR The Italian Institute of Geophysics and Volcanology INGV with the sponsorship of the Italian Antarctic Program PNRA and the Italian Space Agency ASI designed and built the Ultra-Light system together with three Universities in Italy The Pegaso program has been created to investigate the Earth magnetic field and provide a precursor series of small payload launches for the bigger LDB program such as OLIMPO BOOMERanG and BArSPOrt through this collaboration between ASI and ARR The Italian scientific community aware of the big advantages that LDB balloons can offer to their experiments proposed to extend the LDB program to Southern polar regions besides performing launches from the newly initiated Nobile Amundsen Stratospheric Balloon Center in Svalbard Norway Three PEGASO Polar Explorer for Geomagnetics And other Scientific Observations payloads have been launched from the Svalbard No in collaboration with Andoya Rocket Range ASI and ISTAR Operations and logistics during the past two northern summers These stratospheric altitude m 35000 small 10kmc balloons have floated in the stratosphere between 14 to

EVA 5 - MS Grunsfeld and Linnehan in payload bay

NASA Image and Video Library

2002-03-08

STS109-E-5750 (8 March 2002) --- Astronaut John M. Grunsfeld, STS-109 payload commander, floats near the giant Hubble Space Telescope (HST) temporarily hosted in the Space Shuttle Columbia’s cargo bay. Astronaut Richard M. Linnehan (lower right), mission specialist, works in tandem with Grunsfeld during this fifth and final scheduled space walk. Activities for EVA-5 centered around the Near-Infrared Camera and Multi-Object Spectrometer (NICMOS) to install a Cryogenic Cooler and its Cooling System Radiator. The space walk was completed at 10:06 a.m. CST (1606 GMT), March 8, 2002. The image was recorded with a digital still camera.

The October 1973 expendable launch vehicle traffic model, revision 2

NASA Technical Reports Server (NTRS)

1974-01-01

Traffic model data for current expendable launch vehicles (assuming no space shuttle) for calendar years 1980 through 1991 are presented along with some supporting and summary data. This model was based on a payload program equivalent in scientific return to the October 1973 NASA Payload Model, the NASA estimated non NASA/non DoD Payload Model, and the 1971 DoD Mission Model.

Low-cost space flight for attached payloads

NASA Astrophysics Data System (ADS)

Perkins, Frederick W.

1991-07-01

An important addition to the emerging commercial space sector is Standard Space Platforms Corporation's comprehensive low-cost flight service delivery system for small and developmental payloads. Standard provides a privately funded, proprietary, value-added transportation service which dramatically reduces cost and program duration for compliant payloads. It also provides a business-to-business service which is compatible with business investment decision timing and technology development cycles.

Vibroacoustic Payload Environment Prediction System (VAPEPS): VAPEPS management center remote access guide

NASA Technical Reports Server (NTRS)

Fernandez, J. P.; Mills, D.

1991-01-01

A Vibroacoustic Payload Environment Prediction System (VAPEPS) Management Center was established at the JPL. The center utilizes the VAPEPS software package to manage a data base of Space Shuttle and expendable launch vehicle payload flight and ground test data. Remote terminal access over telephone lines to the computer system, where the program resides, was established to provide the payload community a convenient means of querying the global VAPEPS data base. This guide describes the functions of the VAPEPS Management Center and contains instructions for utilizing the resources of the center.

NASA Headquarters/Kennedy Space Center: Organization and Small Spacecraft Launch Services

NASA Technical Reports Server (NTRS)

Sierra, Albert; Beddel, Darren

1999-01-01

The objectives of the Kennedy Space Center's (KSC) Expendable Launch Vehicles (ELV) Program are to provide safe, reliable, cost effective ELV launches, maximize customer satisfaction, and perform advanced payload processing capability development. Details are given on the ELV program organization, products and services, foreign launch vehicle policy, how to get a NASA launch service, and some of the recent NASA payloads.

STS-87 Payload Canister being raised into PCR

NASA Technical Reports Server (NTRS)

1997-01-01

A payload canister containing the primary payloads for the STS-87 mission is lifted into the Payload Changeout Room at Pad 39B at Kennedy Space Center. The STS-87 payload includes the United States Microgravity Payload-4 (USMP-4) and Spartan-201. Spartan- 201 is a small retrievable satellite involved in research to study the interaction between the Sun and its wind of charged particles. USMP-4 is one of a series of missions designed to conduct scientific research aboard the Shuttle in the unique microgravity environment for extended periods of time. In the past, USMP missions have provided invaluable experience in the design of instruments needed for the International Space Station (ISS) and microgravity programs to follow in the 21st century. STS-87 is scheduled for launch Nov. 19.

Operational plans for life science payloads - From experiment selection through postflight reporting

NASA Technical Reports Server (NTRS)

Mccollum, G. W.; Nelson, W. G.; Wells, G. W.

1976-01-01

Key features of operational plans developed in a study of the Space Shuttle era life science payloads program are presented. The data describes the overall acquisition, staging, and integration of payload elements, as well as program implementation methods and mission support requirements. Five configurations were selected as representative payloads: (a) carry-on laboratories - medical emphasis experiments, (b) mini-laboratories - medical/biology experiments, (c) seven-day dedicated laboratories - medical/biology experiments, (d) 30-day dedicated laboratories - Regenerative Life Support Evaluation (RLSE) with selected life science experiments, and (e) Biomedical Experiments Scientific Satellite (BESS) - extended duration primate (Type I) and small vertebrate (Type II) missions. The recommended operational methods described in the paper are compared to the fundamental data which has been developed in the life science Spacelab Mission Simulation (SMS) test series. Areas assessed include crew training, experiment development and integration, testing, data-dissemination, organization interfaces, and principal investigator working relationships.

The New Payload Handling System for the G erman On- Orbit Verification Satellite TET with the Sensor Bus as Example for Payloads

NASA Astrophysics Data System (ADS)

Heyer, H.-V.; Föckersperger, S.; Lattner, K.; Moldenhauer, W.; Schmolke, J.; Turk, M.; Willemsen, P.; Schlicker, M.; Westerdorff, K.

2008-08-01

The technology verification satellite TET (Technologie ErprobungsTräger) is the core element of the German On-Orbit-Verification (OOV) program of new technologies and techniques. The goal of this program is the support of the German space industry and research facilities for on-orbit verification of satellite technologies. The TET satellite is a small satellite developed and built in Germany under leadership of Kayser-Threde. The satellite bus is based on the successfully operated satellite BIRD and the newly developed payload platform with the new payload handling system called NVS (Nutzlastversorgungs-system). The NVS can be detailed in three major parts: the power supply the processor boards and the I/O-interfaces. The NVS is realized via several PCBs in Europe format which are connected to each other via an integrated backplane. The payloads are connected by front connectors to the NVS. This paper describes the concept, architecture, and the hard-/software of the NVS. Phase B of this project was successfully finished last year.

Lightning Imaging Sensor (LIS) on the International Space Station (ISS): Launch, Installation, Activation and First Results

NASA Technical Reports Server (NTRS)

Blakeslee, R. J.; Christian, H. J.; Mach, D. M.; Buechler, D. E.; Wharton, N. A.; Stewart, M. F.; Ellett, W. T.; Koshak, W. J.; Walker, T. D.; Virts, K.;

Microbiological Lessons Learned from the Space Shuttle

NASA Technical Reports Server (NTRS)

Pierson, Duane L.; Ott, C. Mark; Bruce, Rebekah; Castro, Victoria A.; Mehta, Satish K.

2011-01-01

After 30 years of being the centerpiece of NASA s human spacecraft, the Space Shuttle will retire. This highly successful program provided many valuable lessons for the International Space Station (ISS) and future spacecraft. Major microbiological risks to crewmembers include food, water, air, surfaces, payloads, animals, other crewmembers, and ground support personnel. Adverse effects of microorganisms are varied and can jeopardize crew health and safety, spacecraft systems, and mission objectives. Engineering practices and operational procedures can minimize the negative effects of microorganisms. To minimize problems associated with microorganisms, appropriate steps must begin in the design phase of new spacecraft or space habitats. Spacecraft design must include requirements to control accumulation of water including humidity, leaks, and condensate on surfaces. Materials used in habitable volumes must not contribute to microbial growth. Use of appropriate materials and the implementation of robust housekeeping that utilizes periodic cleaning and disinfection will prevent high levels of microbial growth on surfaces. Air filtration can ensure low levels of bioaerosols and particulates in the breathing air. The use of physical and chemical steps to disinfect drinking water coupled with filtration can provide safe drinking water. Thorough preflight examination of flight crews, consumables, and the environment can greatly reduce pathogens in spacecraft. The advances in knowledge of living and working onboard the Space Shuttle formed the foundation for environmental microbiology requirements and operations for the International Space Station (ISS) and future spacecraft. Research conducted during the Space Shuttle Program resulted in an improved understanding of the effects of spaceflight on human physiology, microbial properties, and specifically the host-microbe interactions. Host-microbe interactions are substantially affected by spaceflight. Astronaut immune functions were found to be altered. Selected microorganisms were found to become more virulent during spaceflight. The increased knowledge gained on the Space Shuttle resulted in further studies of the host-microbe interactions on the ISS to determine if countermeasures were necessary. Lessons learned from the Space Shuttle Program were integrated into the ISS resulting in the safest space habitat to date.

Generalized environmental control and life support system computer program (G189A) configuration control. [computer subroutine libraries for shuttle orbiter analyses

NASA Technical Reports Server (NTRS)

Blakely, R. L.

1973-01-01

A G189A simulation of the shuttle orbiter EC/lSS was prepared and used to study payload support capabilities. Two master program libraries of the G189A computer program were prepared for the NASA/JSC computer system. Several new component subroutines were added to the G189A program library and many existing subroutines were revised to improve their capabilities. A number of special analyses were performed in support of a NASA/JSC shuttle orbiter EC/LSS payload support capability study.

Application of shuttle EVA systems to payloads. Volume 1: EVA systems and operational modes description

NASA Technical Reports Server (NTRS)

1976-01-01

Descriptions of the EVA system baselined for the space shuttle program were provided, as well as a compendium of data on available EVA operational modes for payload and orbiter servicing. Operational concepts and techniques to accomplish representative EVA payload tasks are proposed. Some of the subjects discussed include: extravehicular mobility unit, remote manipulator system, airlock, EVA translation aids, restraints, workstations, tools and support equipment.

The Living With a Star Space Environment Testbed Payload

NASA Technical Reports Server (NTRS)

Xapsos, Mike

2015-01-01

This presentation outlines a brief description of the Living With a Star (LWS) Program missions and detailed information about the Space Environment Testbed (SET) payload consisting of a space weather monitor and carrier containing 4 board experiments.

NASA Sounding Rocket Program educational outreach

NASA Astrophysics Data System (ADS)

Eberspeaker, P. J.

2005-08-01

Educational and public outreach is a major focus area for the National Aeronautics and Space Administration (NASA). The NASA Sounding Rocket Program (NSRP) shares in the belief that NASA plays a unique and vital role in inspiring future generations to pursue careers in science, mathematics, and technology. To fulfill this vision, the NASA Sounding Rocket Program engages in a host of student flight projects providing unique and exciting hands-on student space flight experiences. These projects include single stage Orion missions carrying "active" high school experiments and "passive" Explorer School modules, university level Orion and Terrier-Orion flights, and small hybrid rocket flights as part of the Small-scale Educational Rocketry Initiative (SERI) currently under development. Efforts also include educational programs conducted as part of major campaigns. The student flight projects are designed to reach students ranging from Kindergarteners to university undergraduates. The programs are also designed to accommodate student teams with varying levels of technical capabilities - from teams that can fabricate their own payloads to groups that are barely capable of drilling and tapping their own holes. The program also conducts a hands-on student flight project for blind students in collaboration with the National Federation of the Blind. The NASA Sounding Rocket Program is proud of its role in inspiring the "next generation of explorers" and is working to expand its reach to all regions of the United States and the international community as well.

Expendable solid rocket motor upper stages for the Space Shuttle

NASA Technical Reports Server (NTRS)

Davis, H. P.; Jones, C. M.

1974-01-01

A family of expendable solid rocket motor upper stages has been conceptually defined to provide the payloads for the Space Shuttle with performance capability beyond the low earth operational range of the Shuttle Orbiter. In this concept-feasibility assessment, three new solid rocket motors of fixed impulse are defined for use with payloads requiring levels of higher energy. The conceptual design of these motors is constrained to limit thrusting loads into the payloads and to conserve payload bay length. These motors are combined in various vehicle configurations with stage components derived from other programs for the performance of a broad range of upper-stage missions from spin-stabilized, single-stage transfers to three-axis stabilized, multistage insertions. Estimated payload delivery performance and combined payload mission loading configurations are provided for the upper-stage configurations.

Life sciences payload definition and integration study. Volume 1: Management summary

NASA Technical Reports Server (NTRS)

1972-01-01

The objectives of a study program to determine the life sciences payloads required for conducting biomedical experiments during space missions are presented. The objectives are defined as: (1) to identify the research functions which must be performed aboard life sciences spacecraft laboratories and the equipment needed to support these functions and (2) to develop layouts and preliminary conceptual designs of several potential baseline payloads for the accomplishment of life research in space. Payload configurations and subsystems are described and illustrated. Tables of data are included to identify the material requirements for the space missions.

Small self-contained payload overview. [Space Shuttle Getaway Special project management

NASA Technical Reports Server (NTRS)

Miller, D. S.

1981-01-01

The low-cost Small Self-Contained Payload Program, also known as the Getaway Special, initiated by NASA for providing a stepping stone to larger scientific and manufacturing payloads, is presented. The steps of 'getting on board,' the conditions of use, the reimbursement policy and the procedures, and the flight scheduling mechanism for flying the Getaway Special payload are given. The terms and conditions, and the interfaces between NASA and the users for entering into an agreement with NASA for launch and associated services are described, as are the philosophy and the rationale for establishing the policy and the procedures.

Life sciences payload definition and integration study, task C and D. Volume 1: Management summary

NASA Technical Reports Server (NTRS)

1973-01-01

The findings of a study to define the required payloads for conducting life science experiments in space are presented. The primary objectives of the study are: (1) identify research functions to be performed aboard life sciences spacecraft laboratories and necessary equipment, (2) develop conceptual designs of potential payloads, (3) integrate selected laboratory designs with space shuttle configurations, and (4) establish cost analysis of preliminary program planning.

Atmospheric, Magnetospheric and Plasmas in Space (AMPS) spacelab payload definition study; volume 4: Part 2, Labcraft payload general specification

NASA Technical Reports Server (NTRS)

Keeley, J. T.

1976-01-01

The Labcraft Payload General Specification (LPGS) amplifies those general requirements in the Labcraft Program Specification (LPS) to ensure that all hardware, software, and STS elements will successfully function as an integrated system to accomplish the objectives of the first Labcraft mission. Contract End Item Specifications (CEIS) and Procurement Drawings (PDs) prepared and implemented for all deliverable hardware and software elements are discussed.

Miniature vibration isolation system for space applications

NASA Astrophysics Data System (ADS)

Quenon, Dan; Boyd, Jim; Buchele, Paul; Self, Rick; Davis, Torey; Hintz, Timothy L.; Jacobs, Jack H.

2001-06-01

In recent years, there has been a significant interest in, and move towards using highly sensitive, precision payloads on space vehicles. In order to perform tasks such as communicating at extremely high data rates between satellites using laser cross-links, or searching for new planets in distant solar systems using sparse aperture optical elements, a satellite bus and its payload must remain relatively motionless. The ability to hold a precision payload steady is complicated by disturbances from reaction wheels, control moment gyroscopes, solar array drives, stepper motors, and other devices. Because every satellite is essentially unique in its construction, isolating or damping unwanted vibrations usually requires a robust system over a wide bandwidth. The disadvantage of these systems is that they typically are not retrofittable and not tunable to changes in payload size or inertias. Previous work, funded by AFRL, DARPA, BMDO and others, developed technology building blocks that provide new methods to control vibrations of spacecraft. The technology of smart materials enables an unprecedented level of integration of sensors, actuators, and structures; this integration provides the opportunity for new structural designs that can adaptively influence their surrounding environment. To date, several demonstrations have been conducted to mature these technologies. Making use of recent advances in smart materials, microelectronics, Micro-Electro Mechanical Systems (MEMS) sensors, and Multi-Functional Structures (MFS), the Air Force Research Laboratory along with its partner DARPA, have initiated an aggressive program to develop a Miniature Vibration Isolation System (MVIS) (patent pending) for space applications. The MVIS program is a systems-level demonstration of the application of advanced smart materials and structures technology that will enable programmable and retrofittable vibration control of spacecraft precision payloads. The current effort has been awarded to Honeywell Space Systems Operation. AFRL is providing in-house research and testing in support of the program as well. The MVIS program will culminate in a flight demonstration that shows the benefits of applying smart materials for vibration isolation in space and precision payload control.

LAVA subsystem integration and testing for the Resolve payload of the Resource Prospector mission: mass spectrometers and gas chromatography

NASA Astrophysics Data System (ADS)

Stewart, Elaine M.; Coan, Mary R.; Captain, Janine; Santiago-Bond, Josephine

2016-09-01

In-Situ Resource Utilization (ISRU) is a key NASA initiative to exploit resources at the site of planetary exploration for mission-critical consumables, propellants, and other supplies. The Resource Prospector mission, part of ISRU, is scheduled to launch in 2020 and will include a rover and lander hosting the Regolith and Environment Science and Oxygen and Lunar Volatile Extraction (RESOLVE) payload for extracting and analyzing lunar resources, particularly low molecular weight volatiles for fuel, air, and water. RESOLVE contains the Lunar Advanced Volatile Analysis (LAVA) subsystem with a Gas Chromatograph-Mass Spectrometer (GC-MS). RESOLVE subsystems, including the RP15 rover and LAVA, are in NASA's Engineering Test Unit (ETU) phase to assure that all vital components of the payload are space-flight rated and will perform as expected during the mission. Integration and testing of LAVA mass spectrometry verified reproducibility and accuracy of the candidate MS for detecting nitrogen, oxygen, and carbon dioxide. The RP15 testing comprised volatile analysis of water-doped simulant regolith to enhance integration of the RESOLVE payload with the rover. Multiple tests show the efficacy of the GC to detect 2% and 5% water-doped samples.

HIFiRE-1 Preliminary Aerothermodynamic Measurements (Postprint)

DTIC Science & Technology

2012-05-01

surplus military ordnance used extensively in sounding rocket programs. This motor combination was chosen to minimize overall program costs and, based on...out on the forward sections of payload including a cone, a cylinder, and a flare which transitions to the diameter of the second stage motor (0.356 m...HIFiRE-1 payload was a Terrier Mk70 booster–Improved Orion sustainer 17 motor combination. The Terrier and Orion motors have been sourced from

Efficient Reorientation Maneuvers for Spacecraft with Multiple Articulated Payloads

NASA Technical Reports Server (NTRS)

Mcclamroch, N. Harris

1993-01-01

A final report is provided which describes the research program during the period 3 Mar. 1992 to 3 Jun. 1993. A summary of the technical research questions that were studied and of the main results that were obtained is given. The specific outcomes of the research program, including both educational impacts as well as research publications, are listed. The research is concerned with efficient reorientation maneuvers for spacecraft with multiple articulated payloads.

LMSS - From low data rate to voice services

NASA Astrophysics Data System (ADS)

Rogard, R.

1992-03-01

An overview of ESA's approach towards the introduction of Land Mobile Communications in Europe is presented. Emphasis is placed on a description of the payload called EMS to be launched on a host satellite, the Italsat-F2 spacecraft, and the definition of services which are most appropriate for a first-generation-operating Land Mobile Satellite System, namely, PRODAT, a message-handling system, and Europhone, an original approach to 'voice' systems. Attention is given to the EMS payload, characteristics, and capacity, the IF processor and channelization, and market considerations. It is shown that the optimization of the satellite characteristics and the mix of services to be provided are the key elements of a successful entry into the market.

University of Virginia infrared sensor experiment (UVIRSE)

NASA Astrophysics Data System (ADS)

Dawson, Jeffrey R.; Bell, Meredith A.; Powers, Michael C.; Laufer, Gabriel

2001-03-01

A suite consisting of an infrared sensor, optical sensors and a video camera are prepared for launch by a group of students at University of Virginia (UVA) and James Madison University (JMU). The sensors are a first step in the development of a Gas Filter Correlation Radiometer (GFCR) that will detect stratospheric methane (CH4) when flown on sub-orbital sounding rockets and/or from the hypersonic X-34 reusable launch vehicle. The current payload has a threefold purpose: (a) to provide space heritage to a thermoelectrically cooled mercury cadmium telluride sensor, (b) to demonstrate methods for correlating the IR reading of the sensor with ground topography, and (c) to flight test all the payload components that will become part of the sub- orbital methane GFCR sensor. Once completed the system will serve as host to other undergraduate research design projects that require space environment, microgravity, or remote sensing capabilities. The payload components have been received and tested, and the supporting structure has been designed and built. Data from previous rocket flights was used to analyze the environmental strains placed on the experiment and components. Payload components are being integrated and tested as a system to ensure functionality in the flight environment. This includes thermal testing for individual components, vibration testing from individual components and overall payload, and load testing of the external structure. Launch is scheduled for Spring 2001.

Opportunities for Geoscience Research Onboard Virgin Galactic's SpaceShipTwo

NASA Astrophysics Data System (ADS)

Pomerantz, W.; Beerer, I.; Stephens, K.; Griffith, J.; Persall, W.; Tizard, J.

2012-12-01

Virgin Galactic has developed a reusable spaceplane, called SpaceShipTwo (SS2), designed to make routine voyages into suborbital space. SS2 is air-launched from a jet aircraft at an altitude of 50,000 ft. before igniting its rocket motor engine. The vehicle reaches a maximum apogee as high as 110 km before gliding to a conventional runway landing. With the ability to fly multiple times per week, SS2 will be capable of providing routine access to a rarely sampled and poorly understood region of the atmosphere and ionosphere, making it a valuable platform for geoscience research. With a payload capacity up to 1300 lbs., SS2 provides access to space and the upper atmosphere for substantially larger payloads than sounding rockets and at a dramatically lower cost than orbital satellites. The main cabin provides as much as 500 cubic ft. of useable volume in a shirt-sleeve environment and payload mounting interfaces that are compatible with standard architectures, such as Middeck Lockers, Cargo Transfer Bags, and server racks. A flight test engineer will be available on board to operate payloads during flight. In the future, SS2 will also offer a variety of external payload mounting locations, enabling researchers to make frequent in situ measurements in the mesosphere (50-90 km), lower thermosphere (above 80 km), and lower ionosphere (above 60 km). SS2 may also offer optical quality windows, allowing optical investigations from main cabin payloads. Researchers will have access to their payloads until just hours before flight and within three hours post-flight. While commercial operations will begin out of Spaceport America in New Mexico, SS2 may eventually be able to launch from a variety of geographic locations. Funding to develop and fly payloads for SS2 is currently available through many NASA programs including the Flight Opportunities Program and the Game Changing Development Program. Virgin Galactic expects the SS2 research platform to enable significant progress in atmospheric chemistry and dynamics, climate science, space weather, numerical weather predictions, and many other fields of geoscience.

Lessons learned from and the future for NASA's Small Explorer Program

NASA Technical Reports Server (NTRS)

Newton, George P.

1991-01-01

NASA started the Small Explorer Program to provide space scientists with an opportunity to conduct space science research in the Explorer Program using scientific payloads launched on small-class expendable launch vehicles. A series of small payload, scientific missions was envisioned that could be launched at the rate of one to two missions per year. Three missions were selected in April 1989: Solar Anomalous and Magnetospheric Particle Explorer, Fast Auroral Snapshot Explorer, and Sub-millimeter Wave Astronomy. These missions are planned for launch in June 1992, September 1994 and June 1995, respectively. At a program level, this paper presents the history, objectives, status, and lessons learned which may be applicable to similar programs, and discusses future program plans.

External Payload Interfaces on the International Space Station

NASA Astrophysics Data System (ADS)

Voels, S. A.; Eppler, D. B.; Park, B.

2000-12-01

The International Space Station (ISS) includes multiple payload locations that are external to the pressurized environment and that are suitable for astronomical and space science observations. These external or attached payload accommodation locations allow direct access to the space environment and fields of view that include the earth and/or space. NASA sponsored payloads will have access to several different types of standard external locations; the S3/P3 Truss Sites (with an EXPRESS Pallet interface), the Columbus Exposed Payload Facility (EPF), and the Japanese Experiment Module Exposed Facility (JEM-EF). Payload accommodations at each of the standard locations named above will be described, as well as transport to and retrieval from the site. The Office of Space Science's ISS Research Program Office has an allocation equivalent to 25% of the external space and opportunities for proposing to use this allocation will be as Missions of Opportunity through the normal Explorer (UNEX, SMEX, MIDEX) Announcements of Opportunity.

Contamination assessment for OSSA space station IOC payloads

NASA Technical Reports Server (NTRS)

Chinn, S.; Gordon, T.; Rantanen, R.

1987-01-01

The results are presented from a study for the Space Station Planners Group of the Office of Space Sciences and Applications. The objectives of the study are: (1) the development of contamination protection requirements for protection of Space Station attached payloads, serviced payloads and platforms; and (2) the determination of unknowns or major impacts requiring further assessment. The nature, sources, and quantitative properties of the external contaminants to be encountered on the Station are summarized. The OSSA payload contamination protection requirements provided by the payload program managers are reviewed and the level of contamination awareness among them is discussed. Preparation of revisions to the contamination protection requirements are detailed. The comparative impact of flying the Station at constant atmospheric density rather than constant altitude is assessed. The impact of the transverse boom configuration of the Station on contamination is also assessed. The contamination protection guidelines which OSSA should enforce during their development of payloads are summarized.

Interactions Measurement Payload for Shuttle (IMPS) Definition Phase Study.

DTIC Science & Technology

1984-12-15

7 -AS5 222 INTERACTIONS MEASUREMENT PAYLOAD FOR SHUTTLE (IMPS) 1/3 DEFINITION PHASE STUDY(U) JET PROPULSION LAB PASADENA CA G C HILL 15 DEC 84 JPL-D...OF FUNDING NOS. PROGRAM PROJECT TASK WORK UNIT ELEMENT NO. NO NO. NO. S 11 TITLE fnciude Security Classficalion Interactions Measure 63410F 1822 01...block number, d tor Shuttle The Interactions Measurement Payload for hyttle (IMPS) project will study interactions between large space vehicles, such as

Applications of Spacelab Payload Standard Modular Electronics /SPSME/

NASA Technical Reports Server (NTRS)

Wilkinson, D. D.; Kasulka, L. H.

1980-01-01

The NASA sponsored Spacelab Payload Standard Modular Electronics program has been designed with the basic objective of providing a space-qualified set of standardized modular electronics to support investigations identified for Spacelab payloads. These units are reusable, have functional, physical, and interface characteristics which allow them to be conveniently assembled in a multitude of configurations, and functionally interchangeable with their ground-based equivalents. The interfacing and control modules are described and typical hardware applications are presented.

USMP-3 satellite moves into CITE stand

NASA Technical Reports Server (NTRS)

1996-01-01

The United States Microgravity Payload-3 (USMP-3) is readied by KSC workers for its move from the Cargo Interface Test Equipment (CITE) stand in the Operations and Checkout (O&C) Building and installation into a payload canister along with the Tethered Satellite System-1R (TSS-1R). Once in the canister, both payloads were transported to Launch Pad 39B to be integrated into the payload bay of the Space Shuttle Orbiter Columbia during final preparations for the STS-75 mission. During the 12-day, 16-hour space flight, the 5-foot (1.6 meter)-in-diameter TSS-1R satellite will be deployed from its pallet in Columbia's payload bay to a distance of 12.4 miles (20.7) kilometers) above the orbiter as an attached, electrically-conductive tether the diameter of a wooden matchstick unwinds from a motorized reel. The objectives of the TSS program are to demonstrate the ability to deploy and control satellites on long tethers in space and to conduct space plasma experiments that include the generation of electrical power. The USMP-3 is a continuation of NASA's microgravity research program to provide advances in the fields of materials science and condensed matter physics. Four major USMP-3 experiment packages are in Columbia's payload bay, while three combustion experimetns will be conducted by the crew in a Glovebox facility located in the orbiter's middeck area.

Cargo systems manual: Heat Pipe Performance (HPP) STS-66

NASA Technical Reports Server (NTRS)

Napp, Robert

1994-01-01

The purpose of the cargo systems manual (CSM) is to provide a payload reference document for payload and shuttle flight operations personnel during shuttle mission planning, training, and flight operations. It includes orbiter-to-payload interface information and payload system information (including operationally pertinent payload safety data) that is directly applicable to the Mission Operations Directorate (MOD) role in the payload mission. The primary objectives of the heat pipe performance (HPP) are to obtain quantitative data on the thermal performance of heat pipes in a microgravity environment. This information will increase understanding of the behavior of heat pipes in space and be useful for application to design improvements in heat pipes and associated systems. The purpose of HPP-2 is to establish a complete one-g and zero-g data base for axial groove heat pipes. This data will be used to update and correlate data generated from a heat pipe design computer program called Grooved Analysis Program (GAP). The HPP-2 objectives are to: determine heat transport capacity and conductance for open/closed grooved heat pipes and different Freon volumes (nominal, under, and overcharged) using a uniform heat load; determine heat transport capacity and conductance for single/multiple evaporators using asymmetric heat loads; obtain precise static, spin, and rewicking data points for undercharged pipes; investigate heat flux limits (asymmetric heat loads); and determine effects of positive body force on thermal performance.

2015 Annual Report for the Flight Opportunities Program

NASA Technical Reports Server (NTRS)

Van Dijk, Alexander

2015-01-01

Welcome to this third edition of the Flight Opportunities program annual report. In this edition, we continue our story of pathfinding NASA's role in the partnership with the U.S. commercial space and space technology R&D communities to advance national space interests and develop technologies critical to NASA's future missions. 2015 was the year in which a planned change to our payload solicitation strategy saw its first tangible result. As you might remember from our 2014 annual report, in 2015 we set out to facilitate a more direct interaction between flight providers and technology developers by providing fixed funding awards to researchers to directly purchase the flight service(s) that best meet their needs. The selection and award of the first six REDDI-F1 flight grants to non-U.S. government researchers was an important milestone in this regard. From now on, using the REDDI-F1 solicitation appendix, the program will enable non-U.S. government researchers to directly purchase flight services on the emerging suborbital market. The same (or similar) commercial flight services will be available to NASA and other U.S. government agencies (OGA) through commercial contracts that NASA has established through our program. For the latter, our program is available to provide campaign management services, similar to the role we play(ed) for technology payloads remaining in our pool from earlier selections. The full impact of this broader strategic change will likely become more visible in the years ahead as our legacy pool gets depleted and we have implemented a new NASA- and OGA-specific call for proposals. One observation that can already be made after two rounds of REDDI-F1 solicitations is that through this change, the list of commercial flight service providers of interest to non-U.S. government researchers has grown from five in 2014 to nine in 2015. On the industry development front, our Announcement of Collaborative Opportunities (ACO) solicitation was promoted to an STMD-wide solicitation and released in 2015 in combination with the Tipping Point solicitation. A total of 22 awards was announced in November 2015, 12 of which are ACO awards, and six of these are funded by Flight Opportunities. Through these ACO awards, the program funds NASA technical expertise and NASA test facilities to aid industry partners in maturing key space technologies, in our case focusing on small launch vehicle technology development. Flight test activity in 2015 saw a steady 13 campaigns with 31 payload-flights (29 unique payloads). Thirteen new payloads were selected into the program in FY2015, and 14 payloads completed flight testing, bringing the total number of completed technology demonstration payloads to 69. Overall, we are pleased with the evolution and growth of the Flight Opportunities program and look forward to continued success in our partnership with the technology R&D community and the commercial space sector.

An evaluation of Space Shuttle STS-2 payload bay acoustic data and comparison with predictions

NASA Technical Reports Server (NTRS)

Wilby, J. F.; Piersol, A. G.; Wilby, E. G.

1982-01-01

Space average sound pressure levels computed from measurements at 18 locations in the payload bay of the Space Shuttle orbiter vehicle during the STS-2 launch were compared with predicted levels obtained using the PACES computer program. The comparisons were performed over the frequency range 12.5 Hz to 1000 Hz, since the test data at higher frequencies are contaminated by instrumentation background noise. In general the PACES computer program tends to overpredict the space average sound levels in the payload bay, although the magnitude of the discrepancy is usually small. Furthermore the discrepancy depends to some extent on the manner in which the payload is modeled analytically, and the method used to determine the "measured' space average sound pressure levels. Thus the difference between predicted and measured sound levels, averaged over the 20 one third octave bands from 12.5 Hz to 1000 Hz, varies from 1 dB to 3.5 dB.

Automated path planning of the Payload Inspection and Processing System

NASA Technical Reports Server (NTRS)

Byers, Robert M.

1994-01-01

The Payload Changeout Room Inspection and Processing System (PIPS) is a highly redundant manipulator intended for performing tasks in the crowded and sensitive environment of the Space Shuttle Orbiter payload bay. Its dexterity will be exploited to maneuver the end effector in a workspace populated with obstacles. A method is described by which the end effector of a highly redundant manipulator is directed toward a target via a Lyapunov stability function. A cost function is constructed which represents the distance from the manipulator links to obstacles. Obstacles are avoided by causing the vector of joint parameters to move orthogonally to the gradient of the workspace cost function. A C language program implements the algorithm to generate a joint history. The resulting motion is graphically displayed using the Interactive Graphical Robot Instruction Program (IGRIP) produced by Deneb Robotics. The graphical simulation has the potential to be a useful tool in path planning for the PIPS in the Shuttle Payload Bay environment.

STS-95 Post Flight Presentation

NASA Technical Reports Server (NTRS)

1998-01-01

The STS-95 flight crew, Cmdr. Curtis L. Brown, Pilot Steven W. Lindsey, Mission Specialists Scott E. Parazynski, Stephen K. Robinson, and Pedro Duque, and Payload Specialists Chiaki Mukai and John H. Glenn present a video mission over-view of their space flight. Images include prelaunch activities such as eating the traditional breakfast, crew suit-up, and the ride out to the launch pad. Also, included are various panoramic views of the shuttle on the pad. The crew can be seen being readied in the "whiteroom" for their mission. After the closing of the hatch and arm retraction, launch activities are shown including countdown, engine ignition, launch, and the separation of the Solid Rocket Boosters. The primary objectives, which include the conducting of a variety of science experiments in the pressurized SPACEHAB module, the deployment and retrieval of the Spartan free-flyer payload, and operations with the HST Orbiting Systems Test (HOST) and the International Extreme Ultraviolet Hitchhiker (IEH) payloads are discussed in both the video and still photo presentation.

Integrated operations/payloads/fleet analysis. Volume 3: System costs. Appendix A: Program direct costs

NASA Technical Reports Server (NTRS)

1971-01-01

Individualized program direct costs for each satellite program are presented. This breakdown provides the activity level dependent costs for each satellite program. The activity level dependent costs, or, more simply, program direct costs, are comprised of the total payload costs (as these costs are strictly program dependent) and the direct launch vehicle costs. Only those incremental launch vehicle costs associated directly with the satellite program are considered. For expendable launch vehicles the direct costs include the vehicle investment hardware costs and the launch operations costs. For the reusable STS vehicles the direct costs include only the launch operations, recovery operations, command and control, vehicle maintenance, and propellant support. The costs associated with amortization of reusable vehicle investment, RDT&E range support, etc., are not included.

Marshall Space Flight Center Telescience Resource Kit

NASA Technical Reports Server (NTRS)

Wade, Gina

2016-01-01

Telescience Resource Kit (TReK) is a suite of software applications that can be used to monitor and control assets in space or on the ground. The Telescience Resource Kit was originally developed for the International Space Station program. Since then it has been used to support a variety of NASA programs and projects including the WB-57 Ascent Vehicle Experiment (WAVE) project, the Fast Affordable Science and Technology Satellite (FASTSAT) project, and the Constellation Program. The Payloads Operations Center (POC), also known as the Payload Operations Integration Center (POIC), provides the capability for payload users to operate their payloads at their home sites. In this environment, TReK provides local ground support system services and an interface to utilize remote services provided by the POC. TReK provides ground system services for local and remote payload user sites including International Partner sites, Telescience Support Centers, and U.S. Investigator sites in over 40 locations worldwide. General Capabilities: Support for various data interfaces such as User Datagram Protocol, Transmission Control Protocol, and Serial interfaces. Data Services - retrieve, process, record, playback, forward, and display data (ground based data or telemetry data). Command - create, modify, send, and track commands. Command Management - Configure one TReK system to serve as a command server/filter for other TReK systems. Database - databases are used to store telemetry and command definition information. Application Programming Interface (API) - ANSI C interface compatible with commercial products such as Visual C++, Visual Basic, LabVIEW, Borland C++, etc. The TReK API provides a bridge for users to develop software to access and extend TReK services. Environments - development, test, simulations, training, and flight. Includes standalone training simulators.

Retrievable payload carrier, next generation Long Duration Exposure Facility: Update 1992

NASA Technical Reports Server (NTRS)

Perry, A. T.; Cagle, J. A.; Newman, S. C.

1993-01-01

Access to space and cost have been two major inhibitors of low Earth orbit research. The Retrievable Payload Carrier (RPC) Program is a commercial space program which strives to overcome these two barriers to space experimentation. The RPC Program's fleet of spacecraft, ground communications station, payload processing facility, and experienced integration and operations team will provide a convenient 'one-stop shop' for investigators seeking to use the unique vantage point and environment of low Earth orbit for research. The RPC is a regularly launched and retrieved, free-flying spacecraft providing resources adequate to meet modest payload/experiment requirements, and presenting ample surface area, volume, mass, and growth capacity for investigator usage. Enhanced capabilities of ground communications, solar-array-supplied electrical power, central computing, and on-board data storage pick up on the path where NASA's Long Duration Exposure Facility (LDEF) blazed the original technology trail. Mission lengths of 6-18 months, or longer, are envisioned. The year 1992 was designated as the 'International Space Year' and coincides with the 500th anniversary of Christopher Columbus's voyage to the New World. This is a fitting year in which to launch the full scale development of our unique shop of discovery whose intent is to facilitate retrieving technological rewards from another new world: space. Presented is an update on progress made on the RPC Program's development since the November 1991 LDEF Materials Workshop.

High Pressure Earth Storable Rocket Technology Program: Basic Program

NASA Technical Reports Server (NTRS)

Chazen, M. L.; Sicher, D.; Huang, D.; Mueller, T.

1995-01-01

The HIPES Program was conducted for NASA-LeRC by TRW. The Basic Program consisted of system studies, design of testbed engine, fabrication and testing of engine. Studies of both pressure-fed and pump-fed systems were investigated for N2O4 and both MMH and N2H4 fuels with the result that N2H4 provides the maximum payload for all satellites over MMH. The higher pressure engine offers improved performance with smaller envelope and associated weight savings. Pump-fed systems offer maximum payload for large and medium weight satellites while pressure-fed systems offer maximum payload for small light weight satellites. The major benefits of HIPES are high performance within a confined length maximizing payload for lightsats which are length (volume) constrained. Three types of thrust chambers were evaluated -- Copper heatsink at 400, 500 and 600 psia chamber pressures for performance/thermal; water cooled to determine heat absorbed to predict rhenium engine operation; and rhenium to validate the concept. The HIPES engine demonstrated very high performance at 50 lbf thrust (epsilon = 150) and Pc = 500 psia with both fuels: Isp = 337 sec using N2O4-N2H4 and ISP = 327.5 sec using N2O4-MMH indicating combustion efficiencies greater than 98%. A powder metallurgy rhenium engine demonstrated operation with high performance at Pc = 500 psia which indicated the viability of the concept.

Materials experiment carrier concepts definition study. Volume 1: Executive summary, part 2

NASA Technical Reports Server (NTRS)

1981-01-01

The materials experiment carrier (MEC) is an optimized carrier for near term and advanced materials processing in space (MPS) research and commercial payloads. When coupled with the space platform (SP), the MEC can provide the extended duration, high power and low acceleration environment the MPS payload typically requires. The lowest cost, technically reasonable first step MEC that meets the MPS program missions objectives with minimum programmatic risks is defined. The effectiveness of the initial MEC/space platform idea for accommodating high priority, multidiscipline, R&D and commercial MPS payloads, and conducting MPS payload oprations at affordable funding and acceptable productivity levels is demonstrated.

Space Station Simulation Computer System (SCS) study for NASA/MSFC. Concept document

NASA Technical Reports Server (NTRS)

1990-01-01

NASA's Space Station Freedom Program (SSFP) planning efforts have identified a need for a payload training simulator system to serve as both a training facility and as a demonstrator to validate operational concepts. The envisioned MSFC Payload Training Complex (PTC) required to meet this need will train the Space Station Payload of experiments that will be onboard the Space Station Freedom. The simulation will support the Payload Training Complex at MSFC. The purpose of this SCS Study is to investigate issues related to the SCS, alternative requirements, simulator approaches, and state-of-the-art technologies to develop candidate concepts and designs.

Shuttle on-orbit contamination and environmental effects

NASA Technical Reports Server (NTRS)

Leger, L. J.; Jacobs, S.; Ehlers, H. K. F.; Miller, E.

1985-01-01

Ensuring the compatibility of the space shuttle system with payloads and payload measurements is discussed. An extensive set of quantitative requirements and goals was developed and implemented by the space shuttle program management. The performance of the Shuttle system as measured by these requirements and goals was assessed partly through the use of the induced environment contamination monitor on Shuttle flights 2, 3, and 4. Contamination levels are low and generally within the requirements and goals established. Additional data from near-term payloads and already planned contamination measurements will complete the environment definition and allow for the development of contamination avoidance procedures as necessary for any payload.

The use of a cubesat to validate technological bricks in space

NASA Astrophysics Data System (ADS)

Rakotonimbahy, E.; Vives, S.; Dohlen, K.; Savini, G.; Iafolla, V.

2017-11-01

In the framework of the FP7 program FISICA (Far Infrared Space Interferometer Critical Assessment), we are developing a cubesat platform which will be used for the validation in space of two technological bricks relevant for FIRI. The first brick is a high-precision accelerometer which could be used in a future space mission as fundamental element for the dynamic control loop of the interferometer. The second brick is a miniaturized version of an imaging multi-aperture telescope. Ultimately, such an instrument could be composed of numerous space-born mirror segments flying in precise formation on baselines of hundreds or thousands of meters, providing high-resolution glimpses of distant worlds. We are proposing to build a very first space-born demonstrator of such an instrument which will fit into the limited resources of one cubesat. In this paper, we will describe the detailed design of the cubesat hosting the two payloads.

Research and Applications Modules (RAM). Phase B study: Executive summary

NASA Technical Reports Server (NTRS)

1972-01-01

The design, development, and characteristics of the Research and Applications Module (RAM) system is discussed. The RAM system is a family of payload carriers that can be delivered to and retrieved from low earth orbit by the space shuttle. The RAM payload carriers are used to support diverse technological and scientific investigations. The NASA study objectives, the relationship of the RAM payload carriers to other systems in the orbital space program, and recommendations for additional effort are presented.

Space Launch System (SLS) Mission Planner's Guide

NASA Technical Reports Server (NTRS)

Smith, David Alan

2017-01-01

The purpose of this Space Launch System (SLS) Mission Planner's Guide (MPG) is to provide future payload developers/users with sufficient insight to support preliminary SLS mission planning. Consequently, this SLS MPG is not intended to be a payload requirements document; rather, it organizes and details SLS interfaces/accommodations in a manner similar to that of current Expendable Launch Vehicle (ELV) user guides to support early feasibility assessment. Like ELV Programs, once approved to fly on SLS, specific payload requirements will be defined in unique documentation.

The role of EVA on Space Shuttle. [experimental support and maintenance activities

NASA Technical Reports Server (NTRS)

Carson, M. A.

1974-01-01

The purpose of this paper is to present the history of Extravehicular Activity (EVA) through the Skylab Program and to outline the expected tasks and equipment capabilities projected for the Space Shuttle Program. Advantages offered by EVA as a tool to extend payload capabilities and effectiveness and economic advantages of using EVA will be explored. The presentation will conclude with some guidelines and recommendations for consideration by payload investigators in establishing concepts and designs utilizing EVA support.

Automation of Space Processing Applications Shuttle payloads

NASA Technical Reports Server (NTRS)

Crosmer, W. E.; Neau, O. T.; Poe, J.

1975-01-01

The Space Processing Applications Program is examining the effect of weightlessness on key industrial materials processes, such as crystal growth, fine-grain casting of metals, and production of unique and ultra-pure glasses. Because of safety and in order to obtain optimum performance, some of these processes lend themselves to automation. Automation can increase the number of potential Space Shuttle flight opportunities and increase the overall productivity of the program. Five automated facility design concepts and overall payload combinations incorporating these facilities are presented.

Low energy stage study. Volume 5: Program study cost elements and appendices. [orbital launching of space shuttle payloads

NASA Technical Reports Server (NTRS)

1978-01-01

The methodology and rationale used in the development of costs for engineering, manufacturing, testing and operating a low thrust system for placing automated shuttle payloads into earth orbits are described. Cost related information for the recommended propulsion approach is included.

KSC-04pd1397

NASA Image and Video Library

2004-06-30

KENNEDY SPACE CENTER, FLA. - Kimberly Beck, a college trainee in Controlled Biological Systems in the Spaceflight and Life Sciences Training Program, is helping with growth studies supporting payload development. Behind her is part of the WONDER (Water Offset Nutrient Delivery Experiment) flight payload that is investigating hydroponic plant crop production in microgravity.

KSC-04PD-1397

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. Kimberly Beck, a college trainee in Controlled Biological Systems in the Spaceflight and Life Sciences Training Program, is helping with growth studies supporting payload development. Behind her is part of the WONDER (Water Offset Nutrient Delivery Experiment) flight payload that is investigating hydroponic plant crop production in microgravity.

Feasibility of Helicopter Support Seek Frost.

DTIC Science & Technology

1980-05-01

the allowable maximum weight can be used as the payload. The payload is a variable. Small helicopters with full fuel and auxillary tanks can fly...equipment, that the program to obtain icing approval on the S-76 will be finalized for management evaluation, and a decision can be made at that time to

User benefits and funding strategies. [technology assessment and economic analysis of the space shuttles and NASA Programs

NASA Technical Reports Server (NTRS)

Archer, J. L.; Beauchamp, N. A.; Day, C. F.

1975-01-01

The justification, economic and technological benefits of NASA Space Programs (aside from pure scientific objectives), in improving the quality of life in the United States is discussed and outlined. Specifically, a three-step, systematic method is described for selecting relevant and highly beneficial payloads and instruments for the Interim Upper Stage (IUS) that will be used with the space shuttle until the space tug becomes available. Viable Government and private industry cost-sharing strategies which would maximize the number of IUS payloads, and the benefits obtainable under a limited NASA budget were also determined. Charts are shown which list the payload instruments, and their relevance in contributing to such areas as earth resources management, agriculture, weather forecasting, and many others.

Project Explorer - Student experiments aboard the Space Shuttle

NASA Technical Reports Server (NTRS)

Buckbee, E.; Dannenberg, K.; Driggers, G.; Orillion, A.

1979-01-01

Project Explorer, a program of high school student experiments in space in a Space Shuttle self-contained payload unit (Getaway Special), sponsored by the Alabama Space and Rocket Center (ASRC) in cooperation with four Alabama universities is presented. Organizations aspects of the project, which is intended to promote public awareness of the space program and encourage space research, are considered, and the proposal selection procedure is outlined. The projects selected for inclusion in the self-contained payload canister purchased in 1977 and expected to be flown on an early shuttle mission include experiments on alloy solidification, electric plating, whisker growth, chick embryo development and human blood freezing, and an amateur radio experiment. Integration support activities planned and underway are summarized, and possible uses for a second payload canister purchased by ASRC are discussed.

KSC-98pc280

NASA Image and Video Library

1998-02-06

The STS-90 Neurolab payload is honored with a ceremony after being lowered into its payload canister in KSC's Operations and Checkout Building for the last time. This phase of the Shuttle program is winding down as the second phase of the International Space Station (ISS) program gets under way. Microgravity and life science research that formerly was conducted in Spacelab modules, such as Neurolab, will eventually be conducted inside the completed ISS. Investigations during the Neurolab mission will focus on the effects of microgravity on the nervous system. The crew of STS-90, slated for launch in April, will include Commander Richard Searfoss, Pilot Scott Altman, Mission Specialists Richard Linnehan, Dafydd (Dave) Williams, M.D., and Kathryn (Kay) Hire, and Payload Specialists Jay Buckey, M.D., and James Pawelczyk, Ph.D

A technique for incorporating the NASA spacelab payload dedicated experiment processor software into the simulation system for the payload crew training complex

NASA Technical Reports Server (NTRS)

Bremmer, D. A.

1986-01-01

The feasibility of some off-the-shelf microprocessors and state-of-art software is assessed (1) as a development system for the principle investigator (pi) in the design of the experiment model, (2) as an example of available technology application for future PI's experiments, (3) as a system capable of being interactive in the PCTC's simulation of the dedicated experiment processor (DEP), preferably by bringing the PI's DEP software directly into the simulation model, (4) as a system having bus compatibility with host VAX simulation computers, (5) as a system readily interfaced with mock-up panels and information displays, and (6) as a functional system for post mission data analysis.

A Mars Exploration Discovery Program

NASA Astrophysics Data System (ADS)

Hansen, C. J.; Paige, D. A.

2000-07-01

The Mars Exploration Program should consider following the Discovery Program model. In the Discovery Program a team of scientists led by a PI develop the science goals of their mission, decide what payload achieves the necessary measurements most effectively, and then choose a spacecraft with the capabilities needed to carry the payload to the desired target body. The primary constraints associated with the Discovery missions are time and money. The proposer must convince reviewers that their mission has scientific merit and is feasible. Every Announcement of Opportunity has resulted in a collection of creative ideas that fit within advertised constraints. Following this model, a "Mars Discovery Program" would issue an Announcement of Opportunity for each launch opportunity with schedule constraints dictated by the launch window and fiscal constraints in accord with the program budget. All else would be left to the proposer to choose, based on the science the team wants to accomplish, consistent with the program theme of "Life, Climate and Resources". A proposer could propose a lander, an orbiter, a fleet of SCOUT vehicles or penetrators, an airplane, a balloon mission, a large rover, a small rover, etc. depending on what made the most sense for the science investigation and payload. As in the Discovery program, overall feasibility relative to cost, schedule and technology readiness would be evaluated and be part of the selection process.

A Mars Exploration Discovery Program

NASA Technical Reports Server (NTRS)

Hansen, C. J.; Paige, D. A.

2000-01-01

The Mars Exploration Program should consider following the Discovery Program model. In the Discovery Program a team of scientists led by a PI develop the science goals of their mission, decide what payload achieves the necessary measurements most effectively, and then choose a spacecraft with the capabilities needed to carry the payload to the desired target body. The primary constraints associated with the Discovery missions are time and money. The proposer must convince reviewers that their mission has scientific merit and is feasible. Every Announcement of Opportunity has resulted in a collection of creative ideas that fit within advertised constraints. Following this model, a "Mars Discovery Program" would issue an Announcement of Opportunity for each launch opportunity with schedule constraints dictated by the launch window and fiscal constraints in accord with the program budget. All else would be left to the proposer to choose, based on the science the team wants to accomplish, consistent with the program theme of "Life, Climate and Resources". A proposer could propose a lander, an orbiter, a fleet of SCOUT vehicles or penetrators, an airplane, a balloon mission, a large rover, a small rover, etc. depending on what made the most sense for the science investigation and payload. As in the Discovery program, overall feasibility relative to cost, schedule and technology readiness would be evaluated and be part of the selection process.

Space Operations Training Concepts Benchmark Study (Training in a Continuous Operations Environment)

NASA Technical Reports Server (NTRS)

Johnston, Alan E.; Gilchrist, Michael; Underwood, Debrah (Technical Monitor)

2002-01-01

The NASA/USAF Benchmark Space Operations Training Concepts Study will perform a comparative analysis of the space operations training programs utilized by the United States Air Force Space Command with those utilized by the National Aeronautics and Space Administration. The concentration of the study will be focused on Ground Controller/Flight Controller Training for the International Space Station Payload Program. The duration of the study is expected to be five months with report completion by 30 June 2002. The U.S. Air Force Space Command was chosen as the most likely candidate for this benchmark study because their experience in payload operations controller training and user interfaces compares favorably with the Payload Operations Integration Center's training and user interfaces. These similarities can be seen in the dynamics of missions/payloads, controller on-console requirements, and currency/proficiency challenges to name a few. It is expected that the report will look at the respective programs and investigate goals of each training program, unique training challenges posed by space operations ground controller environments, processes of setting up controller training programs, phases of controller training, methods of controller training, techniques to evaluate adequacy of controller knowledge and the training received, and approaches to training administration. The report will provide recommendations to the respective agencies based on the findings. Attached is a preliminary outline of the study. Following selection of participants and an approval to proceed, initial contact will be made with U.S. Air Force Space Command Directorate of Training to discuss steps to accomplish the study.

Conducting Research on the International Space Station Using the EXPRESS Rack Facilities

NASA Technical Reports Server (NTRS)

Thompson, Sean W.; Lake, Robert E.

2014-01-01

EXPRESS Racks provide capability for payload access to ISS resources. The successful on-orbit operations and versatility of the EXPRESS Rack has facilitated the operations of many scientific areas, with the promise of continued payload support for years to come. EXPRESS Racks are currently deployed in the US Lab, Columbus and JEM. Process improvements and enhancements continue to improve the accommodations and make the integration and operations process more efficient. Payload Integration Managers serve as the primary interface between the ISS Program and EXPRESS Payload Developers. EXPRESS Project coordinates across multiple functional areas and organizations to ensure integrated EXPRESS Rack and subrack products and hardware are complete, accurate, on time, safe, and certified for flight. NASA is planning to expand the EXPRESS payload capacity by developing new Basic Express Racks expected to be on ISS in 2018.

Technical draft study report for TOPEX satellite options study, volume 1

NASA Technical Reports Server (NTRS)

1981-01-01

The use of two spacecraft for adaptation to the TOPEX mission, namely the P80-1 and the GPS phase 2 are considered. The mission involved three mission options, each option varying in payload definition, payload weight, orbital altitude and payload power requirements. The P80-1 spacecraft is an Air Force Space Test Program satellite which carries a number of payloads to an orbital altitude of 400 n.mi. at a minimum inclination of 72.5 deg, and which has an orbital life capability of three years. The GPS phase 2 spacecraft is the operational satellite for the Global Positioning NAVSTAR navigation constellation provided for all service (and commercial) use.

Global-scale Observations of the Limb and Disk (GOLD): Hosted Payload Accommodation on a Commercial Satellite

NASA Astrophysics Data System (ADS)

Lankton, M.; Eastes, R.; McClintock, W. E.; Pang, R.; Caffrey, R.; Krywonos, A.

2013-12-01

The Global-Scale Observations of the Limb and Disk (GOLD) mission will perform unprecedented imaging of the Earth's thermosphere and ionosphere (TI) system from geostationary (GEO) orbit. Flying as a hosted payload on a commercial communications satellite, GOLD takes advantage of the resource margins available in the early years of the commercial mission's planned 15-year life. This hosted payload approach is a pathfinder for cost-effective NASA science missions. The affordable ride to GEO makes it possible for an Explorer-class Mission of Opportunity to perform Far UltraViolet (FUV) imaging of nearly a complete hemisphere on a 30-minute cadence. This global-scale, high cadence imaging will enable GOLD to distinguish between spatial and temporal variations in the TI system caused by geomagnetic storms, variations in solar EUV, and forcing from the lower atmosphere. The most significant difference between developing instrumentation for a NASA-owned mission and accomplishing the same task for a commercial satellite is that communications satellites are procured on a faster schedule - 24 to 36 months from satellite contract to launch - than the instrument development. GOLD has partnered with SES Government Solutions (SES-GS), the comsat mission owner-operator, to define instrument interfaces and requirements that will be included in the eventual Request for Proposal to candidate spacecraft vendors. SES-GS launches 3 to 4 missions per year, which allows the GOLD-SES-GS partnership to match the instrument's launch readiness date with a suitable mission. In addition to making geostationary orbit accessible to a science instrument at relatively low cost, commercial communications satellites provides a host platform with very high reliability and long life, easy access to continuous high-speed data downlink and near-real-time data delivery, and stable pointing. SES-GS operates their satellite from established Telemetry, Tracking and Control (TT&C) centers. The GOLD Science Operations Center at the University of Colorado Laboratory for Atmospheric and Space Physics (LASP) will produce instrument command loads for uplink by the TT&C, receive data from the ground station, monitor instrument state of health, and perform quick-look data processing. The GOLD Science Data Center at the University of Central Florida will produce, distribute and archive science data products.

The NASA Sounding Rocket Program and space sciences.

PubMed

Gurkin, L W

1992-10-01

High altitude suborbital rockets (sounding rockets) have been extensively used for space science research in the post-World War II period; the NASA Sounding Rocket Program has been on-going since the inception of the Agency and supports all space science disciplines. In recent years, sounding rockets have been utilized to provide a low gravity environment for materials processing research, particularly in the commercial sector. Sounding rockets offer unique features as a low gravity flight platform. Quick response and low cost combine to provide more frequent spaceflight opportunities. Suborbital spacecraft design practice has achieved a high level of sophistication which optimizes the limited available flight times. High data-rate telemetry, real-time ground up-link command and down-link video data are routinely used in sounding rocket payloads. Standard, off-the-shelf, active control systems are available which limit payload body rates such that the gravitational environment remains less than 10(-4) g during the control period. Operational launch vehicles are available which can provide up to 7 minutes of experiment time for experiment weights up to 270 kg. Standard payload recovery systems allow soft impact retrieval of payloads. When launched from White Sands Missile Range, New Mexico, payloads can be retrieved and returned to the launch site within hours.

The NASA Sounding Rocket Program and space sciences

NASA Technical Reports Server (NTRS)

Gurkin, L. W.

1992-01-01

High altitude suborbital rockets (sounding rockets) have been extensively used for space science research in the post-World War II period; the NASA Sounding Rocket Program has been on-going since the inception of the Agency and supports all space science disciplines. In recent years, sounding rockets have been utilized to provide a low gravity environment for materials processing research, particularly in the commercial sector. Sounding rockets offer unique features as a low gravity flight platform. Quick response and low cost combine to provide more frequent spaceflight opportunities. Suborbital spacecraft design practice has achieved a high level of sophistication which optimizes the limited available flight times. High data-rate telemetry, real-time ground up-link command and down-link video data are routinely used in sounding rocket payloads. Standard, off-the-shelf, active control systems are available which limit payload body rates such that the gravitational environment remains less than 10(-4) g during the control period. Operational launch vehicles are available which can provide up to 7 minutes of experiment time for experiment weights up to 270 kg. Standard payload recovery systems allow soft impact retrieval of payloads. When launched from White Sands Missile Range, New Mexico, payloads can be retrieved and returned to the launch site within hours.

STS-87 Payload installation in LC 39B PCR

NASA Technical Reports Server (NTRS)

1997-01-01

A payload canister, seen here half-open, containing the primary payloads for the STS-87 mission, is moved into the Payload Changeout Room at Pad 39B at Kennedy Space Center. The STS-87 payload includes the United States Microgravity Payload-4 (USMP- 4), seen here on two Multi-Purpose Experiment Support Structures in the center of the photo, and Spartan-201, wrapped in a protective covering directly above the USMP-4 experiments. Spartan-201 is a small retrievable satellite involved in research to study the interaction between the Sun and its wind of charged particles. USMP-4 is one of a series of missions designed to conduct scientific research aboard the Shuttle in the unique microgravity environment for extended periods of time. In the past, USMP missions have provided invaluable experience in the design of instruments needed for the International Space Station (ISS) and microgravity programs to follow in the 21st century. STS-87 is scheduled for launch Nov. 19.

Accomplishing Transformative Research in a Challenging Fiscal Environment

NASA Astrophysics Data System (ADS)

Mitchell, E. J.; Paxton, L. J.; Bust, G.

2014-12-01

The shift in funding is forcing scientists to promise transformative research for a pittance. To accomplish this, researchers need to transform their methodology to include societal buy-in, use of commercial off-the-shelf (COTS) technology, and cross-discipline platform usage. As the cutting edge of research expands to view the system on the global scale with extremely fine resolution, fiscally reasonable budgets present a challenge to be met. Consider how do we measure a specific variable over 45-degrees of latitude in an isolated and hostile region of Earth - the total electron count over the South Pole? This work examines this transformative research using hosted payloads on buoys, balloons, and unmanned aerial vehicles (UAVs). We will show cutting edge research occurring simultaneous with education and public outreach, offering societal buy-in through interactive websites and student-built hosted payloads. These interactions provide a vision to the public and a new database to the scientists. The use of COTS technology and cross-discipline (oceanography and space) platforms keep the cost low. We will discuss a general methodology for accomplishing transformative research in a challenging fiscal environment through integration of COTS technology, assimilative and first principle models, and observing systems simulation experiments (OSSEs).

Payload test philosophy. [JPL views on qualification/acceptance testing

NASA Technical Reports Server (NTRS)

Gindorf, T.

1979-01-01

The general philosophy of how JPL views payload qualification/acceptance testing for programs that are done either in-house or by contractors is described. Particular attention is given to mission risk classifications, preliminary critical design reviews, environmental design requirements, the thermal and dynamics development tests, and the flight spacecraft system test.

Preliminary analysis of an integrated logistics system for OSSA payloads. Volume 2: OSSA integrated logistics support strategy

NASA Technical Reports Server (NTRS)

Palguta, T.; Bradley, W.; Stockton, T.

1988-01-01

The purpose is to outline an Office of Space Science and Applications (OSSA) integrated logistics support strategy that will ensure effective logistics support of OSSA payloads at an affordable life-cycle cost. Program objectives, organizational relationships, and implementation of the logistics strategy are discussed.

Small Satellites and the DARPA/Air Force Falcon Program

NASA Technical Reports Server (NTRS)

Weeks, David J.; Walker, Steven H.; Sackheim, Robert L.

2004-01-01

The FALCON ((Force Application and Launch from CONUS) program is a technology demonstration effort with three major components: a Small Launch Vehicle (SLV), a Common Aero Vehicle (CAV), and a Hypersonic Cruise Vehicle (HCV). Sponsored by DARPA and executed jointly by the United States Air Force and DARPA with NASA participation, the objectives are to develop and demonstrate technologies that will enable both near-term and far-term capability to execute time-critical, global reach missions. The focus of this paper is on the SLV as it relates to small satellites and the implications of lower cost to orbit for small satellites. The target recurring cost for placing 1000 pounds payloads into a circular reference orbit of 28.5 degrees at 100 nautical miles is $5,000,000 per launch. This includes range costs but not the payload or payload integration costs. In addition to the nominal 1000 pounds to LEO, FALCON is seeking delivery of a range of orbital payloads from 220 pounds to 2200 pounds to the reference orbit. Once placed on alert status, the SLV must be capable of launch within 24 hours.

Modernization of NASA's Johnson Space Center Chamber: A Payload Transport Rail System to Support Cryogenic Vacuum Optical Testing of the James Webb Space Telescope (JWST)

NASA Technical Reports Server (NTRS)

Garcia, Sam; Homan, Jonathan; Speed, John

2016-01-01

NASA is the mission lead for the James Webb Space Telescope (JWST), the next of the "Great Observatories", scheduled for launch in 2018. It is directly responsible for the integration and test (I&T) program that will culminate in an end-to-end cryo vacuum optical test of the flight telescope and instrument module in Chamber A at NASA Johnson Space Center. Historic Chamber A is the largest thermal vacuum chamber at Johnson Space Center and one of the largest space simulation chambers in the world. Chamber A has undergone a major modernization effort to support the deep cryogenic, vacuum and cleanliness requirements for testing the JWST. This paper describe the challenges of developing, integrating and modifying new payload rails capable of transporting payloads within the thermal vacuum chamber up to 65,000 pounds. Ambient and Cryogenic Operations required to configure for testing will be explained. Lastly review historical payload configurations stretching from the Apollo program era to current James Webb Space Telescope testing.

Heavy-Lift for a New Paradigm in Space Operations

NASA Technical Reports Server (NTRS)

Morris, Bruce; Burkey, Martin

2010-01-01

NASA is developing an unprecedented heavy-lift capability to enable human exploration beyond low Earth orbit (LEO). This capability could also significantly enhance numerous other missions of scientific, national security, and commercial importance. That capability is currently configured as the Ares V cargo launch vehicle. This capability will eclipse the capability the United States lost with the retirement of the Saturn V. It is capable of launching roughly 53 percent more payload mass to trans lunar injection (TLI) and 30 percent more payload mass to LEO than its Apollo Program predecessor. Ares V is a major element of NASA's Constellation Program, which also includes the Ares I crew launch vehicle (CLV), Orion crew exploration vehicle (CEV), and a lunar lander for crew and cargo. As currently configured, Ares V will be capable of launching 413,800 pounds (187.7 mT) to LEO, 138,500 pounds (63 mT) direct to the Moon or 156,700 pounds (71.1 mT) in its dual-launch architecture role with Ares I. Its 33-foot (10 m) shroud provides unprecedented payload volume. Assessment of astronomy and planetary science payload requirements since spring 2008 has indicated that a Saturn V-class heavy-lift vehicle has the potential to support a range of payloads and missions. This vehicle configuration enables some missions previously considered difficult or impossible and enhances many others. Collaborative design/architecture inputs, exchanges, and analyses have already begun between scientists and payload developers. This early dialogue between NASA engineers and payload designers allows both communities to shape their designs and operational concepts to be mutually supportive to the extent possible with the least financial impact. This paper provides an overview of the capabilities of a heavy-lift vehicle to launch payloads with increased mass and/or volume and reduce technical and cost risk in both design and operations.

Parametric evaluation of the cost effectiveness of Shuttle payload vibroacoustic test plans

NASA Technical Reports Server (NTRS)

Stahle, C. V.; Gongloff, H. R.; Keegan, W. B.; Young, J. P.

1978-01-01

Consideration is given to alternate vibroacoustic test plans for sortie and free flyer Shuttle payloads. Statistical decision models for nine test plans provide a viable method of evaluating the cost effectiveness of alternate vibroacoustic test plans and the associated test levels. The methodology is a major step toward the development of a useful tool for the quantitative tailoring of vibroacoustic test programs to sortie and free flyer payloads. A broader application of the methodology is now possible by the use of the OCTAVE computer code.

The Space Shuttle - A future space transportation system

NASA Technical Reports Server (NTRS)

Thompson, R. F.

1974-01-01

The objective of the Space Shuttle Program is to achieve an economical space transportation system. This paper provides an introductory review of the considerations which led to the Government decisions to develop the Space Shuttle. The role of a space transportation system is then considered within the context of historical developments in the general field of transportation, followed by a review of the Shuttle system, mission profile, payload categories, and payload accommodations which the Shuttle system will provide, and concludes with a forecast of the systems utilization for space science research and payload planning activity.

NASA Enterprise Visual Analysis

NASA Technical Reports Server (NTRS)

Lopez-Tellado, Maria; DiSanto, Brenda; Humeniuk, Robert; Bard, Richard, Jr.; Little, Mia; Edwards, Robert; Ma, Tien-Chi; Hollifield, Kenneith; White, Chuck

2007-01-01

NASA Enterprise Visual Analysis (NEVA) is a computer program undergoing development as a successor to Launch Services Analysis Tool (LSAT), formerly known as Payload Carrier Analysis Tool (PCAT). NEVA facilitates analyses of proposed configurations of payloads and packing fixtures (e.g. pallets) in a space shuttle payload bay for transport to the International Space Station. NEVA reduces the need to use physical models, mockups, and full-scale ground support equipment in performing such analyses. Using NEVA, one can take account of such diverse considerations as those of weight distribution, geometry, collision avoidance, power requirements, thermal loads, and mechanical loads.

A 20k Payload Launch Vehicle Fast Track Development Concept Using an RD-180 Engine and a Centaur Upper Stage

NASA Technical Reports Server (NTRS)

Toelle, Ronald (Compiler)

1995-01-01

A launch vehicle concept to deliver 20,000 lb of payload to a 100-nmi orbit has been defined. A new liquid oxygen/kerosene booster powered by an RD-180 engine was designed while using a slightly modified Centaur upper stage. The design, development, and test program met the imposed 40-mo schedule by elimination of major structural testing by increased factors of safety and concurrent engineering concepts. A growth path to attain 65,000 lb of payload is developed.

Effects of the specular Orbiter forward radiators on a typical Spacelab payload thermal environment

NASA Technical Reports Server (NTRS)

Turner, L. D.; Humphries, W. R.; Littles, J. W.

1981-01-01

Orbiter radiators, having a specular reflection, must be considered when determining the design environment for payloads which can view the forward deployed radiators. Unlike most surfaces on the Orbiter, which reflect energy diffusely, the radiators are covered with a highly specular silverized Teflon material, with high emissivity, and have a concave contour, producing a local concentration of reflected energy towards the region of angle incidence. The combined effects of radiator specularity and geometry were analyzed using the Thermal Radiation Analysis System (TRASYS II), a specialized ray trace program, and a generalized Monte-Carlo-based thermal radiation program. Data given for a 0 deg payload inclination angle at orbital noon at 3.454 m indicate that the maximum total flux and average flux can increase 173% and 63%, respectively, when compared to diffuse radiators.

ELITE Program: Electric Insertion Transfer Experiment

NASA Technical Reports Server (NTRS)

Vondra, Robert

1992-01-01

The topics are presented in viewgraph form and include the following: the Cooperative Research & Development Agreement (CRDA); spacecraft; benefits; program milestones; subsystem status; partners; and payloads.

Users manual for the IMA program

NASA Technical Reports Server (NTRS)

Williams, D. F.

1991-01-01

The Impulsive Mission Analysis (IMA) computer program provides a user-friendly means of designing a complete Earth-orbital mission profile using an 80386-based microcomputer. The IMA program produces a trajectory summary, an output file for use by the new Simplex Computation of Optimum Orbital Trajectories (SCOOT) program, and several graphics, including ground tracks on a world map, altitude profiles, relative motion plots, and sunlight/communication timelines. The user can design missions using any combination of three basic types of mission segments: double co-eliptic rendezvous, payload delivery, and payload de-orbit/spacecraft recovery. Each mission segment is divided into one or more transfers, and each transfer is divided into one or more legs, each leg consisting of a coast arc followed by a burn arc.

Highly reusable space transportation: Approaches for reducing ETO launch costs to $100 - $200 per pound of payload

NASA Technical Reports Server (NTRS)

Olds, John R.

1995-01-01

The Commercial Space Transportation Study (CSTS) suggests that considerable market expansion in earth-to-orbit transportation would take place if current launch prices could be reduced to around $400 per pound of payload. If these low prices can be achieved, annual payload delivered to low earth orbit (LEO) is predicted to reach 6.7 million pounds. The primary market growth will occur in communications, government missions, and civil transportation. By establishing a cost target of $100-$200 per pound of payload for a new launch system, the Highly Reusable Space Transportation (HRST) program has clearly set its sights on removing the current restriction on market growth imposed by today's high launch costs. In particular, achieving the goal of $100-$200 per pound of payload will require significant coordinated efforts in (1) marketing strategy development, (2) business planning, (3) system operational strategy, (4) vehicle technical design, and (5) vehicle maintenance strategy.

Space Launch System Co-Manifested Payload Options for Habitation

NASA Technical Reports Server (NTRS)

Smitherman, David

2015-01-01

The Space Launch System (SLS) has a co-manifested payload capability that will grow over time as the launch vehicle matures and planned upgrades are implemented. The final configuration is planned to be capable of inserting a payload greater than 10 metric tons (mt) into a trans-lunar injection trajectory along with the crew in the Orion capsule and its service module. The co-manifested payload is located below the Orion and its service module in a 10 m high fairing similar to the way the Saturn launch vehicle carried the lunar lander below the Apollo command and service modules. Various approaches that utilize this comanifested payload capability to build up infrastructure in deep space have been explored in support of future asteroid, lunar, and Mars mission scenarios. This paper reports on the findings of the Advanced Concepts Office study team at NASA Marshall Space Flight Center (MSFC) working with the Advanced Exploration Systems Program on the Exploration Augmentation Module Project. It includes some of the possible options for habitation in the co-manifested payload volume of the SLS. Findings include a set of module designs that can be developed in 10 mt increments to support these co-manifested payload missions along with a comparison of this approach to a large-module payload flight configuration for the SLS.

Simulation of electrical and thermal fields in a multimode microwave oven using software written in C++

NASA Astrophysics Data System (ADS)

Abrudean, C.

2017-05-01

Due to multiple reflexions on walls, the electromagnetic field in a multimode microwave oven is difficult to estimate analytically. This paper presents a C++ program that calculates the electromagnetic field in a resonating cavity with an absorbing payload, uses the result to calculate heating in the payload taking its properties into account and then repeats. This results in a simulation of microwave heating, including phenomena like thermal runaway. The program is multithreaded to make use of today’s common multiprocessor/multicore computers.

VAPEPS user's reference manual, version 5.0

NASA Technical Reports Server (NTRS)

Park, D. M.

1988-01-01

This is the reference manual for the VibroAcoustic Payload Environment Prediction System (VAPEPS). The system consists of a computer program and a vibroacoustic database. The purpose of the system is to collect measurements of vibroacoustic data taken from flight events and ground tests, and to retrieve this data and provide a means of using the data to predict future payload environments. This manual describes the operating language of the program. Topics covered include database commands, Statistical Energy Analysis (SEA) prediction commands, stress prediction command, and general computational commands.

Recent sounding rocket highlights and a concept for melding sounding rocket and space shuttle activities

NASA Technical Reports Server (NTRS)

Lane, J. H.; Mayo, E. E.

1980-01-01

Highlights include launching guided vehicles into the African Solar Eclipse, initiation of development of a Three-Stage Black Brant to explore the dayside polar cusp, large payload Aries Flights at White Sands Missile Range, and an active program with the Orion vehicle family using surplus motors. Sounding rocket philosophy and experience is being applied to the shuttle in a Get Away Special and Experiments of Opportunity Payloads Programs. In addition, an orbit selection and targeting software system to support shuttle pallet mounted experiments is under development.

Hitchhiker capabilities

NASA Technical Reports Server (NTRS)

Goldsmith, Theodore C.

1988-01-01

A carrier system has been developed for economical and quick response flight of small attached payloads on the space shuttle. Hitchhiker can accommodate up to 750 lb of customer payloads in canisters or mounted to an exposed side-mount plate, or up to 1200 lb mounted on a cross-bay structure. The carrier connects to the orbiter's electrical systems and provides up to six customers with standard electrical services including power, real time telemetry and commands. A transparent data and command system concept is employed to allow the customer to easily use his own ground support equipment and personnel to control his payload during integration and flight operations. A general description of the Hitchhiker program and the Shuttle Payload of Opportunity Carrier (SPOC) is given and future enhancements are outlined.

Multipurpose satellite bus (MPS)

NASA Technical Reports Server (NTRS)

1991-01-01

The Naval Postgraduate School Advanced Design Project sponsored by the Universities Space Research Association Advanced Design Program is a multipurpose satellite bus (MPS). The design was initiated from a Statement of Work (SOW) developed by the Defense Advanced Research Projects Agency (DARPA). The SOW called for a 'proposal to design a small, low-cost, lightweight, general purpose spacecraft bus capable of accommodating any of a variety of mission payloads. Typical payloads envisioned include those associated with meteorological, communication, surveillance and tracking, target location, and navigation mission areas.' The design project investigates two dissimilar missions, a meteorological payload and a communications payload, mated with a single spacecraft bus with minimal modifications. The MPS is designed for launch aboard the Pegasus Air Launched Vehicle (ALV) or the Taurus Standard Small Launch Vehicle (SSLV).

Space transportation system payload interface verification

NASA Technical Reports Server (NTRS)

Everline, R. T.

1977-01-01

The paper considers STS payload-interface verification requirements and the capability provided by STS to support verification. The intent is to standardize as many interfaces as possible, not only through the design, development, test and evaluation (DDT and E) phase of the major payload carriers but also into the operational phase. The verification process is discussed in terms of its various elements, such as the Space Shuttle DDT and E (including the orbital flight test program) and the major payload carriers DDT and E (including the first flights). Five tools derived from the Space Shuttle DDT and E are available to support the verification process: mathematical (structural and thermal) models, the Shuttle Avionics Integration Laboratory, the Shuttle Manipulator Development Facility, and interface-verification equipment (cargo-integration test equipment).

The Geo Quick Ride (GQR) Program: Providing Inexpensive and Frequent Access to Space

NASA Technical Reports Server (NTRS)

Caffrey, Robert; Baniszewski, John

2004-01-01

This paper examines piggybacking NASA, university, and industry payloads on commercial geosynchronous satellites. NASA's RSDO Office awarded Geo Quick Ride (GQR) study contracts in 1998 to spacecraft manufactures to examine the issues with flying secondary payloads. The study results were very promising. Commercial communication satellites have frequent flights and significant unused resources that could be used to fly secondary payloads. However, manifesting secondary payloads on a commercial revenue-generating satellite is a complex problem to solve. The solution requires multiple simultaneous approaches in order to be successful. There are business, economic, technical, schedule, and organizational issues to be resolved. This paper examines the Geo Quick Ride (GQR) concept, discusses the development issues, and describes how this concept solves many of these issues.

Microgravity Research Results and Experiences from the NASA Mir Space Station Program

NASA Technical Reports Server (NTRS)

Schagheck, R. A.; Trach, B.

2000-01-01

The Microgravity Research Program Office (MRPO) participated aggressively in Phase I of the International Space Station Program using the Russian Mir Space Station. The Mir Station offered an otherwise unavailable opportunity to explore the advantages and challenges to long duration microgravity space research. Payloads with both NASA and commercial backing were included as well as cooperative research with the Canadian Space Agency (CSA). From this experience, much was learned about dealing with long duration on orbit science utilization and developing new working relationships with our Russian partner to promote efficient planning, operations, and integration to solve complexities associated with a multiple partner program. Microgravity participation in the NASA Mir Program began with the first joint NASA Mir flight to the Mir Space Station. The earliest participation setup acceleration measurement capabilities that were used throughout the Program. Research, conducted by all Microgravity science disciplines, continued on each subsequent increment for the entire three-year duration of the Program. The Phase I Program included the Microgravity participation of over 30 Fluids, Combustion, Materials, and Biotechnology Sciences and numerous commercially sponsored research payloads. In addition to the research gained from Microgravity investigations, long duration operation of facility hardware was tested. Microgravity facilities operated on Mir included the Space Acceleration Measurement System (SAMS), the Microgravity Glovebox (MGBX), the Biotechnology System (BTS) and the Canadian Space Agency sponsored Microgravity Isolation Mount (MIM). The Russian OPTIZONE Furnace was also incorporated into our material science research. All of these efforts yielded significant and useful scientific research data. This paper focuses on the microgravity research conducted onboard the Mir space station. It includes the Program preparation and planning necessary to support this type of cross increment research experience; the payloads which were flown; and summaries of significant microgravity science findings. Most importantly this paper highlights the various disciplines of microgravity research conducted during the International Space Station, Phase 1 Program onboard the Mir Station. A capsulation of significant research and the applicability of our findings are provided. In addition, a brief discussion of how future microgravity science gathering capabilities, hardware development and payload operations techniques have enhanced our ability to conduct long duration microgravity research.

Space Access for Small Satellites on the K-1

NASA Astrophysics Data System (ADS)

Faktor, L.

Affordable access to space remains a major obstacle to realizing the increasing potential of small satellites systems. On a per kilogram basis, small launch vehicles are simply too expensive for the budgets of many small satellite programs. Opportunities for rideshare with larger payloads on larger launch vehicles are still rare, given the complications associated with coordinating delivery schedules and deployment orbits. Existing contractual mechanisms are also often inadequate to facilitate the launch of multiple payload customers on the same flight. Kistler Aerospace Corporation is committed to lowering the price and enhancing the availability of space access for small satellite programs through the fully-reusable K-1 launch vehicle. Kistler has been working with a number of entities, including Astrium Ltd., AeroAstro, and NASA, to develop innovative approaches to small satellite missions. The K-1 has been selected by NASA as a Flight Demonstration Vehicle for the Space Launch Initiative. NASA has purchased the flight results during the first four K-1 launches on the performance of 13 advanced launch vehicle technologies embedded in the K-1 vehicle. On K-1 flights #2-#4, opportunities exist for small satellites to rideshare to low-earth orbit for a low-launch price. Kistler's flight demonstration contract with NASA also includes options to fly Add-on Technology Experiment flights. Opportunities exist for rideshare payloads on these flights as well. Both commercial and government customers may take advantage of the rideshare pricing. Kistler is investigating the feasibility of flying dedicated, multiple small payload missions. Such a mission would launch multiple small payloads from a single customer or small payloads from different customers. The orbit would be selected to be compatible with the requirements of as many small payload customers as possible, and make use of reusable hardware, standard interfaces (such as the existing MPAS) and verification plans. With sufficient demand, Kistler can schedule regular fixed "departures" for small payloads. Kistler and Astrium, Ltd., have initiated an effort to design reusable Multiple Payload Adapter Systems (MPAS) for use on the K-1. These adapters borrow from the heritage and standard interfaces used by Astrium in the Ariane Structure for Auxiliary Payloads (ASAP). One of these dispensers may be used to deploy small satellites during K-1 flights #2-#4.

Satellite services system analysis study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1981-01-01

Service requirements are considered. Topics include development of on-orbit operations scenarios, service equipment summary, crew interaction, and satellite features facilitating servicing. Service equipment concepts are considered. Topics include payload deployment, close proximity retrieval, on-orbit servicing, backup/contingency, delivery/retrieval of high energy payloads, Earth return, optional service, and advanced capabilities. Program requirements are assessed.

Life sciences payloads analyses and technical program planning studies. [project planning of space missions of space shuttles in aerospace medicine and space biology

NASA Technical Reports Server (NTRS)

1976-01-01

Contractural requirements, project planning, equipment specifications, and technical data for space shuttle biological experiment payloads are presented. Topics discussed are: (1) urine collection and processing on the space shuttle, (2) space processing of biochemical and biomedical materials, (3) mission simulations, and (4) biomedical equipment.

Impact of low cost refurbishable and standard spacecraft upon future NASA space programs. Payload effects follow-on study, appendix

NASA Technical Reports Server (NTRS)

1972-01-01

Mission analysis is discussed, including the consolidation and expansion of mission equipment and experiment characteristics, and determination of simplified shuttle flight schedule. Parametric analysis of standard space hardware and preliminary shuttle/payload constraints analysis are evaluated, along with the cost impact of low cost standard hardware.

Integrated Payload Data Handling Systems Using Software Partitioning

NASA Astrophysics Data System (ADS)

Taylor, Alun; Hann, Mark; Wishart, Alex

2015-09-01

An integrated Payload Data Handling System (I-PDHS) is one in which multiple instruments share a central payload processor for their on-board data processing tasks. This offers a number of advantages over the conventional decentralised architecture. Savings in payload mass and power can be realised because the total processing resource is matched to the requirements, as opposed to the decentralised architecture here the processing resource is in effect the sum of all the applications. Overall development cost can be reduced using a common processor. At individual instrument level the potential benefits include a standardised application development environment, and the opportunity to run the instrument data handling application on a fully redundant and more powerful processing platform [1]. This paper describes a joint program by SCISYS UK Limited, Airbus Defence and Space, Imperial College London and RAL Space to implement a realistic demonstration of an I-PDHS using engineering models of flight instruments (a magnetometer and camera) and a laboratory demonstrator of a central payload processor which is functionally representative of a flight design. The objective is to raise the Technology Readiness Level of the centralised data processing technique by address the key areas of task partitioning to prevent fault propagation and the use of a common development process for the instrument applications. The project is supported by a UK Space Agency grant awarded under the National Space Technology Program SpaceCITI scheme. [1].

Dynamic stability with the disturbance-free payload architecture as applied to the Large UV/Optical/Infrared (LUVOIR) Mission

NASA Astrophysics Data System (ADS)

Dewell, Larry D.; Tajdaran, Kiarash; Bell, Raymond M.; Liu, Kuo-Chia; Bolcar, Matthew R.; Sacks, Lia W.; Crooke, Julie A.; Blaurock, Carl

2017-09-01

The need for high payload dynamic stability and ultra-stable mechanical systems is an overarching technology need for large space telescopes such as the Large Ultraviolet / Optical / Infrared (LUVOIR) Surveyor. Wavefront error stability of less than 10 picometers RMS of uncorrected system WFE per wavefront control step represents a drastic performance improvement over current space-based telescopes being fielded. Previous studies of similar telescope architectures have shown that passive telescope isolation approaches are hard-pressed to meet dynamic stability requirements and usually involve complex actively-controlled elements and sophisticated metrology. To meet these challenging dynamic stability requirements, an isolation architecture that involves no mechanical contact between telescope and the host spacecraft structure has the potential of delivering this needed performance improvement. One such architecture, previously developed by Lockheed Martin called Disturbance Free Payload (DFP), is applied to and analyzed for LUVOIR. In a noncontact DFP architecture, the payload and spacecraft fly in close proximity, and interact via non-contact actuators to allow precision payload pointing and isolation from spacecraft vibration. Because disturbance isolation through non-contact, vibration isolation down to zero frequency is possible, and high-frequency structural dynamics of passive isolators are not introduced into the system. In this paper, the system-level analysis of a non-contact architecture is presented for LUVOIR, based on requirements that are directly traceable to its science objectives, including astrophysics and the direct imaging of habitable exoplanets. Aspects of architecture and how they contribute to system performance are examined and tailored to the LUVOIR architecture and concept of operation.

Ares V: Shifting the Payload Design Paradigm

NASA Technical Reports Server (NTRS)

Summrall, Phil; Creech, Steve

2009-01-01

NASA's Ares V heavy-lift cargo launch vehicle is being designed send more crew and cargo to more places on the lunar surface than the 1960s-era Apollo program and provide ongoing support to a permanent lunar outpost. In addition to that role, however, its unmatched mass and volume capability represent a global asset for exploration, science, and commerce. The Ares V also is an enabler of a large class of space missions not thought possible by scientists and engineers since the Saturn V program ended over 30 years ago. Compared to current systems, it will offer approximately 5 times the mass and volume to most orbits and locations. This should allow prospective mission planners to build robust payloads with margins that are 3 to 5 times the industry norm. The space inside the planned payload shroud has enough usable volume to launch the volumetric equivalent of approximately 10 Apollo Lunar Excursion Modules or approximately 5 equivalent Hubble Space Telescopes. This mass and volume capability to Low Earth Orbit enables a host of new scientific and observation platforms, such as telescopes, satellites, planetary and solar missions, as well as being able to provide the lift for future large in-space infrastructure missions, such as space based power and mining, Earth asteroid defense, propellant depots, etc. The Ares V team is engaging the potential payload community now, 2-3 years before System Requirements Review, in order to better understand the potential limitations and or additional requirements that could be added to the Ares V from the mission planning community. If a viable mission is determined and added to the Ares V as a design case, tradeoffs will be conducted to determine if other mission design requirements can be included in the system. Multiple shroud options for the Ares V have been analyzed to identify their impact on performance. Ares V is in a conceptual design stage prior to a formal design phase. The initial concept for the cargo launch vehicle (CaLV) that would later be dubbed "Ares V" was produced by the Exploration Systems Architecture Study in 2005. Since then, it has evolved through hundreds of concepts. The current point-of-departure (POD) concept was approved during the Lunar Capabilities Concept Review/Ares V Mission Concept Review in June 2008. This reference concept serves as a starting point for a renewed set of design trades and detailed analysis into its interaction with the other components of the Constellation architecture and existing launch infrastructure. This paper will discuss the Ares V design evolution, the most recent point-of-departure concept, and its capabilities to support future science missions.

Large Payload Ground Transportation and Test Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.

2016-01-01

Many spacecraft concepts under consideration by the National Aeronautics and Space Administration’s (NASA’s) Evolvable Mars Campaign take advantage of a Space Launch System payload shroud that may be 8 to 10 meters in diameter. Large payloads can theoretically save cost by reducing the number of launches needed--but only if it is possible to build, test, and transport a large payload to the launch site in the first place. Analysis performed previously for the Altair project identified several transportation and test issues with an 8.973 meters diameter payload. Although the entire Constellation Program—including Altair—has since been canceled, these issues serve as important lessons learned for spacecraft designers and program managers considering large payloads for future programs. A transportation feasibility study found that, even broken up into an Ascent and Descent Module, the Altair spacecraft would not fit inside available aircraft. Ground transportation of such large payloads over extended distances is not generally permitted, so overland transportation alone would not be an option. Limited ground transportation to the nearest waterway may be possible, but water transportation could take as long as 67 days per production unit, depending on point of origin and acceptance test facility; transportation from the western United States would require transit through the Panama Canal to access the Kennedy Space Center launch site. Large payloads also pose acceptance test and ground processing challenges. Although propulsion, mechanical vibration, and reverberant acoustic test facilities at NASA’s Plum Brook Station have been designed to accommodate large spacecraft, special handling and test work-arounds may be necessary, which could increase cost, schedule, and technical risk. Once at the launch site, there are no facilities currently capable of accommodating the combination of large payload size and hazardous processing such as hypergolic fuels, pyrotechnic devices, and high pressure gasses. Ironically, the limiting factor to a national heavy lift strategy may not be the rocket technology needed to throw a heavy payload, but rather the terrestrial infrastructure—roads, bridges, airframes, and buildings—necessary to transport, acceptance test, and process large spacecraft. Failure to carefully consider where and how large spacecraft are manufactured, tested, and launched could result in unforeseen cost to modify existing (or develop new) infrastructure, or incur additional risk due to increased handling operations or eliminating key verifications. Although this paper focuses on the canceled Altair spacecraft as a case study, the issues identified here have wide applicability to other large payloads, including concepts under consideration for NASA’s Evolvable Mars Campaign.

Operations analysis (study 2.1): Payload designs for space servicing

NASA Technical Reports Server (NTRS)

Wolfe, R. R.

1974-01-01

Potential modes of operating in space in the space shuttle era are documented. The October 1973 NASA Mission Model provides a definition of various NASA and non-DOD automated payload configurations when employed in an expendable mode. The model also specifies a launch schedule for initial deployment of payloads as well as for subsequent replacements at periodic cycles. This model and its associated payload definitions serve as a foundation for the data presented in this report. The reference model has been revised to reflect automated space servicing of payloads as an operational concept instead of the existing expendable approach. The indication is that the bulk of a payload's subsystems and mission equipment require no support over the lifetime of the program. However, failure of a single unit could result in loss of the mission objectives. When space servicing is employed, the approach is to replace only that unit causing the anomaly. This concept affords an opportunity to standardize space replacable units, as well as to reduce the expense of logistics support, by allowing multiple servicing on any single upper stage/shuttle flight.

Optical tools and techniques for aligning solar payloads with the SPARCS control system. [Solar Pointing Aerobee Rocket Control System

NASA Technical Reports Server (NTRS)

Thomas, N. L.; Chisel, D. M.

1976-01-01

The success of a rocket-borne experiment depends not only on the pointing of the attitude control system, but on the alignment of the attitude control system to the payload. To ensure proper alignment, special optical tools and alignment techniques are required. Those that were used in the SPARCS program are described and discussed herein. These tools include theodolites, autocollimators, a 38-cm diameter solar simulator, a high-performance 1-m heliostat to provide a stable solar source during the integration of the rocket payload, a portable 75-cm sun tracker for use at the launch site, and an innovation called the Solar Alignment Prism. Using the real sun as the primary reference under field conditions, the Solar Alignment Prism facilitates the coalignment of the attitude sun sensor with the payload. The alignment techniques were developed to ensure the precise alignment of the solar payloads to the SPARCS attitude sensors during payload integration and to verify the required alignment under field conditions just prior to launch.

ASK Talks with Dennis Grounds

NASA Technical Reports Server (NTRS)

2003-01-01

Dennis Grounds recently finished a one-year assignment at NASA Headquarters in the Office of Bioastronautics as the Acting Flight Program Manager He has returned to Johnson Space Center (JSC), where he is Director of the International Space Station Bioastronautics Research Program Office with the NASA Life Sciences Projects Division. Under his management, the Human Research Facility (HRF) was developed to support a broad range of scientific investigations pertaining to human adaptation to the spaceflight environment and issues of human space exploration. The HRF rack was developed to international standards in order to be compatible with payloads developed anywhere in the world, thereby streamlining the process of getting payloads on the Space Station. Grounds has worked with NASA for more than 15 years. Prior to joining ISS, he worked with General Electric as a manager of payloads and analysis in support of the NASA Life Science Projects Division at JSC. ASK spoke with Grounds in Washington, D.C., during his Headquarters assignment.

KSC-97pc606

NASA Image and Video Library

1997-04-08

KENNEDY SPACE CENTER, FLA. -- With the Space Shuttle Orbiter Columbia in the background, STS-83 Mission Commander James D. Halsell (center) gives a post-landing briefing on Runway 33 at KSC’s Shuttle Landing Facility. Columbia landed at 2:33:11 p. m. EDT, April 8, to conclude the Microgravity Science Laboratory-1 (MSL-1) mission. The other flight crew members (from left) are: Payload Specialist Roger K. Crouch; Payload Commander Janice Voss; Mission Specialist Michael L. Gernhardt; Pilot Susan L. Still; Payload Specialist Gregory T. Linteris; and Mission Specialist Donald A. Thomas. At main gear touchdown, the STS-83 mission duration was 3 days, 23 hours, 12 minutes. The planned 16-day mission was cut short by a faulty fuel cell. This is only the third time in Shuttle program history that an orbiter was brought home early due to mechanical problems. This was also the 36th KSC landing since the program began in 1981

The Pros and Cons of National Defense: A Study of the Proponents, Opponents, Issues, and the Public Affairs and Public Relations Programs Surrounding the B-1 Strategic Bomber

DTIC Science & Technology

1979-08-01

it was noted that I the B-I would be faster, carry more payload, and have a smaller radar cross section than the B-52. Also, in comparison to the B-52...payload or have smaller cross section . (6) Compared to B-52, B-i will: (a) Have higher penetration speeds (b) Have larger payload capacity (c) Have... radar detection range, then S I descend to below radar detection altitudes (literally at treetop levels) and penetrate enemy airspace to within

KSC01kodi072

NASA Image and Video Library

2001-08-08

KODIAK ISLAND, Alaska -- The Sapphire payload is moved into position next to the Starshine 3 payload at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5 p.m. to 7 p.m. p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

KSC01kodi062

NASA Image and Video Library

2001-07-31

KODIAK ISLAND, Alaska -- Technicians prepare the Starshine 3 payload, while the payload fairing of the Athena 1 launch vehicle awaits servicing at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program

NASA sounding rockets, 1958 - 1968: A historical summary

NASA Technical Reports Server (NTRS)

Corliss, W. R.

1971-01-01

The development and use of sounding rockets is traced from the Wac Corporal through the present generation of rockets. The Goddard Space Flight Center Sounding Rocket Program is discussed, and the use of sounding rockets during the IGY and the 1960's is described. Advantages of sounding rockets are identified as their simplicity and payload simplicity, low costs, payload recoverability, geographic flexibility, and temporal flexibility. The disadvantages are restricted time of observation, localized coverage, and payload limitations. Descriptions of major sounding rockets, trends in vehicle usage, and a compendium of NASA sounding rocket firings are also included.

DARPA Orbital Express program: effecting a revolution in space-based systems

NASA Astrophysics Data System (ADS)

Whelan, David A.; Adler, E. A.; Wilson, Samuel B., III; Roesler, Gordon M., Jr.

2000-11-01

A primary goal of the Defense Advanced Research Projects Agency is to develop innovative, high-risk technologies with the potential of a revolutionary impact on missions of the Department of Defense. DARPA is developing a space experiment to prove the feasibility of autonomous on- orbit servicing of spacecraft. The Orbital Express program will demonstrate autonomous on-orbit refueling, as well as autonomous delivery of a small payload representing an avionics upgrade package. The maneuverability provided to spacecraft from a ready refueling infrastructure will enable radical new capabilities for the military, civil and commercial spacecraft. Module replacement has the potential to extend bus lifetimes, and to upgrade the performance of key subsystems (e.g. processors) at the pace of technology development. The Orbital Express technology development effort will include the necessary autonomy for a viable servicing infrastructure; a universal interface for docking, refueling and module transfers; and a spacecraft bus design compatible with this servicing concept. The servicer spacecraft of the future may be able to act as a host platform for microsatellites, extending their capabilities while reducing risk. An infrastructure based on Orbital Express also benefits from, and stimulates the development of, lower-cost launch strategies.

Space Station Simulation Computer System (SCS) study for NASA/MSFC. Volume 2: Baseline architecture report

NASA Technical Reports Server (NTRS)

1990-01-01

NASA's Space Station Freedom Program (SSFP) planning efforts have identified a need for a payload training simulator system to serve as both a training facility and as a demonstrator to validate operational concepts. The envisioned MSFC Payload Training Complex (PTC) required to meet this need will train the Space Station payload scientists, station scientists, and ground controllers to operate the wide variety of experiments that will be onboard the Space Station Freedom. The Simulation Computer System (SCS) is the computer hardware, software, and workstations that will support the Payload Training Complex at MSFC. The purpose of this SCS Study is to investigate issues related to the SCS, alternative requirements, simulator approaches, and state-of-the-art technologies to develop candidate concepts and designs.

Space Station Simulation Computer System (SCS) study for NASA/MSFC. Phased development plan

NASA Technical Reports Server (NTRS)

1990-01-01

NASA's Space Station Freedom Program (SSFP) planning efforts have identified a need for a payload training simulator system to serve as both a training facility and as a demonstrator to validate operational concepts. The envisioned MSFC Payload Training Complex (PTC) required to meet this need will train the Space Station payload scientists, station scientists and ground controllers to operate the wide variety of experiments that will be onboard the Space Station Freedom. The Simulation Computer System (SCS) is made up of computer hardware, software, and workstations that will support the Payload Training Complex at MSFC. The purpose of this SCS Study is to investigate issues related to the SCS, alternative requirements, simulator approaches, and state-of-the-art technologies to develop candidate concepts and designs.

The development of STS payload environmental engineering standards

NASA Technical Reports Server (NTRS)

Bangs, W. F.

1982-01-01

The presently reported effort to provide a single set of standards for the design, analysis and testing of Space Transportation System (STS) payloads throughout the NASA organization must be viewed as essentially experimental, since the concept of incorporating the diverse opinions and experiences of several separate field research centers may in retrospect be judged too ambitious or perhaps even naive. While each STS payload may have unique characteristics, and the project should formulate its own criteria for environmental design, testing and evaluation, a reference source document providing coordinated standards is expected to minimize the duplication of effort and limit random divergence of practices among the various NASA payload programs. These standards would provide useful information to all potential STS users, and offer a degree of standardization to STS users outside the NASA organization.

Space Station Simulation Computer System (SCS) study for NASA/MSFC. Volume 1: Baseline architecture report

NASA Technical Reports Server (NTRS)

1990-01-01

NASA's Space Station Freedom Program (SSFP) planning efforts have identified a need for a payload training simulator system to serve as both a training facility and as a demonstrator to validate operational concepts. The envisioned MSFC Payload Training Complex (PTC) required to meet this need will train the Space Station payload scientists, station scientists, and ground controllers to operate the wide variety of experiments that will be onboard the Space Station Freedom. The Simulation Computer System (SCS) is made up of the computer hardware, software, and workstations that will support the Payload Training Complex at MSFC. The purpose of this SCS Study is to investigate issues related to the SCS, alternative requirements, simulator approaches, and state-of-the-art technologies to develop candidate concepts and designs.

Space Station Simulation Computer System (SCS) study for NASA/MSFC. Operations concept report

NASA Technical Reports Server (NTRS)

1990-01-01

NASA's Space Station Freedom Program (SSFP) planning efforts have identified a need for a payload training simulator system to serve as both a training facility and as a demonstrator to validate operational concepts. The envisioned MSFC Payload Training Complex (PTC) required to meet this need will train the Space Station payload scientists, station scientists, and ground controllers to operate the wide variety of experiments that will be onboard the Space Station Freedom. The Simulation Computer System (SCS) is made up of computer hardware, software, and workstations that will support the Payload Training Complex at MSFC. The purpose of this SCS Study is to investigate issues related to the SCS, alternative requirements, simulator approaches, and state-of-the-art technologies to develop candidate concepts and designs.

STS-102 MPLM Leonardo moves into PCR

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload changeout room on the Rotating Service Structure, Launch Pad 39B, workers move the Multi-Purpose Logistics Module Leonardo out of the payload canister. From the PCR Leonardo then will be transferred into Space Shuttle Discovery'''s payload bay. One of Italy'''s major contributions to the International Space Station program, Leonardo is a reusable logistics carrier. It is the primary delivery system used to resupply and return Station cargo requiring a pressurized environment. Leonardo is the primary payload on mission STS-102 and will deliver up to 10 tons of laboratory racks filled with equipment, experiments and supplies for outfitting the newly installed U.S. Laboratory Destiny. STS-102 is scheduled to launch March 8 at 6:45 a.m. EST.

A Generic Microdisturbanace Transmissibility Model For Reaction Wheels

NASA Astrophysics Data System (ADS)

Penate Castro, Jose; Seiler, Rene

2012-07-01

The increasing demand for space missions with high- precision pointing requirements for their payload instruments is underlining the importance of studying the impact of micro-level disturbances on the overall performance of spacecraft. For example, a satellite with an optical telescope taking high-resolution images might be very sensitive to perturbations, generated by moving equipment and amplified by the structure of the equipment itself as well as that of the host spacecraft that is accommodating both, the sources of mechanical disturbances and sensitive payload instruments. One of the major sources of mechanical disturbances inside a satellite may be found with reaction wheels. For investigation of their disturbance generation and propagation characteristics, a finite element model with parametric geometry definition has been developed. The model covers the main structural features of typical reaction wheel assemblies and can be used for a transmissibility representation of the equipment. With the parametric geometry definition approach, a wide range of different reaction wheel types and sizes can be analysed, without the need for (re-)defining an individual reaction wheel configuration from scratch. The reaction wheel model can be combined with a finite element model of the spacecraft structure and the payload for an end-to-end modelling and simulation of the microdisturbance generation and propagation. The finite element model has been generated in Patran® Command Language (PCL), which provides a powerful and time-efficient way to change parameters in the model, for creating a new or modifying an existing geometry, without requiring comprehensive manual interactions in the modelling pre-processor. As part of the overall modelling approach, a tailored structural model of the mechanical ball bearings has been implemented, which is one of the more complex problems to deal with, among others, due to the anisotropic stiffness and damping characteristics. Together, with the time and frequency domain representations of the local sources of the disturbance forces and moments (e.g. due to rotor unbalance), the new model enables adequate estimation of the disturbances at the mechanical interface of a reaction wheel with a transmissibility representation, furthermore the analysis of their propagation in a host structure and their effects on a payload item.

Evaluation of scheduling techniques for payload activity planning

NASA Technical Reports Server (NTRS)

Bullington, Stanley F.

1991-01-01

Two tasks related to payload activity planning and scheduling were performed. The first task involved making a comparison of space mission activity scheduling problems with production scheduling problems. The second task consisted of a statistical analysis of the output of runs of the Experiment Scheduling Program (ESP). Details of the work which was performed on these two tasks are presented.

Mobile User Objective System (MUOS)

DTIC Science & Technology

2015-12-01

the current UHF Follow-On ( UFO ) constellation. MUOS includes the satellite constellation, a ground control and network management system, and a new...MUOS CAI. Each MUOS satellite carries a legacy payload similar to that flown on UFO -11. These legacy payloads will continue to support legacy...Antecedent Information The antecedent system to MUOS was the Ultra High Frequency (UHF) Follow-on ( UFO ) satellite communications program. Comparisons

Education Payload Operation - Demonstrations

NASA Technical Reports Server (NTRS)

Keil, Matthew

2009-01-01

Education Payload Operation - Demonstrations (EPO-Demos) are recorded video education demonstrations performed on the International Space Station (ISS) by crewmembers using hardware already onboard the ISS. EPO-Demos are videotaped, edited, and used to enhance existing NASA education resources and programs for educators and students in grades K-12. EPO-Demos are designed to support the NASA mission to inspire the next generation of explorers.

Acceleration ground test program to verify GAS payload No. 559 structure/support avionics and experiment structural integrity

NASA Technical Reports Server (NTRS)

Cassanto, John M.; Cassanto, Valerie A.

1988-01-01

Acceleration ground tests were conducted on the Get Away Special (GAS) payload 559 to verify the structural integrity of the structure/support avionics and two of the planned three flight experiments. The ITA (Integrated Test Area) Standardized Experiment Module (ISEM) structure was modified to accommodate the experiments for payload 559. The ISEM avionics consisted of a heavy duty sliver zinc power supply, three orthogonal-mounted low range microgravity accelerometers, a tri-axis high range accelerometer, a solid state recorder/programmer sequencer, and pressure and temperature sensors. The tests were conducted using the Gravitational Plant Physiology Laboratory Centrifuge of the University City Science Center in Philadelphia, PA. The launch-powered flight steady state acceleration profile of the shuttle was simulated from lift-off through jettison of the External Tank (3.0 g's). Additional tests were conducted at twice the nominal powered flight acceleration levels (6 g's) and an over-test condition of four times the powered flight loads to 12.6 g's. The present test program has demonstrated the value of conducting ground tests to verify GAS payload experiment integrity and operation before flying on the shuttle.

Space Station Freedom resource allocation accommodation of technology payload requirements

NASA Technical Reports Server (NTRS)

Avery, Don E.; Collier, Lisa D.; Gartrell, Charles F.

1990-01-01

An overview of the Office of Aeronautics, Exploration, and Technology (OAET) Space Station Freedom Technology Payload Development Program is provided, and the OAET Station resource requirements are reviewed. The requirements are contrasted with current proposed resource allocations. A discussion of the issues and conclusions are provided. It is concluded that an overall 20 percent resource allocation is appropriate to support OAET's technology development program, that some resources are inadequate even at the 20 percent level, and that bartering resources among U.S. users and international partners and increasing the level of automation may be viable solutions to the resource constraint problem.

STS-39 OV-103 reaction control system (RCS) jets fire during onorbit maneuver

NASA Image and Video Library

1991-05-06

STS039-27-016 (28 April-6 May 1991) --- The Space Shuttle Discovery fires reaction control subsystem (RCS) thrusters in this 35mm frame, taken from inside the crew cabin. Seen in Discovery's payload bay are the tops of cannisters on the STP-1 payload, configured on the STS 39 Hitchhiker carrier; and the Air Force Program (AFP) 675 package. AFP-675 consists of the Cryogenic Infrared Radiance Instrumentation for Shuttle (CIRRIS)-1A; Far Ultraviolet Camera (FAR-UV) Experiment; Horizon Ultraviolet Program (HUP); Quadruple Ion Neutral Mass Spectrometer (QINMS); and the Uniformly Redundant Array (URA).

EVA - Don't Leave Earth Without It

NASA Technical Reports Server (NTRS)

Cupples, J. Scott; Smith, Stephen A.

2011-01-01

Modern manned space programs come in two categories: those that need Extravehicular Activity (EVA) and those that will need EVA. This paper discusses major milestones in the Shuttle Program where EVA was used to save payloads, enhance on-orbit capabilities, and build structures in order to ensure success of National Aeronautics and Space Administration (NASA) missions. In conjunction, the Extravehicular Mobility Unit s (EMU) design, and hence, its capabilities evolved as its mission evolved. It is the intent that lessons can be drawn from these case studies so that EVA compatibility is designed into future vehicles and payloads.

Lightning Imaging Sensor (LIS) on the International Space Station (ISS): Launch, Installation, Activation, and First Results

NASA Astrophysics Data System (ADS)

Blakeslee, R. J.; Christian, H. J., Jr.; Mach, D. M.; Buechler, D. E.; Koshak, W. J.; Walker, T. D.; Bateman, M. G.; Stewart, M. F.; O'Brien, S.; Wilson, T. O.; Pavelitz, S. D.; Coker, C.

2016-12-01

Over the past 20 years, the NASA Marshall Space Flight Center, the University of Alabama in Huntsville, and their partners developed and demonstrated the effectiveness and value of space-based lightning observations as a remote sensing tool for Earth science research and applications, and, in the process, established a robust global lightning climatology. The observations included measurements from the Lightning Imaging Sensor (LIS) on the Tropical Rainfall Measuring Mission (TRMM) and its Optical Transient Detector (OTD) predecessor that acquired global observations of total lightning (i.e., intracloud and cloud-to-ground discharges) spanning a period from May 1995 through April 2015. As an exciting follow-on to these prior missions, a space-qualified LIS built as a flight-spare for TRMM will be delivered to the International Space Station (ISS) for a 2 year or longer mission, flown as a hosted payload on the Department of Defense (DoD) Space Test Program-Houston 5 (STP-H5) mission. The STP-H5 payload containing LIS is scheduled launch from NASA's Kennedy Space Center to the ISS in November 2016, aboard the SpaceX Cargo Resupply Services-10 (SpaceX-10) mission, installed in the unpressurized "trunk" of the Dragon spacecraft. After the Dragon is berth to ISS Node 2, the payload will be removed from the trunk and robotically installed in a nadir-viewing location on the external truss of the ISS. Following installation on the ISS, the LIS Operations Team will work with the STP-H5 and ISS Operations Teams to power-on LIS and begin instrument checkout and commissioning. Following successful activation, LIS orbital operations will commence, managed from the newly established LIS Payload Operations Control Center (POCC) located at the National Space Science Technology Center (NSSTC) in Huntsville, AL. The well-established and robust processing, archival, and distribution infrastructure used for TRMM was easily adapted to the ISS mission, assuring that lightning observations from LIS on ISS can be quickly delivered to science and applications users soon after routine operations are underway. Also real-time data, available for the first time with this mission, are being provided to interested users in partnership with NASA's Short Term Prediction Research and Transition (SPoRT) center, also located at the NSSTC.

Project Aether Aurora: STEM outreach near the arctic circle

NASA Astrophysics Data System (ADS)

Longmier, B. W.; Bering, E. A.

2012-12-01

Project Aether is a program designed to immerse high-school through graduate students to field research in some of the fields of STEM. The program leaders launch high altitude weather balloons in collaboration with schools and students to teach physics concepts, experimental research skills, and to make space exploration accessible to students. A weather balloon lifts a specially designed payload package that is composed of HD cameras, GPS tracking devices, and other science equipment. The payload is constructed and attached to the balloon by the students with low-cost materials. The balloon and payload are launched with FAA clearance from a site chosen based on wind patterns and predicted landing locations. The balloon ascends over 2 hours to a maximum altitude of 100,000 feet where it bursts and allows the payload to slowly descend using a built-in parachute. The balloon's location is monitored during its flight by GPS-satellite relay. Most of the science and video data are recorded on SD cards using an Arduino digitizer. The payload is located using the GPS device. The science data are recovered from the payload and shared with the students. In April 2012, Project Aether leaders conducted a field campaign near Fairbanks Alaska, sending several student-built experiments to an altitude of 30km, underneath several strong auroral displays. Auroral physics experiments that can be done on ultra small balloons (5 cubic meters) include electric field and magnetic fluctuation observations, full spectrum and narrow band optical imaging, GPS monitoring of the total electron content of the ionosphere, x-ray detection and infrared and UV spectroscopy. The actual undergraduate student experiments will be reviewed and some data presented.; Balloon deployment underneath aurora, Fairbanks Alaska, 2012.

International Cooperation in the Field of International Space Station (ISS) Payload Safety

NASA Astrophysics Data System (ADS)

Grayson, C.; Sgobba, T.; Larsen, A.; Rose, S.; Heimann, T.; Ciancone, M.; Mulhern, V.

2005-12-01

In the frame of the International Space Station (ISS) Program cooperation, in 1998 the European Space Agency (ESA) approached the National Aeronautics and Space Administration (NASA) with the unique concept of a Payload Safety Review Panel (PSRP) "franchise" based at the European Space Technology Center (ESTEC), where the panel would be capable of autonomously reviewing flight hardware for safety. This paper will recount the course of an ambitious idea as it progressed into a fully functional reality. It will show how a panel initially conceived at NASA to serve a national programme has evolved into an international safety cooperation asset. The PSRP established at NASA began reviewing ISS payloads approximately in late 1994 or early 1995 as an expansion of the pre- existing Shuttle Program PSRP. This paper briefly describes the fundamental Shuttle safety process and the establishment of the safety requirements for payloads intending to use the Space Transportation System and ISS. The paper will also offer some historical statistics about the experiments that completed the payload safety process for Shuttle and ISS. The paper then presents the background of ISS agreements and international treaties that had to be considered when establishing the ESA PSRP. The paper will expound upon the detailed franchising model, followed by an outline of the cooperation charter approved by the NASA Associate Administrator, Office of Space Flight, and ESA Director of Manned Spaceflight and Microgravity. The paper will then address the resulting ESA PSRP implementation and its success statistics to date. Additionally, the paper presents ongoing developments with the Japan Aerospace Exploration Agency (JAXA). The discussion will conclude with ideas for future developments, such to achieve a fully integrated international system of payload safety panels for ISS.

International Cooperation in the Field of International Space Station (ISS) Payload Safety

NASA Technical Reports Server (NTRS)

Heimann, Timothy; Larsen, Axel M.; Rose, Summer; Sgobba, Tommaso

2005-01-01

In the frame of the International Space Station (ISS) Program cooperation, in 1998, the European Space Agency (ESA) approached the National Aeronautics and Space Administration (NASA) with the unique concept of a Payload Safety Review Panel (PSRP) "franchise" based at the European Space Technology Center (ESTEC), where the panel would be capable of autonomously reviewing flight hardware for safety. This paper will recount the course of an ambitious idea as it progressed into a fully functional reality. It will show how a panel initially conceived at NASA to serve a national programme has evolved into an international safety cooperation asset. The PSRP established at NASA began reviewing ISS payloads approximately in late 1994 or early 1995 as an expansion of the pre-existing Shuttle Program PSRP. This paper briefly describes the fundamental Shuttle safety process and the establishment of the safety requirements for payloads intending to use the Space Transportation System and International Space Station (ISS). The paper will also offer some historical statistics about the experiments that completed the payload safety process for Shuttle and ISS. The paper 1 then presents the background of ISS agreements and international treaties that had to be taken into account when establishing the ESA PSRP. The detailed franchising model will be expounded upon, followed by an outline of the cooperation charter approved by the NASA Associate Administrator, Office of Space Flight, and ESA Director of Manned Spaceflight and Microgravity. The resulting ESA PSRP implementation and its success statistics to date will then be addressed. Additionally the paper presents the ongoing developments with the Japan Aerospace Exploration Agency. The discussion will conclude with ideas for future developments, such to achieve a fully integrated international system of payload safety panels for ISS.

Modular space station phase B extension preliminary system design. Volume 7: Ancillary studies

NASA Technical Reports Server (NTRS)

Jones, A. L.

1972-01-01

Sortie mission analysis and reduced payloads size impact studies are presented. In the sortie mission analysis, a modular space station oriented experiment program to be flown by the space shuttle during the period prior to space station IOC is discussed. Experiments are grouped into experiment packages. Mission payloads are derived by grouping experiment packages and by adding support subsystems and structure. The operational and subsystems analyses of these payloads are described. Requirements, concepts, and shuttle interfaces are integrated. The sortie module/station module commonality and a sortie laboratory concept are described. In the payloads size analysis, the effect on the modular space station concept of reduced diameter and reduced length of the shuttle cargo bay is discussed. Design concepts are presented for reduced sizes of 12 by 60 ft, 14 by 40 ft, and 12 by 40 ft. Comparisons of these concepts with the modular station (14 by 60 ft) are made to show the impact of payload size changes.

Results from a tethered rocket experiment (Charge-2)

NASA Astrophysics Data System (ADS)

Kawashima, N.; Sasaki, S.; Oyama, K. I.; Hirao, K.; Obayashi, T.; Raitt, W. J.; White, A. B.; Williamson, P. R.; Banks, P. M.; Sharp, W. F.

A tethered payload experiment (Charge-2) was carried out as an international program between Japan and the USA using a NASA sounding rocket at White Sands Missile Range. The objective of the experiment was to perform a new type of active experiment in space by injecting an electron beam from a mother-daughter rocket system connected with a long tether wire. The electron beam with voltage and current up to 1 kV and 80 mA (nominal) was injected from the mother payload. An insulated conductive wire of 426 m length connected the two payloads, the longest tether system flown so far. The electron gun system and diagnostic instruments (plasma, optical, particle and wave) functioned correctly throughout the flight. The potential rise of the mother payload during the electron beam emission was measured with respect to the daughter payload. The beam trajectory was detected by a camera onboard the mother rocket. Wave generation and current induction in the wire during the beam emission were also studied.

Project Columbiad: Mission to the Moon. Book 2, volume 3: Stage configuration designs; volume 4: Program plan

NASA Technical Reports Server (NTRS)

1992-01-01

The Earth Orbital Rendezvous (EOR) configuration for the piloted mission is composed of three propulsive elements in addition to the Crew Module (CM): Primary Trans-Lunar Injection (PTLI), Lunar Braking Module (LBM), and Earth Return Module (ERM). The precursor mission is also composed of three propulsive elements in addition to its surface payloads: PTLI, LBM and the Payload Landing Module (PLM). Refer to Volume 1, Section 5.1 and 5.2 for a break-up of the different stages into the four launches. A quick summary is as follows: PTLI is on Launch 1 and 3 while the LBM, PLM, and surface payloads are on Launch 2 and another LBM, ERM, and CM on Launch 4. The precursor mission is designed to be as modular as possible with the piloted mission for developmental cost considerations. The following topics are discussed: launch vehicle description; primary trans-lunar injection stage; lunar braking module; earth return module; crew module; payload landing module; and surface payload description.

A study to define an in-flight dynamics measurement and data applications program for space shuttle payloads

NASA Technical Reports Server (NTRS)

Rader, W. P.; Barrett, S.; Payne, K. R.

1975-01-01

Data measurement and interpretation techniques were defined for application to the first few space shuttle flights, so that the dynamic environment could be sufficiently well established to be used to reduce the cost of future payloads through more efficient design and environmental test techniques. It was concluded that: (1) initial payloads must be given comprehensive instrumentation coverage to obtain detailed definition of acoustics, vibration, and interface loads, (2) analytical models of selected initial payloads must be developed and verified by modal surveys and flight measurements, (3) acoustic tests should be performed on initial payloads to establish realistic test criteria for components and experiments in order to minimize unrealistic failures and retest requirements, (4) permanent data banks should be set up to establish statistical confidence in the data to be used, (5) a more unified design/test specification philosophy is needed, (6) additional work is needed to establish a practical testing technique for simulation of vehicle transients.

Graduate Student Researchers Program (GSRP)

NASA Technical Reports Server (NTRS)

Westerhoff, John

2004-01-01

An advanced concept in in-space transportation currently being studied is the Momentum-Exchange/Electrodynamic Reboost Tether System (MXER). The MXER system is a permanently orbiting platform designed to boost payloads from low earth orbit (LEO). Unlike conventional rockets that use propellants, MXER acts as a large momentum wheel, imparting a Av to a payload at the expense of its own orbital energy. After throwing a payload, the system reboosts itself using an electrodynamic tether to push against Earth s magnetic field and brings itself back up to an operational orbit to prepare for the next payload. The ability to reboost itself allows for continued reuse of the system without the expenditure of propellants. Considering the cost of lifting propellant from the ground to LEO to do the same Av boost at $10000 per pound, the system cuts the launch cost of the payload dramatically, and subsequently, the MXER system pays for itself after a small number of missions. As such, this technology is a valuable addition to NASA s mission for in-space transportation.

Performance estimates for space shuttle vehicles using a hydrogen or a methane fueled turboramjet powered first stage

NASA Technical Reports Server (NTRS)

Knip, G., Jr.; Eisenberg, J. D.

1972-01-01

Two- and three-stage (second stage expendable) shuttle vehicles, both having a hydrogen-fueled, turboramjet-powered first stage, are compared with a two-stage, VTOHL, all-rocket shuttle in terms of payload fraction, inert weight, development cost, operating cost, and total cost. All of the vehicles place 22,680 kilograms of payload into a 500-kilometer orbit. The upper stage(s) uses hydrogen-oxygen rockets. The effect on payload fraction and vehicle inert weight of methane and methane-FLOX as a fuel-propellant combination for the three-stage vehicle is indicated. Compared with a rocket first stage for a two-stage shuttle, an airbreathing first stage results in a higher payload fraction and a lower operating cost, but a higher total cost. The effect on cost of program size and first-stage flyback is indicated. The addition of an expendable rocket second stage (three-stage vehicle) improves the payload fraction but is unattractive economically.

Reinventing the International Space Station Payload Integration Processes and Capabilities

NASA Technical Reports Server (NTRS)

Jones, Rod; Price, Carmen; Copeland, Scott; Geiger, Wade; Geiger, Wade; Rice, Amanda; Lauchner, Adam

2011-01-01

The fundamental ISS payload integration philosophy, processes and capabilities were established in the context of how NASA science programs were conducted and executed in the early 1990 s. Today, with the designation of the United States (US) portion of ISS as a National Lab, the ISS payload customer base is growing to include other government agencies, private and commercial research. The fields of research are becoming more diverse expanding from the NASA centric physical, materials and human research sciences to test beds for exploration and technology demonstration, biology and biotechnology, and as an Earth and Space science platform. This new customer base has a broader more diverse set of expectations and requirements for payload design, verification, integration, test, training, and operations. One size fits all processes are not responsive to this broader customer base. To maintain an organization s effectiveness it must listen to its customers, understand their needs, learn from its mistakes, and foster an environment of continual process improvement. The ISS Payloads office is evolving to meet these new customer expectations.

Microgravity research results and experiences from the NASA/MIR space station program.

PubMed

Schlagheck, R A; Trach, B L

2003-12-01

The Microgravity Research Program (MRP) participated aggressively in Phase 1 of the International Space Station Program using the Russian Mir Space Station. The Mir Station offered an otherwise unavailable opportunity to explore the advantages and challenges of long duration microgravity space research. Payloads with both National Aeronautics and Space Agency (NASA) and commercial backing were included as well as cooperative research with the Canadian Space Agency (CSA). From this experience, much was learned about long-duration on-orbit science utilization and developing new working relationships with our Russian partner to promote efficient planning, operations, and integration to solve complexities associated with a multiple partner program. This paper focuses on the microgravity research conducted onboard the Mir space station. It includes the Program preparation and planning necessary to support this type of cross increment research experience; the payloads which were flown; and summaries of significant microgravity science findings. Published by Elsevier Ltd.

International Space Station (ISS)

NASA Image and Video Library

2001-02-01

The International Space Station (ISS) Payload Operations Center (POC) at NASA's Marshall Space Flight Center (MSFC) in Huntsville, Alabama, is the world's primary science command post for the International Space Station (ISS), the most ambitious space research facility in human history. The Payload Operations team is responsible for managing all science research experiments aboard the Station. The center is also home for coordination of the mission-plarning work of variety of international sources, all science payload deliveries and retrieval, and payload training and safety programs for the Station crew and all ground personnel. Within the POC, critical payload information from the ISS is displayed on a dedicated workstation, reading both S-band (low data rate) and Ku-band (high data rate) signals from a variety of experiments and procedures operated by the ISS crew and their colleagues on Earth. The POC is the focal point for incorporating research and experiment requirements from all international partners into an integrated ISS payload mission plan. This photograph is an overall view of the MSFC Payload Operations Center displaying the flags of the countries participating the ISS. The flags at the left portray The United States, Canada, France, Switzerland, Netherlands, Japan, Brazil, and Sweden. The flags at the right portray The Russian Federation, Italy, Germany, Belgium, Spain, United Kingdom, Denmark, and Norway.

International Space Station (ISS)

NASA Image and Video Library

2000-02-01

The International Space Station (ISS) Payload Operations Center (POC) at NASA's Marshall Space Flight Center (MSFC) in Huntsville, Alabama, is the world's primary science command post for the (ISS), the most ambitious space research facility in human history. The Payload Operations team is responsible for managing all science research experiments aboard the Station. The center is also home for coordination of the mission-plarning work of variety of international sources, all science payload deliveries and retrieval, and payload training and safety programs for the Station crew and all ground personnel. Within the POC, critical payload information from the ISS is displayed on a dedicated workstation, reading both S-band (low data rate) and Ku-band (high data rate) signals from a variety of experiments and procedures operated by the ISS crew and their colleagues on Earth. The POC is the focal point for incorporating research and experiment requirements from all international partners into an integrated ISS payload mission plan. This photograph is an overall view of the MSFC Payload Operations Center displaying the flags of the countries participating in the ISS. The flags at the left portray The United States, Canada, France, Switzerland, Netherlands, Japan, Brazil, and Sweden. The flags at the right portray The Russian Federation, Italy, Germany, Belgium, Spain, United Kingdom, Denmark, and Norway.

Unilateral vs. Multilateral Engagement: A Scenario-Based Approach to Guiding America’s Future Foreign Policy

DTIC Science & Technology

2009-04-01

weeks later when another Cessna packed with the same explosive payload plowed into a football stadium hosting the Super Bowl. The two attacks took the...In 2018 , these confrontations reached a pinnacle when Beijing substantiated a decade of rhetoric and military posturing by staging a surprise...leadership in international affairs focused on bolstering multilateral institutions capable of reforming global governance and managing key

KSC-98pc1186

NASA Image and Video Library

1998-09-30

The open doors of the payload bay on Space Shuttle Discovery await the transfer of four of the payloads on mission STS-95: the SPACEHAB single module, Spartan, the Hubble Space Telescope Orbiting Systems Test Platform (HOST), and the International Extreme Ultraviolet Hitchhiker (IEH-3). At the top of bay are the airlock (used for depressurization and repressurization during extravehicular activity and transfer to Mir) and the tunnel adapter (enables the flight crew members to transfer from the pressurized middeck crew compartment to Spacelab's pressurized shirt-sleeve environment). SPACEHAB involves experiments on space flight and the aging process. Spartan is a solar physics spacecraft designed to perform remote sensing of the hot outer layers of the sun's atmosphere or corona. HOST carries four experiments to validate components planned for installation during the third Hubble Space Telescope servicing mission and to evaluate new technologies in an Earth-orbiting environment. IEH-3 comprises several experiments that will study the Jovian planetary system, hot stars, planetary and reflection nebulae, other stellar objects and their environments through remote observation of EUV/FUV emissions; study spacecraft interactions, Shuttle glow, thruster firings, and contamination; and measure the solar constant and identify variations in the value during a solar cycle. Discovery is scheduled to launch on Oct. 29, 1998

Space Station Mission Planning System (MPS) development study. Volume 2

NASA Technical Reports Server (NTRS)

Klus, W. J.

1987-01-01

The process and existing software used for Spacelab payload mission planning were studied. A complete baseline definition of the Spacelab payload mission planning process was established, along with a definition of existing software capabilities for potential extrapolation to the Space Station. This information was used as a basis for defining system requirements to support Space Station mission planning. The Space Station mission planning concept was reviewed for the purpose of identifying areas where artificial intelligence concepts might offer substantially improved capability. Three specific artificial intelligence concepts were to be investigated for applicability: natural language interfaces; expert systems; and automatic programming. The advantages and disadvantages of interfacing an artificial intelligence language with existing FORTRAN programs or of converting totally to a new programming language were identified.

Space Launch System Spacecraft/Payloads Integration and Evolution Office Advanced Development FY 2014 Annual Report

NASA Technical Reports Server (NTRS)

Crumbly, C. M.; Bickley, F. P.; Hueter, U.

2015-01-01

The Advanced Development Office (ADO), part of the Space Launch System (SLS) program, provides SLS with the advanced development needed to evolve the vehicle from an initial Block 1 payload capability of 70 metric tons (t) to an eventual capability Block 2 of 130 t, with intermediary evolution options possible. ADO takes existing technologies and matures them to the point that insertion into the mainline program minimizes risk. The ADO portfolio of tasks covers a broad range of technical developmental activities. The ADO portfolio supports the development of advanced boosters, upper stages, and other advanced development activities benefiting the SLS program. A total of 36 separate tasks were funded by ADO in FY 2014.

A Normal Incidence X-ray Telescope (NIXT) Sounding Rocket Payload

NASA Technical Reports Server (NTRS)

Golub, Leon

1996-01-01

During the past year the changeover from the normal incidence X ray telescope (NIXT) program to the new TXI sounding rocket program was completed. The NIXT effort, aimed at evaluating the viability of the remaining portions of the NIXT hardware and design has been finished and the portions of the NIXT which are viable and flightworthy, such as filters, mirror mounting hardware, electronic and telemetry interface systems, are now part of the new rocket payload. The backup NIXT multilayer-coated X ray telescope and its mounting hardware have been completely fabricated and are being stored for possible future use in the TXI rocket. The h-alpha camera design is being utilized in the TXI program for real-time pointing verification and control via telemetry. Two papers, summarizing scientific results from the NIXT rocket program were published this year.

Mobile User Objective System (MUOS)

DTIC Science & Technology

2013-12-01

system capacity of the current UHF Follow-On ( UFO ) constellation. MUOS includes the satellite constellation, a ground control and network management...terminals able to support the MUOS CAI. Each MUOS satellite carries a legacy payload similar to that flown on UFO -11. These legacy payloads will...Antecedent Information: The antecedent system to MUOS was the Ultra High Frequency (UHF) Follow-on ( UFO ) satellite communications program. Comparisons of O

Safety in earth orbit study. Volume 1: Technical summary

NASA Technical Reports Server (NTRS)

1972-01-01

A summary of the technical results and conclusions is presented of the hazards analyses of earth orbital operations in conjunction with the space shuttle program. The space shuttle orbiter and a variety of manned and unmanned payloads delivered to orbit by the shuttle are considered. The specific safety areas examined are hazardous payloads, docking, on-orbit survivability, tumbling spacecraft, and escape and rescue.

The Tunable XUV Imager (TXI) Sounding Rocket Payload

NASA Technical Reports Server (NTRS)

Brinton, John (Technical Monitor); Golub, Leon

2004-01-01

The TXI was flown successfully on 21 June 2001 (36.199 US). All systems functioned as planned and image data were acquired and sent to the ground. Unfortunately, due to a parachute failure the payload was destroyed. In this report we summarize results from the flight and provide detailed information on the high resolution X-ray imaging detector which was developed as part of the program.

Rideshare programs: a historical perspective

NASA Astrophysics Data System (ADS)

Horais, Brian J.

2000-11-01

In recent years there has been a significant increase in demand for testing, qualification and evaluation of satellite components in space. This will continue to be true with the dramatic growth in remote sensing and communication satellites and constellations. Finding ways to space qualify components and sensors without paying for expensive, dedicated space experiments has prompted a number of aerospace companies (large and small) and government organizations to increase their emphasis on providing low-cost access to space by means of secondary rides on primary payloads and launch vehicle structures. Proactive rideshare brokering is a process that supports space testing by actively providing the information, processes and equipment necessary to support successful space testing. As U.S. space programs have grown in scope and cost, the capacity to accetp risk as part of the development process has diminished - resulting in reduced levels of innovation and erosion of our space industry domination. In contrast, the international space community has instituted a number of innovative processes that support low cost entry to space for small programs. This has stimulated new space systems industries in many countries around the world. This growth is closely coupled with the dynamic growth in the International space launch industry. Proactive rideshare brokering takes a new approach to secondary payload integration. Many commercial and government payload integration services have taken the approach "If you build it they will come." This is not sufficiently aggressive to attract the new technologists who know very little about space testing. Proactive brokering must take a "You must go out and actively seek high-payoff technology payloads" approach to have a true impact on the implementation of new space system technologies. It should also include the application of proven practices from the international payload integration community. The paper draws conclusions by comparing what has been done historically and currently in the international space payload integration community versus what the current practices are in the U.S.. Observations and recommendations are made that reflect a reduced timeline approach and that acknowledge the close coupling between the technology base, the space systems industry, infrastructure and educational processes.

History of POIC Capabilities and Limitations to Conduct International Space Station Payload Operations

NASA Technical Reports Server (NTRS)

Grimaldi, Rebecca; Horvath, Tim; Morris, Denise; Willis, Emily; Stacy, Lamar; Shell, Mike; Faust, Mark; Norwood, Jason

2011-01-01

Payload science operations on the International Space Station (ISS) have been conducted continuously twenty-four hours per day, 365 days a year beginning February, 2001 and continuing through present day. The Payload Operations Integration Center (POIC), located at the Marshall Space Flight Center in Huntsville, Alabama, has been a leader in integrating and managing NASA distributed payload operations. The ability to conduct science operations is a delicate balance of crew time, onboard vehicle resources, hardware up-mass to the vehicle, and ground based flight control team manpower. Over the span of the last ten years, the POIC flight control team size, function, and structure has been modified several times commensurate with the capabilities and limitations of the ISS program. As the ISS vehicle has been expanded and its systems changed throughout the assembly process, the resources available to conduct science and research have also changed. Likewise, as ISS program financial resources have demanded more efficiency from organizations across the program, utilization organizations have also had to adjust their functionality and structure to adapt accordingly. The POIC has responded to these often difficult challenges by adapting our team concept to maximize science research return within the utilization allocations and vehicle limitations that existed at the time. In some cases, the ISS and systems limitations became the limiting factor in conducting science. In other cases, the POIC structure and flight control team size were the limiting factors, so other constraints had to be put into place to assure successful science operations within the capabilities of the POIC. This paper will present the POIC flight control team organizational changes responding to significant events of the ISS and Shuttle programs.

UNH Project SMART 2017: Space Science for High School Students

NASA Astrophysics Data System (ADS)

Smith, C. W.; Broad, L.; Goelzer, S.; Levergood, R.; Lugaz, N.; Moebius, E.

2017-12-01

Every summer for the past 26 years the University of New Hampshire (UNH) has run a month-long, residential outreach program for high school students considering careers in mathematics, science, or engineering. Space science is one of the modules. Students work directly with UNH faculty performing original work with real spacecraft data and hardware and present the results of that effort at the end of the program. This year the student research projects used data from the Messenger, STEREO, and Triana missions. In addition, the students build and fly a high-altitude balloon payload with instruments of their own construction. Students learn circuit design and construction, microcontroller programming, and core atmospheric and space science along with fundamental concepts in space physics and engineering. Our payload design has evolved significantly since the first flight of a simple rectangular box and now involves a stable descent vehicle that does not require a parachute. Our flight hardware includes an on-board flight control computer, in-flight autonomous control and data acquisition of multiple student-built instruments, and real-time camera images sent to ground. This year we developed, built and flew a successful line cutter based on GPS location information that prevents our payload from falling into the ocean while also separating the payload from the balloon remains for a cleaner descent. We will describe that new line cutter design and implementation along with the shielded Geiger counters that we flew as part of our cosmic ray air shower experiment. This is a program that can be used as a model for other schools to follow and that high schools can initiate. More information can be found at .

Space vehicle acoustics prediction improvement for payloads. [space shuttle

NASA Technical Reports Server (NTRS)

Dandridge, R. E.

1979-01-01

The modal analysis method was extensively modified for the prediction of space vehicle noise reduction in the shuttle payload enclosure, and this program was adapted to the IBM 360 computer. The predicted noise reduction levels for two test cases were compared with experimental results to determine the validity of the analytical model for predicting space vehicle payload noise environments in the 10 Hz one-third octave band regime. The prediction approach for the two test cases generally gave reasonable magnitudes and trends when compared with the measured noise reduction spectra. The discrepancies in the predictions could be corrected primarily by improved modeling of the vehicle structural walls and of the enclosed acoustic space to obtain a more accurate assessment of normal modes. Techniques for improving and expandng the noise prediction for a payload environment are also suggested.

STS-102 MPLM Leonardo moves into PCR

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Inside the payload changeout room on the Rotating Service Structure, Launch Pad 39B, the Multi-Purpose Logistics Module Leonardo is ready for the payload ground-handling mechanism (PGHM) to remove it from the canister. A worker beneath the MPLM checks equipment. Leonardo then will be transferred into Space Shuttle Discovery'''s payload bay. One of Italy'''s major contributions to the International Space Station program, Leonardo is a reusable logistics carrier. It is the primary delivery system used to resupply and return Station cargo requiring a pressurized environment. Leonardo is the primary payload on mission STS-102 and will deliver up to 10 tons of laboratory racks filled with equipment, experiments and supplies for outfitting the newly installed U.S. Laboratory Destiny. STS-102 is scheduled to launch March 8 at 6:45 a.m. EST.

The BIMDA shuttle flight mission: a low cost microgravity payload.

PubMed

Holemans, J; Cassanto, J M; Moller, T W; Cassanto, V A; Rose, A; Luttges, M; Morrison, D; Todd, P; Stewart, R; Korszun, R Z; Deardorff, G

1991-01-01

This paper presents the design, operation and experiment protocol of the Bioserve sponsored flights of the ITA Materials Dispersion Apparatus Payload (BIMDA) flown on the Space Shuttle on STS-37. The BIMDA payload represents a joint effort between ITA (Instrumentation Technology Associates, Inc.) and Bioserve Space Technologies, a NASA Center for the Commercial Development of Space, to investigate the methods and commercial potential of biomedical and fluid science applications in the microgravity environment of space. The BIMDA payload, flown in a Refrigerator/Incubator Module (R/IM) in the Orbiter middeck, consists of three different devices designed to mix fluids in space; four Materials Dispersion Apparatus (MDA) Minilabs developed by ITA, six Cell Syringes, and six Bioprocessing Modules both developed by NASA JSC and Bioserve. The BIMDA design and operation reflect user needs for late access prior to launch (<24 h) and early access after landing (<2 h). The environment for the payload is temperature controlled by the R/IM. The astronaut crew operates the payload and documents its operation. The temperature of the payload is recorded automatically during flight. The flight of the BIMDA payload is the first of two development flights of the MDA on the Space Shuttle. Future commercial flights of ITA's Materials Dispersion Apparatus on the Shuttle will be sponsored by NASA's Office of Commercial Programs and will take place over the next three years. Experiments for the BIMDA payload include research into the following areas: protein crystal growth, thin film membrane casting, collagen formation, fibrin clot formation, seed germination, enzymatic catalysis, zeolite crystallization, studies of mixing effects of lymphocyte functions, and solute diffusion and transport.

Reusable Rack Interface Controller Common Software for Various Science Research Racks on the International Space Station

NASA Technical Reports Server (NTRS)

Lu, George C.

2003-01-01

The purpose of the EXPRESS (Expedite the PRocessing of Experiments to Space Station) rack project is to provide a set of predefined interfaces for scientific payloads which allow rapid integration into a payload rack on International Space Station (ISS). VxWorks' was selected as the operating system for the rack and payload resource controller, primarily based on the proliferation of VME (Versa Module Eurocard) products. These products provide needed flexibility for future hardware upgrades to meet everchanging science research rack configuration requirements. On the International Space Station, there are multiple science research rack configurations, including: 1) Human Research Facility (HRF); 2) EXPRESS ARIS (Active Rack Isolation System); 3) WORF (Window Observational Research Facility); and 4) HHR (Habitat Holding Rack). The RIC (Rack Interface Controller) connects payloads to the ISS bus architecture for data transfer between the payload and ground control. The RIC is a general purpose embedded computer which supports multiple communication protocols, including fiber optic communication buses, Ethernet buses, EIA-422, Mil-Std-1553 buses, SMPTE (Society Motion Picture Television Engineers)-170M video, and audio interfaces to payloads and the ISS. As a cost saving and software reliability strategy, the Boeing Payload Software Organization developed reusable common software where appropriate. These reusable modules included a set of low-level driver software interfaces to 1553B. RS232, RS422, Ethernet buses, HRDL (High Rate Data Link), video switch functionality, telemetry processing, and executive software hosted on the FUC computer. These drivers formed the basis for software development of the HRF, EXPRESS, EXPRESS ARIS, WORF, and HHR RIC executable modules. The reusable RIC common software has provided extensive benefits, including: 1) Significant reduction in development flow time; 2) Minimal rework and maintenance; 3) Improved reliability; and 4) Overall reduction in software life cycle cost. Due to the limited number of crew hours available on ISS for science research, operational efficiency is a critical customer concern. The current method of upgrading RIC software is a time consuming process; thus, an improved methodology for uploading RIC software is currently under evaluation.

Far ultraviolet wide field imaging with a SPARTAN /Experiment of Opportunity/ Payload

NASA Technical Reports Server (NTRS)

Carruthers, G. R.; Heckathorn, H. M.; Opal, C. B.

1982-01-01

A wide-field electrographic Schmidt camera, sensitive in the far UV (1230-2000 A), has been developed and utilized in three sounding rocket flights. It is now being prepared for Shuttle flight as an Experiment of Opportunity Payload (EOP) (recently renamed as the SPARTAN program). In this paper, we discuss (1) design of the instrument and payload, particularly as influenced by our experience in rocket flights; (2) special problems of EOP in comparison to sounding rocket missions; (3) relationship of this experiment to, and special capabilities in comparison to, other space astronomy instruments such as Space Telescope; and (4) a tentative observing plan for an EOP mission.

Atmospheric, Magnetospheric and plasmas in Space (AMPS) spacelab payload definition study; Volume 4: Part 3, Labcraft instrument systems general specification

NASA Technical Reports Server (NTRS)

Keeley, J. T.

1976-01-01

Guidelines and general requirements applicable to the development of instrument flight hardware intended for use on the GSFC Shuttle Scientific Payloads Program are given. Criteria, guidelines, and an organized approach to specifying the appropriate level of requirements for each instrument in order to permit its development at minimum cost while still assuring crew safety, are included. It is recognized that the instruments for these payloads will encompass wide ranges of complexity, cost, development risk, and safety hazards. The flexibility required to adapt the controls, documentation, and verification requirements in accord with the specific instrument is provided.

Shuttle communication and tracking systems signal design and interface compatibility analysis

NASA Technical Reports Server (NTRS)

1986-01-01

Various options for the Dedicated Payload Communication Link (DPCL) were evaluated. Specific subjects addressed include: payload to DPCL power transfer in the proximity of the payload, DPCL antenna pointing considerations, and DPCL transceiver implementations which can be mounted on the deployed antenna boom. Additional analysis of the Space Telescope performance was conducted. The feasibility of using the Global Positioning System (GPS) for attitude determination and control for large spacecraft was examined. The objective of the Shuttle Orbiter Radar Test and Evaluation (SORTE) program was to quantify the Ku-band radar tracking accuracy using White Sands Missile Range (WSMR) radar and optical tracking equipment, with helicopter and balloon targets.

KSC01kodi058

NASA Image and Video Library

2001-07-31

KODIAK ISLAND, Alaska -- Technicians prepare the Starshine 3 payload for its launch aboard the Athena 1 launch vehicle, while the payload fairing awaits processing, at Kodiak Island, Alaska, as preparations to launch Kodiak Star proceed. The first orbital launch to take place from Alaska's Kodiak Launch Complex, Kodiak Star is scheduled to lift off on a Lockheed Martin Athena I launch vehicle on Sept. 17 during a two-hour window that extends from 5:00 to 7:00 p.m. ADT. The payloads aboard include the Starshine 3, sponsored by NASA, and the PICOSat, PCSat and Sapphire, sponsored by the Department of Defense (DoD) Space Test Program.

The SPACEHAB payload is installed in the PCR at LC 39A awaiting further STS-89 processing

NASA Technical Reports Server (NTRS)

1997-01-01

The SPACEHAB payload arrived at Launch Pad 39A this morning and was installed in the Payload Changeout Room. Final preparations for liftoff of the STS-89 mission are under way. Endeavour and its crew of seven are targeted for a Jan. 22 launch. STS-89 will be the eighth Shuttle docking with the Russian Space Station Mir as part of Phase 1 of the International Space Station program. Mission Specialist Andy Thomas, Ph.D., will succeed Mission Specialist David Wolf, M.D., as the last NASA astronaut scheduled for a long-duration stay aboard Mir.

Intuitive Tools for the Design and Analysis of Communication Payloads for Satellites

NASA Technical Reports Server (NTRS)

Culver, Michael R.; Soong, Christine; Warner, Joseph D.

2014-01-01

In an effort to make future communications satellite payload design more efficient and accessible, two tools were created with intuitive graphical user interfaces (GUIs). The first tool allows payload designers to graphically design their payload by using simple drag and drop of payload components onto a design area within the program. Information about each picked component is pulled from a database of common space-qualified communication components sold by commerical companies. Once a design is completed, various reports can be generated, such as the Master Equipment List. The second tool is a link budget calculator designed specifically for ease of use. Other features of this tool include being able to access a database of NASA ground based apertures for near Earth and Deep Space communication, the Tracking and Data Relay Satellite System (TDRSS) base apertures, and information about the solar system relevant to link budget calculations. The link budget tool allows for over 50 different combinations of user inputs, eliminating the need for multiple spreadsheets and the user errors associated with using them. Both of the aforementioned tools increase the productivity of space communication systems designers, and have the colloquial latitude to allow non-communication experts to design preliminary communication payloads.

Small Satellites for Secondary Students

NASA Astrophysics Data System (ADS)

Zack, Kevin; Cominsky, Lynn

2012-11-01

Small Satellites for Secondary Students is a program funded by a three-year grant from NASA to bridge the gap in STEM education for secondary-school students. This is accomplished by creating the educational resources that are needed to support the development of a small scientific payload in alignment with scientific and technological education standards. The prototype payloads are flexible multi-experiment platforms designed to accommodate a wide range of student abilities with minimal resource requirements. The heart of each payload is an Arduino microcontroller which communicates with components that provide sensor data, Global Positioning System information, and which offer on-board data storage. The payload is built with off-the-shelf components and a pre-etched, custom-designed connector board. The platform also supports real-time telemetry updates through the use of Wi-Fi. To date, the prototype payloads have been tested on both high-powered rockets reaching over 3km and weather balloons tethered at 300m. Multiple successful rocket test runs reaching 1km have been conducted in partnership with amateur rocket clubs including the Association of Experimental Rocketry of the Pacific. From these flights, we are continuing to improve the payload design in order to increase the likelihood of student success.

Houston, We Have a Podcast. Ep42 The Space Launch System Part.2(2)

NASA Image and Video Library

2018-04-27

Production Transcript for Ep42 The Space Launch System Part.2.mp3 Gary Jordan (Host): Houston, we have a podcast. Welcome to the official podcast of the NASA Johnson Space Center, Episode 42: The Space Launch System, Part 2. I'm Gary Jordan, and I'll be your host today. So in this podcast, we bring in the experts -- NASA scientists, engineers, and astronauts -- all to let you know the coolest information about what's going on right here at NASA. So today, we're talking about the most powerful rocket since the Saturn V moon rocket, NASA's Space Launch System. We've got two guests from the Marshall Space Flight Center in Huntsville, Alabama here with us today to tell us about the rocket, the payloads it can carry, and where it will go. Spoiler alert: It will bring people, big stuff, and little stuff all farther than we've ever gone before. See, I did it again. You had a second chance for Part 2, and you blew it, Gary. If you're slightly confused, it's because this is Part 2 of our two-part episode on NASA's Space Launch System. There's still some good stuff in here, but if you want the full story, just go back and listen to Part 1. So continuing our conversation with us today are David Smith and Paul Bookout. David is the Vice President for Advanced Programs and Victory Solutions in Huntsville, Alabama. He has a long career in aerospace engineering and is a subject matter expert on rocket architecture and how payloads will fit into the rocket. He wrote the SLS Mission Planner's Guide, which gives payload developers a general idea of the capabilities of the rocket and some technical specifications so they can determine how their payloads might fit inside. He looks after the big payloads. Our other guest today is Dr. Paul Bookout, EM1 Secondary Payloads Integration Manager, who manages the integration of five CubeSats in the giant rocket as well the avionics that will control the deployment of all 13 small satellite payloads on the first mission of SLS and Orion called Exploration Mission 1, EM1. He spends his time managing the little payloads, not much bigger than a shoebox, on a skyscraper-sized rocket. So we're going to talk about just how powerful this monster rocket is, its unique capabilities, what it'll be used for, where it is in its development, its first mission with the Orion crew vehicle, and then look ahead to the future to the Moon, to Mars, and throughout the solar system. In this particular episode, we talk a lot about propulsion on this rocket, especially comparing solid and liquid fuel for the rockets. So at a very high level, the key differences are cost and control. Solid rocket fuel systems are generally simpler in design, cost effective, and they produce a large amount of thrust. But once the fuel is ignited, you can't really turn it off. Liquid fuel systems provide more flexibility. You can regulate the thrust through system throttle settings, but liquid fuel systems can be more costly. Very smart engineers have assessed the best way to use these two fuels and, for the SLS, they've come up with a combined design of solid and liquid fuel system. Solid fuel boosters and liquid fuel, the main engines to work in tandem to get you off the ground and moving fat, and then liquid fuel carries, or the liquid fuel engines will carry you where you need to go. So we're go for launch with Mr. David Smith and Dr. Paul Bookout for the Space Launch System program, T minus 5, 4, 3, 2, 1, 0, and liftoff of Episode 42 of Houston We Have a Podcast. Boom, nailed it. [ Music ] Okay. Paul and David, thanks for sticking around. This is going to be Part 2. We're sort of continuing our conversation, and we were talking a little bit during this I guess intermission, but one of the main things that we forgot to touch on was it takes eight minutes to do the first part of this launch. That's the solid rocket boosters and the core stage-- David Smith: Ignition to disposal of those stages. Host: Yes. Yeah, but I guess up to this point, all you need is some sort of injection burn, and you can pretty much go anywhere in the solar system. Is that right? David Smith: That's right. >> So it just depend, you just define what kind of injection burn, and you can go anywhere. David Smith: Well, it's the injection burn, and then the characteristic energy, which is the acceleration to get to that location. You know, it's a curve, so-- Host: Yeah. David Smith: If you go farther out, the less mass you can bring with that injection burn. So it is, it's the timing of the injection burn and the trajectory. But also, the farther away you go in the solar system, obviously, the less mass you can carry. So that's all kind of combined together. Host: That's right. And so for EM1, the injection burn is going to be translunar, right? David Smith: Correct. Host: But you can also do Mars injection burn, or Jupiter injection burn, or, like, anything after this eight minutes, it's just, you can just define it? David Smith: That's right. Yep. Host: So that's really the main thing about this vehicle is after eight minutes, you're ready to go wherever you want, and the fact that it's human rated, and the fact that you can bring really large payloads, right. I guess that, we'll start off with that. So we're building this rocket to pretty much go anywhere, but what are the sorts of missions we're looking at for the future for SLS? David Smith: Yeah, the first missions that are being considered are translunar and perhaps making something that has a, kind of a complicated acronym, LOP-G, Lunar Orbiting Platform/Gateway. What it really is is like a service plaza on a toll road. So think of Saturn V as the rocket that went out and surveyed everything and, you know, there were no roads, and it kind of established these, you know, these paths to go to the Moon, okay. Now, SLS is going to take that survey information and hopefully make this Lunar Orbiting Platform into a service plaza where, what do you get there? Well, you get a safe place for the crew. You can refuel landers that can go to the Moon. You can have a navigational way station. You can have a communication way station. You have a place for internationals to come by and make sure they got everything together before they go to the Moon. This gateway, in fact, gives you universal, total access to any spot on the lunar surface. Apollo is just equatorial. This station will give you access to any place on the Moon. So it has a lot of really great attributes, but it's a different kind of thing. Unlike the Space Station, which is purely science, this Lunar Orbiting Platform is probably going to be a lot more utilitarian and allow a lot more understanding and exploitation of the Moon and the lunar surface, which is, in fact, what we need that experience so that we can actually do the same thing for Mars. So it's three days away versus nine months away with Mars. So that, that's our first stage. It seems in the 2020's, we're going to be putting that together one piece at a time. So the first piece might be an EM2 mission that delivers a solar electric propulsion system that essentially is the way that this station keeps in its place. So it's just a little bit of impulse in this halo orbit around the Moon. You can stay there with very little power using a xenon solar electric propulsion system. The second part might be a habitation module. This isn't where the crew are going to, they're not going to live here full time. Again, it's a way station, so it's a place they can hang out, refresh themselves, get food, change clothing, who knows on their way to the Moon. Then, they're going to have an air lock that allows them to do servicing on perhaps landers and other kind of equipment that comes into that gateway. And then, also, a place for logistics modules to come to resupply this service plaza so that, for the long term, it can service people going to and from the Moon. So that's probably the first part, and that looks like that would be something that would be in the early 2020's, and that's where the current administration seems to be focusing us is on doing lunar first to be prepared for Mars later. Host: Okay. It's kind of like a small truck stop. David Smith: It is. David Smith: It is-- David Smith: Think of it as, yeah. [laughs] Yeah. And it should be kind of looked at that way as it's a way station to greater and better things, either the Moon or Mars. Host: Yeah. That's right. You can shower. You can, [laughs] you can service it. It's got a-- David Smith: Get your eggs and steak. Host: Yeah. David Smith: You know, get your car repaired. Refuel. Get some gas. Tow truck is even there to maybe save you if you have a probably on the Moon. So really, it's a good deal. It's kind of like a lighthouse and service plaza all put into one. Host: But not only will the SLS get us there. It's actually going to get the LOP-G there, right? It'll actually-- David Smith: It'll assemble it. David Smith: It'll assemble it. Host: In pieces. Now-- David Smith: Yeah. David Smith: If we were to do it the best way, instead of doing it in smaller pieces -- and by the way, it's going to do this just using the trunk section underneath the Orion. So the co-manifested payload is what these little elements of the station are going to be. If we were, if we could, it'd be best to just make one giant chunk and put in the, into a fairing, but the way I think the program is unfolding, to use crew to start with, is to bring the station in pieces that the crew can assemble at that location. Host: So going back to the previous episode, Episode 41 -- if you haven't listened to it, go back -- and that was the first part of our conversation, but going back to this co-manifested payload, we're talking about primary payloads, co manifested, secondary. What's the co manifested? David Smith: Yeah, the co manifested, again, is the ten-ton capability that is the trunk space underneath Orion that's going to fly on the Block 1B SLS. So in contrast, if you took off the Orion and its trunk space and put a large fairing on top, you get a primary payload that could be 40 tons the Moon. So it's ten tons the Moon is co manifested, or it's maybe 40 tons the Moon as a primary payload. And the secondary payloads are payloads of opportunity. They kind of fit in little, tiny spaces that are left over. They aren't filled up with other kinds of stuff. Host: And that's where Paul comes in-- Paul Bookout: Yes. Host: Right? [laughter] Paul Bookout: That's my world. Host: That's right. David Smith: So after Lunar Orbiting Platform-Gateway, one of the early missions that's been envisioned is taking a probe to the Europa, the moon, icy moon of Jupiter. What's so neat about this mission is that SLS, is we have to loft this payload and get it to Jupiter in two-and-a-half years, where a current ELV -- Atlas, Delta, even a Falcon 9 Heavy -- couldn't do that in more than seven years. So we're going to cut five years off a trip. Now, what does that mean? Well, one, it means that you're getting quicker returns to the science community. You're helping people not spend their whole career on one science mission. You have younger people come in, work on a mission, do it quicker. And if it costs $100 million a year to maintain a cadre of ground controllers watching this thing, think of the money that you're saving over time if you can eliminate five years of that mission. Plus, the risk of that hardware traveling through space. So this is a real enabler for Europa. In fact, SLS is the only vehicle that can bring it there in that kind of time. Host: Unbelievable. Is it a bigger payload because it's a, it's SLS, or is it just-- David Smith: Well-- Host: It gets it there faster? David Smith: In this case, Atlas could fly the same mass of payload, which is very large, by the way, but it would take over seven years. Host: I see. David Smith: So it had to take a whole bunch of gravity assists around the Earth and Venus to get it there where SLS can send it there directly. Now, to your point is the New Horizons mission, which was the mission to Pluto, I think it was 120-kilogram payload that was finally delivered there after like ten years. In that case, SLS couldn't get you there any faster, but it could double the payload to over 250 kilograms of delivered payload to Pluto. So it just depends on the trajectory and the position of the planets when you do this, on what value you have, but the fact you can do it quick is a unique attribute that only SLS can bring right now. Host: [laughs] Unbelievable what this rocket is capable of. And I kind of wanted to go back and kind of visit the rocket itself, where, the history of it. Where did we start with some, building some of these pieces, and kind of where are we now? So if we can just sort of start at the beginning, whenever SLS was proposed, and we're going to hammer in the first nail, I guess. It's a little bit more complicated than that, but where did this all begin? Paul Bookout: Yes. Of course, the primary design was based off of the shuttle heritage. You know, we're taking components that the shuttle used, the propulsion aspects of it -- the [inaudible] motors, the external tank, and the space shuttle main engines -- and utilizing, upgrading, making more powerful the, those components and assembling the core stage. So that's kind of where the history of where SLS is coming from. So we want to use that existing technology, again, upgrade it, make it better. Also, the manufacturing facilities that go into making these components are in existence, so we want to still utilize that, save money, save schedule to move forward with the SLS rocket. Host: Okay, and so it's kind of, that makes sense, right, because it's, you have, okay, this is a core stage that works. These are components of the shuttle that worked. Let's just sort of fit it and to meet these requirements of building a giant rocket that can take payloads anywhere in the solar system. Paul Bookout: Exactly. Host: And humans too. It's human rated, which is a huge component of this whole thing. Paul Bookout: Definitely. Host: So it's, where is it being built? Is it one location? Paul Bookout: No. Actually, overall, there's 44, over 44 states-- Host: Oh, wow. Paul Bookout: That different components are going to be, are being built in. So this is America's rocket. Host: Yeah. [laughs] Paul Bookout: So it's not just NASA's. It's being built all over. You know, there's more than 1000 contractors working on this, in addition, of course, into, in addition to NASA. The core stage, which is the prime or contractor is Boeing, they're building that in Michoud, which is outside of New Orleans. The engine prime is Aerojet Rocketdyne. They're being developed, or manufactured, or refurbished down at the Stennis Space Center. And then, when they're done, they'll be shipped to Michoud for integration with the core stage. And then, that core stage with the main engines would be sent back to Stennis for testing because Stennis is the primary testing facility for NASA-- Host: I see. Paul Bookout: For rockets. The boosters is the Orbital ATK. They're actually manufactured just north of Salt Lake City in Utah. And it's kind of ironic that the, it's very close to the Golden Spike, where the east and west railroads met when they were building the transcontinental railroad, was very close to that because the motor segments are used in the rail system to ship down to KSC from ATK, Orbital ATK out in Utah. Host: Oh, okay. All right. Paul Bookout: So-- Host: I like that. Paul Bookout: A little history there. [laughs] And the upper stage, of course, where, as Boeing ULA, which is a direct purchase from them for that. And that's being built in Decatur, Alabama. Host: Wow. All over the place is absolutely correct, so-- Paul Bookout: And again, those are just the primary elements. All the subsystems to that are spread out all over the United States. Host: So what is currently built, and then what's on the ticket to be built? David Smith: Well, right now, the core has been built three times so far. The weld confidence article to make sure that friction stir welding is appropriate because it's the world's tallest, biggest weld fixture-- Host: Oh, wow. David Smith: Down at Michoud, so we had to test that first. Then, they're building test articles. And then, the flight hardware. The test articles right now are up at Marshall, so there's this new barge -- actually, it's the same barge they used for shuttle Pegasus. They had to make it a lot longer, so they cut out the middle and put in a new middle section. And that just shipped up, the core section up to Marshall, where it's going under, undergoing static testing. The engine section's already been completed. The testing of that's been completed. And the intertank, the sections between the hydrogen and oxygen tank, has just arrived at Marshall Space Flight Center for testing. The hydrogen and the oxygen tanks will arrive later this year for testing at Marshall too, all for static testing, where they're put under a load to simulate their launch conditions. So this is the largest structural testing campaign since shuttle in the 1970's, and, you know, since this is probably a 50-year rocket, this is really laying the foundation for that kind of generational spacecraft capability that we're building for the Moon and beyond. The upper stage, the exploration upper stage, the NASA one is currently being worked on in design phase, but the ICPS that Paul talked about earlier, the interim cryogenic propulsion stage, is finished and down, already been tested and shipped down to KSC. The engines, the new engine controllers are hot fire tested at Stennis already, and I might even hear a sound of that in a minute. And the boosters, as we talked about, were built in Utah but had full, two full-scale static firing tests at the Orbital ATK facility so far. Core stage and booster avionics testing are undergoing at Marshall right now in specialized, in a specialized, integrated avionics test lab. So the testing is going forward. It's really quite a test campaign. Working on EM1 right at the moment, but, in parallel, getting ready for, I'm sorry, Block 1 to start with, and, in parallel, working on Block 1B for the EM2 mission maybe in 2022. Host: So I'm, I want to understand the full scope. That's, there's a lot of different elements, a lot of different parts of the testing. What are some of the main things that you really want to test? It sounds like structure is one of those things, and how do you do that? How do you test the structure? David Smith: There's a new static test facility at Marshall that's been developed where you essentially set them up vertically, and then you put a load down on the stage, and you do it in many different angles to make sure you can understand not only is it going straight in flight, but if starts experiencing some kind of skew because of the engines, so it undergoes quite a bit of testing that way. That's obviously, the structural modes are the most important. And when we talk about human spaceflight hardware, what that really means for structure is that you test it to a factor of 1.4. So it means there's a 40% margin on the capability of that structure, which is not something that expendable launch vehicles have to worry about. So our rockets are generally a little heavier, a little stiffer, a little more capable, but we do that to provide more margin for the crew in case of emergency. So that's the biggest part of that structural test that's going on right now at Marshall. Host: That goes back to your point, Paul, about one of the main parts of testing this and building SLS is the fact that it is human rated and you have these extra constraints for making sure that safety is and redundancy is one of the primary concerns of building this rocket. Paul Bookout: Exactly, yes. Host: Unbelievable. So the other part is the engines too. You're actually firing the engines. And it's a hot fire test. What's that? David Smith: Well, that's, the shuttle engines are going, they're installed into a test [inaudible] at Stennis. They're put through the same paces as if they were being launched in the vehicle. And remember, some of these engines haven't been test fired in eight years, seven, eight years. Host: Right. David Smith: So it's real important to make sure that they're still, still have the quality that we are looking for at the same time they have a new engine controller. So the controller, the computer that runs these engines have been upgraded from the shuttle days. So it's the first time those two have been mated together. So real important testing. We have I think up to 15 of those engines in inventory, so they're going to be going through those until they, at, probably in the mid-'20's, replacing with a new build of the shuttle engine. So right now, we're still going through the old engines with the new controllers installed. Host: Actually, we do have some audio from that that I really want to play. It's, this is the hot fire test at Stennis, so if you're listening right now, be prepared because it's going to be very loud. [ Engine Sounds ] Host: So that was the hot fire test, and what, you're looking at what components? Are you looking at temperature? Are you looking at propulsion, efficiency? What are the main things that you really want to get out of this test? David Smith: Well, I think the biggest one is, how's the turbo machinery going? You know, if you have turbine blades going at like 3000 rpm and you're spitting out all that fuel at the same time, how is that working out? Is it meeting all the parameters? Is, like you said, that's the temperature? How does it run through its life cycle for that eight-minute burn? That's a long time to run an engine. Host: Yeah. David Smith: So especially, you know, before we launch, you know, the shuttle only had three of these engines firing. Now, we're going to have four of them. So again, that's a unique configuration. So making sure, [inaudible] how these engines will play together will be an important part of the test as well. Host: Did you ever get to see any of these tests in person -- structural tests, hot fire tests, anything like that? David Smith: Yes. Host: Is it really, really loud? David Smith: Well, the Stennis tests, you can get really close to it-- Host: Oh, really? David Smith: Because, you know, it has the flume that comes out the side. And you can get close to a cyclone fence. In fact, you can taste the exhaust because, you know, oxygen and hydrogen comes together and forms water. Host: Right. David Smith: So that, and you have the sprinkler system that's cooling it down. So you get both the sound, right, you get the visual of the flames, and then you get the taste. [laughs] So I don't think you can do that anywhere else. You certainly can't get the taste at Kennedy, so Stennis is really a remarkable opportunity when they do those test fires there. Host: Does it -- I'm imagining like a hot shower or something, just like really-- David Smith: Well, remember, Stennis is pretty humid because it's in Mississippi, so-- Host: Oh, yeah. David Smith: It's going to feel like a hot shower, but, [laughs] yeah. Host: Okay, so I'm, a curious thing -- how does a hot fire test taste? David Smith: Yeah, it has a taste to it. Host: [laughs] So what about the flight hardware for EM1? Where are some of those components? Paul Bookout: Right now, the Orion stage adapter, that's where the 13 CubeSets are going to be housed during launch on EM1. Host: Oh, yeah. Paul Bookout: It's currently at Marshall Space Flight Center. And at the end of, beginning, I'm sorry, of April, it's planned to ship down on the Super Guppy, which is a large carrier aircraft, down to KSC for processing. And once it's down there when we're about six months to launch, that's when the secondary payloads will be integrated into that before stacked on the vehicle. The interim cryogenic propulsion stage, of course, is finished. It was, again, up in Decatur and is already down at KSC doing other final preps on that. The launch vehicle stage adapter, which is being developed at Marshall by Lockheed Martin, they, the primary structure is complete, and they're doing spray foam insulation on the vehicle right now. Again, that's also to help with acoustics aspects of the inside of that, inside of the LVSA. Host: Oh, that's right. Paul Bookout: The core stage, of course, the major components, as David said, the tank, the different tanks will be set up, sent up here for testing. And once they're done testing, they'll be sent back down to Michoud and assembled. And then, the main engines will come over from Stennis and assembled into the full core. That's the liquid oxygen, liquid hydrogen inner tank and the engines. Then, it'll be sent back over to Stennis. As David mentioned earlier, each engine, it would be separately tested, but then all four of these will be tested as, in flight configuration down there at Stennis. So we're running them through the full cycle of, as we're integrating. We're testing as we're putting it together. Host: That's right. Paul Bookout: So we understand that, as we assembled it, is it still operating the way we expected it to? Host: So then, will you, will it be built at Kennedy because that's when it's going to be launched? David Smith: Assembled. Host: I'm sorry, yeah. David Smith: It's built in Michoud, tested at Stennis, and then assembled at Kennedy. Host: Assembled at Kennedy. Paul Bookout: So the solid rocket motors, again, all the segment are, the five segments -- total of ten, five on each side -- have already been cast. They're in final prep for shipping down to KSC on the rail system. And then, just at, similar to shuttle program, once they've reached KSC, they'll be stacked in the VAB one segment at a time, and then the core stage will come in and be connected in the center between them. Then, you have your upper stage or the ICPS, where, I'm sorry, you'll have your LVSA, launch vehicle stage adapter. Then, you'll have your Orion -- let me just start over. Once the core has been installed, then you'll have the launch vehicle stage adapter installed. Then, you'll have your upper stage or the ICPS. And then, on top of that, you'll have the Orion stage adapter where the secondary payloads are. And then, Orion will come in and make, complete the stack. Host: All in this, in the Vertical Assembly Building? Paul Bookout: Yes. Yeah. Remember, it will built to assemble the Saturn V rocket, and-- Host: Yeah. Paul Bookout: We're about that same size, so [laughs] there's plenty of room in there. Host: That's right. It's, going back to that, actually, I don't think we've talked about it on the podcast. The Vertical Assembly Building is, as you can probably tell from the way that this is being assembled, it's gigantic. But it's so big, right, that it has its own weather system that you have to kind of worry about, right? Is that right? David Smith: Yeah, it's-- Paul Bookout: Yes. David Smith: Tall enough where, you know, everything that gets up in there can form its, it could rain a little bit sometimes-- Paul Bookout: Yes. Form clouds up there. David Smith: Yes. Host: Wow. And then, the, you have these giant doors that's going to open, and then you'll just sort of roll the rocket out. David Smith: But one big change is, if you recall, so it's really interesting. You know, a lot of that building was not changed from Saturn V. They only used two of the bays. There's four for shuttle. So they took out the platforms that were for Saturn and put in some shuttle platforms. But for Saturn, excuse me, for Block 1B, they had to do a lot more changes to that. So they had to replace all the platforms for that, and they actually removed a whole bunch of Saturn V, your equipment that had been left, abandoned in place. So it's, that building has really changed from what it was during the shuttle era. Host: So it's really been reconstructed to fit the SLS. That's really the main-- David Smith: Yes. Host: The thing that's going on right now in the VAB. Is it-- David Smith: Right. Host: Is it completed, or is it still going on? David Smith: The platforms are completed. Paul Bookout: Completed. David Smith: For [inaudible] 1, Block 1. Paul Bookout: For Block 1, okay. Host: Right. Paul Bookout: Yeah. And, you know, for SLS, there's still a lot of work at KSC being performed too. It's just not the launch vehicle and all of its hardware for EM1. It's KSC has to go through a redesign on a lot of their components. As David just said, the VAB and all the platforms to be able to reach the hardware where you're stacking SLS. Also, the crawler transporter that takes the mobile launch platform, which has the SLS rocket on -- originally, the Saturn V rocket -- has to be upgraded to fit the SLS rocket. So, in addition, out at the launch pad, they're redoing the flame trenches, re-bricking them because it's going to have a lot more powerful rockets since the S, you know, since the shuttle program. In addition, they're, they have to have a lot bigger water suspension system, you know, because at a lot more power than what shuttle was going through. David Smith: Called rainbirds after the sprinklers. Big rainbirds. Host: Rainbirds. David Smith: Yeah, they kind of go, click, click, click, click, click, on the lawn, but this time, they do it on the engines and stuff. Host: Oh. [laughs] Paul Bookout: So, you know, the water suspension, suppression system is to help with not just the heat but, also, the sound that these rockets, engines, and solid rocket motors, when they ignite, they're very loud. They send out a shock wave. And if you didn't have the water there to suppress or dilute that sound, that would just bounce back off the hard surface up into the vehicle and could damage the vehicle. So it's just not for flame. It's also to protect the vehicle from itself on the acoustics. Host: Okay. That's the, so that's the suppression system? Paul Bookout: Correct. The water that you usually see that starts a couple seconds right before ignition. Host: Actually, I think we do have some audio of that. I don't think this one's quite as loud as a hot fire test, but let's listen to that. This is what the suppression is going to sound like. [ Engine Sounds ] Host: And those are the, that's the clicks, right? That's the, I guess it's basically just like a giant-- David Smith: Sprinkler system. Host: Sprinkler system. Yeah, yeah, yeah. Paul Bookout: Yes. Host: Rocket-size sprinkler system. So you're going to take it from the VAB, and I wanted to get, circle back on that because I think I was calling it Vertical -- is it Vehicle Assembly? David Smith: Vehicle Assembly. Host: Vehicle? So I was getting that wrong. It's Vehicle Assembly Building. You bring it out to a launch pad, and is it going to launch on the same pad that the Saturn V was launching? David Smith: Yes. Host: Okay, so that's 39-- David Smith: In fact, I think -- well, I'm not sure if it's A or B-- Host: A or B. David Smith: But the one that we, that NASA kept, they totally revamped the equipment underneath that concrete mound. Host: Yeah. David Smith: And it's, there's a lot of [inaudible] and electrical equipment that's there in, the remnants from Saturn V, there's still a rubber room. If you know, that's where the, if someone was trapped at the pad, you'd have a safe place in there. So that's still in that same area, which they've now made a historic area, which is kind of interesting. But they, for the first time in 50 years, have to clean out all the old equipment, totally revamp that launch pad for SLS. So it's brand new and ready to go. It's really impressive. Host: So the, what's being suppressed over at this launch pad by that suppression system, is it, is the solid rocket boosters, right, and then are the engines firing at the same time? David Smith: Yes. David Smith: These RS-25-- Paul Bookout: Correct. Host: Engines? Paul Bookout: So-- Host: Everything's all at once? Paul Bookout: Right. Actually, the -- sorry. Actually, the main engines ignite first because we want to make sure all of those are operational and working at peak efficiency because once you start the solid rocket motors, you got to launch because you can't turn off solid rocket motors. So you want to make sure your other four engines are operating nominally, and then you ignite your solid rocket motors. Host: So we've done some testing with the, with these, the main engines, right? The RS-25's? Paul Bookout: Correct. Yes. Also, we have done full-scale testing of the solid rocket motors out there at Orbital ATK in Utah, where they actually constrain him, lay him on the ground sideways, and constrain him, and actually fire, do test fires out there at Utah. Host: Ooh, I've seen that. They actually had a HDR video I think of that -- high dynamic range or something. Paul Bookout: Yes. Host: Yeah, and it was super cool to see. But then, also, just the test itself, actually-- Paul Bookout: Yeah, I've been out there for a couple launches, and it's kind of unique because, with shuttle launch, you listen to the sound, and it's, you know, launching, so it's, after just a few seconds, it, the sound's gone. Where solid rocket motor is, it's operates for two minutes, so you're sitting there feeling that whole sound, you know, [laughs] for two minutes, and it's a really exciting experience to be out there. Host: How did it feel? Did it feel like you were at a loud concert, or even worse than that? Paul Bookout: Well, you're usually about a mile or so away. Host: A mile, okay. Paul Bookout: So, you know, just for safety reasons and everything. Host: That's, yeah. Paul Bookout: So you kind of get to see it off in the distance a little bit, but, yeah, you still feel it and hear it, yeah. And it's kind of unique because you see the smoke, the engines fire off, and the smoke coming out, and then, a couple seconds later, that's when you feel it. So-- Host: How about the RS-25's? Do you feel those too, or not as much? Were out at the RS-25 test? David Smith: Yeah, yeah. Well, the static firing, yeah, you feel it in your, you can get close for that, and you feel it in your stomach. I mean, it's very visceral, the shaking of your, of that sound, so, yeah, you won't forget it once you've had it. Host: That was the sound we played earlier, right? David Smith: Right. Host: Okay. I think the one we still have is the solid rocket booster, I think. Okay, let's play that one. This is the one that Paul was talking, the one out in Utah. >> T minus 10, 9, 8, 7, 6, 5, 4, 3, 2, 1, fire. [ Engine Sounds ] Host: Okay, so that was the test from out in Utah, and if you really, if you turned up the volume on your, on the podcast, you can really feel it. I listened to some of, I would listen to this in the car or hook it up to a nice speaker because you can really feel it there. So those, that's all of those -- the solid rocket boosters, the RS-25, and the suppression systems. So let's go back to the stages and sort of recap the, I guess the stages of all of these engines firing. What's that look like? David Smith: Right. So, you know, the term "stage" means that you have a single entity that provides an impulse for a period of time and then is thrown away. Host: Okay. David Smith: So in the olden days, so that would be Saturn, you know, you'd say Saturn was a three-stage vehicle, right. It had the first stage, the second stage, and then third stage was the injection stage that took, you know, Apollo and the land to the Moon. For both shuttle and for SLS, we really don't, can't call it three stages because these stages work together, which is kind of like they're two-and-a-half stages. So what that means is the core, and, as Paul said, the core starts a little bit earlier, but they're essentially the same time. The core and the booster, the solid rocket motors, boosters, excuse me, turn on at the same time. So they're ignited, and that's the one-and-a-half stage-- Host: Okay. David Smith: Because what happens? After two minutes, the boosters fall off and the core continues, so that's the half stage, in a sense, the boosters. Now, the core continues. And then, finally, the core is expended after eight minutes. It's disposed of in the ocean. And then, you have the upper stage -- in this case, the second of the one-and-a, two-and-a-half stages -- fires to get you to your destination. So you could still call it a three-stage system, but because some of the stages work together they're not really separate stages. So it gets a little confusing. So that's why you really don't hear, that's why people use the term "upper stage" these days and not "third stage" or "second stage" [laughs] because even the expendable vehicles have multiple solids on them, and so they have the same issues. So that's the difference in staging today. And it's more effective to do it this way as well. Host: It's more effective, I guess is it from the perspective of, oh, you can turn this off, you want to make sure everything's working? Is it I guess more reliable? That's why it's more effective? David Smith: Well, it's more effective because you use the power where you need it. At, you know, at sea level, you need the most thrust, so you combine everything together to get you out of the gravity well of Earth. So there's an efficiency with that system that, you know, is improved, is an improvement upon what was done for Saturn and other rockets before then? Host: Okay. So how about the, we're talking about different configurations too -- Block 1, Block 1B -- and how they're going to be different and just sort of evolve. Paul, I think you said you had some secondary payloads I think on 1B. Paul Bookout: Yes, that we're planning for. Host: That we're planning for, okay. Paul Bookout: So, you know, currently, on commercial launch vehicles, CubeSets usually don't have propulsion sets, and they're really going to low Earth orbit or geosynchronous orbit. Host: Yeah. Paul Bookout: And they're pretty much just deployed in those locations, so they don't need a secondary or propulsion system to get to where they need to. On EM1, this is the first opportunity for a secondary payload to be able to have propulsion systems and going to get access to deep space because we're giving them the initial thrust or velocity to get out going to the Moon or into deep space. They only need smaller propulsion system to change their trajectory or where they want to go. So it's, you know, this will be the game changer for secondary payloads. I mean, this is first-time opportunity for these small, little, shoe-size, shoebox-size payloads to be able to get out into deep space. Host: Yeah, and do some great stuff -- orbiting the Moon, land on the Moon. You got some-- Paul Bookout: Right. Host: Great stuff happening in some of these-- Paul Bookout: Right. Host: Secondary payloads. Paul Bookout: As I mentioned in Part 1, EM1's kind of discovering that, well, they really want to be a little bit bigger so they can have a little bit larger propulsion system. So instead of getting off at we call bus stop one right in the middle of the Van Allen belt, they'd like to get off at bus stop two or a little bit past so they don't have to worry about the radiation effects on their systems as much. But they can't do it because they don't have the propulsion system big enough to change their direction that they want to go. So on EM2, because it's a more powerful rocket, there's opportunity for additional mass allocations for secondary payloads. The mass allocation is the mass that's left over that the primary or co-manifested payload doesn't need the full capability of the rocket, so we can use that additional up mass for secondary payloads. So we're offering actually from a 6U- up to a 12U- and even a 27U-size secondary payload. That's huge for secondary payloads wanting to be able to get out into deep space. This allows them to have more power systems, more advanced telemetry, communications, and especially larger propulsion systems so they can get out into different destinations and do all this great science that they want to do in these smaller, less expensive packages. Host: Actually, that blends in nicely to drawing comparisons with SLS to other heavy-lift rockets because SLS is going to be gigantic and take these very, very large payloads. What's the difference between SLS capabilities and some other heavy lift rockets like Delta IV Heavy or Falcon Heavy? Why wouldn't you use just the heavy rockets? Why do you need SLS? Paul Bookout: Existing commercial rockets, they're not destinations going into deep space. They're mainly going into low Earth orbit or geosynchronous orbit. So for a secondary payload to get out into deep space, they'd have to be pretty big, you know, to have a propulsion system larger than a 27U. So the uniqueness of flying on SLS if you want to get out into deep space is that you don't have to have a huge satellite or, and propulsion system. SLS is providing that initial kick or velocity to get you out in the general direction you want to go. And then, you'd have a smaller propulsion system to be able to get out there. So overall, it's a lot less expensive. And again, SLS is giving these small CubeSets the opportunity to get onto deep space. Host: And also, the fact that it's human rated, right. The fact that you can actually put people on it and bring them far into space, right? Paul Bookout: Right. Host: Kind of a big thing. Paul Bookout: Definitely, yes. Host: Is it the only one that's rated for human, for deep space? David Smith: Well, it's the only launch vehicle today that's being designed specifically for that. There's-- Host: I see. David Smith: You could make the argument that a Boeing CST-100 capsule flying on a Falcon, excuse me, on a Atlas is a human-rated system. It's not really. It's an amalgam. And by the way, that's aimed at LEO. So they-- Host: I see. David Smith: You know, it, yes, we are the only ones that are being, designing specifically for that, and it's for safety reasons. Host: So it has to really meet these standards. It has to be redundant. It has to, and the SLS is the big, deep-space rocket that has the standards, has the capabilities, and is going to get you farther. David Smith: Right. Host: Ultimately. Paul Bookout: Exactly. And, you know, to be that safe vehicle for launching humans into space, deep space, you know, we have to have these built-in, redundant systems. We have to do all these testing throughout the whole build of the system. You know, of course, that's a little penalty that we have to have additional mass to be able to have this redundancy, have this extra safety aspects of this vehicle. So that, of course, goes right in against being able to have a larger mass, up mass capability. But we're doing this for human exploration, not robotics exploration, so we're, we have to take those extra steps to make it safe. Host: That's right. So what's the benefit of having this large up mass versus just launching a bunch of rockets with smaller masses? David Smith: Right. We, what's often not fully appreciated is, for human spaceflight, for long duration, you can put together a whole bunch of little modules for humans, but think about it like this: Every time you put together a module, it has to have a hatch. Maybe it has to have two. It has to have a life support system. It has to have a power system, a thermal system. It has to be able to operate autonomously until another small module is joined to it. So you can make a lunar orbiting platform or a Mars deep-space transport out of many small modules brought up over time for that many vehicles, but the problem is it becomes sub optimized. You end up paying maybe 50% more mass for all the structure you don't really have to have. Plus, now, you have many duplicative subsystems for many modules that have to all function flawlessly together and have to wait in space while other modules come up over time and to be joined together. So when you think about this, coming up with this giant, origami-type space station that's deployed over years from many small modules compared to one flight or maybe two flights bringing up a very large module that does everything in one reliable, tested on the ground type of human habitation system, it becomes almost a no-brainer, right. [laughs] If you want to make sure your people are alive over time, you really want that kind of system. Only SLS right now is sized to do that. Other guys can certainly deliver those pieces, but they'd be a lot smaller and you'd have these issues that we just talked about. Host: That's right. And I guess it kind of opens up some opportunities for just, because you can have a larger up mass, because you have more space within the fairing to put things-- David Smith: Right. Host: Now, you have a lot less constraints because even -- I'm going to go back to James Webb, right. James Webb is a wonderful telescope, but it was constrained by what it can-- David Smith: The volume of the fairing. Host: Yeah, so it had to come up with this folding technique to pretty much fit inside the fairing. Otherwise, you couldn't launch the satellite. But I guess you can design, you have a little bit more freedom of design with something a little bit larger, right? David Smith: Or if you wanted to scale up the James Webb design, let's say that was the perfect design for telescopes-- Host: Yeah. David Smith: You could make a telescope that's five times larger with the large fairing that, you know, larger fairings that SLS could fly. So it opens up a whole, either you can have a non-origami type, folding-out type telescope, and it's all great, or, if you want to still do that, it gets you something even larger. So the scale is, the current fairing is, in some cases, the ten-meter fairing would be five times larger than the largest existing fairing today-- Host: Whoa. David Smith: If we could produce that. And that's, you know, we're talking a seven-story building could fit inside that ten, you know, [laughs] that long, the long, ten-meter, diameter, meter, diameter fairing. Host: All right. Just launch my house into space and just-- David Smith: There you go. Host: Kind of get a nice view. David Smith: Well, it'd be your condo building that it would launch-- Host: [laughs] Condo building. David Smith: Not your house. David Smith: Even bigger. Host: Yes. Host: So I kind of wanted to end with just sort of a scope of, we're kind of setting up a scene for what this rocket is capable of. Looking towards the future, and, David, you kind of pointed towards this, was this is a 50-year rocket, right. This is something that we're planning on using for a long time for many missions. How do you see this rocket being used? Like, take us into the future. What is this rocket going to give us? David Smith: So, you know, obviously, the lunar orbiting platform would be the first step. Let's-- Host: Yeah. David Smith: Improve the technologies in our backyard we call the Moon. We use those technologies then to extrapolate a system that can go to Mars safely and start, you know, bringing Mars into this human ring of habitation in our solar system. Some of the more exciting things in tandem are these robotic missions. There's the idea that we can send, because we can go so fast, we, so fast into the deeper reaches of the solar system, that within a five-year mission, we can send out a telescope that could go 200 astronomical units out from the Sun, and actually come back and aim at the Sun, and use the Sun as a gravitational lens to see exoplanets on the other side of the Sun. So we could make the world's largest telescope by having one lens on one side of the Sun and using the Sun's gravity as the other lens, and now seeing planets like we could've never seen them before, all because SLS can send that telescope out in a time frame that we can actually operation a mission, versus, you know, remember, Voyager took 30 years to get outside to, close to the heliosphere. So, you know, it's a, it's such a game changer that the real issue with SLS is we haven't thought about all the stuff we can do with it yet, you know. It kind of bends our imagination in a new way that we haven't been thinking of. Another example is interstellar probe. Again, sending something beyond the heliosphere now. You know, instead of the Voyager drifting out there over 30 to 40 years, we can send something out there in 20 years to break the barrier and see what's on the other side of the heliosphere. And we can do that in an active manner versus we're just getting little pulses from Voyager now still coming back. We can be much more active in that. So a lot of places like JPL are investigating the capability of SLS in ways that we never even thought of recently. So we're just on the very edge of discovering what we can do with the system. Host: Unbelievable. And this just kind of opens up the plan for exploring beyond low Earth orbit, right. You've said the first step for human exploration is going towards the Moon, but now you have a bunch of Moon missions. You kind of develop your skills. You got this Lunar Orbital Platform, the gateway that's going to bring us, the truck stop [laughs] that we call it-- David Smith: Right. Host: Is going to take us further out. And I'm guessing this will be used for the future human missions too beyond this first step. David Smith: Well, if we go to, we talked about I think in the earlier episode, nuclear thermal propulsion. Host: Yeah. David Smith: If we're able to employ that for human transport, we can reduce times to where we can send people maybe even ultimately beyond Mars. So, but only SLS with its capability to loft both mass and volume, when the nuclear, this nuclear thermal propulsion requires large amounts of hydrogen, which requires volume, only the SLS can give us that capability to even see if some of these technologies are usable, versus just relying on the same old technologies as the last 50 years. So we have so much promise in front of us with this. Host: Unbelievable. You guys are getting me all excited for what's to come. I just want to take a time machine, and jump, you know, 20 years into the future, and just see this rocket has done. Paul Bookout: Yep, you're not the only one. David Smith: [laughter] Take us with you. Host: Yeah, that's-- David Smith: We want to be there too. Host: Unbelievable. Hey, David and Paul, thank you so much for coming on, and kind of describing the SLS, and really spending so much time so we can do this in two episodes because there's so much to this story. And honestly, this was the first time that I've actually gone into this much detail for the rocket, so I really appreciate you getting on. And for the listeners, please listen to Parts 1 and 2 and get the whole story of what this rocket is all about. Guys, thanks again for coming on. Houston, we have a podcast. David Smith: You're welcome. Paul Bookout: Thank you very much for having us. Host: Welcome to the official podcast of the NASA Johnson Space Center, Episode 2, Can You Hear Me Now? I'm Gary Jordan, and I'll be your host today. In this podcast, we're bringing in the experts -- NASA scientists, engineers, astronauts, pretty much all the folks that have the coolest information, the stuff that you really want to know. [inaudible] We're talking everything from extraterrestrial [inaudible] to the unknown [inaudible]. So today, we're talking space communication networks with Bill Foster. He's a ground controller-- Hey, thanks for sticking around and listening to the whole full story of the Space Launch System. This was Episode 42, Part 2. If you haven't listened to Part 1, go back. You can listen to some of the more components about EM1 and then just some general ideas about what SLS was. Otherwise, you can go to some social media channels and website. We'll start with the website -- www.NASA.gov/SLS. That's where you can get the latest and greatest. Otherwise, you can follow some social media accounts on Twitter. It's @NASA underscore SLS. On Facebook, it's NASA SLS. Or you can actually go on the web and search "SLS Mission Planner's Guide," and it's a document on the web that you can download and just learn everything about the rocket, some of the constraints. And that was actually one of the things that Mr. David Smith worked on. So we're really looking forward to the launch of the first SLS. Glad you were able to join us on today's podcast to listen about the rocket and some of the missions and capabilities of the Space Launch System. If you have any questions, just use the #askNASA on your favorite platform for the NASA Johnson Space Center accounts on Facebook, Twitter, and Instagram. You can submit a question or an idea for an episode that you want us to cover here on the podcast. Just make sure to mention it's for this podcast, Houston We Have a Podcast. This episode was recorded on March 20th, 2018 thanks to Alex Perryman, Rachel Craft, Laura Reshawn [phonetic], Kelly Humphries, Pat Ryan, Tyler Martin, Bev Perry, and all the folks at the Marshall Space Flight Center for helping to put this together. Thanks again to Dr. Paul Bookout and Mr. David Smith for coming on the show. [inaudible

Integrated medical and behavioral laboratory measurement system engineering analysis and laboratory specification

NASA Technical Reports Server (NTRS)

Grave, C.; Margold, D. W.

1973-01-01

Site selection, program planning, cost and design studies for support of the IMBLMS program were investigated. Accomplishments are reported for the following areas: analysis of responses to site selection criteria, space-oriented biotechnology, life sciences payload definition, and program information transfer.

KENNEDY SPACE CENTER, FLA. -- In Orbiter Processing Facility Bay 1, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) and United Space Alliance (USA) Vice President and Space Shuttle Program Manager Howard DeCastro (right) are briefed by a USA technician (center) on Shuttle processing in the payload bay of orbiter Atlantis. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- In Orbiter Processing Facility Bay 1, NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) and United Space Alliance (USA) Vice President and Space Shuttle Program Manager Howard DeCastro (right) are briefed by a USA technician (center) on Shuttle processing in the payload bay of orbiter Atlantis. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

CubeSat Initiatives at KSC

NASA Technical Reports Server (NTRS)

Berg, Jared J.

2014-01-01

Even though the Small PayLoad Integrated Testing Services or SPLITS line of business is newly established, KSC has been involved in a variety of CubeSat projects and programs. CubeSat development projects have been initiated through educational outreach partnerships with schools and universities, commercial partnerships and internal training initiatives. KSC has also been involved in CubeSat deployment through programs to find launch opportunities to fly CubeSats as auxiliary payloads on previously planned missions and involvement in the development of new launch capabilities for small satellites. This overview will highlight the CubeSat accomplishments at KSC and discuss planning for future projects and opportunities.

GSFC Systems Test and Operation Language (STOL) functional requirements and language description

NASA Technical Reports Server (NTRS)

Desjardins, R.; Hall, G.; Mcguire, J.; Merwarth, P.; Mocarsky, W.; Truszkowski, W.; Villasenor, A.; Brosi, F.; Burch, P.; Carey, D.

1978-01-01

The Systems Tests and Operation Language (STOL) provides the means for user communication with payloads, applications programs, and other ground system elements. It is a systems operation language that enables an operator or user to communicate a command to a computer system. The system interprets each high level language directive from the user and performs the indicated action, such as executing a program, printing out a snapshot, or sending a payload command. This document presents the following: (1) required language features and implementation considerations; (2) basic capabilities; (3) telemetry, command, and input/output directives; (4) procedure definition and control; (5) listing, extension, and STOL nucleus capabilities.

Proposal to National Aeronautics and Space Administration for continuation of a grazing incidence imaging telescope for X-ray astronomy using sounding rockets

NASA Technical Reports Server (NTRS)

Murray, B.

1976-01-01

The construction of a high resolution imaging telescope experiment payload suitable for launch on an Astrobee F sounding rocket was proposed. Also integration, launch, and subsequent data analysis effort were included. The payload utilizes major component subassemblies from the HEAO-B satellite program which were nonflight development units for that program. These were the X ray mirror and high resolution imager brassboard detector. The properties of the mirror and detector were discussed. The availability of these items for a sounding rocket experiment were explored with the HEAO-B project office.

Development of termination and utilization concepts for flat conductor cables. Volume 3: Cost study comparison, flat versus round conductor cable

NASA Technical Reports Server (NTRS)

1972-01-01

A cost study comparing flat conductor cable (FCC) with small-gage wire (SGW) and conventional round conductor cable (RCC) is presented. This study was based on a vehicle wiring system consisting of 110,000 ft of conventional RCC equally divided between AWG sizes 20,22, and 24 using MIL-W-81044-type wire and MIL-C-26500 circular connectors. Basic cost data were developed on a similar-sized commercial jet airplane wiring system on a previous company R&D program in which advanced wiring techniques were carried through equivalent installations on an airplane mockup; and on data developed on typical average bundles during this program. Various cost elements included were engineering labor, operations (manufacturing) labor, material costs, and cost impact on payload. Engineering labor includes design, wiring system integration, wiring diagrams and cable assembly drawings, wire installations, and other related supporting functions such as the electronic data processing for the wiring. Operations labor includes mockup, tooling and production planning, fabrication, assembly, installation, and quality control cost impact on payload is the conversion of wiring system weight variations through use of different wiring concepts to program payload benefits in terms of dollars.

Space shuttle system program definition. Volume 2: Technical report

NASA Technical Reports Server (NTRS)

1972-01-01

The Phase B Extension of the Space Shuttle System Program Definition study was redirected to apply primary effort to consideration of space shuttle systems utilizing either recoverable pressure fed liquids or expendable solid rocket motor boosters. Two orbiter configurations were to be considered, one with a 15x60 foot payload bay with a 65,000 lb, due East, up-payload capability and the other with a 14x45 payload bay with 45,000 lb, of due East, up-payload. Both were to use three SSME engines with 472,000 lb of vacuum thrust each. Parallel and series burn ascent modes were to be considered for the launch configurations of primary interest. A recoverable pump-fed booster is included in the study in a series burn configuration with the 15x60 orbiter. To explore the potential of the swing engine orbiter configuration in the pad abort case, it is included in the study matrix in two launch configurations, a series burn pressure fed BRB and a parallel burn SRM. The resulting matrix of configuration options is shown. The principle objectives of this study are to evaluate the cost and technical differences between the liquid and solid propellant booster systems and to assess the development and operational cost savings available with a smaller orbiter.

Evaluation of propellant tank insulation concepts for low-thrust chemical propulsion systems

NASA Technical Reports Server (NTRS)

Kramer, T.; Brogren, E.; Seigel, B.

1984-01-01

An analytical evaluation of cryogenic propellant tank insulations for liquid oxygen/liquid hydrogen low-thrust 2224N (500 lbf) propulsion systems (LTPS) was conducted. The insulation studied consisted of combinations of N2-purged foam and multilayer insulation (MLI) as well as He-purged MLI-only. Heat leak and payload performance predictions were made for three Shuttle-launched LTPS designed for Shuttle bay packaged payload densities of 56 kg/cu m, 40 kg/cu m and 24 kg/cu m. Foam/MLI insulations were found to increase LTPS payload delivery capability when compared with He-purged MLI-only. An additional benefit of foam/MLI was reduced operational complexity because Orbiter cargo bay N2 purge gas could be used for MLI purging. Maximum payload mass benefit occurred when an enhanced convection, rather than natural convection, heat transfer was specified for the insulation purge enclosure. The enhanced convection environment allowed minimum insulation thickness to be used for the foam/MLI interface temperature selected to correspond to the moisture dew point in the N2 purge gas. Experimental verification of foam/MLI benefits was recommended. A conservative program cost estimate for testing a MLI-foam insulated tank was 2.1 million dollars. It was noted this cost could be reduced significantly without increasing program risk.

STS-65 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-65 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-third flight of the Space Shuttle Program and the seventeenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbits the flight vehicle consisted of an ET that was designated ET-64; three SSME's that were designated as serial numbers 2019, 2030, and 2017 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-066. The RSRM's that were installed in each SRB were designated as 360P039A for the left SRB, and 360W039 for the right SRB. The primary objective of this flight was to complete the operation of the second International Microgravity Laboratory (IML-2). The secondary objectives of this flight were to complete the operations of the Commercial Protein Crystal Growth (CPCG), Orbital Acceleration Research Experiment (OARE), and the Shuttle Amateur Radio Experiment (SAREX) II payloads. Additional secondary objectives were to meet the requirements of the Air Force Maui Optical Site (AMOS) and the Military Application Ship Tracks (MAST) payloads, which were manifested as payloads of opportunity.

A Scalable and Dynamic Testbed for Conducting Penetration-Test Training in a Laboratory Environment

DTIC Science & Technology

2015-03-01

entry point through which to execute a payload to accomplish a higher-level goal: executing arbitrary code, escalating privileges , pivoting...Mobile Ad Hoc Network Emulator (EMANE)26 can emulate the entire network stack (physical to application -layer protocols). 2. Methodology To build a...to host Windows, Linux, MacOS, Android , and other operating systems without much effort. 4 E. A simple and automatic “restore” function: Many

KSC-00padig018

NASA Image and Video Library

2000-05-02

The preliminary design for the Space Experiment Research and Processing Laboratory (SERPL) at Kennedy Space Center is shown in this artist's rendition. The SERPL is a planned 100,000-square-foot laboratory that will provide expanded and upgraded facilities for hosting International Space Station experiment processing. In addition, it will provide better support for other biological and life sciences payload processing at KSC. It will serve as a magnet facility for a planned 400-acre Space Station Commerce Park

Q-Band (37-41 GHz) Satellite Beacon Architecture for RF Propagation Experiments

NASA Technical Reports Server (NTRS)

Simmons, Rainee N.; Wintucky, Edwin G.

2012-01-01

In this paper, the design of a beacon transmitter that will be flown as a hosted payload on a geostationary satellite to enable propagation experiments at Q-band (37-41 GHz) frequencies is presented. The beacon uses a phased locked loop stabilized dielectric resonator oscillator and a solid-state power amplifier to achieve the desired output power. The satellite beacon antenna is configured as an offset-fed cut-paraboloidal reflector.

Q-Band (37 to 41 GHz) Satellite Beacon Architecture for RF Propagation Experiments

NASA Technical Reports Server (NTRS)

Simons, Rainee N.; Wintucky, Edwin G.

2014-01-01

In this paper, the design of a beacon transmitter that will be flown as a hosted payload on a geostationary satellite to enable propagation experiments at Q-band (37 to 41 GHz) frequencies is presented. The beacon uses a phased locked loop stabilized dielectric resonator oscillator and a solid-state power amplifier to achieve the desired output power. The satellite beacon antenna is configured as an offset-fed cutparaboloidal reflector.

Nineteenth Space Simulation Conference Cost Effective Testing for the 21st Century

NASA Technical Reports Server (NTRS)

Stecher, Joseph L., III (Compiler)

1997-01-01

The Nineteenth Space Simulation Conference was hosted by the Institute of Environmental Sciences (IES) and was supported by the American Institute of Aeronautics and Astronautics (AIAA), the American Society for Testing and Materials (ASTM), the National Aeronautics and Space Administration (NASA), and the Canadian Space Agency (CSA). These proceedings attest to the scope of the conference; papers were presented on topics as diverse as shuttle payload contamination effects, simulating Martian environment for testing, to state-of-the-art 6-axis hydraulic shaker testing system. A good cross section of the international aerospace community took advantage of the opportunity to get together, to share their experiences, and to participate in the technical sessions. The two invited keynote speakers were Lieutenant General Malcolm O'Neill (USA, Ret.), past Director of BMDO, and Mr. Thomas Coughlin, Space Programs Manager at the Johns Hopkins University Applied Physics Laboratory. Their most informative and thought provoking talks were on cost effective testing approaches in Defense Department programs for the 21st Century and what part testing plays in the faster, better, cheaper approach for the NEAR and APL programs, respectively. The preceding tutorial and the tour of the Garber Facility of the Air and Space Museum rounded out a comprehensive conference contributing to the knowledge base vital to cost effective testing for successful missions into the 21st Century.

Early Program Development

NASA Image and Video Library

1970-01-01

This 1970 artist's concept shows a Nuclear Shuttle in flight. As envisioned by Marshall Space Flight Center Program Development engineers, the Nuclear Shuttle would deliver payloads to lunar orbit or other destinations then return to Earth orbit for refueling and additional missions.

A self-reliant RSI payload development in Taiwan

NASA Astrophysics Data System (ADS)

Weng, Shui-Lin; Lian, Yu-Yung

2011-10-01

Instead of outsourcing the whole FORMOSAT-2 satellite to a foreign prime contractor, the National Space Organization in Taiwan is stepping ahead to take the full responsibility of consolidating self-reliant space technology capabilities. A newly initiated program FORMOSAT-5 satellite, not only to build a heritage design of a spacecraft bus but also, selfreliantly, to leap a big step toward Remote Sensing Instrument payload development, is sailing on its voyage. Among the payload development effort, an integrated circuit of the kind Complementary Metal Oxide Semiconductor instead of Charge-coupled Device is chosen as the image sensor playing the lead role for the instrument. Despite the foreseen technical concerns, management issues over scheduling and documentation are constantly emerging owing to the payload development underwent is collaborated by several domestic industries and research centers. Regardless of challenges we may confront with, a carefully planned strategy especially emphasizing on the product realization processes is considered, discussed, and implemented.

STS-1 mission contamination evaluation approach

NASA Technical Reports Server (NTRS)

Jacobs, S.; Ehlers, H.; Miller, E. R.

1980-01-01

The space transportation system 1 mission will be the first opportunity to assess the induced environment of the orbiter payload bay region. Two tools were developed to aid in this assessment. The shuttle payload contamination evaluation computer program was developed to provide an analytical tool for prediction of the induced molecular contamination environment of the space shuttle orbiter during its onorbit operations. An induced environment contamination monitor was constructed and tested to measure the space shuttle orbiter contamination environment inside the payload bay during ascent and descent and inside and outside the payload bay during the onorbit phase. Measurements are to be performed during the four orbital flight test series. Measurements planned for the first flight are described and predicted environmental data are discussed. The results indicate that the expected data are within the measurement range of the induced environment contamination monitor instruments evaluated, and therefore it is expected that useful contamination environmental data will be available after the first flight.

Results of the 1974 through 1977 NASA/JPL balloon flight solar cell calibration program

NASA Technical Reports Server (NTRS)

Sidwell, L. B.

1978-01-01

From 1974 through 1977, seven solar cell calibration flights and two R&D flights with a spectroradiometer as a payload were attempted. There were two R&D flights, and one calibration flight that failed. Each calibration flight balloon was designed to carry its payload to an altitude of 36.6 km (120 kft). The R&D flight balloons were designed for a payload altitude of 47.5 km (150 kft). At the end of the flight period, the upper (solar cell calibration system) and lower (consolidated instrument package (DIP) payloads were separated from the balloon and descend via parachutes. The calibrated solar cells recovered in this manner were used as primary intensity reference standards during solar simulator testing of solar cells and solar arrays with similar spectral response characteristics. This method of calibration has become the most widely accepted technique for developing space standard solar cells.

Space Station Freedom Data Assessment Study

NASA Technical Reports Server (NTRS)

Johnson, Anngienetta R.; Deskevich, Joseph

1990-01-01

The SSF Data Assessment Study was initiated to identify payload and operations data requirements to be supported in the Space Station era. To initiate the study payload requirements from the projected SSF user community were obtained utilizing an electronic questionnaire. The results of the questionnaire were incorporated in a personal computer compatible database used for mission scheduling and end-to-end communications analyses. This paper discusses data flow paths and associated latencies, communications bottlenecks, resource needs versus availability, payload scheduling 'warning flags' and payload data loading requirements for each major milestone in the Space Station buildup sequence. This paper also presents the statistical and analytical assessments produced using the data base, an experiment scheduling program, and a Space Station unique end-to-end simulation model. The modeling concepts and simulation methodologies presented in this paper provide a foundation for forecasting communication requirements and identifying modeling tools to be used in the SSF Tactical Operations Planning (TOP) process.

The Extended Duration Sounding Rocket (EDSR): Low Cost Science and Technology Missions

NASA Astrophysics Data System (ADS)

Cruddace, R. G.; Chakrabarti, S.; Cash, W.; Eberspeaker, P.; Figer, D.; Figueroa, O.; Harris, W.; Kowalski, M.; Maddox, R.; Martin, C.; McCammon, D.; Nordsieck, K.; Polidan, R.; Sanders, W.; Wilkinson, E.; Asrat

2011-12-01

The 50-year old NASA sounding rocket (SR) program has been successful in launching scientific payloads into space frequently and at low cost with a 85% success rate. In 2008 the NASA Astrophysics Sounding Rocket Assessment Team (ASRAT), set up to review the future course of the SR program, made four major recommendations, one of which now called Extended Duration Sounding Rocket (EDSR). ASRAT recommended a system capable of launching science payloads (up to 420 kg) into low Earth orbit frequently (1/yr) at low cost, with a mission duration of approximately 30 days. Payload selection would be based on meritorious high-value science that can be performed by migrating sub-orbital payloads to orbit. Establishment of this capability is a essential for NASA as it strives to advance technical readiness and lower costs for risk averse Explorers and flagship missions in its pursuit of a balanced and sustainable program and achieve big science goals within a limited fiscal environment. The development of a new generation of small, low-cost launch vehicles (SLV), primarily the SpaceX Falcon 1 and the Orbital Sciences Minotaur I has made this concept conceivable. The NASA Wallops Flight Facility (WFF)conducted a detailed engineering concept study, aimed at defining the technical characteristics of all phases of a mission, from design, procurement, assembly, test, integration and mission operations. The work was led by Dr. Raymond Cruddace, a veteran of the SR program and the prime mover of the EDSR concept. The team investigated details such as, the "FAA licensed contract" for launch service procurement, with WFF and NASA SMD being responsible for mission assurance which results in a factor of two cost savings over the current approach. These and other creative solutions resulted in a proof-of-concept Class D mission design that could have a sustained launch rate of at least 1/yr, a mission duration of up to about 3 months, and a total cost of $25-30 million for each mission. The payload includes a pointing system with arc second precision, a command and data system which can be configured to meet the unique requirements of a particular mission, and a solar cell-battery power system. Anticipating the tremendous need of access to space, Cruddace and his team included a capability of inclusion of a number of smaller secondary instruments, ranging in size from CubeSats to instruments weighing up to 100 lb. These secondary payloads could be ejected as needed by P-PODs. In this talk, we will summarize EDSR, a legacy of Ray Cruddace.

Reusable experiment controllers, case studies

NASA Astrophysics Data System (ADS)

Buckley, Brian A.; Gaasbeck, Jim Van

1996-03-01

Congress has given NASA and the science community a reality check. The tight and ever shrinking budgets are trimming the fat from many space science programs. No longer can a Principal Investigator (PI) afford to waste development dollars on re-inventing spacecraft controllers, experiment/payload controllers, ground control systems, or test sets. Inheritance of the Ground Support Equipment (GSE) from one program to another is not a significant re-use of technology to develop a science mission in these times. Reduction of operational staff and highly autonomous experiments are needed to reduce the sustaining cost of a mission. The re-use of an infrastructure from one program to another is needed to truly attain the cost and time savings required. Interface and Control Systems, Inc. (ICS) has a long history of re-usable software. Navy, Air Force, and NASA programs have benefited from the re-use of a common control system from program to program. Several standardization efforts in the AIAA have adopted the Spacecraft Command Language (SCL) architecture as a point solution to satisfy requirements for re-use and autonomy. The Environmental Research Institute of Michigan (ERIM) has been a long-standing customer of ICS and are working on their 4th generation system using SCL. Much of the hardware and software infrastructure has been re-used from mission to mission with little cost for re-hosting a new experiment. The same software infrastructure has successfully been used on Clementine, and an end-to-end system is being deployed for the Far Ultraviolet Spectroscopic Explorer (FUSE) for Johns Hopkins University. A case study of the ERIM programs, Clementine and FUSE will be detailed in this paper.

KSC-97PC1208

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97PC1206

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97PC1209

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97PC1204

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97PC1202

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97PC1203

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97PC1210

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97pc1205

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

KSC-97PC1207

NASA Image and Video Library

1997-08-07

KENNEDY SPACE CENTER, Fla. -- Blasting through the hazy late morning sky, the Space Shuttle Discovery soars from Launch Pad 39A at 10:41 a.m. EDT Aug. 7 on the 11-day STS-85 mission. Aboard Discovery are Commander Curtis L. Brown, Jr.; Pilot Kent V. Rominger, Payload Commander N. Jan Davis, Mission Specialist Robert L. Curbeam, Jr., Mission Specialist Stephen K. Robinson and Payload Specialist Bjarni V. Tryggvason, a Canadian Space Agency astronaut . The primary payload aboard the Space Shuttle orbiter Discovery is the Cryogenic Infrared Spectrometers and Telescopes for the Atmosphere-Shuttle Pallet Satellite-2 (CRISTA-SPAS-2) free-flyer. The CRISTA-SPAS-2 will be deployed on flight day 1 to study trace gases in the Earth’s atmosphere as a part of NASA’s Mission to Planet Earth program. Also aboard the free-flying research platform will be the Middle Atmosphere High Resolution Spectrograph Instrument (MAHRSI). Other payloads on the 11-day mission include the Manipulator Flight Demonstration (MFD), a Japanese Space Agency-sponsored experiment. Also in Discovery’s payload bay are the Technology Applications and Science-1 (TAS-1) and International Extreme Ultraviolet Hitchhiker-2 (IEH-2) experiments

The Urey Instrument: An Advanced In Situ Organic and Oxidant Detector for Mars Exploration

NASA Astrophysics Data System (ADS)

Aubrey, Andrew D.; Chalmers, John H.; Bada, Jeffrey L.; Grunthaner, Frank J.; Amashukeli, Xenia; Willis, Peter; Skelley, Alison M.; Mathies, Richard A.; Quinn, Richard C.; Zent, Aaron P.; Ehrenfreund, Pascale; Amundson, Ron; Glavin Daniel P.; Botta, Oliver; Barron, Laurence; Blaney, Diana L.; Clark, Benton C.; Coleman, Max; Hofmann, Beda A.; Josset, Jean-Luc; Rettberg, Petra; Ride, Sally; Musée, François Robert; Sephton, Mark A.; Yen, Albert

2008-06-01

The Urey organic and oxidant detector consists of a suite of instruments designed to search for several classes of organic molecules in the martian regolith and ascertain whether these compounds were produced by biotic or abiotic processes using chirality measurements. These experiments will also determine the chemical stability of organic molecules within the host regolith based on the presence and chemical reactivity of surface and atmospheric oxidants. Urey has been selected for the Pasteur payload on the European Space Agency's (ESA's) upcoming 2013 ExoMars rover mission. The diverse and effective capabilities of Urey make it an integral part of the payload and will help to achieve a large portion of the mission's primary scientific objective: "to search for signs of past and present life on Mars." This instrument is named in honor of Harold Urey for his seminal contributions to the fields of cosmochemistry and the origin of life.

The Simbol-X Anticoincidence

NASA Astrophysics Data System (ADS)

Chabaud, J.; Laurent, P.; Colonges, S.; Barbay, J.; Baronick, J. P.; Benallou, M.; Ferrando, P.; Gilliot, M.; Jaeger, J. J.; Nicolas, M.; Ollivier, E.; Waisbard, J.; Yoffo, B.

2009-05-01

The Simbol-X telescope will be constitued by two satellites in formation flight. One will host the mirror module and the other the detector payload. This payload will be built with two main detectors able to measure the position, energy and arrival time of each focused photon, between 0.5 and 80 keV. The high sensitivity required by Simbol-X will necessitate low noise background detectors. To achieve this goal, those detectors will be surrounded by a passive graded shield, aimed to stop the out of field of view photons, and an active anticoïncidence system to tag the passing particles. This anticoïncidence detector, whose conception, optimisation and realization are under responsibility of the APC Laboratory, Paris, is based on plastic scintillator plates associated to multi-anodes photo-multipliers via optical fibers. In this paper, we will present the present status of the anticoïncidence system and its expected performances.

The Urey instrument: an advanced in situ organic and oxidant detector for Mars exploration.

PubMed

Aubrey, Andrew D; Chalmers, John H; Bada, Jeffrey L; Grunthaner, Frank J; Amashukeli, Xenia; Willis, Peter; Skelley, Alison M; Mathies, Richard A; Quinn, Richard C; Zent, Aaron P; Ehrenfreund, Pascale; Amundson, Ron; Glavin, Daniel P; Botta, Oliver; Barron, Laurence; Blaney, Diana L; Clark, Benton C; Coleman, Max; Hofmann, Beda A; Josset, Jean-Luc; Rettberg, Petra; Ride, Sally; Robert, François; Sephton, Mark A; Yen, Albert

2008-06-01

The Urey organic and oxidant detector consists of a suite of instruments designed to search for several classes of organic molecules in the martian regolith and ascertain whether these compounds were produced by biotic or abiotic processes using chirality measurements. These experiments will also determine the chemical stability of organic molecules within the host regolith based on the presence and chemical reactivity of surface and atmospheric oxidants. Urey has been selected for the Pasteur payload on the European Space Agency's (ESA's) upcoming 2013 ExoMars rover mission. The diverse and effective capabilities of Urey make it an integral part of the payload and will help to achieve a large portion of the mission's primary scientific objective: "to search for signs of past and present life on Mars." This instrument is named in honor of Harold Urey for his seminal contributions to the fields of cosmochemistry and the origin of life.

Land mobile satellite services in Europe

NASA Astrophysics Data System (ADS)

Bartholomé, P.; Berretta, G.; Rogard, R.

The demand for land-mobile communications on a Europe-wide basis is an important and pressing problem. The pan-European cellular network now in the planning stage will be slow in coming and it will have its limitations. A regional satellite system for Europe to complement the cellular network is the only practical way to satisfy a specialised market that encompasses a population of several hundred thousand mobiles, including road vehicles, merchant shipping, fishing boats, and trains. The deployment of a regional system would take place in a number of phases, the first being based on a simple payload embarked on a host satellite belonging to a European organisation. Further phases will involve the development of more advanced payloads on dedicated satellites. For the long-term future, the use of satellites in highly inclined orbits is being considered as a means of improving their visibility and hence the service quality.

Phase A conceptual design study of the Atmospheric, Magnetospheric and Plasmas in Space (AMPS) payload

NASA Technical Reports Server (NTRS)

1974-01-01

The 12 month Phase A Conceptual Design Study of the Atmospheric, Magnetospheric and Plasmas in Space (AMPS) payload performed within the Program Development Directorate of the Marshall Space Flight Center is presented. The AMPS payload makes use of the Spacelab pressurized module and pallet, is launched by the space shuttle, and will have initial flight durations of 7 days. Scientific instruments including particle accelerators, high power transmitters, optical instruments, and chemical release devices are mounted externally on the Spacelab pallet and are controlled by the experimenters from within the pressurized module. The capability of real-time scientist interaction on-orbit with the experiment is a major characteristic of AMPS.

Sensor deployment on unmanned ground vehicles

NASA Astrophysics Data System (ADS)

Gerhart, Grant R.; Witus, Gary

2007-10-01

TARDEC has been developing payloads for small robots as part of its unmanned ground vehicle (UGV) development programs. These platforms typically weigh less than 100 lbs and are used for various physical security and force protection applications. This paper will address a number of technical issues including platform mobility, payload positioning, sensor configuration and operational tradeoffs. TARDEC has developed a number of robots with different mobility mechanisms including track, wheel and hybrid track/wheel running gear configurations. An extensive discussion will focus upon omni-directional vehicle (ODV) platforms with enhanced intrinsic mobility for positioning sensor payloads. This paper also discusses tradeoffs between intrinsic platform mobility and articulated arm complexity for end point positioning of modular sensor packages.

GAS-007: First step in a series of Explorer payloads

NASA Technical Reports Server (NTRS)

Kitchens, Philip H.

1987-01-01

As part of the NASA Get Away Special program for flying small, self-contained payloads onboard the Space Shuttle, the Alabama Space and Rocket Center (ASRC) in Huntsville has sponsored three such payloads for its Project Explorer. One of these is GAS-007, which was carried originally on STS mission 41-G in early October 1984. Due to an operational error it was not turned on and was, therefore, subsequently rescheduled and flown on mission 61-C. This paper will review Explorer's history, outline its experiments, present some preliminary experimental results, and describe future ASRC plans for Get Away Special activities, including follow-on Explorers GAS-105 and GAS-608.

Safety in earth orbit study. Volume 2: Analysis of hazardous payloads, docking, on-board survivability

NASA Technical Reports Server (NTRS)

1972-01-01

Detailed and supporting analyses are presented of the hazardous payloads, docking, and on-board survivability aspects connected with earth orbital operations of the space shuttle program. The hazards resulting from delivery, deployment, and retrieval of hazardous payloads, and from handling and transport of cargo between orbiter, sortie modules, and space station are identified and analyzed. The safety aspects of shuttle orbiter to modular space station docking includes docking for assembly of space station, normal resupply docking, and emergency docking. Personnel traffic patterns, escape routes, and on-board survivability are analyzed for orbiter with crew and passenger, sortie modules, and modular space station, under normal, emergency, and EVA and IVA operations.

Ribbon cutting opens new ELV offices

NASA Technical Reports Server (NTRS)

2000-01-01

Bobby Bruckner, manager, ELV and Payload Carrier Programs, speaks at the ribbon-cutting ceremony of the E&O Building at KSC. Home for NASA's unmanned missions since 1964, the building has been renovated to house the Expendable Launch Vehicle Program.

Expedite the Processing of Unpressurized Payloads to the International Space Station Using the ExPRESS Pallet

NASA Technical Reports Server (NTRS)

Bacskay, Allen S.; Gilbert, Paul A. (Technical Monitor)

2002-01-01

The Expedite the PRocessing of Experiments to Space Station (ExPRESS) Pallet will be used as an experiment platform for external/unpressurized payloads to be flown aboard the International Space Station (ISS). The purpose of the ExPRESS Pallet is to provide an easy access to the ISS for Scientific Investigators that require an external platform for their experiment hardware. As the name of the ExPRESS Pallet implies, the objective of the ExPRESS program is to provide a simplified integration process in a short time period (24 months) for payloads to be flown on the ISS. The ExPRESS Pallet provides unique opportunities for research across many science disciplines, including earth observation, communications, solar and deep space viewing, and long-term exposure. The ExPRESS Pallet provides access to Ram, Wake, Nadir, Zenith and Earth Limb for viewing and exposure to the space environment. The ExPRESS Pallet will provide standard physical payload interfaces, and a standard integration template. The ExPS consists of the Pallet structure, payload Adapters, a subsystem assembly that includes data controller, power distribution and conversion, and Extra Vehicular Robotics compatibility. The ExPRESS Pallet provides the capability to changeout payloads on-orbit via the ExPRESS Pallet Adapter (ExPA). The following paragraphs will describe the Services and Accommodations available to the Payload developers by the ExPRESS Pallet and a brief description of the Integration process. More detailed information on the ExPRESS Pallet can be found in the ExPRESS Pallet Payload Accommodations Handbook, SSP 52000-PAH-EPP.

Preliminary analysis of an integrated logistics system for OSSA payloads. Volume 4: Supportability analysis of the 1.8m centrifuge

NASA Technical Reports Server (NTRS)

Palguta, T.; Bradley, W.; Stockton, T.

1988-01-01

Supportability issues for the 1.8 meter centrifuge in the Life Science Research Facility are addressed. The analysis focuses on reliability and maintainability and the potential impact on supportability and affordability. Standard logistics engineering methodologies that will be applied to all Office of Space Science and Applications' (OSSA) payload programs are outlined. These methodologies are applied to the 1.8 meter centrifuge.

Commerce Lab: Mission analysis and payload integration study

NASA Technical Reports Server (NTRS)

1984-01-01

The needs of an aggressive commercial microgravity program are identified, space missions are defined, and infrastructural issues are identified and analyzed. A commercial laboratory, commerce lab, is conceived to be one or more an array of carriers which would fly aboard the space shuttle and accommodate microgravity science experiment payloads. Commerce lab is seen as a logical transition between currently planned space shuttle missions and future microgravity missions centered around the space station.

Scheduling Algorithm for Mission Planning and Logistics Evaluation (SAMPLE). Volume 1: User's guide

NASA Technical Reports Server (NTRS)

Dupnick, E.; Wiggins, D.

1980-01-01

An interactive computer program for automatically generating traffic models for the Space Transportation System (STS) is presented. Information concerning run stream construction, input data, and output data is provided. The flow of the interactive data stream is described. Error messages are specified, along with suggestions for remedial action. In addition, formats and parameter definitions for the payload data set (payload model), feasible combination file, and traffic model are documented.

A knowledge-based decision support system for payload scheduling

NASA Technical Reports Server (NTRS)

Floyd, Stephen; Ford, Donnie

1988-01-01

The role that artificial intelligence/expert systems technologies play in the development and implementation of effective decision support systems is illustrated. A recently developed prototype system for supporting the scheduling of subsystems and payloads/experiments for NASA's Space Station program is presented and serves to highlight various concepts. The potential integration of knowledge based systems and decision support systems which has been proposed in several recent articles and presentations is illustrated.

Payload Safety: Risk and Characteristic-Based Control of Engineered Nanomaterials

NASA Astrophysics Data System (ADS)

Abou, Seraphin Chally; Saad, Maarouf

2013-09-01

In the last decade progress has been made to assist organizations that are developing payloads intended for flight on the International Space Station (ISS) and/or Space Shuttle. Collaboration programs for comprehensive risk assessment have been initiated between the U.S. and the European Union to generate requirements and data needed to comply with payloads safety and to perform risk assessment and controls guidance. Yet, substantial research gaps remain, as do challenges in the translation of these research findings to control for exposure to nanoscale material payloads, and the health effects. Since nanomaterial structures are different from traditional molecules, some standard material properties can change at size of 50nm or less. Changes in material properties at this scale challenge our understanding of hazards posed by nanomaterial payloads in the ISS realistic exposure conditions, and our ability to anticipate, evaluate, and control potential health issues, and safety. The research question addressed in this framework is: what kind of descriptors can be developed for nanomaterial payloads risks assessment? Methods proposed incorporate elements of characteristic- based risk an alysis: (1) to enable characterization of anthropogenic nanomaterials which can result in incidental from natural nanoparticles; and (2) to better understand safety attributes in terms of human health impacts from exposure to varying types of engineered nanomaterials.

KSC-00padig019

NASA Image and Video Library

2000-05-02

Researchers perform tests at Kennedy Space Center. New facilities for such research will be provided at the Space Experiment Research Procession Laboratory (SERPL). The SERPL is a planned 100,000-square-foot laboratory that will provide expanded and upgraded facilities for hosting International Space Station experiment processing. In addition, it will provide better support for other biological and life sciences payload processing at KSC. It will serve as a magnet facility for a planned 400-acre Space Station Commerce Park

KSC00padig019

NASA Image and Video Library

2000-05-02

Researchers perform tests at Kennedy Space Center. New facilities for such research will be provided at the Space Experiment Research Procession Laboratory (SERPL). The SERPL is a planned 100,000-square-foot laboratory that will provide expanded and upgraded facilities for hosting International Space Station experiment processing. In addition, it will provide better support for other biological and life sciences payload processing at KSC. It will serve as a magnet facility for a planned 400-acre Space Station Commerce Park

Fish-eye view of the STS-90 Columbia's payload bay with sunburst

NASA Image and Video Library

1998-05-07

STS090-361-022 (17 April - 3 May 1998) --- A special lens on a 35mm camera gives a fish-eye effect to this out-the-window view from the Space Shuttle Columbia's cabin. The Spacelab Science Module, hosting 16-days of Neurolab research, is in frame center. This picture clearly depicts the configuration of the tunnel that leads from the cabin to the module in the center of the cargo bay.

KSC-00PADIG-020

NASA Image and Video Library

2002-05-02

This diagram shows the planned locations of the Space Experiment Research and Processing Laboratory (SERPL) and the Space Station Commerce Park at Kennedy Space Center. The SERPL is a planned 100,000-square-foot laboratory that will provide expanded and upgraded facilities for hosting International Space Station experiment processing. In addition, it will provide better support for other biological and life sciences payload processing at KSC. It will serve as a magnet facility for the planned 400-acre Commerce Park.

HERO: Program Status and Fist Images from a Balloon-Borne Focusing Hard-X-ray Telescope

NASA Technical Reports Server (NTRS)

Ramsey, B. D.; Alexander, C. D.; Apple, J. A.; Benson, C. M.; Dietz, K. L.; Elsner, R. F.; Engelhaupt. D. E.; Ghosh, K. K.; Kolodziejczak, J. J.; ODell, S. L.;

SSUSI-lite: next generation far-ultraviolet sensor for characterizing geospace

NASA Astrophysics Data System (ADS)

Paxton, Larry J.; Hicks, John E.; Grey, Matthew P.; Parker, Charles W.; Hourani, Ramsay S.; Marcotte, Kathryn M.; Carlsson, Uno P.; Kerem, Samuel; Osterman, Steven N.; Maas, Bryan J.; Ogorzalek, Bernard S.

2016-10-01

SSUSI-Lite is an update of an existing sensor, SSUSI. The current generation of Defense Meteorological Satellite Program (DMSP) satellites (Block 5D3) includes a hyperspectral, cross-tracking imaging spectrograph known as the Special Sensor Ultraviolet Spectrographic Imager (SSUSI). SSUSI has been part of the DMSP program since 1990. SSUSI is designed to provide space weather information such as: auroral imagery, ionospheric electron density profiles, and neutral density composition changes. The sensors that are flying today (see http://ssusi.jhuapl.edu) were designed in 1990 - 1992. There have been some significant improvements in flight hardware since then. The SSUSI-Lite instrument is more capable than SSUSI yet consumes ½ the power and is ½ the mass. The total package count (and as a consequence, integration cost and difficulty) was reduced from 7 to 2. The scan mechanism was redesigned and tested and is a factor of 10 better. SSUSI-Lite can be flown as a hosted payload or a rideshare - it only needs about 10 watts and weighs under 10 kg. We will show results from tests of an interesting intensified position sensitive anode pulse counting detector system. We use this approach because the SSUSI sensor operates in the far ultraviolet - from about 110 to 180 nm or 0.11 to 0.18 microns.

About White Sands Missile Range

NASA Technical Reports Server (NTRS)

1991-01-01

Information on the White Sands Missile Range is given in viewgraph form. Navy programs, test sites, rocket programs, research rockets' booster capacity, current boost capabilities, ordnance and payload assembly areas, commercial space launch history and agreements, and lead times are among the topics covered.

Expedition Earth and Beyond: Using Crew Earth Observation Imagery from the International Space Station to Facilitate Student-Led Authentic Research

NASA Technical Reports Server (NTRS)

Graff, P. V.; Stefanov, W. L.; Willis, K. J.; Runco, S.

2012-01-01

Student-led authentic research in the classroom helps motivate students in science, technology, engineering, and mathematics (STEM) related subjects. Classrooms benefit from activities that provide rigor, relevance, and a connection to the real world. Those real world connections are enhanced when they involve meaningful connections with NASA resources and scientists. Using the unique platform of the International Space Station (ISS) and Crew Earth Observation (CEO) imagery, the Expedition Earth and Beyond (EEAB) program provides an exciting way to enable classrooms in grades 5-12 to be active participants in NASA exploration, discovery, and the process of science. EEAB was created by the Astromaterials Research and Exploration Science (ARES) Education Program, at the NASA Johnson Space Center. This Earth and planetary science education program has created a framework enabling students to conduct authentic research about Earth and/or planetary comparisons using the captivating CEO images being taken by astronauts onboard the ISS. The CEO payload has been a science payload onboard the ISS since November 2000. ISS crews are trained in scientific observation of geological, oceanographic, environmental, and meteorological phenomena. Scientists on the ground select and periodically update a series of areas to be photographed as part of the CEO science payload.

The STS-91 crew participate in the CEIT for their mission

NASA Technical Reports Server (NTRS)

1998-01-01

The STS-91 crew participate in the Crew Equipment Interface Test (CEIT) for their upcoming Space Shuttle mission at the SPACEHAB Payload Processing Facility in Cape Canaveral. The CEIT gives astronauts an opportunity to get a hands-on look at the payloads with which they will be working on-orbit. STS-91 will be the ninth and final scheduled Mir docking and will include a single module of SPACEHAB, used mainly as a large pressurized cargo container for science, logistical equipment and supplies to be exchanged between the orbiter Discovery and the Russian Space Station Mir. The nearly 10-day flight of STS-91 also is scheduled to include the return of the last astronaut to live and work aboard the Russian orbiting outpost, Mission Specialist Andy Thomas, Ph.D. Liftoff of Discovery and its six-member crew is targeted for May 28, 1998, at 8:05 p.m. EDT from Launch Pad 39A. From left to right are STS-91 Pilot Dominic Gorie, STS-91 Commander Charles Precourt, Boeing SPACEHAB Payload Operations Senior Engineer Jim Behling, Boeing SPACEHAB Program Senior Engineer Shawn Hicks, Boeing SPACEHAB Program Specialist in Engineering Ed Saenger, STS-91 Mission Specialist Valery Ryumin with the Russian Space Agency, Boeing SPACEHAB Program Manager in Engineering Brad Reid, and Russian Interpreter Olga Belozerova.

Design criteria for payload workstation accommodations

NASA Technical Reports Server (NTRS)

Watters, H. H.; Stokes, J. W.

1975-01-01

Anticipated shuttle sortie payload man-system design criteria needs are investigated. Man-system interactions for the scientific disciplines are listed and the extent is assessed to which documented Skylab experience is expected to provide system design guidance for each of the identified interactions. Where the analysis revealed that the reduced Skylab data does not answer the anticipated needs candidate criteria, based on unreduced Skylab data, available prior research, original analysis, or related requirements derived from previous space programs, are provided.

STS-95 Payload Specialist Mukai participates in a parade in Cocoa Beach

NASA Technical Reports Server (NTRS)

1998-01-01

STS-95 Payload Specialist Chiaki Mukai is perched on the back of a red 1999 C-5 Corvette convertible during a parade down State Road A1A in nearby Cocoa Beach. Organizers of the parade include the Cocoa Beach Area Chamber of Commerce, the Brevard County Tourist Development Council, and the cities of Cape Canaveral and Cocoa Beach. The parade is reminiscent of those held after missions during the Mercury Program.

STS-95 Payload Specialist Glenn participates in a parade in Cocoa Beach

NASA Technical Reports Server (NTRS)

1998-01-01

STS-95 Payload Specialist John H. Glenn Jr. waves to spectators from the back of a silver 1999 C-5 Corvette convertible during a parade down State Road A1A in nearby Cocoa Beach. Organizers of the parade include the Cocoa Beach Area Chamber of Commerce, the Brevard County Tourist Development Council, and the cities of Cape Canaveral and Cocoa Beach. The parade is reminiscent of those held after missions during the Mercury Program.

Teacher in Space Christa McAuliffe on the KC-135 for zero-G training

NASA Image and Video Library

1986-01-08

S86-25191 (for release January 1986) --- The two representatives of the Teacher-in-Space Project continue their training program at the Johnson Space Center with an additional flight aboard NASA?s KC-135 ?zero gravity? aircraft. Sharon Christa McAuliffe, left, is prime crew payload specialist, and Barbara R. Morgan is in training as backup payload specialist. The photo was taken by Keith Meyers of New York Times. Photo credit: NASA

Second United States Microgravity Payload: One Year Report

NASA Technical Reports Server (NTRS)

Curreri, Peter A. (Editor); McCauley, Dannah E. (Editor)

1996-01-01

The second United States Microgravity Payload (USMP-2), flown in March 1994, carried four major microgravity experiments plus a sophisticated accelerometer system. The USMP program is designed to accommodate experiments requiring extensive resources short of a full Spacelab mission. The four USMP-2 experiments dealt with understanding fundamental aspects of materials behavior, three with the formation of crystals from melts and one with the critical point of a noble gas. This successful, scientifically rich mission also demonstrated telescience operations.

The space shuttle payload planning working groups: Executive summaries

NASA Technical Reports Server (NTRS)

1973-01-01

The findings of a space shuttle payload planning group session are presented. The purpose of the workshop is: (1) to provide guidance for the design and development of the space shuttle and the spacelab and (2) to plan a space science and applications program for the 1980 time period. Individual groups were organized to cover the various space sciences, applications, technologies, and life sciences. Summaries of the reports submitted by the working groups are provided.

Extravehicular Crewman Work System (ECWS) study program: Prebreathe elimination study

NASA Technical Reports Server (NTRS)

Wilde, R. L.

1981-01-01

The study examined impacts of changing Orbiter cabin pressure and EMU EVA pressure to eliminate pure O2 prebreathing prior to EVA. The investigation defines circumscribing physiological boundaries and identifies changes required within Orbiter to reduce cabin pressure. The study also identifies payload impacts, payload flight assignment constraints, and impacts upon EMU resulting from raising EVA pressure. The study presents the trade-off which optimizes the choice of reduced cabin pressure and increased EVA pressure.

Spacehab

NASA Technical Reports Server (NTRS)

Rossi, David

1991-01-01

Information is given in viewgraph form on the Spacehab company and its work on a pressurized module to be carried on the Space Shuttle. The module augments the Shuttle's capability to support man-tended microgravity experiments. The augmentation modules are designed to duplicate the resources, such as power, environmental control, and data management that are available in the Shuttle's middeck. Topics covered include a company overview, company financing, system overview, module description, payload resources, locker accommodations, program status, and a listing of candidate payloads.

STS-64 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1995-01-01

The STS-64 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-fourth flight of the Space Shuttle Program and the nineteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-66; three SSMEs that were designated as serial numbers 2031, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's that were designated Bl-068. The RSRM's that were installed in each SRB were designated as 360L041 A for the left SRB, and 360L041 B for the right SRB. The primary objective of this flight was to successfully perform the planned operations of the Lidar In-Space Technology Experiment (LITE), and to deploy the Shuttle Pointed Autonomous Research Tool for Astronomy (SPARTAN) -201 payload. The secondary objectives were to perform the planned activities of the Robot Operated Materials Processing System (ROMPS), the Shuttle Amateur Radio Experiment - 2 (SAREX-2), the Solid Surface Combustion Experiment (SSCE), the Biological Research in Canisters (BRIC) experiment, the Radiation Monitoring Equipment-3 (RME-3) payload, the Military Application of Ship Tracks (MAST) experiment, and the Air Force Maui Optical Site Calibration Test (AMOS) payload.

STS-47 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1992-01-01

The STS-47 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the fiftieth Space Shuttle Program flight and the second flight of the Orbiter Vehicle Endeavour (OV-105). In addition to the Endeavour vehicle, the flight vehicle consisted of the following: an ET which was designated ET-45 (LWT-38); three SSME's which were serial numbers 2026, 2022, and 2029 and were located in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-053. The lightweight/redesigned RSRM that was installed in the left SRB was designated 360L026A, and the RSRM that was installed in the right SRB was 360W026B. The primary objective of the STS-47 flight was to successfully perform the planned operations of the Spacelab-J (SL-J) payload (containing 43 experiments--of which 34 were provided by the Japanese National Space Development Agency (NASDA)). The secondary objectives of this flight were to perform the operations of the Israeli Space Agency Investigation About Hornets (ISAIAH) payload, the Solid Surface Combustion Experiment (SSCE), the Shuttle Amateur Radio Experiment-2 (SAREX-2), and the Get-Away Special (GAS) payloads. The Ultraviolet Plume Instrument (UVPI) was flown as a payload of opportunity.

KSC-98pc639

NASA Image and Video Library

1998-05-26

The Alpha Magnetic Spectrometer (AMS) experiment and four Get Away Special (GAS) payload canisters are secure in Discovery's payload bay shortly before the payload bay doors are closed for the flight of STS-91 at Launch Pad 39A. Launch is planned for June 2 with a window opening around 6:10 p.m. EDT. The AMS experiment is the first of a new generation of space-based experiments which will use particles, instead of light, to study the Universe and will search for both antimatter and "dark matter," as well as measure normal matter cosmic and gamma rays. The GAS Program, initiated to provide extremely low-cost access to space, is managed by the Shuttle Small Payloads Project at NASA's Goddard Space Flight Center. Eight GAS experiments will be conducted on STS-91. The mission will also feature the ninth Shuttle docking with the Russian Space Station Mir, the first Mir docking for Discovery, the conclusion of Phase I of the joint U.S.-Russian International Space Station Program, and the first flight of the new Space Shuttle super lightweight external tank. The STS-91 flight crew includes Commander Charles Precourt; Pilot Dominic Gorie; and Mission Specialists Wendy B. Lawrence; Franklin Chang-Diaz, Ph.D.; Janet Kavandi, Ph.D.; and Valery Ryumin, with the Russian Space Agency. Andrew Thomas, Ph.D., will be returning to Earth with the crew after living more than four months aboard Mir

Evaluation of propellent tank insulation concepts for low-thrust chemical propulsion systems: Executive summary

NASA Technical Reports Server (NTRS)

Kramer, T.; Brogren, E.; Siegel, B.

1984-01-01

Cryogenic propellant tank insulations or liquid oxygen/liquid hydrogen low-thrust 2224N (500 lbf) propulsion systems (LTPS) were assessed. The insulation studied consisted of combinations of N2-purged foam and multilayer insulation (MLI) as well as He-purged MLI-only. Heat leak and payload performance predictions were made for three shuttle-launched LTPS designed for shuttle bay packaged payload densities of 56 kg cu/m (3.5 lbm/cu ft), 40 kg/cu m (2.5 lbm/cu ft) and 24 kg/cu m (1.5 lbm/cu ft). Foam/MLI insulations were found to increase LTPS payload delivery capability when compared with He-purged MLI-only. An additional benefit of foam/MLI was reduced operational complexity because orbiter cargo bay N2 purge gas could be used for MLI purging. Maximum payload mass benefit occurred when an enhanced convection, rather than natural convection, heat transfer was specified for the insulation purge enclosure. The enhanced convection environment allowed minimum insulation thickness to be used for the foam/MLI interface temperature selected to correspond to the moisture dew point in the N2 purge gas. Experimental verification of foam/MLI benefits was recommended. A conservative program cost estimate for testing a MLI-foam insulated tank was 2.1 million dollars. This cost could be reduced significantly without increasing program risk.

STS-47 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W., Jr.

1992-10-01

The STS-47 Space Shuttle Program Mission Report provides a summary of the Orbiter, External Tank (ET), Solid Rocket Booster/Redesigned Solid Rocket Motor (SRB/RSRM), and the Space Shuttle main engine (SSME) subsystem performance during the fiftieth Space Shuttle Program flight and the second flight of the Orbiter Vehicle Endeavour (OV-105). In addition to the Endeavour vehicle, the flight vehicle consisted of the following: an ET which was designated ET-45 (LWT-38); three SSME's which were serial numbers 2026, 2022, and 2029 and were located in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-053. The lightweight/redesigned RSRM that was installed in the left SRB was designated 360L026A, and the RSRM that was installed in the right SRB was 360W026B. The primary objective of the STS-47 flight was to successfully perform the planned operations of the Spacelab-J (SL-J) payload (containing 43 experiments--of which 34 were provided by the Japanese National Space Development Agency (NASDA)). The secondary objectives of this flight were to perform the operations of the Israeli Space Agency Investigation About Hornets (ISAIAH) payload, the Solid Surface Combustion Experiment (SSCE), the Shuttle Amateur Radio Experiment-2 (SAREX-2), and the Get-Away Special (GAS) payloads. The Ultraviolet Plume Instrument (UVPI) was flown as a payload of opportunity.

The Athena Mars Rover Investigation

NASA Technical Reports Server (NTRS)

Squyres, S. W.; Arvidson, R. E.; Bell, J. F., III; Carr, M.; Christensen, P.; DesMarais, D.; Economou, T.; Gorevan, S.; Haskin, L.; Herkenhoff, K.

2000-01-01

The Mars Surveyor program requires tools for martian surface exploration, including remote sensing, in-situ sensing, and sample collection. The Athena Mars rover payload is a suite of scientific instruments and sample collection tools designed to: (1) Provide color stereo imaging of martian surface environments, and remotely-sensed point discrimination of mineralogical composition; (2) Determine the elemental and mineralogical composition of martian surface materials; (3) Determine the fine-scale textural properties of these materials; and (4) Collect and store samples. The Athena payload is designed to be implemented on a long-range rover such as the one now under consideration for the 2003 Mars opportunity. The payload is at a high state of maturity, and most of the instruments have now been built for flight.

KSC-99pd-812-06

NASA Image and Video Library

1999-08-01

KENNEDY SPACE CENTER, FLA. -- An orbiter has more than 300 miles of wires such as these shown here in the cable tray inside Columbia's payload bay. During launch of Columbia on mission STS-93, a damaged wire caused a short circuit in two separate main engine controllers. As a result of the findings, Shuttle program managers have decided to conduct inspections of the wiring in Endeavour's payload bay before its next mission, STS-99. The inspection and possible repair work will lead to a delayed launch date no earlier than Oct.7. The primary payload of the mission is the Shuttle Radar Topography Mission, a specially modified radar system that will gather data for the most accurate and complete topographic map of the Earth's surface that has ever been assembled

STS-39 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W.

1991-01-01

The STS-39 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the fortieth flight of the Space Shuttle and the twelfth flight of the Orbiter Vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of the following: an External Tank (ET) (designated as ET-46 (LWT-39); three Space Shuttle main engines (SSME's) (serial numbers 2026, 2030, and 2029 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-043. The primary objective of this flight was to successfully perform the planned operations of the Infrared Background Signature Survey (IBSS), Air Force Payload (AFP)-675, Space Test Payload (STP)-1, and the Multipurpose Experiment Canister (MPEC) payloads.

KSC-2012-3842

NASA Image and Video Library

2012-07-16

CAPE CANAVERAL, Fla. - Inside the Vehicle Assembly Building at NASA’s Kennedy Space Center in Florida, United Space Alliance workers monitor the progress as the container holding the remote manipulator system, or RMS, is lowered onto a flatbed truck for shipment back to the Canadian Space Agency. The RMS, also called the Canadarm, was manufactured for NASA’s Space Shuttle Program by SPAR Aerospace Ltd., which later became a part of MD Robotics in Ontario, Canada. During shuttle missions, the RMS was attached in the payload bay. Mission specialists operated the arm to remove payloads from the payload bay and hand them off to the larger Canadarm 2 on the International Space Station. The shuttle arm also was used during astronaut spacewalks. Photo credit: NASA/Kim Shiflett

STS-39 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W.

1991-06-01

The STS-39 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the fortieth flight of the Space Shuttle and the twelfth flight of the Orbiter Vehicle Discovery (OV-103). In addition to the Discovery vehicle, the flight vehicle consisted of the following: an External Tank (ET) (designated as ET-46 (LWT-39); three Space Shuttle main engines (SSME's) (serial numbers 2026, 2030, and 2029 in positions 1, 2, and 3, respectively); and two Solid Rocket Boosters (SRB's) designated as BI-043. The primary objective of this flight was to successfully perform the planned operations of the Infrared Background Signature Survey (IBSS), Air Force Payload (AFP)-675, Space Test Payload (STP)-1, and the Multipurpose Experiment Canister (MPEC) payloads.

Space station executive summary

NASA Technical Reports Server (NTRS)

1972-01-01

An executive summary of the modular space station study is presented. The subjects discussed are: (1) design characteristics, (2) experiment program, (3) operations, (4) program description, and (5) research implications. The modular space station is considered a candidate payload for the low cost shuttle transportation system.

Electronic collection system for spacelab mission timeline requirements

NASA Technical Reports Server (NTRS)

Lindberg, James P.; Piner, John R.; Huang, Allen K. H.

1995-01-01

This paper describes the Functional Objective Requirements Collection System (FORCS) software tool that has been developed for use by Principal Investigators (PI's) and Payload Element Developers (PED's) on their own personal computers to develop on-orbit timelining requirements for their payloads. The FORCS tool can be used either in a totally stand-alone mode, storing the information in a local file on the user's personal computer hard disk or in a remote mode where the user's computer is linked to a host computer containing the integrated database of the timeline requirements for all of the payloads on a mission. There are a number of features incorporated in the FORCS software to assist the user. The user may move freely back and forth between the various forms for inputting the data. Several methods are used to input the information, depending on the type of the information. These methods range from filling in text boxes, using check boxes and radio buttons, to inputting information into a spreadsheet format. There are automated features provided to assist in developing the proper format for the data, ranging from limit checking on some of the parameters to automatic conversion of different formats of time data inputs to the one standard format used for the timeline scheduling software.

Sounding Rocket Launches Successfully from Alaska

NASA Image and Video Library

2015-01-28

Caption: Time lapse photo of the NASA Oriole IV sounding rocket with Aural Spatial Structures Probe as an aurora dances over Alaska. All four stages of the rocket are visible in this image. Credit: NASA/Jamie Adkins More info: On count day number 15, the Aural Spatial Structures Probe, or ASSP, was successfully launched on a NASA Oriole IV sounding rocket at 5:41 a.m. EST on Jan. 28, 2015, from the Poker Flat Research Range in Alaska. Preliminary data show that all aspects of the payload worked as designed and the principal investigator Charles Swenson at Utah State University described the mission as a “raging success.” “This is likely the most complicated mission the sounding rocket program has ever undertaken and it was not easy by any stretch," said John Hickman, operations manager of the NASA sounding rocket program office at the Wallops Flight Facility, Virginia. "It was technically challenging every step of the way.” “The payload deployed all six sub-payloads in formation as planned and all appeared to function as planned. Quite an amazing feat to maneuver and align the main payload, maintain the proper attitude while deploying all six 7.3-pound sub payloads at about 40 meters per second," said Hickman. Read more: www.nasa.gov/content/assp-sounding-rocket-launches-succes... NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

Sounding Rocket Launches Successfully from Alaska

NASA Image and Video Library

2015-01-28

A NASA Oriole IV sounding rocket with the Aural Spatial Structures Probe leaves the launch pad on Jan. 28, 2015, from the Poker Flat Research Range in Alaska. Credit: NASA/Lee Wingfield More info: On count day number 15, the Aural Spatial Structures Probe, or ASSP, was successfully launched on a NASA Oriole IV sounding rocket at 5:41 a.m. EST on Jan. 28, 2015, from the Poker Flat Research Range in Alaska. Preliminary data show that all aspects of the payload worked as designed and the principal investigator Charles Swenson at Utah State University described the mission as a “raging success.” “This is likely the most complicated mission the sounding rocket program has ever undertaken and it was not easy by any stretch," said John Hickman, operations manager of the NASA sounding rocket program office at the Wallops Flight Facility, Virginia. "It was technically challenging every step of the way.” “The payload deployed all six sub-payloads in formation as planned and all appeared to function as planned. Quite an amazing feat to maneuver and align the main payload, maintain the proper attitude while deploying all six 7.3-pound sub payloads at about 40 meters per second," said Hickman. Read more: www.nasa.gov/content/assp-sounding-rocket-launches-succes... NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

An EXPRESS Rack Overview and Support for Microgravity Research on the International Space Station (ISS)

NASA Technical Reports Server (NTRS)

Pelfrey, Joseph J.; Jordan, Lee P.

2008-01-01

The EXpedite the PRocessing of Experiments to Space Station or EXPRESS Rack System has provided accommodations and facilitated operations for microgravity-based research payloads for over 6 years on the International Space Station (ISS). The EXPRESS Rack accepts Space Shuttle middeck type lockers and International Subrack Interface Standard (ISIS) drawers, providing a modular-type interface on the ISS. The EXPRESS Rack provides 28Vdc power, Ethernet and RS-422 data interfaces, thermal conditioning, vacuum exhaust, and Nitrogen supply for payload use. The EXPRESS Rack system also includes payload checkout capability with a flight rack or flight rack emulator prior to launch, providing a high degree of confidence in successful operations once an-orbit. In addition, EXPRESS trainer racks are provided to support crew training of both rack systems and subrack operations. Standard hardware and software interfaces provided by the EXPRESS Rack simplify the integration processes for ISS payload development. The EXPRESS Rack is designed to accommodate multidiscipline research, allowing for the independent operation of each subrack payload within a single rack. On-orbit operations began for the EXPRESS Rack Project on April 24, 2001, with one rack operating continuously to support high-priority payloads. The other on-orbit EXPRESS Racks operate based on payload need and resource availability. Over 50 multi-discipline payloads have now been supported on-orbit by the EXPRESS Rack Program. Sustaining engineering, logistics, and maintenance functions are in place to maintain hardware, operations and provide software upgrades. Additional EXPRESS Racks are planned for launch prior to ISS completion in support of long-term operations and the planned transition of the U.S. Segment to a National Laboratory.

STS-60 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-60 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixtieth flight of the Space Shuttle Program and eighteenth flight of the Orbiter vehicle Discovery (OV-103). In addition to the Orbiter, the flight vehicle consisted of an ET designated at ET-61 (Block 10); three SSME's which were designated as serial numbers 2012, 2034, and 2032 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-062. The RSRM's that were installed in each SRB were designated as 360L035A (lightweight) for the left SRB, and 360Q035B (quarterweight) for the right SRB. This STS-60 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume VIII, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-60 mission were to deploy and retrieve the Wake Shield Facility-1 (WSF-1), and to activate the Spacehab-2 payload and perform on-orbit experiments. Secondary objectives of this flight were to activate and command the Capillary Pumped Loop/Orbital Debris Radar Calibration Spheres/Breman Satellite Experiment/Getaway Special (GAS) Bridge Assembly (CAPL/ODERACS/BREMSAT/GBA) payload, the Auroral Photography Experiment-B (APE-B), and the Shuttle Amateur Radio Experiment-II (SAREX-II).

Autonomous mine detection system (AMDS) neutralization payload module

NASA Astrophysics Data System (ADS)

Majerus, M.; Vanaman, R.; Wright, N.

2010-04-01

The Autonomous Mine Detection System (AMDS) program is developing a landmine and explosive hazards standoff detection, marking, and neutralization system for dismounted soldiers. The AMDS Capabilities Development Document (CDD) has identified the requirement to deploy three payload modules for small robotic platforms: mine detection and marking, explosives detection and marking, and neutralization. This paper addresses the neutralization payload module. There are a number of challenges that must be overcome for the neutralization payload module to be successfully integrated into AMDS. The neutralizer must meet stringent size, weight, and power (SWaP) requirements to be compatible with a small robot. The neutralizer must be effective against a broad threat, to include metal and plastic-cased Anti-Personnel (AP) and Anti-Tank (AT) landmines, explosive devices, and Unexploded Explosive Ordnance (UXO.) It must adapt to a variety of threat concealments, overburdens, and emplacement methods, to include soil, gravel, asphalt, and concrete. A unique neutralization technology is being investigated for adaptation to the AMDS Neutralization Module. This paper will describe review this technology and how the other two payload modules influence its design for minimizing SWaP. Recent modeling and experimental efforts will be included.

Communication satellite payload technologies - State of the art and trends in Europe

NASA Astrophysics Data System (ADS)

Mica, G.; Coirault, R.

1982-09-01

Communication satellite payload technologies are examined, in terms of past, present, and future ESA guidelines. Various existing payload systems are presented, such as Marecs, ECS, and L-Sat (which will carry four payloads). Future services within the market include 2 Mb/sec high speed data, 2-8 Mb/sec video conference, and 64 Mb/sec television distribution, and growth in these areas is dependent on traffic requirements. Pre-operational satellites are outlined, for example Telecom 1 has an estimated system capacity of 150 Mb/sec, Italsat has an expected 1180 Mb/sec, and DFS demonstrates a possible 1540 Mb/sec capacity. It is found that the 20/30 GHz band should be applied for use in wideband and high capacity trunks among heavy traffic centers. To accommodate for the noise in this waveband, the parametric amplifier developed for L-Sat must be used. Finally, development objectives for future programs include improving spectrum and geostationary orbit utilization, cost-efficiency, and standardization of systems.

Life sciences payload definition and integration study, task C and D. Volume 2: Payload definition, integration, and planning studies

NASA Technical Reports Server (NTRS)

1973-01-01

The Life Sciences Payload Definition and Integration Study was composed of four major tasks. Tasks A and B, the laboratory definition phase, were the subject of prior NASA study. The laboratory definition phase included the establishment of research functions, equipment definitions, and conceptual baseline laboratory designs. These baseline laboratories were designated as Maxi-Nom, Mini-30, and Mini-7. The outputs of Tasks A and B were used by the NASA Life Sciences Payload Integration Team to establish guidelines for Tasks C and D, the laboratory integration phase of the study. A brief review of Tasks A and B is presented provide background continuity. The tasks C and D effort is the subject of this report. The Task C effort stressed the integration of the NASA selected laboratory designs with the shuttle sortie module. The Task D effort updated and developed costs that could be used by NASA for preliminary program planning.

Vibroacoustic test plan evaluation: Parameter variation study

NASA Technical Reports Server (NTRS)

Stahle, C. V.; Gongloef, H. R.

1976-01-01

Statistical decision models are shown to provide a viable method of evaluating the cost effectiveness of alternate vibroacoustic test plans and the associated test levels. The methodology developed provides a major step toward the development of a realistic tool to quantitatively tailor test programs to specific payloads. Testing is considered at the no test, component, subassembly, or system level of assembly. Component redundancy and partial loss of flight data are considered. Most and probabilistic costs are considered, and incipient failures resulting from ground tests are treated. Optimums defining both component and assembly test levels are indicated for the modified test plans considered. modeling simplifications must be considered in interpreting the results relative to a particular payload. New parameters introduced were a no test option, flight by flight failure probabilities, and a cost to design components for higher vibration requirements. Parameters varied were the shuttle payload bay internal acoustic environment, the STS launch cost, the component retest/repair cost, and the amount of redundancy in the housekeeping section of the payload reliability model.

KSC-2011-7228

NASA Image and Video Library

2011-09-28

CAPE CANAVERAL, Fla. -- This transporter has moved its last space shuttle payload canister. The transporter was enlisted to move payload canister #2 from the Canister Rotation Facility to the Reutilization, Recycling and Marketing Facility on Ransom Road at NASA's Kennedy Space Center in Florida. The two payload canisters used to transport space shuttle payloads to the launch pad for installation in the shuttles' cargo bays are being decommissioned following the end of the Space Shuttle Program. Each canister weighs 110,000 pounds and is 65 feet long, 22 feet wide, and 18 feet, 7 inches high. The canisters were prescreened through NASA Headquarters as possible artifacts, but their size makes them difficult to transport to locations off the center. Federal and state agencies now will be given the opportunity to screen the canisters for potential use before a final decision is made on their disposition. For more information, visit http://www.nasa.gov/centers/kennedy/pdf/167403main_CRF-06.pdf. Photo credit: NASA/Jim Grossmann

Artist rendition of the planned Space Experiment Research and Processing Laboratory

NASA Technical Reports Server (NTRS)

2000-01-01

The preliminary design for the Space Experiment Research and Processing Laboratory (SERPL) at Kennedy Space Center is shown in this artist's rendition. The SERPL is a planned 100,000-square- foot laboratory that will provide expanded and upgraded facilities for hosting International Space Station experiment processing. In addition, it will provide better support for other biological and life sciences payload processing at KSC. It will serve as a magnet facility for a planned 400-acre Space Station Commerce Park.

Location for the planned Space Experiment Research and Processing Laboratory

NASA Technical Reports Server (NTRS)

2000-01-01

This diagram shows the planned locations of the Space Experiment Research and Processing Laboratory (SERPL) and the Space Station Commerce Park at Kennedy Space Center. The SERPL is a planned 100,000-square-foot laboratory that will provide expanded and upgraded facilities for hosting International Space Station experiment processing. In addition, it will provide better support for other biological and life sciences payload processing at KSC. It will serve as a magnet facility for the planned 400- acre commerce park.

Research and the planned Space Experiment Research and Processing Laboratory

NASA Technical Reports Server (NTRS)

2000-01-01

Researchers perform tests at Kennedy Space Center. New facilities for such research will be provided at the Space Experiment Research Procession Laboratory (SERPL). The SERPL is a planned 100,000-square-foot laboratory that will provide expanded and upgraded facilities for hosting International Space Station experiment processing. In addition, it will provide better support for other biological and life sciences payload processing at KSC. It will serve as a magnet facility for a planned 400-acre Space Station Commerce Park.

Vector systems for prenatal gene therapy: principles of retrovirus vector design and production.

PubMed

Howe, Steven J; Chandrashekran, Anil

2012-01-01

Vectors derived from the Retroviridae family have several attributes required for successful gene delivery. Retroviral vectors have an adequate payload size for the coding regions of most genes; they are safe to handle and simple to produce. These vectors can be manipulated to target different cell types with low immunogenicity and can permanently insert genetic information into the host cells' genome. Retroviral vectors have been used in gene therapy clinical trials and successfully applied experimentally in vitro, in vivo, and in utero.

An Engineering Trade Space Analysis for a Space-Based Hyperspectral Chromotomographic Scanner

DTIC Science & Technology

2009-03-26

The Hyperion’s EO-1 host satellite is in a polar, circular, sun -synchronous or- bit at 98.7 inclination . The orbit follows that of Landsat-7 by one...science orbit around Mars 13 months after launch. The orbit is a near circular (apogee of 320 km, perigee of 255 km), near polar, sun -synchronous orbit ...payload design, operating scheme and orbit to demonstrate this technology in low- earth orbit . This instrument promises the capability of adding a time

Evaluation of the Military Utility of Employing an Angle of Arrival Payload Hosted on a CubeSat as an Augmentation to Existing Geolocation Systems

DTIC Science & Technology

2015-03-26

SYSTEMS THESIS Presented to the Faculty Department of Aeronautics and Astronautics Graduate School of Engineering and Management Air Force Institute...Geolocation (SAMSON) project , led by the Distributed Space Systems Lab and the Asher Space Research Institute at the Technion-Israel Institute of...Technology, is an operationally focused CubeSat mission that is scheduled to launch in 2016. The goals of the SAMSON project are to demon- strate long-term

ARIM-1: The Atmospheric Refractive Index Measurements Sounding Rocket Mission

NASA Technical Reports Server (NTRS)

Ruiz, B. Ian (Editor)

1995-01-01

A conceptual design study of the ARIM-1 sounding rocket mission, whose goal is to study atmospheric turbulence in the tropopause region of the atmosphere, is presented. The study was conducted by an interdisciplinary team of students at the University of Alaska Fairbanks who were enrolled in a Space Systems Engineering course. The implementation of the ARIM-1 mission will be carried out by students participating in the Alaska Student Rocket Program (ASRP), with a projected launch date of August 1997. The ARIM-1 vehicle is a single stage sounding rocket with a 3:1 ogive nose cone, a payload diameter of 8 in., a motor diameter of 7.6 in., and an overall height of 17.0 ft including the four fins. Emphasis is placed on standardization of payload support systems. The thermosonde payload will measure the atmospheric turbulence by direct measurement of the temperature difference over a distance of one meter using two 3.45-micron 'hot-wire' probes. The recovery system consists of a 6 ft. diameter ribless guide surface drogue chute and a 33 ft. diameter main cross parachute designed to recover a payload of 31 pounds and slow its descent rate to 5 m/s through an altitude of 15 km. This document discusses the science objectives, mission analysis, payload mechanical configuration and structural design, recovery system, payload electronics, ground station, testing plans, and mission implementation.

Optimizing communication satellites payload configuration with exact approaches

NASA Astrophysics Data System (ADS)

Stathakis, Apostolos; Danoy, Grégoire; Bouvry, Pascal; Talbi, El-Ghazali; Morelli, Gianluigi

2015-12-01

The satellite communications market is competitive and rapidly evolving. The payload, which is in charge of applying frequency conversion and amplification to the signals received from Earth before their retransmission, is made of various components. These include reconfigurable switches that permit the re-routing of signals based on market demand or because of some hardware failure. In order to meet modern requirements, the size and the complexity of current communication payloads are increasing significantly. Consequently, the optimal payload configuration, which was previously done manually by the engineers with the use of computerized schematics, is now becoming a difficult and time consuming task. Efficient optimization techniques are therefore required to find the optimal set(s) of switch positions to optimize some operational objective(s). In order to tackle this challenging problem for the satellite industry, this work proposes two Integer Linear Programming (ILP) models. The first one is single-objective and focuses on the minimization of the length of the longest channel path, while the second one is bi-objective and additionally aims at minimizing the number of switch changes in the payload switch matrix. Experiments are conducted on a large set of instances of realistic payload sizes using the CPLEX® solver and two well-known exact multi-objective algorithms. Numerical results demonstrate the efficiency and limitations of the ILP approach on this real-world problem.

Space Launch System Co-Manifested Payload Options for Habitation

NASA Technical Reports Server (NTRS)

Smitherman, David

2015-01-01

The Space Launch System (SLS) has a co-manifested payload capability that will grow over time as the rocket matures and planned upgrades are implemented. The final configuration is planned to be capable of inserting a payload greater than 10 metric tons (mt) into a trans-lunar injection trajectory along with the crew in the Orion capsule and the service module. The co-manifested payload is located below the Orion and its service module in a 10-meter high fairing similar to the way the Saturn launch vehicle carried the lunar lander below the Apollo command and service modules. A variety of approaches have been explored that utilizes this co-manifested payload capability to build up infrastructure in deep space in support of future asteroid, lunar, and Mars mission scenarios. This paper is a report on the findings from the Advanced Concepts Office study team at the NASA Marshall Space Flight Center, working with the Advanced Exploration Systems Program on the Exploration Augmentation Module Project. It includes some of the possible options for habitation in the co-manifested payload volume on SLS. Findings include module designs that can be developed in 10mt increments to support these missions, including overall conceptual layouts, mass properties, and approaches for integration into various scenarios for near-term support of deep space habitat research and technology development, support to asteroid exploration, and long range support for Mars transfer flights.

System Critical Design Audit (CDA). Books 1, 2 and 3; [Small Satellite Technology Initiative (SSTI Lewis Spacecraft Program)

NASA Technical Reports Server (NTRS)

1995-01-01

Small Satellite Technology Initiative (SSTI) Lewis Spacecraft Program is evaluated. Spacecraft integration, test, launch, and spacecraft bus are discussed. Payloads and technology demonstrations are presented. Mission data management system and ground segment are also addressed.

Early Program Development

NASA Image and Video Library

1970-01-01

This artist's concept from 1970 shows a Nuclear Shuttle taking on fuel from an orbiting Liquid Hydrogen Depot. As envisioned by Marshall Space Flight Center Program Development persornel, the Nuclear Shuttle would deliver payloads to lunar orbit or other destinations then return to Earth orbit for refueling and additional missions.

Early Program Development

NASA Image and Video Library

1971-01-01

This 1971 artist's concept shows the Nuclear Shuttle in both its lunar logistics configuraton and geosynchronous station configuration. As envisioned by Marshall Space Flight Center Program Development persornel, the Nuclear Shuttle would deliver payloads to lunar orbits or other destinations then return to Earth orbit for refueling and additional missions.

Raven: An On-Orbit Relative Navigation Demonstration Using International Space Station Visiting Vehicles

NASA Technical Reports Server (NTRS)

Strube, Matthew; Henry, Ross; Skeleton, Eugene; Eepoel, John Van; Gill, Nat; McKenna, Reed

2015-01-01

Since the last Hubble Servicing Mission five years ago, the Satellite Servicing Capabilities Office (SSCO) at the NASA Goddard Space Flight Center (GSFC) has been focusing on maturing the technologies necessary to robotically service orbiting legacy assets-spacecraft not necessarily designed for in-flight service. Raven, SSCO's next orbital experiment to the International Space Station (ISS), is a real-time autonomous non-cooperative relative navigation system that will mature the estimation algorithms required for rendezvous and proximity operations for a satellite-servicing mission. Raven will fly as a hosted payload as part of the Space Test Program's STP-H5 mission, which will be mounted on an external ExPRESS Logistics Carrier (ELC) and will image the many visiting vehicles arriving and departing from the ISS as targets for observation. Raven will host multiple sensors: a visible camera with a variable field of view lens, a long-wave infrared camera, and a short-wave flash lidar. This sensor suite can be pointed via a two-axis gimbal to provide a wide field of regard to track the visiting vehicles as they make their approach. Various real-time vision processing algorithms will produce range, bearing, and six degree of freedom pose measurements that will be processed in a relative navigation filter to produce an optimal relative state estimate. In this overview paper, we will cover top-level requirements, experimental concept of operations, system design, and the status of Raven integration and test activities.

STS-95 Payload Specialist Glenn participates in a parade in Cocoa Beach

NASA Technical Reports Server (NTRS)

1998-01-01

STS-95 Payload Specialist John H. Glenn Jr. waves to a dense crowd of well-wishers from the back of a silver 1999 C-5 Corvette convertible during a parade down State Road A1A in nearby Cocoa Beach. Organizers of the parade include the Cocoa Beach Area Chamber of Commerce, the Brevard County Tourist Development Council, and the cities of Cape Canaveral and Cocoa Beach. The parade is reminiscent of those held after missions during the Mercury Program.

ACTS Operational Performance Review: September 1995

NASA Technical Reports Server (NTRS)

Krawczyk, Richard J.

1996-01-01

The Advanced Communications Technology Satellite (ACTS) utilized a proven spacecraft bus with a payload that qualified new technologies to provide a wide range of on-orbit demonstrations. A comprehensive development, qualification and ground test program was implemented to reduce technology risks. Since launch in September, 1993, and insertion into its geostationary slot ACTS has accumulated over 16,000 hours of successful operation. This paper briefly reviews the technology development background then provides a summary of the operational performance observed for the spacecraft bus and communication payload subsystems and units.

Development and analysis of a modular approach to payload specialist training. [training of spacecrews for Spacelab

NASA Technical Reports Server (NTRS)

Watters, H.; Steadman, J.

1976-01-01

A modular training approach for Spacelab payload crews is described. Representative missions are defined for training requirements analysis, training hardware, and simulations. Training times are projected for each experiment of each representative flight. A parametric analysis of the various flights defines resource requirements for a modular training facility at different flight frequencies. The modular approach is believed to be more flexible, time saving, and economical than previous single high fidelity trainer concepts. Block diagrams of training programs are shown.

The space shuttle payload planning working groups. Volume 10: Space technology

NASA Technical Reports Server (NTRS)

1973-01-01

The findings and recommendations of the Space Technology group of the space shuttle payload planning activity are presented. The elements of the space technology program are: (1) long duration exposure facility, (2) advanced technology laboratory, (3) physics and chemistry laboratory, (4) contamination experiments, and (5) laser information/data transmission technology. The space technology mission model is presented in tabular form. The proposed experiments to be conducted by each test facility are described. Recommended approaches for user community interfacing are included.

KSC-2012-1862

NASA Image and Video Library

2012-02-17

Satellites: The principal objectives of the Launch Services Program are to provide safe, reliable, cost-effective and on schedule launch services for NASA and NASA-sponsored payloads seeking launch on expendable vehicles. These payloads have a number of purposes. Scientific satellites obtain information about the space environment and transmit it to stations on Earth. Applications satellites designed to perform experiments that have everyday usefulness for people on Earth, such as weather forecasting and communications. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

A Common Lunar Lander (CLL) for the Space Exploration Initiative

NASA Technical Reports Server (NTRS)

Bailey, Stephen

1991-01-01

Information is given in viewgraph form on the Artemis project, a plan to establish a permanent base on the Moon. Information includes a summary of past and future events, the program rationale, a summary of potential payloads, the physical characteristics of experiments, sketches of equipment, design study objectives, and details of such payloads as the Geophysical Station Network, teleoperated rovers, astronomical telescopes, a Moon-Earth radio interferometer, very low frequency radio antennas, the Lunar Polar Crater Telescope, Lunar Resource Utilization Experiments, and biological experiments.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians confirm that the spacecraft is secured onto a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians prepare the spacecraft for its move to a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians help secure the spacecraft onto a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. The spacecraft is being prepared for its move to a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

CD Bridges and STS-95 Payload Specialist Glenn greet well-wishers following a parade in Cocoa Beach

NASA Technical Reports Server (NTRS)

1998-01-01

Center Director Roy Bridges and STS-95 Payload Specialist John H. Glenn Jr. greet well-wishers at a reception at the Double Tree Oceanfront Hotel following a parade down State Road A1A in nearby Cocoa Beach. Organizers of the parade included the Cocoa Beach Area Chamber of Commerce, the Brevard County Tourist Development Council, and the cities of Cape Canaveral and Cocoa Beach. The parade is reminiscent of those held after missions during the Mercury Program.

STS-95 Payload Specialist Glenn greets baseball legend Williams following a parade in Cocoa Beach

NASA Technical Reports Server (NTRS)

1998-01-01

STS-95 Payload Specialist John H. Glenn Jr. (left) greets baseball legend Ted Williams at a reception at the Double Tree Oceanfront Hotel following a parade down State Road A1A in nearby Cocoa Beach. Organizers of the parade included the Cocoa Beach Area Chamber of Commerce, the Brevard County Tourist Development Council, and the cities of Cape Canaveral and Cocoa Beach. The parade is reminiscent of those held after missions during the Mercury Program.

STS-45 backup Payload Specialist Chappell during water egress training at JSC

NASA Image and Video Library

1991-11-26

S91-52074 (26 Nov 1991) --- Charles R. (Rick) Chappell, alternate payload specialist, equipped with simulated parachute gear, descends into the water during bail-out training exercises in the Johnson Space Center's weightless environment training facility (WET-F). In this phase of the training program, Shuttle crewmembers learn the proper measures to take in the event of ejection and subsequent parachute landing into a body of water. A number of SCUBA-equipped swimmers who assisted in the training are pictured.

JPSS-1 Spacecraft Mate to Payload Attach Fittings

NASA Image and Video Library

2017-10-19

NOAA's Joint Polar Satellite System-1, or JPSS-1, remains wrapped in a protective covering after removal from its shipping container at the Astrotech Processing Facility at Vandenberg Air Force Base in California. Technicians assist as a crane lowers the spacecraft toward a payload attach fitting. JPSS-1 will liftoff aboard a United Launch Alliance Delta II rocket from Vandenberg's Space Launch Complex-2. JPSS-1 is the first in a series of four next-generation environmental satellites in a collaborative program between NOAA and NASA.

SPARTAN high resolution solar studies

NASA Technical Reports Server (NTRS)

Bruner, Marilyn E.

1993-01-01

This report summarizes the work performed on Contract NAS5-29739, a sub-orbital research program directed toward the study of the geometry of and physical conditions in matter found in the upper layers of the solar atmosphere. The report describes a new sounding rocket payload developed under the contract, presents a guide to the contents of semiannual reports submitted during the contract, discusses the results of the first flight of the payload and the progress on scientific analysis. A bibliography of papers and publications is included.

Design, Development, and Integration of A Space Shuttle Orbiter Bay 13 Payload Carrier

NASA Technical Reports Server (NTRS)

Spencer, Susan H.; Phillips, Michael W.; Upton, Lanny (Technical Monitor)

2002-01-01

Bay 13 of the Space Shuttle Orbiter has been limited to small sidewall mounted payloads and ballast. In order to efficiently utilize this space, a concept was developed for a cross-bay cargo carrier to mount Orbital Replacement Units (ORU's) for delivery to the International Space Station and provide additional opportunities for science payloads, while meeting the Orbiter ballast requirements. The Lightweight Multi-Purpose Experiment Support Structure (MPESS) Carrie (LMC) was developed and tested by NASA's Marshall Space Flight Center and the Boeing Company. The Multi-Purpose Experiment Support Structure (MPESS), which was developed for the Spacelab program was modified, removing the keel structure and relocating the sill trunnions to fit in Bay 13. Without the keel fitting, the LMC required a new and innovative concept for transferring Y loads into the Orbiter structure. Since there is no keel fitting available in the Bay 13 location, the design had to utilize the longeron bridge T-rail to distribute the Y loads. This concept has not previously been used in designing Shuttle payloads. A concept was developed to protect for Launch-On-Need ORU's, while providing opportunities for science payloads. Categories of potential ORU's were defined, and Get-Away Special (GAS) payloads of similar mass properties were provided by NASA's Goddard Space Flight Center. Four GAS payloads were manifest as the baseline configuration, preserving the capability to swap up to two ORU's for the corresponding science payloads, after installation into the Orbiter cargo bay at the pad, prior to closeout. Multiple configurations were considered for the analytical integration, to protect for all defined combinations of ORU's and GAS payloads. The first physical integration of the LMC war performed by Goddard Space Flight Center and Kennedy Space Center at an off-line facility at Kennedy Space Center. This paper will discuss the design challenges, structural testing, analytical and physical integration for the LMC's successful maiden flight on STS-108/ISS UF-1 mission in December 2001.

Space-Shuttle Emulator Software

NASA Technical Reports Server (NTRS)

Arnold, Scott; Askew, Bill; Barry, Matthew R.; Leigh, Agnes; Mermelstein, Scott; Owens, James; Payne, Dan; Pemble, Jim; Sollinger, John; Thompson, Hiram;

Capillary acquisition devices for high-performance vehicles: Executive summary. [evaluation of cryogenic propellant management techniques using the centaur launch vehicle

NASA Technical Reports Server (NTRS)

Blatt, M. H.; Bradshaw, R. D.; Risberg, J. A.

1980-01-01

Technology areas critical to the development of cryogenic capillary devices were studied. Passive cooling of capillary devices was investigated with an analytical and experimental study of wicking flow. Capillary device refilling with settled fluid was studied using an analytical and experimental program that resulted in successful correlation of a versatile computer program with test data. The program was used to predict Centaur D-1S LO2 and LH2 start basket refilling. Comparisons were made between the baseline Centaur D-1S propellant feed system and feed system alternatives including systems using capillary devices. The preferred concepts from the Centaur D-1S study were examined for APOTV and POTV vehicles for delivery and round trip transfer of payloads between LEO and GEO. Mission profiles were determined to provide propellant usage timelines and the payload partials were defined.

NASA's Space Launch System (SLS) Program: Mars Program Utilization

NASA Technical Reports Server (NTRS)

May, Todd A.; Creech, Stephen D.

2012-01-01

NASA's Space Launch System is being designed for safe, affordable, and sustainable human and scientific exploration missions beyond Earth's orbit (BEO), as directed by the NASA Authorization Act of 2010 and NASA's 2011 Strategic Plan. This paper describes how the SLS can dramatically change the Mars program's science and human exploration capabilities and objectives. Specifically, through its high-velocity change (delta V) and payload capabilities, SLS enables Mars science missions of unprecedented size and scope. By providing direct trajectories to Mars, SLS eliminates the need for complicated gravity-assist missions around other bodies in the solar system, reducing mission time, complexity, and cost. SLS's large payload capacity also allows for larger, more capable spacecraft or landers with more instruments, which can eliminate the need for complex packaging or "folding" mechanisms. By offering this capability, SLS can enable more science to be done more quickly than would be possible through other delivery mechanisms using longer mission times.

International Space Station (ISS) Accommodation of a Single US Assured Crew Return Vehicle (ACRV)

NASA Technical Reports Server (NTRS)

Mazanek, Daniel D.; Garn, Michelle A.; Troutman, Patrick A.; Wang, Yuan; Kumar, Renjith; Heck, Michael L.

1997-01-01

The following report was generated to give the International Space Station (ISS) Program some additional insight into the operations and issues associated with accommodating a single U.S. developed Assured Crew Return Vehicle (ACRV). During the generation of this report, changes in both the ISS and ACRV programs were factored into the analysis with the realization that most of the work performed will eventually need to be repeated once the two programs become more integrated. No significant issues associated with the ISS accommodating the ACRV were uncovered. Kinematic analysis of ACRV installation showed that there are viable methods of using Shuttle and Station robotic manipulators. Separation analysis demonstrated that the ACRV departure path clears the Station structure for all likely contingency scenarios. The payload bay packaging analysis identified trades that can be made between payload bay location, Shuttle Remote Manipulator System (SRMS) reach and eventual designs of de-orbit stages and docking adapters.

Cost and Business Analysis Module (CABAM). Revision A

NASA Technical Reports Server (NTRS)

Lee, Michael Hosung

1997-01-01

In the recent couple of decades, due to international competition, the US launchers lost a considerable amount of market share in the international space launch industry'. Increased international competition has continuously affected the US dominance to eventually place great pressure on future US space launch programs. To compete for future payload and passenger delivery markets, new launch vehicles must first be capable of reliably reaching a number of desired orbital destinations with customer-desired payload capacities. However, the ultimate success of a new launch vehicle program will depend on the launch price it is capable of offering it's customers. Extremely aggressive pricing strategies will be required for a new domestic launch service to compete with low-price international launchers. Low launch prices, then, naturally require a tight budget for the launch program economy. Therefore, budget constraints established by low-pricing requirements eventually place pressure on new launch vehicles to have unprecedentedly low Life Cycle Costs (LCC's).

Integrated orbital servicing study for low-cost payload programs. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Derocher, W. L., Jr.

1975-01-01

Various operating methodologies to achieve low-cost space operations were investigated as part of the Space Transportation System (STS) planning. The emphasis was to show that the development investment, initial fleet costs, and supporting facilities for the STS could be effectively offset by exploiting the capabilities of the STS to satisfy mission requirements and reduce the cost of payload programs. The following major conclusions were reached: (1) the development of an on-orbit servicer maintenance system is compatible with many spacecraft programs and is recommended as the most cost-effective system, (2) spacecraft can be designed to be serviceable with acceptable design, weight, volume, and cost effects, (3) use of on-orbit servicing over a 12 year period results in savings ranging between four and nine billion dollars, (4) the pivoting arm on-orbit servicer was selected and a preliminary design was prepared, (5) orbital maintenance has no significant impact on the STS.

Space shuttle and life sciences

NASA Technical Reports Server (NTRS)

Mason, J. A.

1977-01-01

During the 1980's, some 200 Spacelab missions will be flown on space shuttle in earth-orbit. Within these 200 missions, it is planned that at least 20 will be dedicated to life sciences research, projects which are yet to be outlined by the life sciences community. Objectives of the Life Sciences Shuttle/Spacelab Payloads Program are presented. Also discussed are major space life sciences programs including space medicine and physiology, clinical medicine, life support technology, and a variety of space biology topics. The shuttle, spacelab, and other life sciences payload carriers are described. Concepts for carry-on experiment packages, mini-labs, shared and dedicated spacelabs, as well as common operational research equipment (CORE) are reviewed. Current NASA planning and development includes Spacelab Mission Simulations, an Announcement of Planning Opportunity for Life Sciences, and a forthcoming Announcement of Opportunity for Flight Experiments which will together assist in forging a Life Science Program in space.

Feasibility study for the application of the large format camera as a payload for the Orbiter program

NASA Technical Reports Server (NTRS)

1978-01-01

The large format camera (LFC) designed as a 30 cm focal length cartographic camera system that employs forward motion compensation in order to achieve the full image resolution provided by its 80 degree field angle lens is described. The feasibility of application of the current LFC design to deployment in the orbiter program as the Orbiter Camera Payload System was assessed and the changes that are necessary to meet such a requirement are discussed. Current design and any proposed design changes were evaluated relative to possible future deployment of the LFC on a free flyer vehicle or in a WB-57F. Preliminary mission interface requirements for the LFC are given.

Space Congress, 27th, Cocoa Beach, FL, Apr. 24-27, 1990, Proceedings

NASA Technical Reports Server (NTRS)

1990-01-01

The present symposium on aeronautics and space encompasses DOD research and development, science payloads, small microgravity carriers, the Space Station, technology payloads and robotics, commercial initiatives, STS derivatives, space exploration, and DOD space operations. Specific issues addressed include the use of AI to meet space requirements, the Astronauts Laboratory Smart Structures/Skins Program, the Advanced Liquid Feed Experiment, an overview of the Spacelab program, the Autonomous Microgravity Industrial Carrier Initiative, and the Space Station requirements and transportation options for a lunar outpost. Also addressed are a sensor-data display for telerobotic systems, the Pegasus and Taurus launch vehicles, evolutionary transportation concepts, the upgrade of the Space Shuttle avionics, space education, orbiting security sentinels, and technologies for improving launch-vehicle responsiveness.

Early Spacelab physics and astronomy missions

NASA Technical Reports Server (NTRS)

Chapman, R. D.

1976-01-01

Some of the scientific problems which will be investigated during the early Spacelab physics and astronomy missions are reviewed. The Solar Terrestrial Programs will include the Solar Physics Spacelab Payloads (SPSP) and the Atmospheres, Magnetospheres and Plasmas in Space (AMPS) missions. These missions will study the sun as a star and the influence of solar phenomena on the earth, including sun-solar wind interface, the nature of the solar flares, etc. The Astrophysics Spacelab Payloads (ASP) programs are divided into the Ultraviolet-Optical Astronomy and the High Energy Astrophysics areas. The themes of astrophysics Spacelab investigations will cover the nature of the universe, the fate of matter and the life cycles of stars. The paper discusses various scientific experiments and instruments to be used in the early Spacelab missions.

Cassini/Titan-4 Acoustic Blanket Development and Testing

NASA Technical Reports Server (NTRS)

Hughes, William O.; McNelis, Anne M.

1996-01-01

NASA Lewis Research Center recently led a multi-organizational effort to develop and test verify new acoustic blankets. These blankets support NASA's goal in reducing the Titan-4 payload fairing internal acoustic environment to allowable levels for the Cassini spacecraft. To accomplish this goal a two phase acoustic test program was utilized. Phase One consisted of testing numerous blanket designs in a flat panel configuration. Phase Two consisted of testing the most promising designs out of Phase One in a full scale cylindrical payload fairing. This paper will summarize this highly successful test program by providing the rationale and results for each test phase, the impacts of this testing on the Cassini mission, as well as providing some general information on blanket designs.

ERTS-1 - Teaching us a new way to see.

NASA Technical Reports Server (NTRS)

Mercanti, E. P.

1973-01-01

The ERTS-1 payload is discussed, giving attention to three television cameras, which view the same area in three different spectral bands. The payload includes also a multispectral scanner subsystem and a data collection system which collects information from some 150 remote, unattended, instrumented ground platforms. Many government agencies use ERTS-1 data as integral parts of their ongoing programs. Through its EROS program, the Interior Department represents the largest single recipient and user agency of data obtained from NASA aircraft and spacecraft designed to gather repetitive information related to a wide variety of earth-science and natural-resources disciplines. Questions of environmental impact are considered together with applications in agriculture, forestry, marine resources, geography, and the survey of water resources.

IMIS desktop & smartphone software solutions for monitoring spacecrafts' payload from anywhere

NASA Astrophysics Data System (ADS)

Baroukh, J.; Queyrut, O.; Airaud, J.

In the past years, the demand for satellite remote operations has increased guided by on one hand, the will to reduce operations cost (on-call operators out of business hours), and on the other hand, the development of cooperation space missions resulting in a world wide distribution of engineers and science team members. Only a few off-the-shelf solutions exist to fulfill the need of remote payload monitoring, and they mainly use proprietary devices. The recent advent of mobile technologies (laptops, smartphones and tablets) as well as the worldwide deployment of broadband networks (3G, Wi-Fi hotspots), has opened up a technical window that brings new options. As part of the Mars Science Laboratory (MSL) mission, the Centre National D'Etudes Spatiales (CNES, the French space agency) has developed a new software solution for monitoring spacecraft payloads. The Instrument Monitoring Interactive Software (IMIS) offers state-of-the-art operational features for payload monitoring, and can be accessed remotely. It was conceived as a generic tool that can be used for heterogeneous payloads and missions. IMIS was designed as a classical client/server architecture. The server is hosted at CNES and acts as a data provider while two different kinds of clients are available depending on the level of mobility required. The first one is a rich client application, built on Eclipse framework, which can be installed on usual operating systems and communicates with the server through the Internet. The second one is a smartphone application for any Android platform, connected to the server thanks to the mobile broadband network or a Wi-Fi connection. This second client is mainly devoted to on-call operations and thus only contains a subset of the IMIS functionalities. This paper describes the operational context, including security aspects, that led IMIS development, presents the selected software architecture and details the various features of both clients: the desktop and the sm- rtphone application.

Improved Tumor Penetration and Single-Cell Targeting of Antibody-Drug Conjugates Increases Anticancer Efficacy and Host Survival.

PubMed

Cilliers, Cornelius; Menezes, Bruna; Nessler, Ian; Linderman, Jennifer; Thurber, Greg M

2018-02-01

Current antibody-drug conjugates (ADC) have made advances in engineering the antibody, linker, conjugation site, small-molecule payload, and drug-to-antibody ratio (DAR). However, the relationship between heterogeneous intratumoral distribution and efficacy of ADCs is poorly understood. Here, we compared trastuzumab and ado-trastuzumab emtansine (T-DM1) to study the impact of ADC tumor distribution on efficacy. In a mouse xenograft model insensitive to trastuzumab, coadministration of trastuzumab with a fixed dose of T-DM1 at 3:1 and 8:1 ratios dramatically improved ADC tumor penetration and resulted in twice the improvement in median survival compared with T-DM1 alone. In this setting, the effective DAR was lowered, decreasing the amount of payload delivered to each targeted cell but increasing the number of cells that received payload. This result is counterintuitive because trastuzumab acts as an antagonist in vitro and has no single-agent efficacy in vivo , yet improves the effectiveness of T-DM1 in vivo Novel dual-channel fluorescence ratios quantified single-cell ADC uptake and metabolism and confirmed that the in vivo cellular dose of T-DM1 alone exceeded the minimum required for efficacy in this model. In addition, this technique characterized cellular pharmacokinetics with heterogeneous delivery after 1 day, degradation and payload release by 2 days, and in vitro cell killing and in vivo tumor shrinkage 2 to 3 days later. This work demonstrates that the intratumoral distribution of ADC, independent of payload dose or plasma clearance, plays a major role in ADC efficacy. Significance: This study shows how lowering the drug-to-antibody ratio during treatment can improve the intratumoral distribution of a antibody-drug conjugate, with implications for improving the efficacy of this class of cancer drugs. Cancer Res; 78(3); 758-68. ©2017 AACR . ©2017 American Association for Cancer Research.

Multi-Spectral Stereo Atmospheric Remote Sensing (STARS) for Retrieval of Cloud Properties and Cloud-Motion Vectors

NASA Astrophysics Data System (ADS)

Kelly, M. A.; Boldt, J.; Wilson, J. P.; Yee, J. H.; Stoffler, R.

2017-12-01

The multi-spectral STereo Atmospheric Remote Sensing (STARS) concept has the objective to provide high-spatial and -temporal-resolution observations of 3D cloud structures related to hurricane development and other severe weather events. The rapid evolution of severe weather demonstrates a critical need for mesoscale observations of severe weather dynamics, but such observations are rare, particularly over the ocean where extratropical and tropical cyclones can undergo explosive development. Coincident space-based measurements of wind velocity and cloud properties at the mesoscale remain a great challenge, but are critically needed to improve the understanding and prediction of severe weather and cyclogenesis. STARS employs a mature stereoscopic imaging technique on two satellites (e.g. two CubeSats, two hosted payloads) to simultaneously retrieve cloud motion vectors (CMVs), cloud-top temperatures (CTTs), and cloud geometric heights (CGHs) from multi-angle, multi-spectral observations of cloud features. STARS is a pushbroom system based on separate wide-field-of-view co-boresighted multi-spectral cameras in the visible, midwave infrared (MWIR), and longwave infrared (LWIR) with high spatial resolution (better than 1 km). The visible system is based on a pan-chromatic, low-light imager to resolve cloud structures under nighttime illumination down to ¼ moon. The MWIR instrument, which is being developed as a NASA ESTO Instrument Incubator Program (IIP) project, is based on recent advances in MWIR detector technology that requires only modest cooling. The STARS payload provides flexible options for spaceflight due to its low size, weight, power (SWaP) and very modest cooling requirements. STARS also meets AF operational requirements for cloud characterization and theater weather imagery. In this paper, an overview of the STARS concept, including the high-level sensor design, the concept of operations, and measurement capability will be presented.

In-flight performance of the solar UV radiometer LYRA/PROBA-2

NASA Astrophysics Data System (ADS)

Stockman, Y.; BenMoussa, A.; Dammasch, I.; Defise, J.-M.; Dominique, M.; Halain, J.-P.; Hochedez, J.-F.; Koller, S.; Schmutz, W.; Schühle, U.

2017-11-01

LYRA is a solar radiometer, part of the PROBA-2 micro-satellite payload (Fig. 1). The PROBA-2 [1] mission has been launched on 02 November 2009 with a Rockot launcher to a Sun-synchronous orbit at an altitude of 725 km. Its nominal operation duration is two years with possible extension of 2 years. PROBA-2 is a small satellite developed under an ESA General Support Technology Program (GSTP) contract to perform an in-flight demonstration of new space technologies and support a scientific mission for a set of selected instruments [2]. PROBA-2 host 17 technological demonstrators and 4 scientific instruments. The mission is tracked by the ESA Redu Mission Operation Center. One of the four scientific instruments is LYRA that monitors the solar irradiance at a high cadence (> 20 Hz) in four soft X-Ray to VUV large passbands: the "Lyman-Alpha" channel, the "Herzberg" continuum range, the "Aluminium" and "Zirconium" filter channels. The radiometric calibration is traceable to synchrotron source standards [3]. LYRA benefits from wide bandgap detectors based on diamond. It is the first space assessment of these revolutionary UV detectors for astrophysics. Diamond sensors make the instruments radiation-hard and solar-blind (insensitive to the strong solar visible light) and, therefore, visible light blocking filters become superfluous. To correlate the data of this new detector technology, silicon detectors with well known characteristics are also embarked. Due to the strict allocated mass and power budget (5 kg, 5W), and poor priority to the payload needs on such platform, an optimization and a robustness of the instrument was necessary. The first switch-on occured on 16 November 2009. Since then the instrument performances have been monitored and analyzed during the commissioning period. This paper presents the first-light and preliminary performance analysis.

The SLICE, CHESS, and SISTINE Ultraviolet Spectrographs: Rocket-Borne Instrumentation Supporting Future Astrophysics Missions

NASA Astrophysics Data System (ADS)

France, Kevin; Hoadley, Keri; Fleming, Brian T.; Kane, Robert; Nell, Nicholas; Beasley, Matthew; Green, James C.

2016-03-01

NASA’s suborbital program provides an opportunity to conduct unique science experiments above Earth’s atmosphere and is a pipeline for the technology and personnel essential to future space astrophysics, heliophysics, and atmospheric science missions. In this paper, we describe three astronomy payloads developed (or in development) by the Ultraviolet Rocket Group at the University of Colorado. These far-ultraviolet (UV) (100-160nm) spectrographic instruments are used to study a range of scientific topics, from gas in the interstellar medium (accessing diagnostics of material spanning five orders of magnitude in temperature in a single observation) to the energetic radiation environment of nearby exoplanetary systems. The three instruments, Suborbital Local Interstellar Cloud Experiment (SLICE), Colorado High-resolution Echelle Stellar Spectrograph (CHESS), and Suborbital Imaging Spectrograph for Transition region Irradiance from Nearby Exoplanet host stars (SISTINE) form a progression of instrument designs and component-level technology maturation. SLICE is a pathfinder instrument for the development of new data handling, storage, and telemetry techniques. CHESS and SISTINE are testbeds for technology and instrument design enabling high-resolution (R>105) point source spectroscopy and high throughput imaging spectroscopy, respectively, in support of future Explorer, Probe, and Flagship-class missions. The CHESS and SISTINE payloads support the development and flight testing of large-format photon-counting detectors and advanced optical coatings: NASA’s top two technology priorities for enabling a future flagship observatory (e.g. the LUVOIR Surveyor concept) that offers factors of ˜50-100 gain in UV spectroscopy capability over the Hubble Space Telescope. We present the design, component level laboratory characterization, and flight results for these instruments.

Atmospheric, Magnetospheric and Plasmas in space (AMPS) spacelab payload definition study. Volume 4. Part 1, AMPS program specification

NASA Technical Reports Server (NTRS)

Keeley, J. T.

1976-01-01

The AMPS Program Specification delineates the AMPS Program requirements consistent with the resources defined in the AMPS Project Plan. All subsidiary specifications and requirements shall conform to the requirements presented. The requirements hierarchy for the AMPS program is illustrated. A brief description of each of the requirements documents and their intended use is provided.

Information systems requirements for the Microgravity Science and Applications Program

NASA Technical Reports Server (NTRS)

Kicza, M. E.; Kreer, J. R.

1991-01-01

NASA's Microgravity Science and Applications (MSAD) Program is presented. Additionally, the types of information produced wiithin the program and the anticipated growth in information system requirements as the program transitions to Space Station Freedom utilization are discussed. Plans for payload operations support in the Freedom era are addressed, as well as current activities to define research community requirements for data and sample archives.

Information systems requirements for the microgravity science and applications program

NASA Technical Reports Server (NTRS)

Kicza, M. E.; Kreer, J. R.

1990-01-01

NASA's Microgravity Science and Applications (MSAD) Program is presented. Additionally, the types of information produced within the program and the anticipated growth in information system requirements as the program transitions to Space Station Freedom utilization are discussed. Plans for payload operations support in the Freedom era are addressed, as well as current activities to define research community requirements for data and sample archives.

Systematic Propulsion Optimization Tools (SPOT)

NASA Technical Reports Server (NTRS)

Bower, Mark; Celestian, John

1992-01-01

This paper describes a computer program written by senior-level Mechanical Engineering students at the University of Alabama in Huntsville which is capable of optimizing user-defined delivery systems for carrying payloads into orbit. The custom propulsion system is designed by the user through the input of configuration, payload, and orbital parameters. The primary advantages of the software, called Systematic Propulsion Optimization Tools (SPOT), are a user-friendly interface and a modular FORTRAN 77 code designed for ease of modification. The optimization of variables in an orbital delivery system is of critical concern in the propulsion environment. The mass of the overall system must be minimized within the maximum stress, force, and pressure constraints. SPOT utilizes the Design Optimization Tools (DOT) program for the optimization techniques. The SPOT program is divided into a main program and five modules: aerodynamic losses, orbital parameters, liquid engines, solid engines, and nozzles. The program is designed to be upgraded easily and expanded to meet specific user needs. A user's manual and a programmer's manual are currently being developed to facilitate implementation and modification.

Computer program development and user's manual for program PARACH. [to investigate parachute spent solid rocket booster during terminal descent

NASA Technical Reports Server (NTRS)

Murphree, H. I.

1979-01-01

A user's manual is provided for program PARACH, a FORTRAN digital computer program operational on the Univac 1108. A description of the program and operating instructions for it are included. Program PARACH is used to study the interaction dynamics of a parachute and its payload during terminal descent. Operating instructions, required input data, program options and limitations, and output data are described. Subroutines used in this program are also listed and explained.

HICOV - Newton-Raphson calculus of variation with automatic transversalities

NASA Technical Reports Server (NTRS)

Heintschel, T. J.

1968-01-01

Computer program generates trajectories that are optimum with respect to payload placed in an earth orbit. It uses a subroutine package which produces the terminal and transversality conditions and their partial derivatives. This program is written in FORTRAN 4 and FORMAC for the IBM 7094 computer.

Database of proposed payloads and instruments for SEI missions

NASA Technical Reports Server (NTRS)

Barlow, N. G.

1992-01-01

A database of all payloads and instruments proposed for lunar and Mars missions was compiled by the author for the Exploration Programs Office at NASA's Johnson Sapce Center. The database is an outgrowth of the document produced by C. J. Budney et al. at the Jet Propulsion Laboratory in 1991. The present database consists not only of payloads proposed for human exploratory missions of the Moon and Mars, but also experiments selected or proposed for robotic precursor missions such as Lunar Scout, Mars Observer, and MESUR. The database consists of two parts: a written payload description and a matrix that provides a breakdown of payload components. Each payload description consists of the following information: (1) the rationale for why the instrument or payload package is being proposed for operation on the Moon or Mars; (2) a description of how the instrument works; (3) a breakdown of the payload, providing detailed information about the mass, volume, power requirements, and data rates for the constituent pieces of the experiment; (4) estimates of the power consumption and data rate; (5) how the data will be returned to Earth and distributed to the scientific community; (6) any constraints on the location or conditions under which the instrument can or cannot operate; (7) what type of crew interaction (if any) is needed; (8) how the payload is to be delivered to the lunar or martian surface (along with alternative delivery options); (9) how long the instrument or payload package will take to set up; (10) what type of maintenance needs are anticipated for the experiment; (11) stage of development for the instrument and environmental conditions under which the instrument has been tested; (12) an interface required by the instrument with the lander, a rover, an outpost, etc.; (13) information about how often the experiment will need to be resupplied with parts or consumables, if it is to be resupplied; (14) the name and affiliation of a contact person for the experiment; and (15) references where further information about the experiment can be found.

How differential deflection of the inboard and outboard leading-edge flaps affected the handling qua

NASA Technical Reports Server (NTRS)

2002-01-01

How differential deflection of the inboard and outboard leading-edge flaps affected the handling qualities of this modified F/A-18A was evaluated during the first check flight in the Active Aeroelastic Wing program at NASA's Dryden Flight Research Center. The Active Aeroelastic Wing program at NASA's Dryden Flight Research Center seeks to determine the advantages of twisting flexible wings for primary maneuvering roll control at transonic and supersonic speeds, with traditional control surfaces such as ailerons and leading-edge flaps used to aerodynamically induce the twist. From flight test and simulation data, the program intends to develop structural modeling techniques and tools to help design lighter, more flexible high aspect-ratio wings for future high-performance aircraft, which could translate to more economical operation or greater payload capability. AAW flight tests began in November, 2002 with checkout and parameter-identification flights. Based on data obtained during the first flight series, new flight control software will be developed and a second series of research flights will then evaluate the AAW concept in a real-world environment. The program uses wings that were modified to the flexibility of the original pre-production F-18 wing. Other modifications include a new actuator to operate the outboard leading edge flap over a greater range and rate, and a research flight control system to host the aeroelastic wing control laws. The Active Aeroelastic Wing Program is jointly funded and managed by the Air Force Research Laboratory and NASA Dryden Flight Research Center, with Boeing's Phantom Works as prime contractor for wing modifications and flight control software development. The F/A-18A aircraft was provided by the Naval Aviation Systems Test Team and modified for its research role by NASA Dryden technicians.

Photographing the Earth G324: The Can Do GeoCam payload

NASA Technical Reports Server (NTRS)

Nicholson, James H.; Obrien, Thomas J.; Tempel, Carol A.

1995-01-01

The flight of the Charleston County School District Can Do Project GeoCam payload on STS-57 was the climax of a decade long endeavor to bring the promise and excitement of the space program directly into the classroom. The payload carried four cameras designed to take high resolution photographs of the Earth under the direction of children operating the first ever student control room. During the course of the flight, the students followed the Shuttle's orbital tract, satellite weather images and selected a target list that was sent up to the crew each night as part of the execute package. Targets from this list, as well as ones chosen by the crew visually, resulted in the successful collection of photographic runs at many interesting sites on three on three continents.

KSC-99pd-812-03

NASA Image and Video Library

1999-08-01

KENNEDY SPACE CENTER, FLA. -- KSC workers stand inside the payload bay of the orbiter Columbia following completion of electrical wiring inspections. In the background is the open cable tray with the wiring. During launch of Columbia on mission STS-93, a damaged wire caused a short circuit in two separate main engine controllers. As a result of the findings, Shuttle program managers decided to conduct inspections of the wiring in Endeavour's payload bay before its next mission, STS-99. The inspection and possible repair work will lead to a delayed launch date no earlier than Oct.7. The primary payload of the mission is the Shuttle Radar Topography Mission, a specially modified radar system that will gather data for the most accurate and complete topographic map of the Earth's surface that has ever been assembled

KSC-99pd-812-01

NASA Image and Video Library

1999-08-01

KENNEDY SPACE CENTER, FLA. -- KSC workers stand inside the payload bay of the orbiter Columbia following completion of electrical wiring inspections. At right, behind and below them is the cable tray with the wiring. During launch of Columbia on mission STS-93, a damaged wire caused a short circuit in two separate main engine controllers. As a result of the findings, Shuttle program managers decided to conduct inspections of the wiring in Endeavour's payload bay before its next mission, STS-99. The inspection and possible repair work will lead to a delayed launch date no earlier than Oct.7. The primary payload of the mission is the Shuttle Radar Topography Mission, a specially modified radar system that will gather data for the most accurate and complete topographic map of the Earth's surface that has ever been assembled

Follow-the-Leader Control for the PIPS Prototype Hardware

NASA Technical Reports Server (NTRS)

Williams, Robert L. II; Lippitt, Thimas

1996-01-01

This report describes the payload inspection and processing system (PIPS), an automated system programmed off-line for inspection of space shuttle payloads after integration and prior to launch. PIPS features a hyper-redundant 18-degree of freedom (DOF) serpentine truss manipulator capable of snake like motions to avoid obstacles. During the summer of 1995, the author worked on the same project, developing a follow-the-leader (FTL) algorithm in graphical simulation which ensures whole arm collision avoidance by forcing ensuing links to follow the same tip trajectory. The summer 1996 work was to control the prototype PIPS hardware in follow-the-leader mode. The project was successful in providing FTL control in hardware. The STS-82 payload mockup was used in the laboratory to demonstrate serpentine motions to avoid obstacles in a realistic environment.

Workshop Report on Ares V Solar System Science

NASA Technical Reports Server (NTRS)

Langhoff, Stephanie; Spilker, Tom; Martin, Gary; Sullivan, Greg

2008-01-01

The workshop blended three major themes: (1) How can elements of the Constellation program, and specifically, the planned Ares-V heavy-launch vehicle, benefit the planetary community by enabling the launch of large planetary payloads that cannot be launched on existing vehicles, and how can the capabilities of an Ares V allow the planetary community to redesign missions to achieve lower risk, and perhaps lower cost on these missions? (2) What are some of the planetary missions that either can be significantly enhanced or enabled by an Ares-V launch vehicle? What constraints do these mission concepts place on the payload environment of the Ares V? (3) Technology challenges that need to be addressed for launching large planetary payloads. Presentations varied in length from 15-40 minutes. Ample time was provided for discussion.

STS-40 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W.

1991-01-01

The STS-40 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-first flight of the Space Shuttle and the eleventh flight of the Orbiter Vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of an External Tank (ET) designated as ET-41 (LWT-34), three Space Shuttle main engines (SSME's) (serial numbers 2015, 2022, and 2027 in positions 1, 2, and 3, respectively), and two Solid Rocket Boosters (SRB's) designated as BI-044. The primary objective of the STS-40 flight was to successfully perform the planned operations of the Spacelab Life Sciences-1 (SLS-1) payload. The secondary objectives of this flight were to perform the operations required by the Getaway Special (GAS) payloads and the Middeck O-Gravity Dynamics Experiment (MODE) payload.

STS-40 Space Shuttle mission report

NASA Astrophysics Data System (ADS)

Fricke, Robert W.

1991-07-01

The STS-40 Space Shuttle Program Mission Report contains a summary of the vehicle subsystem operations during the forty-first flight of the Space Shuttle and the eleventh flight of the Orbiter Vehicle Columbia (OV-102). In addition to the Columbia vehicle, the flight vehicle consisted of an External Tank (ET) designated as ET-41 (LWT-34), three Space Shuttle main engines (SSME's) (serial numbers 2015, 2022, and 2027 in positions 1, 2, and 3, respectively), and two Solid Rocket Boosters (SRB's) designated as BI-044. The primary objective of the STS-40 flight was to successfully perform the planned operations of the Spacelab Life Sciences-1 (SLS-1) payload. The secondary objectives of this flight were to perform the operations required by the Getaway Special (GAS) payloads and the Middeck O-Gravity Dynamics Experiment (MODE) payload.

STS-114: Discovery L-3 Countdown Status Briefing

NASA Technical Reports Server (NTRS)

2005-01-01

Bruce Buckingham of NASA Public Affair hosted this briefing. Jeff Spaulding, NASA Test Director; Scott Higgenbotham, STS-114 Payload-Mission Manager; Cathy Winters, Shuttle Weather Officer were present. Jeff specifically noted that the mission represents NASA's first step towards fulfilling the President's visions of returning to the Moon and then on to Mars and beyond. Scott reports that the 28,000 pounds of ISS hardware that is in the payload bay of the Discovery is ready to go, and completed final close outs. Cathy mentioned that Hurricane Dennis is not a threat, however, main threat of inland thunderstorms would result to 30% weather prohibiting launch. Cathy further gave current weather forecast supported with charts: the Launch Forecast, Tanking Forecast, SRB (Shuttle Solid Rocket Booster) Forecast, CONUS and TAL Launch Sites Forecast and with 24 hours and 48 hours turn around plan. Final inspections, ice formation, ice inspection, effect of weather conditions to the external tank, delays and contingencies were some of the topics covered with the News Media.

Open-Loop Performance of COBALT Precision Landing Payload on a Commercial Sub-Orbital Rocket

NASA Technical Reports Server (NTRS)

Restrepo, Carolina I.; Carson, John M., III; Amzajerdian, Farzin; Seubert, Carl R.; Lovelace, Ronney S.; McCarthy, Megan M.; Tse, Teming; Stelling, Richard; Collins, Steven M.

2018-01-01

An open-loop flight test campaign of the NASA COBALT (CoOperative Blending of Autonomous Landing Technologies) platform was conducted onboard the Masten Xodiac suborbital rocket testbed. The COBALT platform integrates NASA Guidance, Navigation and Control (GN&C) sensing technologies for autonomous, precise soft landing, including the Navigation Doppler Lidar (NDL) velocity and range sensor and the Lander Vision System (LVS) Terrain Relative Navigation (TRN) system. A specialized navigation filter running onboard COBALT fuses the NDL and LVS data in real time to produce a navigation solution that is independent of GPS and suitable for future, autonomous, planetary, landing systems. COBALT was a passive payload during the open loop tests. COBALT's sensors were actively taking data and processing it in real time, but the Xodiac rocket flew with its own GPS-navigation system as a risk reduction activity in the maturation of the technologies towards space flight. A future closed-loop test campaign is planned where the COBALT navigation solution will be used to fly its host vehicle.

NASA Pathways: Intern Employment Program Work Report Summer 2014

NASA Technical Reports Server (NTRS)

Davidson, Kyle B.

2014-01-01

This report documents the work experience and project involvement of Kyle Davidson during his tenure at Kennedy Space Center for the summer of 2014. Projects include the Nitrogen Oxygen Recharge System (NORS), Restore satellite servicing program, and mechanical handling operations for the SAGE III and Rapidscat payloads.

Freedom to act fast.

NASA Technical Reports Server (NTRS)

Pickering, W. H.

1972-01-01

The history of the development program that culminated in the Explorer and Pioneer launchings is outlined. Earlier work on launching rockets, and the discovery of the Van Allen belts is discussed. The Explorer program was carried out in less than three months, and the different Explorers launched later carried widely different payloads.

Evaluation of Dual-Launch Lunar Architectures Using the Mission Assessment Post Processor

NASA Technical Reports Server (NTRS)

Stewart, Shaun M.; Senent, Juan; Williams, Jacob; Condon, Gerald L.; Lee, David E.

2010-01-01

The National Aeronautics and Space Administrations (NASA) Constellation Program is currently designing a new transportation system to replace the Space Shuttle, support human missions to both the International Space Station (ISS) and the Moon, and enable the eventual establishment of an outpost on the lunar surface. The present Constellation architecture is designed to meet nominal capability requirements and provide flexibility sufficient for handling a host of contingency scenarios including (but not limited to) launch delays at the Earth. This report summarizes a body of work performed in support of the Review of U.S. Human Space Flight Committee. It analyzes three lunar orbit rendezvous dual-launch architecture options which incorporate differing methodologies for mitigating the effects of launch delays at the Earth. NASA employed the recently-developed Mission Assessment Post Processor (MAPP) tool to quickly evaluate vehicle performance requirements for several candidate approaches for conducting human missions to the Moon. The MAPP tool enabled analysis of Earth perturbation effects and Earth-Moon geometry effects on the integrated vehicle performance as it varies over the 18.6-year lunar nodal cycle. Results are provided summarizing best-case and worst-case vehicle propellant requirements for each architecture option. Additionally, the associated vehicle payload mass requirements at launch are compared between each architecture and against those of the Constellation Program. The current Constellation Program architecture assumes that the Altair lunar lander and Earth Departure Stage (EDS) vehicles are launched on a heavy lift launch vehicle. The Orion Crew Exploration Vehicle (CEV) is separately launched on a smaller man-rated vehicle. This strategy relaxes man-rating requirements for the heavy lift launch vehicle and has the potential to significantly reduce the cost of the overall architecture over the operational lifetime of the program. The crew launch occurs first, four days prior to the optimal trans-lunar injection (TLI) departure window. This is done to allow for launch delays in the Altair/EDS launch. During this time, the Orion vehicle is required to conduct orbit maintenance while loitering in low Earth orbit (LEO). The alternative architectures presented aim to eliminate the need for costly orbit maintenance maneuvers while loitering in LEO. In all of the alternative architectures considered, it is assumed that the Altair and Orion vehicles are nominally launched 90 minutes apart, depart the Earth separately, and complete the rendezvous and docking sequence at the Moon. In this lunar orbit rendezvous (LOR) strategy, both the Altair and Orion vehicles will require separate EDS stages, and each will be required to perform lunar orbit insertion (LOI). This has the effect of balancing payload requirements between the two launch vehicles at the Earth. In this case, the overall payload mass is increased slightly, but the increased mission costs could potentially be offset by requiring the construction of two rockets similar in size and nature, unlike the current Constellation architecture. Three dual-launch architecture options with LOR were evaluated, which incorporate differing methodologies for mitigating the effects of launch delays at the Earth. Benefits and drawbacks of each of the dual-launch architecture options with LOR are discussed and the overall mission performance is compared with that of the existing Constellation Program lunar architecture.

STS-62 Space Shuttle mission report

NASA Technical Reports Server (NTRS)

Fricke, Robert W., Jr.

1994-01-01

The STS-62 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSHE) systems performance during the sixty-first flight of the Space Shuttle Program and sixteenth flight of the Orbiter vehicle Columbia (OV-102). In addition to the Orbiter, the flight vehicle consisted of an ET designated as ET-62; three SSME's which were designated as serial numbers 2031, 2109, and 2029 in positions 1, 2, and 3, respectively; and two SRB's which were designated BI-064. The RSRM's that were installed in each SRB were designated as 360L036A (lightweight) for the left SRB, and 36OWO36B (welterweight) for the right SRB. This STS-62 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS 07700, Volume 8, Appendix E. That document requires that each major organizational element supporting the Program report the results of its hardware evaluation and mission performance plus identify all related in-flight anomalies. The primary objectives of the STS-62 mission were to perform the operations of the United States Microgravity Payload-2 (USMP-2) and the Office of Aeronautics and Space Technology-2 (OAST-2) payload. The secondary objectives of this flight were to perform the operations of the Dexterous End Effector (DEE), the Shuttle Solar Backscatter Ultraviolet/A (SSBUV/A), the Limited Duration Space Environment Candidate Material Exposure (LDCE), the Advanced Protein Crystal Growth (APCG), the Physiological Systems Experiments (PSE), the Commercial Protein Crystal Growth (CPCG), the Commercial Generic Bioprocessing Apparatus (CGBA), the Middeck Zero-Gravity Dynamics Experiment (MODE), the Bioreactor Demonstration System (BDS), the Air Force Maui Optical Site Calibration Test (AMOS), and the Auroral Photography Experiment (APE-B).

Research Opportunities on board Virgin Galactic's SpaceShipTwo

NASA Astrophysics Data System (ADS)

Attenborough, S.; Pomerantz, W.; Stephens, K.

2013-09-01

Virgin Galactic is building the world's first commercial spaceline. Our suborbital spaceflight system, pictured in Figure 1, consists of two vehicles: WhiteKnightTwo (WK2) and SpaceShipTwo (SS2). WhiteKnightTwo is a four-engine, dual-fuselage jet aircraft capable of high-altitude heavy lift missions, including, but not limited to fulfilling its role as a mothership for SpaceShipTwo, an air-launched, suborbital spaceplane capable of routinely reaching an apogee up to 110 kilometers. In conjunction, these two vehicles allow access to space and to regions of the atmosphere ranging from the troposphere to the thermosphere; additionally, they provide extended periods of microgravity in a reliable and affordable way. SpaceShipTwo, with a payload capacity of up to 1,300 lbs. (~600 kg), features payload mounting interfaces that are compatible with standard architectures such as NASA Space Shuttle Middeck Lockers, Cargo Transfer Bags, and server racks, in addition to custom structures. With the standard interface, payloads are allowed access to the large 17 inch diameter cabin windows for external observations. Each dedicated research flight will be accompanied by a Virgin Galactic Flight Test Engineer, providing an opportunity for limited in-flight interaction. In addition, tended payloads - a flight that includes the researcher and his or her payload - are also an option. At a price point that is highly competitive with parabolic aircraft and sounding rockets and significantly cheaper than orbital flights, SpaceShipTwo is a unique platform that can provide frequent and repeatable research opportunities. Suborbital flights on SpaceShipTwo offer researchers several minutes of microgravity time and views of the external environment in the upper atmosphere and in outer space. In addition to serving as an important research platform in and of itself, SpaceShipTwo also offers researchers a means to test, iterate, and calibrate experiments designed for orbital platforms, including the International Space Station as well as LauncherOne, Virgin Galactic's dedicated launch vehicle for small (~500 lbs. / ~225 kg) satellites. Flights on SpaceShipTwo can be booked directly through Virgin Galactic. Various funding sources may be available for the research, including through NASA programs such as the Flight Opportunities Program, Game Changing Development Program, or Research Opportunities in Space and Earth Science (ROSES). More information about the SpaceShipTwo research platform, including a detailed Payload User's Guide, can be found at our website: http://www.virgingalactic.com/research.

NASA's Space Launch System: Deep-Space Delivery for SmallSats

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Norris, George

2017-01-01

Designed for human exploration missions into deep space, NASA's Space Launch System (SLS) represents a new spaceflight infrastructure asset, enabling a wide variety of unique utilization opportunities. While primarily focused on launching the large systems needed for crewed spaceflight beyond Earth orbit, SLS also offers a game-changing capability for the deployment of small satellites to deep-space destinations, beginning with its first flight. Currently, SLS is making rapid progress toward readiness for its first launch in two years, using the initial configuration of the vehicle, which is capable of delivering more than 70 metric tons (t) to Low Earth Orbit (LEO). On its first flight, an uncrewed test of the Orion spacecraft into distant retrograde orbit around the moon, accompanying Orion on SLS will be 13 small-satellite secondary payloads, which will deploy in cislunar space. These secondary payloads will include not only NASA research, but also spacecraft from industry and international partners and academia. The payloads also represent a variety of disciplines including, but not limited to, studies of the moon, Earth, sun, and asteroids. The Space Launch System Program is working actively with the developers of the payloads toward vehicle integration. Following its first flight and potentially as early as its second, SLS will evolve into a more powerful configuration with a larger upper stage. This configuration will initially be able to deliver 105 t to LEO, and will continue to be upgraded to a performance of greater than 130 t to LEO. While the addition of the more powerful upper stage will mean a change to the secondary payload accommodations from those on the first launch, the SLS Program is already evaluating options for future secondary payload opportunities. Early discussions are also already underway for the use of SLS to launch spacecraft on interplanetary trajectories, which could open additional opportunities for small satellites. This presentation will include an overview of the SLS vehicle and its capabilities, including the current status of progress toward first launch. It will also explain the opportunities the vehicle offers for small satellites, including an overview of the CubeSat manifest for Exploration Mission-1 in 2018 and a discussion of future capabilities.

National Report on the NASA Sounding Rocket and Balloon Programs

NASA Technical Reports Server (NTRS)

Eberspeaker, Philip; Fairbrother, Debora

2013-01-01

The U. S. National Aeronautics and Space Administration (NASA) Sounding Rockets and Balloon Programs conduct a total of 30 to 40 missions per year in support of the NASA scientific community and other users. The NASA Sounding Rockets Program supports the science community by integrating their experiments into the sounding rocket payloads, and providing both the rocket vehicle and launch operations services. Activities since 2011 have included two flights from Andoya Rocket Range, more than eight flights from White Sands Missile Range, approximately sixteen flights from Wallops Flight Facility, two flights from Poker Flat Research Range, and four flights from Kwajalein Atoll. Other activities included the final developmental flight of the Terrier-Improved Malemute launch vehicle, a test flight of the Talos-Terrier-Oriole launch vehicle, and a host of smaller activities to improve program support capabilities. Several operational missions have utilized the new Terrier-Malemute vehicle. The NASA Sounding Rockets Program is currently engaged in the development of a new sustainer motor known as the Peregrine. The Peregrine development effort will involve one static firing and three flight tests with a target completion data of August 2014. The NASA Balloon Program supported numerous scientific and developmental missions since its last report. The program conducted flights from the U.S., Sweden, Australia, and Antarctica utilizing standard and experimental vehicles. Of particular note are the successful test flights of the Wallops Arc Second Pointer (WASP), the successful demonstration of a medium-size Super Pressure Balloon (SPB), and most recently, three simultaneous missions aloft over Antarctica. NASA continues its successful incremental design qualification program and will support a science mission aboard WASP in late 2013 and a science mission aboard the SPB in early 2015. NASA has also embarked on an intra-agency collaboration to launch a rocket from a balloon to conduct supersonic decelerator tests. An overview of NASA's Sounding Rockets and Balloon Operations, Technology Development and Science support activities will be presented.

The Lunar Crater Observation and Sensing Satellite (LCROSS) Payload Development and Performance in Flight

NASA Astrophysics Data System (ADS)

Ennico, Kimberly; Shirley, Mark; Colaprete, Anthony; Osetinsky, Leonid

2012-05-01

The primary objective of the Lunar Crater Observation and Sensing Satellite (LCROSS) was to confirm the presence or absence of water ice in a permanently shadowed region (PSR) at a lunar pole. LCROSS was classified as a NASA Class D mission. Its payload, the subject of this article, was designed, built, tested and operated to support a condensed schedule, risk tolerant mission approach, a new paradigm for NASA science missions. All nine science instruments, most of them ruggedized commercial-off-the-shelf (COTS), successfully collected data during all in-flight calibration campaigns, and most importantly, during the final descent to the lunar surface on October 9, 2009, after 112 days in space. LCROSS demonstrated that COTS instruments and designs with simple interfaces, can provide high-quality science at low-cost and in short development time frames. Building upfront into the payload design, flexibility, redundancy where possible even with the science measurement approach, and large margins, played important roles for this new type of payload. The environmental and calibration approach adopted by the LCROSS team, compared to existing standard programs, is discussed. The description, capabilities, calibration and in-flight performance of each instrument are summarized. Finally, this paper goes into depth about specific areas where the instruments worked differently than expected and how the flexibility of the payload team, the knowledge of instrument priority and science trades, and proactive margin maintenance, led to a successful science measurement by the LCROSS payload's instrument complement.

Evaluation of Oxygen Interactions with Materials 3: Mission and induced environments

NASA Technical Reports Server (NTRS)

Koontz, Steven L.; Leger, Lubert J.; Rickman, Steven L.; Hakes, Charles L.; Bui, David T.; Hunton, Donald; Cross, Jon B.

1995-01-01

The Evaluation of Oxygen Interactions with Materials 3 (EOIM-3) flight experiment was developed to obtain benchmark atomic oxygen/material reactivity data. The experiment was conducted during Space Shuttle mission 46 (STS-46), which flew July 31 to August 7, 1992. Quantitative interpretation of the materials reactivity measurements requires a complete and accurate definition of the space environment exposure, including the thermal history of the payload, the solar ultraviolet exposure, the atomic oxygen fluence, and any spacecraft outgassing contamination effects. The thermal history of the payload was measured using twelve thermocouple sensors placed behind selected samples and on the EOIM-3 payload structure. The solar ultraviolet exposure history of the EOIM-3 payload was determined by analysis of the as-flown orbit and vehicle attitude combined with daily average solar ultraviolet and vacuum ultraviolet (UV/VUV) fluxes. The atomic oxygen fluence was assessed in three different ways. First, the O-atom fluence was calculated using a program that incorporates the MSIS-86 atmospheric model, the as-flown Space Shuttle trajectory, and solar activity parameters. Second, the oxygen atom fluence was estimated directly from Kapton film erosion. Third, ambient oxygen atom measurements were made using the quadrupole mass spectrometer on the EOIM-3 payload. Our best estimate of the oxygen atom fluence as of this writing is 2.3 +/- 0.3 x 10(exp 20) atoms/sq cm. Finally, results of post-flight X-ray photoelectron spectroscopy (XPS) surface analyses of selected samples indicate low levels of contamination on the payload surface.

An affordable RBCC-powered 2-stage small orbital payload transportation systems concept based on test-proven hardware

NASA Astrophysics Data System (ADS)

Escher, William J. D.

1998-01-01

Deriving from the initial planning activity of early 1965, which led to NASA's Advanced Space Transportation Program (ASTP), an early-available airbreathing/rocket combined propulsion system powered ``ultralight payload'' launcher was defined at the conceptual design level. This system, named the ``W Vehicle,'' was targeted to be a ``second generation'' successor to the original Bantam Lifter class, all-rocket powered systems presently being pursued by NASA and a selected set of its contractors. While this all-rocket vehicle is predicated on a fully expendable approach, the W-Vehicle system was to be a fully reusable 2-stage vehicle. The general (original) goal of the Bantam class of launchers was to orbit a 100 kg payload for a recurring per-launch cost of less than one million dollars. Reusability, as the case for larger vehicles focusing on single stage to orbit (SSTO) configurations, is considered the principal key to affordability. In the general context of a range of space transports, covering the payload range of 0.1 to 10 metric ton payloads, the W Vehicle concept-predicated mainly on ground- and flight-test proven hardware-is described in this paper, along with a nominal development schedule and budgetary estimate (recurring costs were not estimated).

Rocket propulsion hazard summary: Safety classification, handling experience and application to space shuttle payload

NASA Technical Reports Server (NTRS)

Pennington, D. F.; Man, T.; Persons, B.

1977-01-01

The DOT classification for transportation, the military classification for quantity distance, and hazard compatibility grouping used to regulate the transportation and storage of explosives are presented along with a discussion of tests used in determining sensitivity of propellants to an impact/shock environment in the absence of a large explosive donor. The safety procedures and requirements of a Scout launch vehicle, Western and Eastern Test Range, and the Minuteman, Delta, and Poseidon programs are reviewed and summarized. Requirements of the space transportation system safety program include safety reviews from the subsystem level to the completed payload. The Scout safety procedures will satisfy a portion of these requirements but additional procedures need to be implemented to comply with the safety requirements for Shuttle operation from the Eastern Test Range.

High altitude chemical release systems for project BIME (Brazilian Ionospheric Modification Experiments) project IMS (Ionospheric Modification Studies) project PIIE (Polar Ionospheric Irregularities Experiment) project polar arcs

NASA Astrophysics Data System (ADS)

Stokes, Charles S.; Murphy, William J.

1987-07-01

Project BIME, a Spread F observation program involved the launching of two Nike-Black Brant rockets each containing a payload of Ammonium Nitrate Fuel Oil (ANFO). The rockets were launched from Barriera Do Inferno Launch Site in Natal, Brazil in August of 1982. Project IMS, an F-layer modification experiment involved three launch vehicles, a Nike-Tomahawk and two Sonda III rockets. The Nike-Tomahawk carried a sulfur hexafluoride (SF6) payload. One of the Sonda III rockets carried a payload that consisted of an SF6 canister and a samarium/strontium thermite canister. The remaining Sonda III carried a trifluorobromo methane (CF3Br) canister and a samarium thermite canister. The rockets were launched from Wallops Island Launch Facility, Virginia in November of 1984. Project PIIE and Polar Arcs, a program to investigate polar ionospheric irregularities, involved a Nike-Black Brant rocket carrying one samarium thermite canister and six barium canisters. An attempted launch failed when launch criteria could not be met. The rocket was launched successfully from Sondrestrom Air Base, Greenland in March 1987.

NASA's Space Launch System Program Update

NASA Technical Reports Server (NTRS)

May, Todd; Lyles, Garry

2015-01-01

Hardware and software for the world's most powerful launch vehicle for exploration is being welded, assembled, and tested today in high bays, clean rooms and test stands across the United States. NASA's Space Launch System (SLS) continued to make significant progress in the past year, including firing tests of both main propulsion elements, manufacturing of flight hardware, and the program Critical Design Review (CDR). Developed with the goals of safety, affordability, and sustainability, SLS will deliver unmatched capability for human and robotic exploration. The initial Block 1 configuration will deliver more than 70 metric tons (t) (154,000 pounds) of payload to low Earth orbit (LEO). The evolved Block 2 design will deliver some 130 t (286,000 pounds) to LEO. Both designs offer enormous opportunity and flexibility for larger payloads, simplifying payload design as well as ground and on-orbit operations, shortening interplanetary transit times, and decreasing overall mission risk. Over the past year, every vehicle element has manufactured or tested hardware, including flight hardware for Exploration Mission 1 (EM-1). This paper will provide an overview of the progress made over the past year and provide a glimpse of upcoming milestones on the way to a 2018 launch readiness date.

Spacelab

NASA Image and Video Library

1992-10-22

This is a Space Shuttle Columbia (STS-52) onboard photograph of the United States Microgravity Payload-1 (USMP-1) in the cargo bay. The USMP program is a series of missions developed by NASA to provide scientists with the opportunity to conduct research in the unique microgravity environment of the Space Shuttle's payload bay. The USMP-1 mission was designed for microgravity experiments that do not require the hands-on environment of the Spacelab. Science teams on the ground would remotely command and monitor instruments and analyze data from work stations at NASA's Spacelab Mission Operation Control facility at the Marshall Space Flight Center (MSFC). The USMP-1 payload carried three investigations: two studied basic fluid and metallurgical processes in microgravity, and the third would characterize the microgravity environment onboard the Space Shuttle. The three experiments that made up USMP-1 were the Lambda Point Experiment, the Space Acceleration Measurement System, and the Materials for the Study of Interesting Phenomena of Solidification Earth and in Orbit (MEPHISTO). The three experiments were mounted on two cornected Mission Peculiar Equipment Support Structures (MPESS) mounted in the orbiter's cargo bay. The USMP program was managed by the MSFC and the MPESS was developed by the MSFC.