Advanced transportation system study: Manned launch vehicle concepts for two way transportation system payloads to LEO. Work breakdown structure and work breakdown structure dictionary

NASA Technical Reports Server (NTRS)

Duffy, James B.

1992-01-01

The report describes the work breakdown structure (WBS) and its associated WBS dictionary for task area 1 of contract NAS8-39207, advanced transportation system studies (ATSS). This WBS format is consistent with the preliminary design level of detail employed by both task area 1 and task area 4 in the ATSS study and is intended to provide an estimating structure for parametric cost estimates.

DART: Delta Advanced Reusable Transport. An alternate manned space system proposal

NASA Technical Reports Server (NTRS)

1991-01-01

The Delta Advanced Reusable Transport (DART) craft is being developed to add, multiple, rapid, and cost effective space access to the U.S. capability and to further the efforts towards a permanent space presence. The DART craft provides an augmentative and an alternative system to the Shuttle. As a supplement launch vehicle, the DART adds low cost and easily accessible transport of crew and cargo to specific space destinations to the U.S. program. This adds significant opportunities for manned rated missions that do not require Shuttle capabilities. In its alternative role, the DART can provide emergency space access and satellite repair, the continuation of scientific research, and the furthering of U.S. manned efforts in the event of Shuttle incapabilities. In addition, the DART is being designed for Space Station Freedom compatibility, including its use as a 'lifeboat' emergency reentry craft for Freedom astronauts, as well as the transport of crew and cargo for station resupply.

Composite Dry Structure Cost Improvement Approach

NASA Technical Reports Server (NTRS)

Nettles, Alan; Nettles, Mindy

2015-01-01

This effort demonstrates that by focusing only on properties of relevance, composite interstage and shroud structures can be placed on the Space Launch System vehicle that simultaneously reduces cost, improves reliability, and maximizes performance, thus providing the Advanced Development Group with a new methodology of how to utilize composites to reduce weight for composite structures on launch vehicles. Interstage and shroud structures were chosen since both of these structures are simple in configuration and do not experience extreme environments (such as cryogenic or hot gas temperatures) and should represent a good starting point for flying composites on a 'man-rated' vehicle. They are used as an example only. The project involves using polymer matrix composites for launch vehicle structures, and the logic and rationale behind the proposed new methodology.

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.

Integrated hydrogen/oxygen technology applied to auxiliary propulsion systems

NASA Technical Reports Server (NTRS)

Gerhardt, David L.

1990-01-01

The purpose of the Integrated Hydrogen/Oxygen Technology (IHOT) study was to determine if the vehicle/mission needs and technology of the 1990's support development of an all cryogenic H2/O2 system. In order to accomplish this, IHOT adopted the approach of designing Integrated Auxiliary Propulsion Systems (IAPS) for a representative manned vehicle; the advanced manned launch system. The primary objectives were to develop IAPS concepts which appeared to offer viable alternatives to state-of-the-art (i.e., hypergolic, or earth-storable) APS approaches. The IHOT study resulted in the definition of three APS concepts; two cryogenic IAPS, and a third concept utilizing hypergolic propellants.

NASA study backs SSTO, urges shuttle phaseout

NASA Astrophysics Data System (ADS)

Asker, James R.

1994-03-01

A brief discusion of a Congressionally ordered NASA study on how to meet future US Government space launch needs is presented. Three options were examined: (1) improvement ofthe Space Shuttle; (2) development of expendable launch vehicles (ELVs); and (3) development of a single-stage-to-orbit (SSTO), manned vehicle that is reusable with advanced technology. After examining the three options, it was determined that the most economical approach to space access through the year 2030 would be to develop the SSTO vehicle and phase out Space Shuttle operations within 15 years and ELVs within 20 years. Other aspects of the study's findings are briefly covered.

Crew Members - First Manned Apollo Flight - Unmanned Mission Launch - Cape

NASA Image and Video Library

1968-01-22

S68-18700 (22 Jan. 1968) --- Two prime crew members of the first manned Apollo space flight were present at Cape Kennedy for the launch of the Apollo V (LM-1/Saturn 204) unmanned space mission. On left is astronaut Walter M. Schirra Jr.; and on right is astronaut R. Walter Cunningham. In background is the Apollo V stack at Launch Complex 37 ready for launch.

A Rocket Powered Single-Stage-to-Orbit Launch Vehicle With U.S. and Soviet Engineers

NASA Technical Reports Server (NTRS)

MacConochie, Ian O.; Stnaley, Douglas O.

1991-01-01

A single-stage-to-orbit launch vehicle is used to assess the applicability of Soviet Energia high-pressure-hydrocarbon engine to advanced U.S. manned space transportation systems. Two of the Soviet engines are used with three Space Shuttle Main Engines. When applied to a baseline vehicle that utilized advanced hydrocarbon engines, the higher weight of the Soviet engines resulted in a 20 percent loss of payload capability and necessitated a change in the crew compartment size and location from mid-body to forebody in order to balance the vehicle. Various combinations of Soviet and Shuttle engines were evaluated for comparison purposes, including an all hydrogen system using all Space Shuttle Main Engines. Operational aspects of the baseline vehicle are also discussed. A new mass properties program entitles Weights and Moments of Inertia (WAMI) is used in the study.

Mercury-Redstone: The first American man-rated space launch vehicle

NASA Astrophysics Data System (ADS)

Burkhalter, Bettye B.; Sharpe, Mitchell R.

1990-12-01

This paper describes the development of the Mercury-Redstone launch vehicle used by the U.S.A. in 1961 to project two manned spacecraft along suborbital ballistic trajectories. It shows that progress in ballistic missile technology dating from World War II contributed to the development of the Redstone missile, which itself was adapted for the Mercury spacecraft launch missions. Among other subjects, the proposal to use a modified Redstone as a manned launch vehicle in the proposed project Adam is recounted as is the role played by the Hermes C1. Particular attention is focused on the engineering adaptations and rigid reliability program of the Redstone missile to fulfill the requirements of launching man. The process of "man-rating" the Mercury-Redstone for this category of mission is explained. Also described are the design, development, and testing procedures developed for Mercury-Redstone. Key points in the design process and decisions made to insure mission success and astronaut safety are reviewed. Finally, the results of the flights of the Mercury Freedom 7 spacecraft piloted by Astronaut Alan B. Shepard on 6 May 1961 and the Mercury Liberty Bell 7 spacecraft piloted by Astronaut Virgil I. Grissom on 21 July 1961 are summarized.

Radar waveform requirements for reliable detection of an aircraft-launched missile

NASA Astrophysics Data System (ADS)

Blair, W. Dale; Brandt-Pearce, Maite

1996-06-01

When tracking a manned aircraft with a phase array radar, detecting a missile launch (i.e., a target split) is particularly important because the missile can have a very small radar cross section (RCS) and drop below the horizon of the radar shortly after launch. Reliable detection of the launch is made difficult because the RCS of the missile is very small compared to that of the manned aircraft and the radar typically revisits a manned aircraft every few seconds. Furthermore, any measurements of the aircraft and missile taken shortly after the launch will be merged until the two targets are resolved in range, frequency, or space. In this paper, detection of the launched missile is addressed through the detection of the presence of target multiplicity with the in-phase and quadrature monopulse measurements. The probability of detecting the launch using monopulse processing will be studied with regard to the tracking signal-to-noise ratio and the number of pulses n the radar waveform.

Ascent performance issues of a vertical-takeoff rocket launch vehicle

NASA Astrophysics Data System (ADS)

Powell, Richard W.; Naftel, J. C.; Cruz, Christopher I.

1991-04-01

Advanced manned launch systems studies under way at the NASA Langley Research Center are part of a broader effort that is examining options for the next manned space transportation system to be developed by the United States. One promising concept that uses near-term technologies is a fully reusable, two-stage vertical-takeoff rocket vehicle. This vehicle features parallel thrusting of the booster and orbiter with the booster cross-feeding the propellant to the orbiter until staging. In addition, after staging, the booster glides back unpowered to the launch site. This study concentrated on two issues that could affect the ascent performance of this vehicle. The first is the large gimbal angle range required for pitch trim until staging because of the propellant cross-feed. Results from this analysis show that if control is provided by gimballing of the rocket engines, they must gimbal greater than 20 deg, which is excessive when compared with current vehicles. However, this analysis also showed that this limit could be reduced to 10 deg if gimballing were augmented by throttling the booster engines. The second issue is the potential influence of off-nominal atmospheric conditions (density and winds) on the ascent performance. This study showed that a robust guidance algorithm could be developed that would insure accurate insertion, without prelaunch atmospheric knowledge.

Vented Launch Vehicle Adaptor for a Manned Spacecraft with "Pusher" Launch Abort System

NASA Technical Reports Server (NTRS)

Vandervort, Robert E. (Inventor)

2017-01-01

A system, method, and apparatus for a vented launch vehicle adaptor (LVA) for a manned spacecraft with a "pusher" launch abort system are disclosed. The disclosed LVA provides a structural interface between a commercial crew vehicle (CCV) crew module/service module (CM/SM) spacecraft and an expendable launch vehicle. The LVA provides structural attachment of the module to the launch vehicle. It also provides a means to control the exhaust plume from a pusher-type launch abort system that is integrated into the module. In case of an on-pad or ascent abort, which requires the module to jettison away from the launch vehicle, the launch abort system exhaust plume must be safely directed away from critical and dangerous portions of the launch vehicle in order to achieve a safe and successful jettison.

Geostationary platform study: Advanced ESGP/evolutionary SSF accommodation study

NASA Technical Reports Server (NTRS)

1990-01-01

The implications on the evolutionary space station of accommodating geosynchronous Earth Orbit (GEO) facilities including unmanned satellites and platforms, manned elements, and transportation and servicing vehicles/elements. The latest existing definitions of typical unmanned GEO facilities and transportation and servicing vehicles/elements are utilized. The physical design, functional design, and operations implications at the space station are determined. Various concepts of the space station from past studies are utilized ranging from the IOC Multifunction Space Station to a branched transportation node space station, and the implications of the accommodation the GEO infrastructure of each type are assessed. Where possible, parametric data are provided to show the implications of variations in sizes and quantities of elements, launch rates, crew sizes, etc. The use of advanced automation, robotics equipment, and an efficient mix of manned/automated support for accomplishing necessary activities at the space station are identified and assessed. The products of this study are configuration sketches, resource requirements, trade studies, and parametric data.

Development of Advanced Plant Habitat Flight Unit

NASA Technical Reports Server (NTRS)

Johnson, Curtis J., Jr

2013-01-01

With NASA's current goals and resources moving forward to bring the idea of Manned Deep-Space missions from a long-thought concept to a reality, innovative research methods and expertise are being utilized for studies that integrate human needs with that of technology to make for the most efficient operations possible. Through the capability to supply food, provide oxygen from what was once carbon dioxide, and various others which help to make plant research one of the prime factors of future long-duration mission, the Advanced Plant Habitat will be the largest microgravity plant growth chamber on the International Space Station when it is launched in the near future (2014- 2015). Soon, the Advanced Plant Habitat unit will continue on and enrich the discoveries and studies on the long-term effects of microgravity on plants.

LAUNCH - APOLLO 9 - CAPE

NASA Image and Video Library

1969-03-03

S69-25861 (3 March 1969) --- The Apollo 9 (Spacecraft 104/Lunar Module 3/ Saturn 504) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC) at 11 a.m. (EST), March 3, 1969. Aboard the spacecraft are astronauts James A. McDivitt, commander; David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight. Apollo 9 is the second manned Saturn V mission.

A Personnel Launch System for safe and efficient manned operations

NASA Astrophysics Data System (ADS)

Petro, Andrew J.; Andrews, Dana G.; Wetzel, Eric D.

1990-10-01

Several Conceptual designs for a simple, rugged Personnel Launch System (PLS) are presented. This system could transport people to and from Low Earth Orbit (LEO) starting in the late 1990's using a new modular Advanced Launch System (ALS) developed for the Space Exploration Initiative (SEI). The PLS is designed to be one element of a new space transportation architecture including heavy-lift cargo vehicles, lunar transfer vehicles, and multiple-role spcecraft such as the current Space Shuttle. The primary role of the PLS would be to deliver crews embarking on lunar or planetary missions to the Space Station, but it would also be used for earth-orbit sortie missions, space rescue missions, and some satellite servicing missions. The PLS design takes advantage of emerging electronic and structures technologies to offer a robust vehicle with autonomous operating and quick turnaround capabilities. Key features include an intact abort capability anywhere in the operating envelope, and elimination of all toxic propellants to streamline ground operations.

Laser-boosted lightcraft technology demonstrator

NASA Technical Reports Server (NTRS)

Antonison, M.; Myrabo, Leik; Chen, S.; Decusatis, C.; Kusche, K.; Minucci, M.; Moder, J.; Morales, C.; Nelson, C.; Richard, J.

1989-01-01

The ultimate goal for this NASA/USRA-sponsored 'Apollo Lightcraft Project' is to develop a revolutionary manned launch vehicle technology that can potentially reduce payload transport costs by a factor of 1000 below the space shuttle orbiter. The Rensellaer design team proposes to utilize advanced, highly energetic, beamed-energy sources (laser, microwave) and innovative combined-cycle (airbreathing/rocket) engines to accomplish this goal. This year's effort, the detailed description and performance analysis of an unmanned 1.4-m Lightcraft Technology Demonstrator (LTD) drone, is presented. The novel launch system employs a 100-MW-class ground-based laser to transmit power directly to an advanced combined-cycle engine that propels the 120-kg LTD to orbit, with a mass ratio of two. The single-stage-to-orbit (SSTO) LTD machine then becomes an autonomous sensor satellite that can deliver precise, high-quality information typical of today's large orbital platforms. The dominant motivation behind this study is to provide an example of how laser propulsion and its low launch costs can induce a comparable order-of-magnitude reduction in sensor satellite packaging costs. The issue is simply one of production technology for future, survivable SSTO aerospace vehicles that intimately share both laser propulsion engine and satellite functional hardware. A mass production cost goal of 10(exp 3)/kg for the LTD vehicle is probably realizable.

Two stage launch vehicle

NASA Technical Reports Server (NTRS)

1987-01-01

The Advanced Space Design project for 1986-87 was the design of a two stage launch vehicle, representing a second generation space transportation system (STS) which will be needed to support the space station. The first stage is an unmanned winged booster which is fully reusable with a fly back capability. It has jet engines so that it can fly back to the landing site. This adds safety as well as the flexibility to choose alternate landing sites. There are two different second stages. One of the second stages is a manned advanced space shuttle called Space Shuttle II. Space Shuttle II has a payload capability of delivering 40,000 pounds to the space station in low Earth orbit (LEO), and returning 40,000 pounds to Earth. Servicing the space station makes the ability to return a heavy payload to Earth as important as being able to launch a heavy payload. The other second stage is an unmanned heavy lift cargo vehicle with ability to deliver 150,000 pounds of payload to LEO. This vehicle will not return to Earth; however, the engines and electronics can be removed and returned to Earth in the Space Shuttle II. The rest of the vehicle can then be used on orbit for storage or raw materials, supplies, and space manufactured items awaiting transport back to Earth.

Project APEX: Advanced manned exploration of the Martian moon Phobos

NASA Technical Reports Server (NTRS)

Eisley, Joe G.; Akers, Jim

1992-01-01

A preliminary design has been developed for a manned mission to the Martian moon Phobos. The spacecraft is to carry a crew of five and will be launched from Low Earth Orbit in the year 2010. The outbound trajectory to Mars uses a gravitational assisted swingby of Venus and takes eight months to complete. The stay at Phobos is scheduled for 60 days. During this time, the crew will be busily engaged in setting up a prototype fuel processing facility. The vehicle will then return to Earth orbit after a total mission duration of 656 days. The spacecraft is powered by three nuclear thermal rockets which also provide the primary electrical power via dual mode operation. The overall spacecraft length is 110 m, and the total mass departing from Low Earth Orbit is 900 metric tons.

LAUNCH - APOLLO 9 - CAPE

NASA Image and Video Library

1969-03-03

S69-25862 (3 March 1969) --- Framed by palm trees in the foreground, the Apollo 9 (Spacecraft 104/Lunar Module 3/ Saturn 504) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC) at 11 a.m. (EST), March 3, 1969. Aboard the spacecraft are astronauts James A. McDivitt, commander; David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight. Apollo 9 is the second manned Saturn V mission.

NASA Launches Five Rockets in Five Minutes

NASA Image and Video Library

2017-12-08

NASA image captured March 27, 2012 NASA successfully launched five suborbital sounding rockets this morning from its Wallops Flight Facility in Virginia as part of a study of the upper level jet stream. The first rocket was launched at 4:58 a.m. EDT and each subsequent rocket was launched 80 seconds apart. Each rocket released a chemical tracer that created milky, white clouds at the edge of space. Tracking the way the clouds move can help scientists understand the movement of the winds some 65 miles up in the sky, which in turn will help create better models of the electromagnetic regions of space that can damage man-made satellites and disrupt communications systems. The launches and clouds were reported to be seen from as far south as Wilmington, N.C.; west to Charlestown, W. Va.; and north to Buffalo, N.Y. Credit: NASA/Wallops To watch a video of the launch and to read more go to: www.nasa.gov/mission_pages/sunearth/missions/atrex-launch... 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

NASA Launches Five Rockets in Five Minutes

NASA Image and Video Library

2012-03-27

NASA image captured March 27, 2012 NASA successfully launched five suborbital sounding rockets this morning from its Wallops Flight Facility in Virginia as part of a study of the upper level jet stream. The first rocket was launched at 4:58 a.m. EDT and each subsequent rocket was launched 80 seconds apart. Each rocket released a chemical tracer that created milky, white clouds at the edge of space. Tracking the way the clouds move can help scientists understand the movement of the winds some 65 miles up in the sky, which in turn will help create better models of the electromagnetic regions of space that can damage man-made satellites and disrupt communications systems. The launches and clouds were reported to be seen from as far south as Wilmington, N.C.; west to Charlestown, W. Va.; and north to Buffalo, N.Y. Credit: NASA/Wallops To watch a video of the launch and to read more go to: www.nasa.gov/mission_pages/sunearth/missions/atrex-launch... 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

Manned Mars mission cost estimate

NASA Technical Reports Server (NTRS)

Hamaker, Joseph; Smith, Keith

1986-01-01

The potential costs of several options of a manned Mars mission are examined. A cost estimating methodology based primarily on existing Marshall Space Flight Center (MSFC) parametric cost models is summarized. These models include the MSFC Space Station Cost Model and the MSFC Launch Vehicle Cost Model as well as other modes and techniques. The ground rules and assumptions of the cost estimating methodology are discussed and cost estimates presented for six potential mission options which were studied. The estimated manned Mars mission costs are compared to the cost of the somewhat analogous Apollo Program cost after normalizing the Apollo cost to the environment and ground rules of the manned Mars missions. It is concluded that a manned Mars mission, as currently defined, could be accomplished for under $30 billion in 1985 dollars excluding launch vehicle development and mission operations.

Transforming KSC to be the World's Premier 21st Century Launch Complex

NASA Technical Reports Server (NTRS)

Engler, Tom

2011-01-01

This slide presentation reviews the work being done to transform the Kennedy Space Center into what is hoped to be the world's premier launch complex, capable of launching commercial and government satellites and manned spacecraft.

GEMINI SPACECRAFT - ARTIST CONCEPT

NASA Image and Video Library

1964-01-01

S64-22331 (1964) --- Artist concept illustrating the relative sizes of the one-man Mercury spacecraft, the two-man Gemini spacecraft, and the three-man Apollo spacecraft. Also shows line drawing of launch vehicles to show their relative size in relation to each other. Photo credit: NASA

Saturn Apollo Program

NASA Image and Video Library

1973-05-01

SA-206 lifts off from Kennedy Space Center's launch complex 39B, in Florida, on May 25, 1973, for the first manned Skylab mission (SL-2) with astronauts Pete Conrad, Joseph Kerwin, and Paul Weitz. The Saturn IB, developed under the direction of the Marshall Space Flight Center (MSFC), launched five manned Earth-orbital missions between 1968 and 1975: Apollo 7, Skylab 2, Skylab 3, Skylab 4, and the Apollo-Soyuz Test Project (ASTP).

46 CFR 122.520 - Abandon ship and man overboard drills and training.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 46 Shipping 4 2014-10-01 2014-10-01 false Abandon ship and man overboard drills and training. 122... OPERATIONS Preparations for Emergencies § 122.520 Abandon ship and man overboard drills and training. (a) The... launched with its assigned crew aboard and maneuvered in the water as if during the actual man overboard...

46 CFR 122.520 - Abandon ship and man overboard drills and training.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 46 Shipping 4 2012-10-01 2012-10-01 false Abandon ship and man overboard drills and training. 122... OPERATIONS Preparations for Emergencies § 122.520 Abandon ship and man overboard drills and training. (a) The... launched with its assigned crew aboard and maneuvered in the water as if during the actual man overboard...

46 CFR 122.520 - Abandon ship and man overboard drills and training.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 46 Shipping 4 2013-10-01 2013-10-01 false Abandon ship and man overboard drills and training. 122... OPERATIONS Preparations for Emergencies § 122.520 Abandon ship and man overboard drills and training. (a) The... launched with its assigned crew aboard and maneuvered in the water as if during the actual man overboard...

46 CFR 122.520 - Abandon ship and man overboard drills and training.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 4 2011-10-01 2011-10-01 false Abandon ship and man overboard drills and training. 122... OPERATIONS Preparations for Emergencies § 122.520 Abandon ship and man overboard drills and training. (a) The... launched with its assigned crew aboard and maneuvered in the water as if during the actual man overboard...

Advanced Durability and Damage Tolerance Design and Analysis Methods for Composite Structures: Lessons Learned from NASA Technology Development Programs

NASA Technical Reports Server (NTRS)

Harris, Charles E.; Starnes, James H., Jr.; Shuart, Mark J.

2003-01-01

Aerospace vehicles are designed to be durable and damage tolerant. Durability is largely an economic life-cycle design consideration whereas damage tolerance directly addresses the structural airworthiness (safety) of the vehicle. However, both durability and damage tolerance design methodologies must address the deleterious effects of changes in material properties and the initiation and growth of microstructural damage that may occur during the service lifetime of the vehicle. Durability and damage tolerance design and certification requirements are addressed for commercial transport aircraft and NASA manned spacecraft systems. The state-of-the-art in advanced design and analysis methods is illustrated by discussing the results of several recently completed NASA technology development programs. These programs include the NASA Advanced Subsonic Technology Program demonstrating technologies for large transport aircraft and the X-33 hypersonic test vehicle demonstrating technologies for a single-stage-to-orbit space launch vehicle.

Performance potential of gas-core and fusion rockets - A mission applications survey.

NASA Technical Reports Server (NTRS)

Fishbach, L. H.; Willis, E. A., Jr.

1971-01-01

This paper reports an evaluation of the performance potential of five nuclear rocket engines for four mission classes. These engines are: the regeneratively cooled gas-core nuclear rocket; the light bulb gas-core nuclear rocket; the space-radiator cooled gas-core nuclear rocket; the fusion rocket; and an advanced solid-core nuclear rocket which is included for comparison. The missions considered are: earth-to-orbit launch; near-earth space missions; close interplanetary missions; and distant interplanetary missions. For each of these missions, the capabilities of each rocket engine type are compared in terms of payload ratio for the earth launch mission or by the initial vehicle mass in earth orbit for space missions (a measure of initial cost). Other factors which might determine the engine choice are discussed. It is shown that a 60 day manned round trip to Mars is conceivable.-

Optimal control theory determination of feasible return-to-launch-site aborts for the HL-20 Personnel Launch System vehicle

NASA Technical Reports Server (NTRS)

Dutton, Kevin E.

1994-01-01

The personnel launch system (PLS) being studied by NASA is a system to complement the space shuttle and provide alternative access to space. The PLS consists of a manned spacecraft launched by an expendable launch vehicle (ELV). A candidate for the manned spacecraft is the HL-20 lifting body. In the event of an ELV malfunction during the initial portion of the ascent trajectory, the HL-20 will separate from the rocket and perform an unpowered return to launch site (RTLS) abort. This work details an investigation, using optimal control theory, of the RTLS abort scenario. The objective of the optimization was to maximize final altitude. With final altitude as the cost function, the feasibility of an RTLS abort at different times during the ascent was determined. The method of differential inclusions was used to determine the optimal state trajectories, and the optimal controls were then calculated from the optimal states and state rates.

KSC-2012-1846

NASA Image and Video Library

2012-02-17

Apollo/Saturn Program: In January 1962, NASA initiated development of the large launch vehicle for the Project Apollo manned lunar flights. The Saturn V configuration comprised the S-IC first stage, the S-II second stage and the S-IVB third stage, all integrated and stacked in the Vehicle Assembly Building. The first manned Apollo spacecraft launched on the mighty Saturn V was Apollo 8 on December 21, 1968. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

Catalog of lunar mission data

NASA Technical Reports Server (NTRS)

Mantel, E. J. (Editor); Miller, E. R. (Editor)

1977-01-01

Several series of spacecraft were developed, designed, built and launched to determine different characteristics of the lunar surface and environment for a manned landing. Both unmanned and manned spacecrafts, spacecraft equipment and lunar missions are documented.

LIFTOFF - APOLLO/SATURN (A/S)-202 MISSION - KSC

NASA Image and Video Library

1966-08-25

A/S Mission 202 was launched from the KSC Launch Complex (LC)-34 at 12:15 p.m., 08/25/1966. The mission was a step toward qualifying the Apollo Command and Service Modules (CSM)'s and the uprated Saturn I launch vehicle for manned flight. KSC, FL

Corrosion Protection for Space and Beyond

NASA Technical Reports Server (NTRS)

Calle, Luz Marina

2007-01-01

Florida is home to NASA's Launch Operations Center. Since its establishment in July 1962, the spaceport has served as the departure gate for every American manned mission and hundreds of advanced scientific spacecraft under the Launch Services Program. The center was renamed the John F. Kennedy Space Center in late 1963 to honor the president who put America on the path to the moon. Today, NASA is on the edge of a bold new chaIlenge: the ConsteIlation Program. ConsteIlation is a NASA program to create a new generation of spacecraft for human spaceflight, consisting primarily of the Ares I and Ares V launch vehicles, the Orion crew capsule, the Earth Departure stage and the Lunar access module. These spacecraft will be capable of performing a variety of missions, from Space Station resupply to lunar landings. The ambitious new endeavor caIls for NASA to return human explorers to the moon and then venture even farther, to Mars and beyond. As the nation's premier spaceport, Kennedy Space Center (KSC) will playa critical role in this new chapter in exploration, particularly in the conversion of the launch facilities to accommodate the new launch vehicles. To prepare for this endeavor, the launch site and facilities for the next generation of crew and cargo vehicles must be redesigned, assembled and tested. One critical factor that is being carefuIly considered during the renovation is protecting the new facilities and structures from corrosion and deterioration.

Launch - Apollo 9 - KSC

NASA Image and Video Library

1969-03-03

S69-25881 (3 March 1969) --- The Apollo 9 crew leaves the Kennedy Space Center's Manned Spacecraft Operations Building during the Apollo 9 prelaunch countdown. The crewman entered the special transfer van which transported them to their waiting spacecraft at Pad A, Launch Complex 39. Astronaut James A. McDivitt (back to camera) is the commander. McDivitt appears to be inviting astronaut David R. Scott, command module pilot, to step first into van. In background is astronaut Russell L. Schweickart, lunar module pilot. Walking along almost behind Schweickart is astronaut Alan B. Shepard Jr., chief, Astronaut Office, Manned Spacecraft Center. Apollo 9 was launched at 11 a.m. (EST), March 3, 1969, on a 10-day Earth-orbital mission.

Apollo 11 Launched Via Saturn V Rocket

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Developed by the Marshall Space Flight Center (MSFC), the Saturn V vehicle produced a holocaust of flames as it rose from its pad at Launch complex 39. The 363 foot tall, 6,400,000 pound rocket hurled the spacecraft into Earth parking orbit and then placed it on the trajectory to the moon for man's first lunar landing. Aboard the spacecraft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Apollo 11 Launched Via Saturn V Rocket

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. The Saturn V vehicle produced a holocaust of flames as it rose from its pad at Launch complex 39. The 363 foot tall, 6,400,000 pound rocket hurled the spacecraft into Earth parking orbit and then placed it on the trajectory to the moon for man's first lunar landing. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module pilot; and Edwin E. Aldrin Jr., Lunar Module pilot. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Propulsion requirements for reusable single-stage-to-orbit rocket vehicles

NASA Astrophysics Data System (ADS)

Stanley, Douglas O.; Engelund, Walter C.; Lepsch, Roger

1994-05-01

The conceptual design of a single-stage-to-orbit (SSTO) vehicle using a wide variety of evolutionary technologies has recently been completed as a part of NASA's Advanced Manned Launch System (AMLS) study. The employment of new propulsion system technologies is critical to the design of a reasonably sized, operationally efficient SSTO vehicle. This paper presents the propulsion system requirements identified for this near-term AMLS SSTO vehicle. Sensitivities of the vehicle to changes in specific impulse and sea-level thrust-to-weight ratio are examined. The results of a variety of vehicle/propulsion system trades performed on the near-term AMLS SSTO vehicle are also presented.

Requirement for a standard language for test and ground operations

NASA Technical Reports Server (NTRS)

Medlock, J. R.

1971-01-01

The basic requirements for a standard test and checkout language applicable to all phases of the space shuttle test and ground operations are determined. The general characteristics outlined here represent the integration of selected ideas and concepts from operational elements within Kennedy Space Center (KSC) that represent diverse disciplines associated with space vehicle testing and launching operations. Special reference is made to two studies conducted in this area for KSC as authorized by the Advanced Development Element of the Office of Manned Space Flight (MSF). Information contained in reports from these studies have contributed significantly to the final selection of language features depicted in this technical report.

Life support system definition for a low cost shuttle launched space station.

NASA Technical Reports Server (NTRS)

Nelson, W. G.; Cody, J.

1972-01-01

Discussion of the tradeoffs and EC/LS definition for a low cost shuttle launched space station to be launched in the late 1970s for use as a long-term manned scientific laboratory. The space station consists of 14-ft-diam modules, clustered together to support a six-man crew at the initial space station (ISS) level and a 12-man crew at the growth space station (GSS) level. Key design guidelines specify low initial cost and low total program cost and require two separate pressurized habitable compartments with independent lift support capability. The methodology used to select the EC/LS design consisted of systematically reducing quantitative parameters to a common denominator of cost. This approach eliminates many of the inconsistencies that can occur in such decision making. The EC/LS system selected is a partially closed system which recovers urine, condensate, and wash water and concentrates crew expired CO2 for use in a low thrust resistojet propulsion system.

Official Portrait of Astronaut Neil Armstrong

NASA Technical Reports Server (NTRS)

1969-01-01

Neil Armstrong, donned in his space suit, poses for his official Apollo 11 portrait. Armstrong began his flight career as a naval aviator. He flew 78 combat missions during the Korean War. Armstrong joined the NASA predecessor, NACA (National Advisory Committee for Aeronautics), as a research pilot at the Lewis Laboratory in Cleveland and later transferred to the NACA High Speed Flight Station at Edwards AFB, California. He was a project pilot on many pioneering high speed aircraft, including the 4,000 mph X-15. He has flown over 200 different models of aircraft, including jets, rockets, helicopters, and gliders. In 1962, Armstrong was transferred to astronaut status. He served as command pilot for the Gemini 8 mission, launched March 16, 1966, and performed the first successful docking of two vehicles in space. In 1969, Armstrong was commander of Apollo 11, the first manned lunar landing mission, and gained the distinction of being the first man to land a craft on the Moon and the first man to step on its surface. Armstrong subsequently held the position of Deputy Associate Administrator for Aeronautics, NASA Headquarters Office of Advanced Research and Technology, from 1970 to 1971. He resigned from NASA in 1971.

Saturn Apollo Program

NASA Image and Video Library

1969-01-09

Neil Armstrong, donned in his space suit, poses for his official Apollo 11 portrait. Armstrong began his flight career as a naval aviator. He flew 78 combat missions during the Korean War. Armstrong joined the NASA predecessor, NACA (National Advisory Committee for Aeronautics), as a research pilot at the Lewis Laboratory in Cleveland and later transferred to the NACA High Speed Flight Station at Edwards AFB, California. He was a project pilot on many pioneering high speed aircraft, including the 4,000 mph X-15. He has flown over 200 different models of aircraft, including jets, rockets, helicopters, and gliders. In 1962, Armstrong was transferred to astronaut status. He served as command pilot for the Gemini 8 mission, launched March 16, 1966, and performed the first successful docking of two vehicles in space. In 1969, Armstrong was commander of Apollo 11, the first manned lunar landing mission, and gained the distinction of being the first man to land a craft on the Moon and the first man to step on its surface. Armstrong subsequently held the position of Deputy Associate Administrator for Aeronautics, NASA Headquarters Office of Advanced Research and Technology, from 1970 to 1971. He resigned from NASA in 1971.

A Dynamic Risk Model for Evaluation of Space Shuttle Abort Scenarios

NASA Technical Reports Server (NTRS)

Henderson, Edward M.; Maggio, Gaspare; Elrada, Hassan A.; Yazdpour, Sabrina J.

2003-01-01

The Space Shuttle is an advanced manned launch system with a respectable history of service and a demonstrated level of safety. Recent studies have shown that the Space Shuttle has a relatively low probability of having a failure that is instantaneously catastrophic during nominal flight as compared with many US and international launch systems. However, since the Space Shuttle is a manned. system, a number of mission abort contingencies exist to primarily ensure the safety of the crew during off-nominal situations and to attempt to maintain the integrity of the Orbiter. As the Space Shuttle ascends to orbit it transverses various intact abort regions evaluated and planned before the flight to ensure that the Space Shuttle Orbiter, along with its crew, may be returned intact either to the original launch site, a transoceanic landing site, or returned from a substandard orbit. An intact abort may be initiated due to a number of system failures but the highest likelihood and most challenging abort scenarios are initiated by a premature shutdown of a Space Shuttle Main Engine (SSME). The potential consequences of such a shutdown vary as a function of a number of mission parameters but all of them may be related to mission time for a specific mission profile. This paper focuses on the Dynamic Abort Risk Evaluation (DARE) model process, applications, and its capability to evaluate the risk of Loss Of Vehicle (LOV) due to the complex systems interactions that occur during Space Shuttle intact abort scenarios. In addition, the paper will examine which of the Space Shuttle subsystems are critical to ensuring a successful return of the Space Shuttle Orbiter and crew from such a situation.

Apollo 11 Launched Via Saturn V Rocket

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. The Saturn V vehicle produced a holocaust of flames as it rose from its pad at Launch complex 39. The 363 foot tall, 6,400,000 pound rocket hurled the spacecraft into Earth parking orbit and then placed it on the trajectory to the moon for man's first lunar landing. The Saturn V was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun. Aboard the spacecraft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module pilot; and Edwin E. Aldrin Jr., Lunar Module pilot. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Research on sleep, circadian rhythms and aging - Applications to manned spaceflight

NASA Technical Reports Server (NTRS)

Czeisler, Charles A.; Chiasera, August J.; Duffy, Jeanne F.

1991-01-01

Disorders of sleep and circadian rhythmicity are characteristic of both advancing age and manned spaceflight. Sleep fragmentation, reduced nocturnal sleep tendency and sleep efficiency, reduced daytime alertness, and increased daytime napping are common to both of these conditions. Recent research on the pathophysiology and treatment of disrupted sleep in older people has led to a better understanding of how the human circadian pacemaker regulates the timing of the daily sleep-wake cycle and how it responds to the periodic changes in the light-dark cycle to which we are ordinarily exposed. These findings have led to new treatments for some of the sleep disorders common to older individuals, using carefully timed exposure to bright light and darkness to manipulate the phase and/or amplitude of the circadian timing system. These insights and treatment approaches have direct applications in the design of countermeasures allowing astronauts to overcome some of the challenges which manned spaceflight poses for the human circadian timing system. We have conducted an operational feasibility study on the use of scheduled exposure to bright light and darkness prior to launch in order to facilitate adaptation of the circadian system of a NASA Space Shuttle crew to the altered sleep-wake schedule required for their mission. The results of this study illustrate how an understanding of the properties of the human circadian timing system and the consequences of circadian disruption can be applied to manned spaceflight.

Research on sleep, circadian rhythms and aging: applications to manned spaceflight.

PubMed

Czeisler, C A; Chiasera, A J; Duffy, J F

1991-01-01

Disorders of sleep and circadian rhythmicity are characteristic of both advancing age and manned spaceflight. Sleep fragmentation, reduced nocturnal sleep tendency and sleep efficiency, reduced daytime alertness, and increased daytime napping are common to both of these conditions. Recent research on the pathophysiology and treatment of disrupted sleep in older people has led to a better understanding of how the human circadian pacemaker regulates the timing of the daily sleep-wake cycle and how it responds to the periodic changes in the light-dark cycle to which we are ordinarily exposed. These findings have led to new treatments for some of the sleep disorders common to older individuals, using carefully timed exposure to bright light and darkness to manipulate the phase and/or amplitude of the circadian timing system. These insights and treatment approaches have direct applications in the design of countermeasures allowing astronauts to overcome some of the challenges which manned spaceflight poses for the human circadian timing system. We have conducted an operational feasibility study on the use of scheduled exposure to bright light and darkness prior to launch in order to facilitate adaptation of the circadian system of a NASA space shuttle crew to the altered sleep-wake schedule required for their mission. The results of this study illustrate how an understanding of the properties of the human circadian timing system and the consequences of circadian disruption can be applied to manned spaceflight.

General Thomas Dresser White: Renaissance Man in a Dark Age

DTIC Science & Technology

2015-06-01

Interview with Maj Gen Haywood S. Hansell,” interview by Edgar F. Puryear, Jr., February 25, 1979 , Air Force Historical Research Agency. 66 Puryear...man in space, the Air Force collaborated with NASA to develop the Dyna- Soar , a manned spacecraft launched via a Titan rocket and returned as a...glider. For White, “The Dyna- Soar …is the first vehicle which will combine the advantages of manned aircraft and missiles into a

APOLLO VIII - LAUNCH - KSC

NASA Image and Video Library

1968-12-21

S68-56002 (21 Dec. 1968) --- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 was the first manned Saturn V launch. (F-ls 1/3 way from top of mobile launch tower.)

Launch of Apollo 8 lunar orbit mission

NASA Image and Video Library

1968-12-21

S68-56001 (21 Dec. 1968) --- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center, at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 was the first manned Saturn V launch. (Just after ignition)

75 FR 37742 - Addition of New Export Control Classification Number 6A981 Passive Infrasound Sensors to the...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-06-30

... or man-made infrasound sources including earthquakes, volcanic eruptions, rocket launch, and/or... rocket launch and/or nuclear explosions, or whether the parameters are overly broad. If the controls are...

Flight Performance of a Man Portable Guided Projectile Concept

DTIC Science & Technology

2014-02-01

include precision guided technologies. The focus of this study is maneuvering projectiles launched from man portable weapon systems . A novel guided...5 Figure 5. Body-fixed coordinate system and aerodynamic angles...20 Figure 20. Earth and body-fixed coordinate systems and Euler angles. ........................................24

Preliminary definition of a lunar landing and launch facility (Complex 39L)

NASA Technical Reports Server (NTRS)

Matthews, H. Dennis; Jenson, Eric B.; Linsley, Jerald N.

1992-01-01

A preliminary definition of a lunar landing and launch facility has been formulated. A permanently manned lunar base and a baseline lunar module are assumed. The major features of the facility are specified and major design areas are described.

Apollo 7 - Press Kit

NASA Technical Reports Server (NTRS)

1968-01-01

Contents include the following: General release. Mission objectives. Mission description. Flight plan. Alternate missions. Experiments. Abort model. Spacecraft structure system. The Saturn 1B launch vehicle. Flight sequence. Launch preparations. Mission control center-Houston. Manned space flight network. Photographic equipment. Apollo 7 crew. Apollo 7 test program.

Launch of Apollo 8 lunar orbit mission

NASA Image and Video Library

1968-12-21

S68-56050 (21 Dec. 1968)--- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 is the first manned Saturn V launch. (water in foreground, seagulls)

Launch vehicle test and checkout plan. - Volume 2: Saturn 1B launch vehicle Skylab R (rescue) and AS-208 flow plan and listings

NASA Technical Reports Server (NTRS)

1973-01-01

The launch operations test and checkout plan is a planning document that establishes all launch site checkout activity, including the individual tests and sequence of testing required to fulfill the development center and KSC test and checkout requirements. This volume contains the launch vehicle test and checkout plan encompassing S-1B, S-4B, IU stage, and ground support equipment tests. The plan is based upon AS-208 flow utilizing a manned spacecraft, LUT 1, and launch pad 39B facilities.

The exploration about the means of lunar-landing based on space-launch

NASA Astrophysics Data System (ADS)

Yi, Jiang; Zheming, Zhang; Debin, Fu

The lunar exploration and lunar-landing is the first step of china s deep space exploration On the basement of our country s achievements and the experiences of the foreign countries the paper brings forward the idea that use the existing transportation technology to sent the Launch vehicles and cosmonauts to the near-earth orbit in batches assemble the components together on the Space-launch Platform and then launch them to the Moon to fulfill our dream of manned landing on the moon The paper also discusses the Space-launch Platform and the launching way

Proceedings of the Second Manned Space Flight Meeting

NASA Technical Reports Server (NTRS)

1964-01-01

The papers presented in this report represent the classified portion of the Second Manned Space Flight Meeting which was held in Dallas, TX, on April 22-24, 1963. The meeting was co-sponsored by the American Institute of Aeronautics and Astronautics and the National Aeronautics and Space Administration. The following subjects are discussed in the report: Manned Space Flight Programs, Launch Vehicles, Spacecraft Design, and Guidance and Control.

Performance Optimization of the Gasdynamic Mirror Propulsion System

NASA Technical Reports Server (NTRS)

Emrich, William J., Jr.; Kammash, Terry

1999-01-01

Nuclear fusion appears to be a most promising concept for producing extremely high specific impulse rocket engines. Engines such as these would effectively open up the solar system to human exploration and would virtually eliminate launch window restrictions. A preliminary vehicle sizing and mission study was performed based on the conceptual design of a Gasdynamic Mirror (GDM) fusion propulsion system. This study indicated that the potential specific impulse for this engine is approximately 142,000 sec. with about 22,100 N of thrust using a deuterium-tritium fuel cycle. The engine weight inclusive of the power conversion system was optimized around an allowable engine mass of 1500 Mg assuming advanced superconducting magnets and a Field Reversed Configuration (FRC) end plug at the mirrors. The vehicle habitat, lander, and structural weights are based on a NASA Mars mission study which assumes the use of nuclear thermal propulsion' Several manned missions to various planets were analyzed to determine fuel requirements and launch windows. For all fusion propulsion cases studied, the fuel weight remained a minor component of the total system weight regardless of when the missions commenced. In other words, the use of fusion propulsion virtually eliminates all mission window constraints and effectively allows unlimited manned exploration of the entire solar system. It also mitigates the need to have a large space infrastructure which would be required to support the transfer of massive amounts of fuel and supplies to lower a performing spacecraft.

Space Operations Center - A concept analysis

NASA Technical Reports Server (NTRS)

1980-01-01

The Space Operations Center (SOC) which is a concept for a Shuttle serviced, permanent, manned facility in low earth orbit is viewed as a major candidate for the manned space flight following the completion of an operational Shuttle. The primary objectives of SOC are: (1) the construction, checkout, and transfer to operational orbit of large, complex space systems, (2) on-orbit assembly, launch, recovery, and servicing of manned and unmanned spacecraft, (3) managing operations of co-orbiting free-flying satellites, and (4) the development of reduced dependence on earth for control and resupply. The structure of SOC, a self-contained orbital facility containing several Shuttle launched modules, includes the service, habitation, and logistics modules as well as construction, and flight support facilities. A schedule is proposed for the development of SOC over ten years and costs for the yearly programs are estimated.

An Analysis of Undersea Glider Architectures and an Assessment of Undersea Glider Integration into Undersea Applications

DTIC Science & Technology

2012-09-01

Marine Mammal Survey • Inspection and Security • Environmental Monitoring Launch & Recovery • Man Portable (1-2 people) Features • Length: 2.2 m...Oceanography & Science • Pollution Detection • Water Quality Monitoring • Rapid Environment Assessment • Marine Mammals Assessment Launch & Recovery...Figure 29. Slocum Electric Launch from Surface Ship Guide Rails from (Quest Marine Services, 2007

Saturn Apollo Program

NASA Image and Video Library

1975-07-01

SA-210 Apollo-Soyuz Test Project (ASTP) awaits the launch scheduled on July 15, 1975 on the launch pad at the Kennedy Space Center, the ASTP mission with astronauts Thomas Stafford, Vance Brand, and Donald "Deke" Slayton. The Saturn IB, developed under the direction of the Marshall Space Flight Center (MSFC), launched five manned Earth-orbital missions between 1968 and 1975: Apollo 7, Skylab 2, Skylab 3, Skylab 4, and the Apollo-Soyuz Test Project .

Saturn Apollo Program

NASA Image and Video Library

1969-07-16

This photograph shows the Saturn V launch vehicle (SA-506) for the Apollo 11 mission liftoff at 8:32 am CDT, July 16, 1969, from launch complex 39A at the Kennedy Space Center. Apollo 11 was the first manned lunar landing mission with a crew of three astronauts: Mission commander Neil A. Armstrong, Command Module pilot Michael Collins, and Lunar Module pilot Edwin E. Aldrin, Jr. It placed the first humans on the surface of the moon and returned them back to Earth. Astronaut Armstrong became the first man on the lunar surface, and astronaut Aldrin became the second. Astronaut Collins piloted the Command Module in a parking orbit around the Moon.

Autonomous Flight Safety System

NASA Technical Reports Server (NTRS)

Ferrell, Bob; Santuro, Steve; Simpson, James; Zoerner, Roger; Bull, Barton; Lanzi, Jim

2004-01-01

Autonomous Flight Safety System (AFSS) is an independent flight safety system designed for small to medium sized expendable launch vehicles launching from or needing range safety protection while overlying relatively remote locations. AFSS replaces the need for a man-in-the-loop to make decisions for flight termination. AFSS could also serve as the prototype for an autonomous manned flight crew escape advisory system. AFSS utilizes onboard sensors and processors to emulate the human decision-making process using rule-based software logic and can dramatically reduce safety response time during critical launch phases. The Range Safety flight path nominal trajectory, its deviation allowances, limit zones and other flight safety rules are stored in the onboard computers. Position, velocity and attitude data obtained from onboard global positioning system (GPS) and inertial navigation system (INS) sensors are compared with these rules to determine the appropriate action to ensure that people and property are not jeopardized. The final system will be fully redundant and independent with multiple processors, sensors, and dead man switches to prevent inadvertent flight termination. AFSS is currently in Phase III which includes updated algorithms, integrated GPS/INS sensors, large scale simulation testing and initial aircraft flight testing.

High Voltage EEE Parts for EMA/EHA Applications on Manned Launch Vehicles

NASA Technical Reports Server (NTRS)

Griffin, Trent; Young, David

2011-01-01

The objective of this paper is an assessment of high voltage electronic components required for high horsepower electric thrust vector control (TVC) systems for human spaceflight launch critical application. The scope consists of creating of a database of available Grade 1 electrical, electronic and electromechanical (EEE) parts suited to this application, a qualification path for potential non-Grade 1 EEE parts that could be used in these designs, and pathfinder testing to validate aspects of the proposed qualification plan. Advances in the state of the art in high power electric power systems enable high horsepower electric actuators, such as the electromechnical actuator (EMA) and the electro-hydrostatic actuator (EHA), to be used in launch vehicle TVC systems, dramaticly reducing weight, complexity and operating costs. Designs typically use high voltage insulated gate bipolar transistors (HV-IGBT). However, no Grade 1 HV-IGBT exists and it is unlikely that market factors alone will produce such high quality parts. Furthermore, the perception of risk, the lack of qualification methodoloy, the absence of manned space flight heritage and other barriers impede the adoption of commercial grade parts onto the critical path. The method of approach is to identify high voltage electronic component types and key parameters for parts currently used in high horsepower EMA/EHA applications, to search for higher quality substitutes and custom manufacturers, to create a database for these parts, and then to explore ways to qualify these parts for use in human spaceflight launch critical application, including grossly derating and possibly treating hybrid parts as modules. This effort is ongoing, but results thus far include identification of over 60 HV-IGBT from four manufacturers, including some with a high reliability process flow. Voltage ranges for HV-IGBT have been identified, as has screening tests used to characterize HV-IGBT. BSI BS ISO 21350 Space systems Off-the-shelf item utilization, developed from Marshall Work Instruction MWI8060.1 OFF-THE-SHELF HARDWARE UTILIZATION IN FLIGHT HARDWARE DEVELOPMENTwas found to provide guidance for including commercial off-the-shelf (COTS) hardware for use in critical applications.

National space transportation systems planning

NASA Technical Reports Server (NTRS)

Lucas, W. R.

1985-01-01

In the fall of 1984, the DOD and NASA had been asked to identify launch vehicle technologies which could be made available for use in 1995 to 2010. The results of the studies of the two groups were integrated, and a consumer report, dated December 1984, was forwarded to the President. Aspects of mission planning and analysis are discussed along with a combined mission model, future launch system requirements, a launch vehicle planning background, Shuttle derivative vehicle program options, payload modularization, launch vehicle technology implications, a new engine program for the mid-1990's. Future launch systems goals are to achieve an order of magnitude reduction in future launch cost and meet the lift requirements and launch rates. Attention is given to an advanced cryogenic engine, advanced LOX/hydrocarbon engine, advanced power systems, aerodynamics/flight mechanics, reentry/recovery systems, avionics/software, advanced manufacturing techniques, autonomous ground and mission operations, advanced structures/materials, and air breathing propulsion.

Space Station Freedom avionics technology

NASA Technical Reports Server (NTRS)

Edwards, A.

1990-01-01

The Space Station Freedom Program (SSFP) encompasses the design, development, test, evaluation, verification, launch, assembly, and operation and utilization of a set of spacecraft in low earth orbit (LEO) and their supporting facilities. The spacecraft set includes: the Space Station Manned Base (SSMB), a European Space Agency (ESA) provided Man-Tended Free Flyer (MTFF) at an inclination of 28.5 degrees and nominal attitude of 410 km, a USA provided Polar Orbiting Platform (POP), and an ESA provided POP in sun-synchronous, near polar orbits at a nominal altitude of 822 km. The SSMB will be assembled using the National Space Transportation System (NSTS). The POPs and the MTFF will be launched by Expendable Launch Vehicles (ELVs): a Titan 4 for the US POP and an Ariane for the ESA POP and MTFF. The US POP will for the most part use derivatives of systems flown on unmanned LEO spacecraft. The SSMB portion of the overall program is presented.

Project Minerva: A low-cost manned Mars mission based on indigenous propellant production

NASA Technical Reports Server (NTRS)

Bruckner, Adam P.; Anderson, Hobie; Caviezel, Kelly; Daggert, Todd; Folkers, Mike; Fornia, Mark; Hamling, Steven; Johnson, Bryan; Kalberer, Martin; Machula, Mike

1992-01-01

Project Minerva is a low-cost manned Mars mission designed to deliver a crew of four to the Martian surface, using only two sets of two launches. Key concepts which make this mission realizable are the use of near-term technologies and in-situ propellant production, following the senario originally proposed by R. Zubrin of Martin Marietta. The first set of launches delivers two unmanned payloads into low earth orbit (LEO): one consists of an Earth Return Vehicle (ERV), a propellant production plant, and a set of robotic vehicles, and the second consists of the upper stage/trans-Mars injection (TMI) booster. In LEO, the two payloads are joined and inserted into a Mars transfer orbit. The landing on Mars is performed with the aid of multiple aerobraking maneuvers. On the Martian surface, the propellant production plant uses a Sabatier/electrolysis-type process to combine six tons of hydrogen brought from earth with carbon dioxide from the Martian atmosphere to produce 100 tons of liquid oxygen and methane, which are later used as the propellants for the rover expeditions and the manned return journey of the ERV. Once the in-situ propellant production is completed, approximately two years after the first set of launches, the manned portion of the mission leaves earth. This set of two launches is similar to that of the unmanned vehicles; the two payloads are the Manned Transfer Vehicle (MTV) and the upper stage/TMI booster. The MTV contains the manned rover and the habitat which houses the astronauts enroute to Mars and on the Martian surface. During the 180-day trip to Mars, artificial gravity is created by tethering the MTV to the TMI booster and inducing rotation. Upon arrival the MTV performs aerobraking maneuvers to land near the fully-fueled ERV, which will be used by the crew a year and a half later to return to earth. The mission entails moderate travel times with relatively low-energy conjunction-class trajectories and allows ample time for scientific exploration. This set of missions can be repeated every two years in order to continue exploration at a variety of sites and gradually establish the infrastructure for a permanent base on Mars.

Study of launch site processing and facilities for future launch vehicles

NASA Astrophysics Data System (ADS)

Shaffer, Rex

1995-03-01

The purpose of this research is to provide innovative and creative approaches to assess the impact to the Kennedy Space Center and other launch sites for a range of candidate manned and unmanned space transportation systems. The general scope of the research includes the engineering activities, analyses, and evaluations defined in the four tasks below: (1) development of innovative approaches and computer aided tools; (2) operations analyses of launch vehicle concepts and designs; (3) assessment of ground operations impacts; and (4) development of methodologies to identify promising technologies.

Study of launch site processing and facilities for future launch vehicles

NASA Technical Reports Server (NTRS)

Shaffer, Rex

1995-01-01

The purpose of this research is to provide innovative and creative approaches to assess the impact to the Kennedy Space Center and other launch sites for a range of candidate manned and unmanned space transportation systems. The general scope of the research includes the engineering activities, analyses, and evaluations defined in the four tasks below: (1) development of innovative approaches and computer aided tools; (2) operations analyses of launch vehicle concepts and designs; (3) assessment of ground operations impacts; and (4) development of methodologies to identify promising technologies.

KSC-04PD-0610

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0612

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with the Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0604

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1), stored in the Industrial Area of KSC, is being demolished using a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear being used for demolition is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0607

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0608

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Launch Umbilical Tower No. 1 (LUT- 1) stored in the Industrial Area of KSC is being demolished with a Caterpillar excavator and 48-inch shear attachment. Seen is the base of tower; the upright tower extended more than 398 feet above the launch pad. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

Aeronautics and space report of the President, 1983 activities

NASA Technical Reports Server (NTRS)

1984-01-01

Achievements in communication; space science; space transportation; aeronautics; and Earth resources and environment are summarized. Activities of the various Federal agencies and cooperation with NASA in these areas are described. The Presidential policy announcement on the endorsement of commercial operation of expendable launch vehicles is included. Tables show, the space activities budget; a historical budget summary, U.S. space launch vehicles; U.S. and Soviet manned spaceflights, 1961 to 1983; U.S. launched space probes, 1975 to 1983; U.S. launched scientific and applications satellites, 1978 to 1983; the U.S. spacecraft record; the world record of space launches successful in attaining Earth orbit or beyond; and successful U.S. launchings for 1983.

Launch Pad Escape System Design (Human Spaceflight)

NASA Technical Reports Server (NTRS)

Maloney, Kelli

2011-01-01

A launch pad escape system for human spaceflight is one of those things that everyone hopes they will never need but is critical for every manned space program. Since men were first put into space in the early 1960s, the need for such an Emergency Escape System (EES) has become apparent. The National Aeronautics and Space Administration (NASA) has made use of various types of these EESs over the past 50 years. Early programs, like Mercury and Gemini, did not have an official launch pad escape system. Rather, they relied on a Launch Escape System (LES) of a separate solid rocket motor attached to the manned capsule that could pull the astronauts to safety in the event of an emergency. This could only occur after hatch closure at the launch pad or during the first stage of flight. A version of a LES, now called a Launch Abort System (LAS) is still used today for all manned capsule type launch vehicles. However, this system is very limited in that it can only be used after hatch closure and it is for flight crew only. In addition, the forces necessary for the LES/LAS to get the capsule away from a rocket during the first stage of flight are quite high and can cause injury to the crew. These shortcomings led to the development of a ground based EES for the flight crew and ground support personnel as well. This way, a much less dangerous mode of egress is available for any flight or ground personnel up to a few seconds before launch. The early EESs were fairly simple, gravity-powered systems to use when thing's go bad. And things can go bad very quickly and catastrophically when dealing with a flight vehicle fueled with millions of pounds of hazardous propellant. With this in mind, early EES designers saw such a passive/unpowered system as a must for last minute escapes. This and other design requirements had to be derived for an EES, and this section will take a look at the safety design requirements had to be derived for an EES, and this section will take a look at the safety design aspects for a launch pad escape system.

Computer graphic of Lockheed Martin X-33 Reusable Launch Vehicle (RLV) mounted on NASA 747 ferry air

NASA Technical Reports Server (NTRS)

1997-01-01

This is an artist's conception of the NASA/Lockheed Martin X-33 Advanced Technology Demonstrator being carried on the back of the 747 Shuttle Carrier Aircraft. This was a concept for moving the X-33 from its landing site back to NASA's Dryden Flight Research Center, Edwards, California. The X-33 was a technology demonstrator vehicle for the Reusable Launch Vehicle (RLV). The RLV technology program was a cooperative agreement between NASA and industry. The goal of the RLV technology program was to enable significant reductions in the cost of access to space, and to promote the creation and delivery of new space services and other activities that will improve U.S. economic competitiveness. NASA Headquarter's Office of Space Access and Technology oversaw the RLV program, which was being managed by the RLV Office at NASA's Marshall Space Flight Center, located in Huntsville, Alabama. Responsibilities of other NASA Centers included: Johnson Space Center, Houston, Texas, guidance navigation and control technology, manned space systems, and health technology; Ames Research Center, Mountain View, CA., thermal protection system testing; Langley Research Center, Langley, Virginia, wind tunnel testing and aerodynamic analysis; and Kennedy Space Center, Florida, RLV operations and health management. Lockheed Martin's industry partners in the X-33 program are: Astronautics, Inc., Denver, Colorado, and Huntsville, Alabama; Engineering & Science Services, Houston, Texas; Manned Space Systems, New Orleans, LA; Sanders, Nashua, NH; and Space Operations, Titusville, Florida. Other industry partners are: Rocketdyne, Canoga Park, California; Allied Signal Aerospace, Teterboro, NJ; Rohr, Inc., Chula Vista, California; and Sverdrup Inc., St. Louis, Missouri.

Space station accommodations for lunar base elements: A study

NASA Technical Reports Server (NTRS)

Weidman, Deene J.; Cirillo, William; Llewellyn, Charles; Kaszubowski, Martin; Kienlen, E. Michael, Jr.

1987-01-01

The results of a study conducted at NASA-LaRC to assess the impact on the space station of accommodating a Manned Lunar Base are documented. Included in the study are assembly activities for all infrastructure components, resupply and operations support for lunar base elements, crew activity requirements, the effect of lunar activities on Cape Kennedy operations, and the effect on space station science missions. Technology needs to prepare for such missions are also defined. Results of the study indicate that the space station can support the manned lunar base missions with the addition of a Fuel Depot Facility and a heavy lift launch vehicle to support the large launch requirements.

Skylab (SL)-3 Crew - KSC

NASA Image and Video Library

1973-08-03

S73-31801 (28 July 1973) --- The three crewmen of the second manned Skylab mission (Skylab 3) leave the Manned Spacecraft Operations Building at the Kennedy Space Center on the morning of the Skylab 3 launch. Leading is astronaut Alan L. Bean, commander; followed by scientist-astronaut Owen K. Garriott, science pilot; and astronaut Jack R. Lousma, pilot. They entered the special van which carried them to Pad B at KSC?s Launch Complex 39 where the Skylab 3/Saturn 1B space vehicle awaited them. The Skylab 3 liftoff was at 7:11 a.m. (EDT), Saturday, July 28, 1973. The three astronauts were scheduled to spend 59 days at the Skylab space station in Earth orbit. Photo credit: NASA

KSC-04pd0611

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Like a dinosaur crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0611

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Like a dinosaur crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

Alternatives for Future U.S. Space-Launch Capabilities

DTIC Science & Technology

2006-10-01

directive issued on January 14, 2004—called the new Vision for Space Exploration (VSE)—set out goals for future exploration of the solar system using...of the solar system using manned spacecraft. Among those goals was a proposal to return humans to the moon no later than 2020. The ultimate goal...U.S. launch capacity exclude the Sea Launch system operated by Boeing in partnership with RSC- Energia (based in Moscow), Kvaerner ASA (based in Oslo

LAUNCH - APOLLO VII - KSC

NASA Image and Video Library

1968-10-11

S68-48666 (11 Oct. 1968) --- The Apollo 7/Saturn IB space vehicle is launched from the Kennedy Space Center's Launch Complex 34 at 11:03 a.m. (EDT), Oct. 11, 1968. Apollo 7 (Spacecraft 101/Saturn 205) is the first of several manned flights aimed at qualifying the spacecraft for the half-million-mile round trip to the moon. Aboard the Apollo spacecraft are astronauts Walter M. Schirra Jr., commander; Donn F. Eisele, command module pilot; and Walter Cunningham, lunar module pilot.

Diverse applications of advanced man-telerobot interfaces

NASA Technical Reports Server (NTRS)

Mcaffee, Douglas A.

1991-01-01

Advancements in man-machine interfaces and control technologies used in space telerobotics and teleoperators have potential application wherever human operators need to manipulate multi-dimensional spatial relationships. Bilateral six degree-of-freedom position and force cues exchanged between the user and a complex system can broaden and improve the effectiveness of several diverse man-machine interfaces.

U.S. advanced launch vehicle technology programs : Quarterly Launch Report : special report

DOT National Transportation Integrated Search

1996-01-01

U.S. firms and U.S. government agencies are jointly investing in advanced launch vehicle technology. This Special Report summarizes U.S. launch vehicle technology programs and highlights the changing : roles of government and industry players in pick...

Apollo 14 crew arrive at White Room atop Pad A, Launch Complex 39

NASA Technical Reports Server (NTRS)

1971-01-01

The three Apollo 14 astronauts arrive at the White Room atop Pad A, Launch Complex 39, during the Apollo 14 prelaunch countdown. Note identifying red bands on the sleeve and leg of Shepard. Standing in the center background is Astronaut Thomas P. Stafford, Chief of the Manned Spacecraft Center Astronaut Office.

MSFC Skylab operations support summary

NASA Technical Reports Server (NTRS)

Martin, J. R.

1974-01-01

A summary of the actions and problems involved in preparing the Skylab-one vehicle is presented. The subjects discussed are: (1) flight operations support functions and organization, (2) launch operations and booster flight support functions and organization, (3) Skylab launch vehicle support teams, (4) Skylab orbital operations support performance analysis, (5) support manning and procedures, and (6) data support and facilities.

Integration and Testing of LCS Software

NASA Technical Reports Server (NTRS)

Wang, John

2014-01-01

Kennedy Space Center is in the midst of developing a command and control system for the launch of the next generation manned space vehicle. The Space Launch System (SLS) will launch using the new Spaceport Command and Control System (SCCS). As a member of the Software Integration and Test (SWIT) Team, command scripts, and bash scripts were written to assist in integration and testing of the Launch Control System (LCS), which is a component of SCCS. The short term and midterm tasks are for the most part completed. The long term tasks if time permits will require a presentation and demonstration.

Adaptive Attitude Control of the Crew Launch Vehicle

NASA Technical Reports Server (NTRS)

Muse, Jonathan

2010-01-01

An H(sub infinity)-NMA architecture for the Crew Launch Vehicle was developed in a state feedback setting. The minimal complexity adaptive law was shown to improve base line performance relative to a performance metric based on Crew Launch Vehicle design requirements for all most all of the Worst-on-Worst dispersion cases. The adaptive law was able to maintain stability for some dispersions that are unstable with the nominal control law. Due to the nature of the H(sub infinity)-NMA architecture, the augmented adaptive control signal has low bandwidth which is a great benefit for a manned launch vehicle.

KSC-04PD-0606

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0605

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04PD-0609

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0609

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0606

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0605

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- Looking like a prehistoric monster crunching on its prey, the Caterpillar excavator and 48-inch shear attachment tear down Launch Umbilical Tower No. 1 (LUT-1) stored in the Industrial Area of KSC. The LUT-1 was part of the launch system used for Apollo-Saturn V, launching Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

Saturn Apollo Program

NASA Image and Video Library

1975-01-01

This montage illustrates the various configurations and missions of the three classes of the Saturn vehicles developed by the Marshall Space Flight Center. The missions for the Saturn I included atmospheric science investigations and the deployment of the Pegasus meteroid-detection satellite as well as launch vehicle development. The Saturn IB vehicle tested the Apollo spacecraft and launched the three marned Skylab missions as well as the Apollo Soyuz test project. The Saturn V vehicle launched the manned lunar orbital/landing missions, and the Skylab Orbital Workshop in 1973.

Manned Mars mission accommodation: Sprint mission

NASA Technical Reports Server (NTRS)

Cirillo, William M.; Kaszubowski, Martin J.; Ayers, J. Kirk; Llewellyn, Charles P.; Weidman, Deene J.; Meredith, Barry D.

1988-01-01

The results of a study conducted at the NASA-LaRC to assess the impacts on the Phase 2 Space Station of Accommodating a Manned Mission to Mars are documented. In addition, several candidate transportation node configurations are presented to accommodate the assembly and verification of the Mars Mission vehicles. This study includes an identification of a life science research program that would need to be completed, on-orbit, prior to mission departure and an assessment of the necessary orbital technology development and demonstration program needed to accomplish the mission. Also included is an analysis of the configuration mass properties and a preliminary analysis of the Space Station control system sizing that would be required to control the station. Results of the study indicate the Phase 2 Space Station can support a manned mission to Mars with the addition of a supporting infrastructure that includes a propellant depot, assembly hangar, and a heavy lift launch vehicle to support the large launch requirements.

ASTP (SA-210) Launch vehicle operational flight trajectory. Part 3: Final documentation

NASA Technical Reports Server (NTRS)

Carter, A. B.; Klug, G. W.; Williams, N. W.

1975-01-01

Trajectory data are presented for a nominal and two launch window trajectory simulations. These trajectories are designed to insert a manned Apollo spacecraft into a 150/167 km. (81/90 n. mi.) earth orbit inclined at 51.78 degrees for rendezvous with a Soyuz spacecraft, which will be orbiting at approximately 225 km. (121.5 n. mi.). The launch window allocation defined for this launch is 500 pounds of S-IVB stage propellant. The launch window opening trajectory simulation depicts the earliest launch time deviation from a planar flight launch which conforms to this constraint. The launch window closing trajectory simulation was developed for the more stringent Air Force Eastern Test Range (AFETR) flight azimuth restriction of 37.4 degrees east-of-north. These trajectories enclose a 12.09 minute launch window, pertinent features of which are provided in a tabulation. Planar flight data are included for mid-window reference.

Ideal Biological Characteristics for Long-Duration Manned Space Travel

NASA Astrophysics Data System (ADS)

Cardion, A. L.

As we consider the technical challenges we will overcome to launch our first interstellar mission, it is natural that we envision our own view from the deck of that starship. However, the cold reality of the vast distances of interstellar space, in keeping with the history of space flight, clearly indicates that our first forays into such missions will likely be unmanned probes. Indeed, it is the limitations of our own biology and psychology, primarily in their fragility and brevity, that anchor us to the terrestrial environment upon which we depend. But by considering the diversity of biological adaptation documented on Earth, in combination with the promise of an advanced bioengineering program, we can begin to imagine how evolution or design could adapt the intrepid travellers to long-duration stresses inherent to interstellar flight.

Challenge '95 - The Ariane 5 Development Programme

NASA Astrophysics Data System (ADS)

Vedrenne, M.; van Gaver, M.

1987-10-01

The Ariane-5 launcher has been assigned to the following types of missions: (1) launching geostationary and sun-synchronous commercial satellites, and scientific and trial applications satellites; (2) launching the Hermes spaceplane, and (3) launching elements of the Columbus system such as the man-tended free-flyer module, and the polar platform. A new launch complex, the ELA-3, is being built for the Ariane-5 launcher close to ESA's ELA-1 and ELA-2 launch complexes at Kourou. After two qualification flights in the automatic version in 1995 (501 and 502), it is expected that Ariane-5 will be declared operational with its first commercial flight planned for early 1996 to put an automatic payload into orbit.

PRELAUNCH - (SUITING-UP) APOLLO 15 - KSC

NASA Image and Video Library

1971-07-26

S71-41408 (26 July 1971) --- The three Apollo 15 astronauts go through suiting up operations in the Kennedy Space Center's (KSC) Manned Spacecraft Operations Building (MSOB) during the Apollo 15 prelaunch countdown. They are David R. Scott (foreground), commander; Alfred M. Worden (center), command module pilot; and James B. Irwin (background), lunar module pilot. Minutes later the crew rode a special transport van over to Pad A, Launch Complex 39, where their spacecraft awaited them. With the crew was Dr. Donald (Deke) K. Slayton (wearing dark blue sport shirt), director of Flight Crew Operations, Manned Spacecraft Center (MSC). The Apollo 15 space vehicle was launched at 9:34:00:79 a.m. (EDT), July 26, 1971, on a lunar landing mission.

Failure to Launch: Confronting the Male College Student Achievement Gap

ERIC Educational Resources Information Center

Glenn, Lane A.; Van Wert, Suzanne

2010-01-01

A few years ago, Mathew McConaughey and Sarah Jessica Parker generated big laughs and big box office sales in "Failure to Launch," an absurd comedy about a 26-year old man still living in his parents' basement, spending his days watching television and playing video games while the world passed him by. The film was closer to the truth…

Dr. Wernher Von Braun near the mobile launcher.

NASA Technical Reports Server (NTRS)

1999-01-01

Dr. George Mueller, NASA associate administrator for manned space flight, and Dr. Wernher Von Braun (right), director of the Marshall Space Flight Center, are seen near the mobile launcher carrying a 363 foot tall Saturn V space launch vehicle as the rocket is rolled from the vehicle assembly building at KSC for its three mile trip to the launch pad.

Advanced information processing system for advanced launch system: Avionics architecture synthesis

NASA Technical Reports Server (NTRS)

Lala, Jaynarayan H.; Harper, Richard E.; Jaskowiak, Kenneth R.; Rosch, Gene; Alger, Linda S.; Schor, Andrei L.

1991-01-01

The Advanced Information Processing System (AIPS) is a fault-tolerant distributed computer system architecture that was developed to meet the real time computational needs of advanced aerospace vehicles. One such vehicle is the Advanced Launch System (ALS) being developed jointly by NASA and the Department of Defense to launch heavy payloads into low earth orbit at one tenth the cost (per pound of payload) of the current launch vehicles. An avionics architecture that utilizes the AIPS hardware and software building blocks was synthesized for ALS. The AIPS for ALS architecture synthesis process starting with the ALS mission requirements and ending with an analysis of the candidate ALS avionics architecture is described.

Advanced Chemical Propulsion

NASA Technical Reports Server (NTRS)

Bai, S. Don

2000-01-01

Design, propellant selection, and launch assistance for advanced chemical propulsion system is discussed. Topics discussed include: rocket design, advance fuel and high energy density materials, launch assist, and criteria for fuel selection.

The 21st century propulsion

NASA Technical Reports Server (NTRS)

Haloulakos, V. E.; Boehmer, C.

1990-01-01

The prediction of future space travel in the next millennium starts by examining the past and extrapolating into the far future. Goals for the 21st century include expanded space travel and establishment of permanent manned outposts, and representation of Lunar and Mars outposts as the most immediate future in space. Nuclear stage design/program considerations; launch considerations for manned Mars missions; and far future propulsion schemes are outlined.

LAUNCH - STS-1 - KSC

NASA Image and Video Library

1981-04-12

S81-30498 (12 April 1981) --- After six years of silence, the thunder of manned spaceflight is heard again, as the successful launch of the first space shuttle ushers in a new concept in utilization of space. The April 12, 1981 launch, at Pad 39A, just seconds past 7 a.m., carries astronaut John Young and Robert Crippen into an Earth-orbital mission scheduled to last for 54 hours, ending with unpowered landing at Edwards Air Force Base in California. STS-1, the first in a series of shuttle vehicles planned for the Space Transportation System, utilizes reusable launch and return components. Photo credit: NASA or National Aeronautics and Space Administration

Aeronautics and space report of the President, 1982 activities

NASA Technical Reports Server (NTRS)

1983-01-01

Achievements of the space program are summerized in the area of communication, Earth resources, environment, space sciences, transportation, aeronautics, and space energy. Space program activities of the various deprtments and agencies of the Federal Government are discussed in relation to the agencies' goals and policies. Records of U.S. and world spacecraft launchings, successful U.S. launches for 1982, U.S. launched applications and scientific satellites and space probes since 1975, U.S. and Soviet manned spaceflights since 1961, data on U.S. space launch vehicles, and budget summaries are provided. The national space policy and the aeronautical research and technology policy statements are included.

Automated Rendezvous and Capture System Development and Simulation for NASA

NASA Technical Reports Server (NTRS)

Roe, Fred D.; Howard, Richard T.; Murphy, Leslie

2004-01-01

The United States does not have an Automated Rendezvous and Capture/Docking (AR and C) capability and is reliant on manned control for rendezvous and docking of orbiting spacecraft. This reliance on the labor intensive manned interface for control of rendezvous and docking vehicles has a significant impact on the cost of the operation of the International Space Station (ISS) and precludes the use of any U.S. expendable launch capabilities for Space Station resupply. The Soviets have the capability to autonomously dock in space, but their system produces a hard docking with excessive force and contact velocity. Automated Rendezvous and Capture/Docking has been identified as a key enabling technology for the Space Launch Initiative (SLI) Program, DARPA Orbital Express and other DOD Programs. The development and implementation of an AR&C capability can significantly enhance system flexibility, improve safety, and lower the cost of maintaining, supplying, and operating the International Space Station. The Marshall Space Flight Center (MSFC) has conducted pioneering research in the development of an automated rendezvous and capture (or docking) (AR and C) system for U.S. space vehicles. This AR&C system was tested extensively using hardware-in-the-loop simulations in the Flight Robotics Laboratory, and a rendezvous sensor, the Video Guidance Sensor was developed and successfully flown on the Space Shuttle on flights STS-87 and STS-95, proving the concept of a video- based sensor. Further developments in sensor technology and vehicle and target configuration have lead to continued improvements and changes in AR&C system development and simulation. A new Advanced Video Guidance Sensor (AVGS) with target will be utilized on the Demonstration of Autonomous Rendezvous Technologies (DART) flight experiment in 2004.

APOLLO XII - LAUNCH DAY ACTIVITIES - LAUNCH COMPLEX 39A - KSC

NASA Image and Video Library

1969-11-14

S69-58880 (14 Nov. 1969) --- Astronaut Alan L. Bean, Apollo 12 lunar module pilot, suits up in the Kennedy Space Center's (KSC) Manned Spacecraft Operations Building during the Apollo 12 prelaunch countdown. Minutes later astronauts Bean; Charles Conrad Jr., commander; and Richard F. Gordon Jr., command module pilot, rode a special transport van over to Pad A, Launch Complex 39, where their spacecraft awaited. The Apollo 12 liftoff occurred at 11:22 a.m. (EST), Nov. 14, 1969. Apollo 12 is the United States' second lunar landing mission.

SKYLAB IV - LAUNCH

NASA Image and Video Library

1973-11-27

S73-37285 (16 Nov. 1973) --- The Skylab 4/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 9:01:23 a.m. (EST), Friday, Nov. 16, 1973. Skylab 4 is the third and last of three scheduled manned Skylab missions. Aboard the Skylab 4 Command/Service Module were astronauts Gerald P. Carr, Edward G. Gibson and William R. Pogue. In addition to the CSM and its launch escape system, the Skylab 4 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-IVB) stage. (The Skylab 1/Saturn V unmanned space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

SKYLAB IV - LAUNCH

NASA Image and Video Library

1973-11-27

S73-37286 (16 Nov. 1973) --- The Skylab 4/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 9:01:23 a.m. (EST), Friday, Nov. 16, 1973. Skylab 4 is the third and last of three scheduled manned Skylab missions. Aboard the Skylab 4 Command/Service Module were astronauts Gerald P. Carr, Edward G. Gibson and William R. Pogue. In addition to the CSM and its launch escape system, the Skylab 4 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-IVB) stage. (The Skylab 1/Saturn V unmanned space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

AAFE man-made noise experiment project. Volume 3: Appendices

NASA Technical Reports Server (NTRS)

1974-01-01

Management and operational considerations involved in the project to measure man-made electromagnetic noise at earth orbital altitudes are discussed. The subjects considered are: (1) launch and orbit of the Scout D vehicles, (2) experiment management, (3) receiver scanning considerations, (4) data handling, and (5) threshold measurements. The storage requirements for a high resolution, complete data storage library are defined. Mathematical models of signal detection probability are developed.

Project Mercury: NASA's first manned space programme

NASA Astrophysics Data System (ADS)

Catchpole, John

Project Mercury will offer a developmental resume of the first American manned spaceflight programme and its associated infrastructure, including accounts of space launch vehicles. The book highlights the differences in Redstone/Atlas technology, drawing similar comparisons between ballistic capsules and alternative types of spacecraft. The book also covers astronaut selection and training, as well as tracking systems, flight control, basic principles of spaceflight and detailed accounts of individual flights.

Historical aspects of the early Soviet/Russian manned space program.

PubMed

West, J B

2001-10-01

Human spaceflight was one of the great physiological and engineering triumphs of the 20th century. Although the history of the United States manned space program is well known, the Soviet program was shrouded in secrecy until recently. Konstantin Edvardovich Tsiolkovsky (1857-1935) was an extraordinary Russian visionary who made remarkable predictions about space travel in the late 19th century. Sergei Pavlovich Korolev (1907-1966) was the brilliant "Chief Designer" who was responsible for many of the Soviet firsts, including the first artificial satellite and the first human being in space. The dramatic flight of Sputnik 1 was followed within a month by the launch of the dog Laika, the first living creature in space. Remarkably, the engineering work for this payload was all done in less than 4 wk. Korolev's greatest triumph was the flight of Yuri Alekseyevich Gagarin (1934-1968) on April 12, 1961. Another extraordinary feat was the first extravehicular activity by Aleksei Arkhipovich Leonov (1934-) using a flexible airlock that emphasized the entrepreneurial attitude of the Soviet engineers. By the mid-1960s, the Soviet program was overtaken by the United States program and attempts to launch a manned mission to the Moon failed. However, the early Soviet manned space program has a preeminent place in the history of space physiology.

A Geometric Analysis to Protect Manned Assets from Newly Launched Objects - COLA Gap Analysis

NASA Technical Reports Server (NTRS)

Hametz, Mark E.; Beaver, Brian A.

2012-01-01

A safety risk was identified for the International Space Station (ISS) by The Aerospace Corporation following the launch of GPS IIR-20 (March 24, 2009), when the spent upper stage of the launch vehicle unexpectedly crossed inside the ISS notification box shortly after launch. This event highlighted a 56-hour vulnerability period following the end of the launch Collision Avoidance (COLA) process where the ISS would be unable to react to a conjunction with a newly launched object. Current launch COLA processes screen each launched object across the launch window to determine if an object's nominal trajectory is predicted to pass within 200 km of the ISS (or any other manned/mannable object), resulting in a launch time closure. These launch COLA screens are performed from launch through separation plus I 00 minutes. Once the objects are in orbit, they are cataloged and evaluated as part of routine on-orbit conjunction assessment processes. However, as the GPS IIR-20 scenario illustrated, there is a vulnerability period in the time line between the end of launch COLA coverage and the beginning of standard on-orbit COLA assessment activities. The gap between existing launch and on-orbit COLA processes is driven by the time it takes to track and catalog a launched object, identify a conjunction, and plan and execute a collision avoidance maneuver. For the ISS, the total time required to accomplish an of these steps is 56 hours. To protect human lives, NASA/JSC has requested that an US launches take additional steps to protect the ISS during this "COLA gap" period. The uncertainty in the state of a spent upper stage can be quite large after all bums are complete and all remaining propellants are expelled to safe the stage. Simply extending the launch COLA process an additional 56 hours is not a viable option as the 3-sigma position uncertainty will far exceed the 200 km miss-distance criterion. Additionally, performing a probability of collision (Pc) analysis over this period is also not practical due to the limiting effects of these large orbit state uncertainties. An estimated upper bound for Pc for a typical spent upper stage if nominally aligned for a direct broadside collision with the ISS is only on the order of 10-6. For a smaller manned object such as a Soyuz capsule, the risk level decreases to an order of 10'8 . In comparison, the Air Force Range policy (AFI 91-217) for launch COLAs would only eliminate launch opportunities when conjunctions with objects exceed a Pc of 10'5 This paper demonstrates a conservative geometry-based methodology that may be used to determine if launch opportunities pose a threat to the ISS during the COLA gap period. The NASA Launch Services Program at Kennedy Space Center has developed this COLA gap analysis method and employed it fQr three NASA missions to identify potential ISS conjunctions and corresponding launch window closures during the 56-hour at-risk period. In the analysis, for each launch opportunity, the nominal trajectory of the spent upper stage and the orbit state of the ISS are propagated over the 56 hour period. Each time the upper stage crosses the orbit plane of the ISS, the relative radial and argument of latitude separations are calculated. A window cutout is identified if these separation differences fall within a mission-specific violation box, which is determined from the evaluation of a Monte Carlo dispersions analysis that quantifies the potential variation in the upper stage radial and argument of latitude differences. This paper details the results of these analyses and their impacts to each mission.

ASTRONAUT CHARLES CONRAD, JR. - SKYLAB (SL)-2 - JSC

NASA Image and Video Library

1973-02-27

S73-17859 (January 1973) --- Astronaut Paul J. Weitz, pilot for Skylab 2 (first Skylab manned) mission, looks over off-duty recreational equipment in the crew quarters of the Skylab Orbital Workshop (OWS) trainer during Skylab simulation activity at the Manned Spacecraft Center. The equipment includes such items as tape decks and stereo music equipment, playing cards, darts, etc. The OWS is a component of the Skylab space station cluster which will be launched unmanned aboard a Saturn V in summer of 1973, and will be visited three times by three-man crews over an eight month period. Photo credit: NASA

Climbing to stars

NASA Astrophysics Data System (ADS)

Maksimov, A. I.

2011-06-01

Development of cosmonautics and preparation to the first manned space flights are briefly observed. Details of the development of the first Soviet intercontinental ballistic missile R-7, which served as a basis for creating Sputnik, Vostok, Voskhod, Molniya, and Soyuz launchers, are given. The contributions of the outstanding designers of space engineering, W. von Braun, S.P. Korolev, V.P. Glushko, and academician M.V. Keldysh, to the development of astronautics and first manned space missions are demonstrated. A list of test launches and manned flights of Vostok and Mercury spacecrafts and the basic characteristics of Vostok, Redstone, Atlas-D, Voskhod, and Soyuz launchers are presented.

Evolution of the Baseline ISS ECLSS Technologies: The Next Logical Steps

NASA Technical Reports Server (NTRS)

Carrasquillo, Robyn L.; Bagdigian, Bob; Perry, Jay; Lewis, John; Williams, Dave

2004-01-01

The baseline Environmental Control and Life Support Systems which are currently deployed on the International Space Station or planned to be launched in Node 3 are based on technologies selected in the early 1990's. While they are generally meeting or exceeding requirements for supporting the ISS crew, lessons learned from years of on orbit and ground testing, new advances in technology state of the art, and requirements for future manned missions prompt consideration of the next logical step to enhance these systems to increase performance, robustness, reliability, and reduce on-orbit and logistical resource requirements. This paper discusses the current state of the art in ISS ECLSS technologies, and possible areas for enhancement/improvement. Potential utilization of the ISS as a testbed for on-orbit checkout of selected technology improvements is also addressed.

The Apollo Lightcraft Project

NASA Technical Reports Server (NTRS)

1988-01-01

The overall goal for this NASA/USRA-sponsored 'Apollo Lightcraft Project' is to develop a revolutionary launch vehicle technology that can reduce payload transport costs by a factor of 1000 below the Space Shuttle Orbiter. The RPI design team proposes to utilize advanced, highly energetic, beamed-energy sources (laser, microwave) and innovative combined-cycle (airbreathing/rocket) engines to accomplish this goal. This second year focused on systems integration and analysis of the 'Apollo Lightcraft'. This beam-powered, single-stage-to-orbit vehicle is envisioned as the globe-trotting family shuttlecraft of the 21st century. Detailed investigations of the Apollo Lightcraft Project during the second year of study helped evolve the propulsion system design, while focusing on the following areas: (1) man/machine interface; (2) flight control systems; (3) power beaming system architecture; (4) reentry aerodynamics; (5) shroud structural dynamics; and (6) optimal trajectory analysis.

Aeromechanics and man-machine integration technology opportunities for rotorcraft of the 1990s and beyond

NASA Technical Reports Server (NTRS)

Kerr, Andrew W.

1989-01-01

Programs related to rotorcraft aeromechanics and man-machine integration are discussed which will support advanced army rotorcraft design. In aeromechanics, recent advances in computational fluid dynamics will be used to characterize the complex unsteady flowfields of rotorcraft, and a second-generation comprehensive helicopter analysis system will be used along with models of aerodynamics, engines, and control systems to study the structural dynamics of rotor/body configurations. The man-machine integration program includes the development of advanced cockpit design technology and the evaluation of cockpit and mission equipment concepts in a real-time full-combat environment.

An Earth Orbiting Satellite Service and Repair Facility

NASA Technical Reports Server (NTRS)

Berndt, Andrew; Cardoza, Mike; Chen, John; Daley, Gunter; Frizzell, Andy; Linton, Richard; Rast, Wayne

1989-01-01

A conceptual design was produced for the Geosynchronous Satellite Servicing Platform (GSSP), an orbital facility capable of repairing and servicing satellites in geosynchronous orbit. The GSSP is a man-tended platform, which consists of a habitation module, operations module, service bay and truss assembly. This design review includes an analysis of life support systems, thermal and power requirements, robotic and automated systems, control methods and navigation, and communications systems. The GSSP will utilize existing technology available at the time of construction, focusing mainly on modifying and integrating existing systems. The entire facility, along with two satellite retrieval vehicles (SRV), will be placed in geosynchronous orbit by the Advanced Launch System. The SRV will be used to ferry satellites to and from the GSSP. Technicians will be transferred from Earth to the GSSP and back in an Apollo-derived Crew Transfer Capsule (CTC). These missions will use advanced telerobotic equipment to inspect and service satellites. Four of these missions are tentatively scheduled per year. At this rate, the GSSP will service over 650 satelites during the projected 25 year lifespan.

Current CFD Practices in Launch Vehicle Applications

NASA Technical Reports Server (NTRS)

Kwak, Dochan; Kiris, Cetin

2012-01-01

The quest for sustained space exploration will require the development of advanced launch vehicles, and efficient and reliable operating systems. Development of launch vehicles via test-fail-fix approach is very expensive and time consuming. For decision making, modeling and simulation (M&S) has played increasingly important roles in many aspects of launch vehicle development. It is therefore essential to develop and maintain most advanced M&S capability. More specifically computational fluid dynamics (CFD) has been providing critical data for developing launch vehicles complementing expensive testing. During the past three decades CFD capability has increased remarkably along with advances in computer hardware and computing technology. However, most of the fundamental CFD capability in launch vehicle applications is derived from the past advances. Specific gaps in the solution procedures are being filled primarily through "piggy backed" efforts.on various projects while solving today's problems. Therefore, some of the advanced capabilities are not readily available for various new tasks, and mission-support problems are often analyzed using ad hoc approaches. The current report is intended to present our view on state-of-the-art (SOA) in CFD and its shortcomings in support of space transport vehicle development. Best practices in solving current issues will be discussed using examples from ascending launch vehicles. Some of the pacing will be discussed in conjunction with these examples.

LAUNCH - STS-28/51J - KSC

NASA Image and Video Library

1985-11-20

S85-44776 (3 Oct 1985) --- Space Shuttle Atlantis soars toward Florida blue skies to mark the maiden mission of NASA's fourth and newest orbiter vehicle. Launch occurred at 11:15 a.m. (EDT), October 3, 1985. A five member crew mans the orbiter for the DOD flight. They are Karol J. Bobko, Ronald J. Grabe, Robert L. Stewart, David C. Hilmers-- all of NASA-- and William A. Pailes of the USAF.

Saturn Apollo Program

NASA Image and Video Library

1971-01-31

In the launch control center at Kennedy Space Flight Center (KSC), Walter J. Kapryan, Director of Launch Operations (center), discusses an aspect of the Apollo 14 flight with Marshall Space Flight Center’s (MSFC) Dr. Rocco A. Petrone, Apollo Program Director (right). The Apollo 14, carrying a crew of three astronauts: Mission commander Alan B. Shepard Jr., Command Module pilot Stuart A. Roosa, and Lunar Module pilot Edgar D. Mitchell, lifted off from launch complex 39A at KSC on January 31, 1971. It was the third manned lunar landing, the first manned landing in exploration of the lunar highlands, and it demonstrated pinpoint landing capability. The major goal of Apollo 14 was the scientific exploration of the Moon in the foothills of the rugged Fra Mauro region. The extravehicular activity (EVA) of astronauts Shepard and Mitchell included setting up an automated scientific laboratory called Apollo Lunar Scientific Experiments Package (ALSEP), and collecting a total of about 95 pounds (43 kilograms) of Moon rock and soil for a geological investigation back on the Earth. Apollo 14 safely returned to Earth on February 9, 1971.

A Study for Mars Manned Exploration

NASA Technical Reports Server (NTRS)

Dorney, Daniel J.; Scimemi, Sam

2012-01-01

Over the last five decades there have been numerous studies devoted to developing, launching and conducting a manned mission to Mars by both Russian and U.S. organizations. These studies have proposed various crew sizes, mission length, propulsion systems, habitation modules, and scientific goals. As a first step towards establishing an international partnership approach to a Mars mission, the most recent Russian concepts are explored and then compared to NASA's latest Mars reference mission.

Possible Scenarios for Mars Manned Exploration

NASA Technical Reports Server (NTRS)

Dorney, Daniel J.; Schumacher, Daniel M.

2012-01-01

Over the last five decades there have been numerous studies devoted to developing, launching and conducting a manned mission to Mars by both Russian and U.S. organizations. These studies have proposed various crew sizes, mission length, propulsion systems, habitation modules, and scientific goals. As a first step towards establishing an international partnership approach to a Mars mission, the most recent Russian concepts are explored and then compared to NASA's current Mars reference mission.

Impact of lunar oxygen production on direct manned Mars missions

NASA Technical Reports Server (NTRS)

Young, Roy M., Jr.; Tucker, William B.

1992-01-01

A manned Mars program made up of six missions is evaluated to determine the impact of using lunar liquid oxygen (LOX) as a propellant. Two departure and return nodes, low Earth orbit and low lunar orbit, are considered, as well as two return vehicle configurations, a full 70,000-kg vehicle and a 6800-kg capsule. The cost of lunar LOX delivered to orbit is expressed as a ratio of Earth launch cost.

ASTRONAUT CONRAD, CHARLES - SKYLAB-II - JSC

NASA Image and Video Library

1973-05-09

S73-25283 (8 May 1973) --- Astronaut Paul J. Weitz, prime crew pilot of the first manned Skylab mission, is suited up in Bldg. 5 at Johnson Space Center during prelaunch training activity. He is assisted by astronaut Charles Conrad Jr., prime crew commander. The man in the left background is wearing a face mask to insure that Conrad, Joseph Kerwin and Weitz are not exposed to disease prior to launch. Photo credit: NASA

China’s Manned Space Program: Sun Tzu or Apollo Redux

DTIC Science & Technology

2003-01-01

sustainable development and making the de - velopment of space activities . . . serve the state’s comprehensive development strat- egy. The Chinese...perspective, it is a historical necessity for man to travel into space,” a poster pro- claimed. A six-wheeled robotic detector was unveiled as potentially...likely either with the parachutes or the retro-rockets. The Chinese de - nied such allegations. Shenzhou III was launched on 24 March 2002 and

Alisse : Advanced life support system evaluator

NASA Astrophysics Data System (ADS)

Brunet, Jean; Gerbi, Olivier; André, Philippe; Davin, Elisabeth; Avezuela Rodriguez, Raul; Carbonero, Fernando; Soumalainen, Emilia; Lasseur, Christophe

Long duration missions, such as the establishment of permanent bases on the lunar surface or the travel to Mars, require such an amount of life support consumables (e.g. food, water and oxygen) that direct supply or re-supply from Earth is not an option anymore. Regenerative Life Support Systems are therefore necessary to sustain long-term manned space mission to increase recycling rates and so reduce the launched mass. The architecture of an Environmental Controlled Life Support System widely depends on the mission scenario. Even for a given mission scenario, different architectures could be envisaged which need to be evaluated and compared with appropriate tools. As these evaluation and comparison, based on the single criterion of Equivalent System Mass, was not considered com-prehensive enough, ESA is developing a multi-criteria evaluation tool: ALISSE (Advanced Life Support System Evaluator). The main objective of ALISSE, and of the work presented here, is the definition and implemen-tation of a metrics system, addressing the complexity of any ECLSS along its Life Cycle phases. A multi-dimensional and multi-criteria (i.e. mass, energy, efficiency, risk to human, reliability, crew time, sustainability, life cycle cost) approach is proposed through the development of a computing support platform. Each criterion being interrelated with the others, a model based system approach is used. ALISSE is expected to provide significant inputs to the ESA Concurrent Design Facility and, as a consequence, to be a highly valuable tool for decision process linked to any manned space mission. Full contact detail for the contact author : Jean Brunet Sherpa Engineering General Manager Phone : 0033(0)608097480 j.brunet@sherpa-eng.com

Earth orbital operations supporting manned interplanetary missions

NASA Astrophysics Data System (ADS)

Sherwood, Brent; Buddington, Patricia A.; Whittaker, William L.

The orbital operations required to accumulate, assemble, test, verify, maintain, and launch complex manned space systems on interplanetary missions from earth orbit are as vital as the flight hardware itself. Vast numbers of orbital crew are neither necessary nor desirable for accomplishing the required tasks. A suite of robotic techniques under human supervisory control, relying on sensors, software and manipulators either currently emergent or already applied in terrestrial settings, can make the job tractable. The mission vehicle becomes largely self-assembling, using its own rigid aerobrake as a work platform. The Space Station, having been used as a laboratory testbed and to house an assembly crew of four, is not dominated by the process. A feasible development schedule, if begun soon, could emplace orbital support technologies for exploration missions in time for a 2004 first interplanetary launch.

Earth orbital operations supporting manned interplanetary missions

NASA Technical Reports Server (NTRS)

Sherwood, Brent; Buddington, Patricia A.; Whittaker, William L.

1989-01-01

The orbital operations required to accumulate, assemble, test, verify, maintain, and launch complex manned space systems on interplanetary missions from earth orbit are as vital as the flight hardware itself. Vast numbers of orbital crew are neither necessary nor desirable for accomplishing the required tasks. A suite of robotic techniques under human supervisory control, relying on sensors, software and manipulators either currently emergent or already applied in terrestrial settings, can make the job tractable. The mission vehicle becomes largely self-assembling, using its own rigid aerobrake as a work platform. The Space Station, having been used as a laboratory testbed and to house an assembly crew of four, is not dominated by the process. A feasible development schedule, if begun soon, could emplace orbital support technologies for exploration missions in time for a 2004 first interplanetary launch.

ksc-81pc-382

NASA Image and Video Library

1981-04-12

KENNEDY SPACE CENTER, FLA. -- After six years of silence, the thunder of manned space flight is heard again as the successful launch of the first Space Shuttle ushers in a new concept in utilization of space. The April 12 launch at Pad 39A, just seconds past 7 a.m., carries astronauts John Young and Robert Crippen into an Earth orbital mission scheduled to last for 54 hours, ending with unpowered landing at Edwards Air Force Base in California. STS-1, the first in a series of shuttle vehicles planned for the Space Transportation sysstem, utilizes reusable launch and return components

Soyuz Spacecraft Transported to Launch Pad

NASA Technical Reports Server (NTRS)

2003-01-01

The Soyuz TMA-3 spacecraft and its booster rocket (front view) is shown on a rail car for transport to the launch pad where it was raised to a vertical launch position at the Baikonur Cosmodrome, Kazakhstan on October 16, 2003. Liftoff occurred on October 18th, transporting a three man crew to the International Space Station (ISS). Aboard were Michael Foale, Expedition-8 Commander and NASA science officer; Alexander Kaleri, Soyuz Commander and flight engineer, both members of the Expedition-8 crew; and European Space agency (ESA) Astronaut Pedro Duque of Spain. Photo Credit: 'NASA/Bill Ingalls'

Soyuz Spacecraft Transported to Launch Pad

NASA Technical Reports Server (NTRS)

2003-01-01

The Soyuz TMA-3 spacecraft and its booster rocket (rear view) is shown on a rail car for transport to the launch pad where it was raised to a vertical launch position at the Baikonur Cosmodrome, Kazakhstan on October 16, 2003. Liftoff occurred on October 18th, transporting a three man crew to the International Space Station (ISS). Aboard were Michael Foale, Expedition-8 Commander and NASA science officer; Alexander Kaleri, Soyuz Commander and flight engineer, both members of the Expedition-8 crew; and European Space agency (ESA) Astronaut Pedro Duque of Spain. Photo Credit: 'NASA/Bill Ingalls'

Short rendezvous missions for advanced Russian human spacecraft

NASA Astrophysics Data System (ADS)

Murtazin, Rafail F.; Budylov, Sergey G.

2010-10-01

The two-day stay of crew in a limited inhabited volume of the Soyuz-TMA spacecraft till docking to ISS is one of the most stressful parts of space flight. In this paper a number of possible ways to reduce the duration of the free flight phase are considered. The duration is defined by phasing strategy that is necessary for reduction of the phase angle between the chaser and target spacecraft. Some short phasing strategies could be developed. The use of such strategies creates more comfortable flight conditions for crew thanks to short duration and additionally it allows saving spacecraft's life support resources. The transition from the methods of direct spacecraft rendezvous using one orbit phasing (first flights of " Vostok" and " Soyuz" vehicles) to the currently used methods of two-day rendezvous mission can be observed in the history of Soviet manned space program. For an advanced Russian human rated spacecraft the short phasing strategy is recommended, which can be considered as a combination between the direct and two-day rendezvous missions. The following state of the art technologies are assumed available: onboard accurate navigation; onboard computations of phasing maneuvers; launch vehicle with high accuracy injection orbit, etc. Some operational requirements and constraints for the strategies are briefly discussed. In order to provide acceptable phase angles for possible launch dates the experience of the ISS altitude profile control can be used. As examples of the short phasing strategies, the following rendezvous missions are considered: direct ascent, short mission with the phasing during 3-7 orbits depending on the launch date (nominal or backup). For each option statistical modeling of the rendezvous mission is fulfilled, as well as an admissible phase angle range, accuracy of target state vector and addition fuel consumption coming out of emergency is defined. In this paper an estimation of pros and cons of all options is conducted.

Human Adaptation to the Computer.

DTIC Science & Technology

1986-09-01

advance in man’s civilization [Ref. 3:p. 4]. This advance has caused dramatic changes in man’s way of life. It has caused several emotions in man that...their program run or com- pleting their work project can create within them a loss of human feeling and emotion . There have been a lot of jokes made...aggression 44 3. violence 4. antisocial activity 5. grievances 6. work slowdowns/missed deadlines 7. strikes B. absenteeism 9. tardiness 10. turnover

Apollo 11 Launched Via the Saturn V Rocket-High Angle View

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first lunar landing mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. The Saturn V vehicle produced a holocaust of flames as it rose from its pad at Launch complex 39. The 363 foot tall, 6,400,000 pound rocket hurled the spacecraft into Earth parking orbit and then placed it on the trajectory to the moon for man's first lunar landing. This high angle view of the launch was provided by a `fisheye' camera mounted on the launch tower. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module pilot; and Edwin E. Aldrin Jr., Lunar Module pilot. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Space station operations management

NASA Technical Reports Server (NTRS)

Cannon, Kathleen V.

1989-01-01

Space Station Freedom operations management concepts must be responsive to the unique challenges presented by the permanently manned international laboratory. Space Station Freedom will be assembled over a three year period where the operational environment will change as significant capability plateaus are reached. First Element Launch, Man-Tended Capability, and Permanent Manned Capability, represent milestones in operational capability that is increasing toward mature operations capability. Operations management concepts are being developed to accomodate the varying operational capabilities during assembly, as well as the mature operational environment. This paper describes operations management concepts designed to accomodate the uniqueness of Space Station Freedoom, utilizing tools and processes that seek to control operations costs.

Skylab 2 prime crew suit up during prelaunch training activity

NASA Image and Video Library

1973-05-08

S73-25399 (8 May 1973) --- Astronaut Paul J. Weitz, prime crew pilot of the first manned Skylab mission, is suited up in Bldg. 5 at Johnson Space Center (JSC) during prelaunch training activity. He is assisted by astronaut Charles Conrad, Jr., prime crew commander. The man in the left background is wearing a face mask to insure that Conrad, Joseph Kerwin and Weitz are not exposed to disease prior to launch. Photo credit: NASA

First Apollo 11 Lunar Samples Arrive at the Manned Spacecraft Center (MSC)

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named 'Eagle'', carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. This photograph was taken as the mission's first loaded sample return container arrived at Ellington Air Force Base by air from the Pacific recovery area. The rock box was immediately taken to the Lunar Receiving Laboratory at the Manned Spacecraft Center (MSC) in Houston, Texas. Happily posing for the photograph with the rock container are (L-R) Richard S. Johnston (back), special assistant to the MSC Director; George M. Low, MSC Apollo Spacecraft Program manager; George S. Trimble (back), MSC Deputy Director; Lt. General Samuel C. Phillips, Apollo Program Director, Office of Manned Spaceflight at NASA headquarters; Eugene G. Edmonds, MSC Photographic Technology Laboratory; Dr. Thomas O. Paine, NASA Administrator; and Dr. Robert R. Gilruth, MSC Director.

Columbus future evolution potential

NASA Astrophysics Data System (ADS)

Altmann, G.; Rausch, G.; Sax, H.

Europe is at a crossroads in the evolution of manned space flight. Following the invitation of President Reagan to participate in the US Space Station Programme, Europe is now to decide on the content and financial envelope for such a programme. The actual path chosen will determine the way forward to the end of this century and beyond. The preparatory Columbus programme initiated in 1985 and planned to be completed by the end of 1987 has now reached a critical point with the definition of a new programme baseline for further study in phase B2 running from November 1986 to May 1987. The new programme baseline as described in chapter 3 covers the following elements: ∘ A pressurised module for permanent attachment to the NASA Space Station, to be launched by the NASA STS. ∘ A man-tended free flyer (MTFF) consisting of a pressurised module and a resource module to be designed and developed for a launch by ARIANE 5. ∘ A polar platform primarily dedicated to Earth Observation user requirements designed for launch by ARIANE 5. ∘ As an option an enhanced version of the present EURECA carrier to be deployed as a coorbiting platform dedicated primarily to microgravity and space sciences. The planned contribution to the international Space Station based on the above space segment definition must be viewed in the light of a European long term plan, the ultimate goal of which is an autonomous capability. Considering that the core element of a potential European Space Station is the MTFF the paper will describe in more detail how the presently defined MTFF capability could grow further to satisfy the needs of interested user communities in the long term. The evolution of this element will essentially pass through two stages, the man-tended stage during which automated systems (robotics) will assist with the implementation of research and commercial processes and the manned stage where permanent presence of man in combination with automated systems will bring about the degree of flexibility needed for efficient operations in space. The present assumptions made in the context of describing the future potential of the MTFF are subject to revision as further results become available from the ongoing COLUMBUS programme definition process.

The Advanced X-ray Imaging Satellite (AXIS)

NASA Astrophysics Data System (ADS)

Reynolds, Christopher S.; Mushotzky, Richard

2017-08-01

The Advanced X-ray Imaging Satellite (AXIS) will follow in the footsteps of the spectacularly successful Chandra X-ray Observatory with similar or higher angular resolution and an order of magnitude more collecting area in the 0.3-10keV band. These capabilities will enable major advances in many of the most active areas of astrophysics, including (i) mapping event horizon scale structure in AGN accretion disks and the determination of supermassive black hole (SMBH) spins through monitoring of gravitationally-microlensed quasars; (ii) dramatically deepening our understanding of AGN feedback in galaxies and galaxy clusters out to high-z through the direct imaging of AGN winds and the interaction of jets with the hot interstellar/intracluster medium; (iii) understanding the fueling of AGN by probing hot flows inside of the SMBH sphere of influence; (iv) obtaining geometric distance measurements using dust scattering halos. With a nominal 2028 launch, AXIS will be enormously synergistic with LSST, ALMA, WFIRST and ATHENA, and will be a valuable precursor to Lynx. AXIS is enabled by breakthroughs in the construction of light-weight X-ray optics from mono-crystalline silicon blocks, building on recent developments in the semiconductor industry. Here, we describe the straw-man concept for AXIS, some of the high profile science that this observatory will address, and how you can become involved.

Astronautics and aeronautics, 1970. Chronology on science, technology, and policy

NASA Technical Reports Server (NTRS)

1972-01-01

An immediate reference to aerospace-related events of 1970 is provided to help historians in preserving historical accuracy and precision. Chronologies of major NASA launches, and manned space flights for 1970 are included.

The X-20 space plane: Past innovation, future vision

NASA Astrophysics Data System (ADS)

Sunday, Terry L.; London, John R.

In November 1957, the U.S. Air Force initiated an aerospace project that was one of the most innovative concepts of its day, and also provided an accurate glimpse into the future. The X-20 space plane, known as Dyna-Soar, never reached operational status—it was cancelled in December 1963, before the first prototype was built. But even though the diminutive vehicle never flew, technological advances made during its development laid the foundation for many later manned space systems, including some as new as tomorrow's headlines. The paper examines both the history and the technology of Dyna-Soar. The space plane's unique design and its proposed missions are examined, along with the ever-changing political, economic and programmatic environments that led to its conception, its long, painful gestation period, and its demise. The X-20 premiered many innovations to solve the challenges of launch, manned orbital operations and re-entry for a re-usable spacecraft. Many of these technologies did not reach fruition until decades later. Based largely on recently declassified material, this paper places Dyna-Soar into a broad historical context as an interesting research vehicle concept from three decades past, and as the purveyor of a technological legacy whose impacts are still being felt today.

The comparative analysis of the forecasts of development of rocket propulsion in past and now

NASA Astrophysics Data System (ADS)

Nedaivoda, A.; Prisniakov, V.

2001-03-01

Consideration is being given to use the known long and short forecasts of development of rocket engines in past - at the beginning of development of a missile engineering (K. Tsiolkovsky etc. pioneers of rocket propulsion); on the eve of launching of the artificial satellite of Earth (A. Blagonravov); after manned flight of Yu. Gagarin (V. Gluchko); after manned flight on Moon (" The Forecasts on 2001 " on materials of readings R. Goddard in USA); in middle of 70-s' years (D. Sevruk, V. Prisniakov) and at the end of 20 centure. Last years under the initiative R. Beichel and M. Pouliquen IAA. Advanced Propulsion Working Group carries out large researches on definition of the tendencies of development of rocket propulsion for the next forty years, the outcomes which one will be used in the report. The comparison of development of rocket propulsion expected to the end of 20 century and real-life is given. The report analyses the errors of the forecasts of the past - the absence reliable prognostic procedure; the euphoria of the maiden successes of conquest of space; dominance of military and political- propaganda motives of implementation of the space programs before economical; to keep developments secret; competition of two super-powers USSR and USA etc.

Moving Towards a Common Ground and Flight Data Systems Architecture for NASA's Exploration Missions

NASA Technical Reports Server (NTRS)

Rader. Steve; Kearney, Mike; McVittie, Thom; Smith, Dan

2006-01-01

The National Aeronautics and Space Administration has embarked on an ambitious effort to return man to the moon and then on to Mars. The Exploration Vision requires development of major new space and ground assets and poses challenges well beyond those faced by many of NASA's recent programs. New crewed vehicles must be developed. Compatible supply vehicles, surface mobility modules and robotic exploration capabilities will supplement the manned exploration vehicle. New launch systems will be developed as well as a new ground communications and control infrastructure. The development must take place in a cost-constrained environment and must advance along an aggressive schedule. Common solutions and system interoperability and will be critical to the successful development of the Exploration data systems for this wide variety of flight and ground elements. To this end, NASA has assembled a team of engineers from across the agency to identify the key challenges for Exploration data systems and to establish the most beneficial strategic approach to be followed. Key challenges and the planned NASA approach for flight and ground systems will be discussed in the paper. The described approaches will capitalize on new technologies, and will result in cross-program interoperability between spacecraft and ground systems, from multiple suppliers and agencies.

Technology advancement of the electrochemical CO2 concentrating process

NASA Technical Reports Server (NTRS)

Schubert, F. H.; Woods, R. R.; Hallick, T. M.; Heppner, D. B.

1977-01-01

A five-cell, liquid-cooled advanced electrochemical depolarized carbon dioxide concentrator module was fabricated. The cells utilized the advanced, lightweight, plated anode current collector concept and internal liquid-cooling. The five cell module was designed to meet the carbon dioxide removal requirements of one man and was assembled using plexiglass endplates. This one-man module was tested as part of an integrated oxygen generation and recovery subsystem.

Apollo 12 Mission Summary and Splashdown

NASA Technical Reports Server (NTRS)

1999-01-01

This NASA Kennedy Space Center (KSC) video release presents footage of the November 14, 1969 Apollo-12 space mission begun from launch complex pad 39-A at Kennedy Space Center, Florida. Charles Conrad, Jr., Richard F. Gordon, Jr., and Alan L. Bean make up the three-man spacecrew. The video includes the astronaut's pre-launch breakfast, President Nixon, his wife, and daughter arriving at Cape Kennedy in time to see the launch, as well as countdown and liftoff. After the launch, President Nixon gives a brief congratulatory speech to the members of launch control at KSC. The video also presents views of the astronauts and spacecraft in space as well as splashdown of the command module on November 24, 1969. The video ends with the recovery, by helicopter and additional personnel, of the spacecrew from the command module floating in the waters of the Atlantic.

SKYLAB (SL)-III - LAUNCH - KSC

NASA Image and Video Library

1973-08-17

S73-32570 (28 July 1973) --- The Skylab 3/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 7:11 a.m. (EDT), Saturday, July 28, 1973. Skylab 3 is the second of three scheduled Skylab manned missions. Aboard the Skylab 3 Command/Service Module were astronauts Alan L. Bean, Owen K. Garriott and Jack R. Lousma. The Skylab 3 CSM later docked with the Skylab space station cluster in Earth orbit. In addition to the CSM and its launch escape system, the Skylab 3 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-1VB) stage. (The Skylab 1/Saturn V space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

Skylab mission report, third visit

NASA Technical Reports Server (NTRS)

1974-01-01

An evaluation is presented of the operational and engineering aspects of the third Skylab visit, including information on the performance of the command and service module and the experiment hardware, the crew's evaluation of the visit, and other visit-related areas of interest such as biomedical observations. The specific areas discussed are contained in the following: (1) solar physics and astrophysics investigations; (2) Comet Kohoutek experiments; (3) medical experiments; (4) earth observations, including data for the multispectral photographic facility, the earth terrain camera, and the microwave radiometer/scattermometer and altimeter; (5) engineering and technology experiments; (6) food and medical operational equipment; (7) hardware and experiment anomalies; and (8) mission support, mission objectives, flight planning, and launch phase summary. Conclusions discussed as a result of the third visit to Skylab involve the advancement of the sciences, practical applications, the durability of man and systems in space, and spaceflight effectiveness and economy.

Application of dual-fuel propulsion to a single stage AMLS vehicle

NASA Technical Reports Server (NTRS)

Lepsch, Roger A., Jr.; Stanley, Douglas O.; Unal, Resit

1993-01-01

As part of NASA's Advanced Manned Launch System (AMLS) study to determine a follow-on, or complement, to the Space Shuttle, a reusable single-stage-to-orbit concept utilizing dual-fuel rocket propulsion has been examined. Several dual-fuel propulsion concepts were investigated. These include: a separate engine concept combining Russian RD-170 kerosene-fueled engines with SSME-derivative engines; the kerosene and hydrogen-fueled Russian RD-701 engine concept; and a dual-fuel, dual-expander engine concept. Analysis to determine vehicle weight and size characteristics was performed using conceptual level design techniques. A response surface methodology for multidisciplinary design was utilized to optimize the dual-fuel vehicle concepts with respect to several important propulsion system and vehicle design parameters in order to achieve minimum empty weight. Comparisons were then made with a hydrogen-fueled reference, single-stage vehicle. The tools and methods employed in the analysis process are also summarized.

Editorial Research Reports on Modern Man.

ERIC Educational Resources Information Center

Dickinson, William B., Jr., Ed.

Nine reports published in this volume study the uneasy coexistence of modern man and the complex society he has wrought. Man's apparent disorganized behavior is attributed to his inability to adapt readily to the charged pace of technological change. To combat the advancement of machine over man, he must, therefore, insist that moral and…

Straw man trade between multi-junction, gallium arsenide, and silicon solar cells

NASA Technical Reports Server (NTRS)

Gaddy, Edward M.

1995-01-01

Multi-junction (MJ), gallium arsenide (GaAs), and silicon (Si) solar cells have respective test efficiencies of approximately 24%, 18.5% and 14.8%. Multi-junction and gallium arsenide solar cells weigh more than silicon solar cells and cost approximately five times as much per unit power at the cell level. A straw man trade is performed for the TRMM spacecraft to determine which of these cell types would have offered an overall performance and price advantage to the spacecraft. A straw man trade is also performed for the multi-junction cells under the assumption that they will cost over ten times that of silicon cells at the cell level. The trade shows that the TRMM project, less the cost of the instrument, ground systems and mission operations, would spend approximately $552 thousand dollars per kilogram to launch and service science in the case of the spacecraft equipped with silicon solar cells. If these cells are changed out for gallium arsenide solar cells, an additional 31 kilograms of science can be launched and serviced at a price of approximately $90 thousand per kilogram. The weight reduction is shown to derive from the smaller area of the array and hence reductions in the weight of the array substrate and supporting structure. If the silicon solar cells are changed out for multi-junction solar cells, an additional 45 kilograms of science above the silicon base line can be launched and serviced at a price of approximately $58 thousand per kilogram. The trade shows that even if the multi-junction arrays are priced over ten times that of silicon cells, a price that is much higher than projected, that the additional 45 kilograms of science are launched and serviced at $182 thousand per kilogram. This is still much less than original $552 thousand per kilogram to launch and service the science. Data and qualitative factors are presented to show that these figures are subject to a great deal of uncertainty. Nonetheless, the benefit of the higher efficiency solar cells for TRMM is far greater than the uncertainties in the analysis.

Advanced Space Transportation Program (ASTP)

NASA Image and Video Library

1995-01-23

Pictured here is a DC-XA Reusable Launch Vehicle (RLV) prototype concept with an RLV logo. The Delta Clipper-Experimental (DC-X) was originally developed by McDornell Douglas for the Department of Defense (DOD). The DC-XA is a single-stage-to-orbit, vertical takeoff/vertical landing, launch vehicle concept, whose development is geared to significantly reduce launch costs and will provide a test bed for NASA Reusable Launch Vehicle (RLV) technology as the Delta Clipper-Experimental Advanced (DC-XA).

Saturn Apollo Program

NASA Image and Video Library

1969-07-27

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. In this close up of the MQF, commander Armstrong can be seen through the facility window after its arrival at the MSC.

Database Tool for Master Console Operators

NASA Technical Reports Server (NTRS)

Ferrell, Sean

2018-01-01

The Spaceport Command and Control System (SCCS) is the National Aeronautics and Space Administration's (NASA) launch control system for the Orion capsule and Space Launch System, the next generation manned rocket currently in development. This large system requires highly trained and knowledgeable personnel. Master Console Operators (MCO) are currently working on familiarizing themselves with any possible scenario that they may encounter. An intern was recruited to help assist them with creating a tool to use for the process.

KSC-04pd0651

NASA Image and Video Library

2004-03-26

KENNEDY SPACE CENTER, FLA. -- This aerial photo shows the storage area containing Launch Umbilical Towers that were used during the early years of the Space Program. In the lower left corner of the storage field is a Caterpillar excavator with a 48-inch shear demolishing LUT-1, used to launch Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0649

NASA Image and Video Library

2004-03-26

KENNEDY SPACE CENTER, FLA. -- This aerial photo shows the storage area containing Launch Umbilical Towers that were used during the early years of the Space Program. In the lower right corner of the storage field is a Caterpillar excavator with a 48-inch shear demolishing LUT-1, used to launch Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

KSC-04pd0648

NASA Image and Video Library

2004-03-26

KENNEDY SPACE CENTER, FLA. -- This aerial photo shows the storage area containing Launch Umbilical Towers that were used during the early years of the Space Program. In the upper right corner of the storage field is a Caterpillar excavator with a 48-inch shear demolishing LUT-1, used to launch Apollo 8, Apollo 11, Skylab manned missions and the Apollo-Soyuz Test Project. The shear is one used in the deconstruction of the Twin Towers in New York City after 9/11.

Shoulder Launched Missiles (A.K.A. MANPADS): The Ominous Threat to Commercial Aviation

DTIC Science & Technology

2006-12-01

global trade and just-in-time delivery, along with its leadership status in the world’s largest industry , travel and tourism , make it even more...vulnerability to shoulder launched missiles, also known as MANPADS (Man Portable Air Defense Systems). This industry sustains the flow of goods...that “a credible threat to the viability of America’s commercial airline industry could have profound effects on the nation’s economy and on

Skylab

NASA Image and Video Library

1969-01-01

This cutaway drawing illustrates major Skylab components in launch configuration on top of the Saturn V. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab Program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Manned space flight nuclear system safety. Volume 3: Reactor system preliminary nuclear safety analysis. Part 1: Reference Design Document (RDD)

NASA Technical Reports Server (NTRS)

1972-01-01

The Reference Design Document, of the Preliminary Safety Analysis Report (PSAR) - Reactor System provides the basic design and operations data used in the nuclear safety analysis of the Rector Power Module as applied to a Space Base program. A description of the power module systems, facilities, launch vehicle and mission operations, as defined in NASA Phase A Space Base studies is included. Each of two Zirconium Hydride Reactor Brayton power modules provides 50 kWe for the nominal 50 man Space Base. The INT-21 is the prime launch vehicle. Resupply to the 500 km orbit over the ten year mission is provided by the Space Shuttle. At the end of the power module lifetime (nominally five years), a reactor disposal system is deployed for boost into a 990 km high altitude (long decay time) earth orbit.

Skylab

NASA Image and Video Library

1971-01-01

This illustration depicts the Skylab-1 and Skylab-2 mission sequence. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Thermal protection systems manned spacecraft flight experience

NASA Technical Reports Server (NTRS)

Curry, Donald M.

1992-01-01

Since the first U.S. manned entry, Mercury (May 5, 1961), seventy-five manned entries have been made resulting in significant progress in the understanding and development of Thermal Protection Systems (TPS) for manned rated spacecraft. The TPS materials and systems installed on these spacecraft are compared. The first three vehicles (Mercury, Gemini, Apollo) used ablative (single-use) systems while the Space Shuttle Orbiter TPS is a multimission system. A TPS figure of merit, unit weight lb/sq ft, illustrates the advances in TPS material performance from Mercury (10.2 lb/sq ft) to the Space Shuttle (1.7 lb/sq ft). Significant advances have been made in the design, fabrication, and certification of TPS on manned entry vehicles (Mercury through Shuttle Orbiter). Shuttle experience has identified some key design and operational issues. State-of-the-art ceramic insulation materials developed in the 1970's for the Space Shuttle Orbiter have been used in the initial designs of aerobrakes. This TPS material experience has identified the need to develop a technology base from which a new class of higher temperature materials will emerge for advanced space transportation vehicles.

Advanced small launch vehicle study

NASA Technical Reports Server (NTRS)

Reins, G. E.; Alvis, J. F.

1972-01-01

A conceptual design study was conducted to determine the most economical (lowest cost/launch) approach for the development of an advanced small launch vehicle (ASLV) for use over the next decade. The ASLV design objective was to place a 340 kg (750 lb) payload into a 556 km (300 n.mi.) circular orbit when launched due east from Wallops Island, Virginia. The investigation encompassed improvements to the current Scout launch vehicle; use of existing military and NASA launch vehicle stages; and new, optionally staged vehicles. Staging analyses included use of liquid, solid, and hybrid propellants. Improvements in guidance, controls, interstages, telemetry, and payload shroud were also considered. It was concluded that the most economical approach is to progressively improve the Scout launch vehicle in three phased steps which are discussed.

Comparison of mission design options for manned Mars missions

NASA Technical Reports Server (NTRS)

Babb, Gus R.; Stump, William R.

1986-01-01

A number of manned Mars mission types, propulsion systems, and operational techniques are compared. Conjunction and opposition class missions for cryogenic, hybrid (cryo/storable), and NERVA propulsion concepts are addressed. In addition, both Earth and Mars orbit aerobraking, direct entry of landers, hyperbolic rendezvous, and electric propulsion cases are examined. A common payload to Mars was used for all cases. The basic figure of merit used was weight in low Earth orbit (LEO) at mission initiation. This is roughly proportional to launch costs.

Skylab: The Second Manned Mission. A Scientific Harvest

NASA Technical Reports Server (NTRS)

1974-01-01

This black and white video presentation covers the Skylab launch activities and docking with unmanned SL-1 workshop. Included are observations of student experiments (the Minchmog minnows and Arabella, the spider), observations of student experiments, exercise routines, and the enabling of the Earth Resources Experiments Package. Also shown is planet Earth documentation, manned operation of the Apollo Telescope Mount for observations of the Sun and beyond, outside EVA activity, testing of the Astronaut Maneuvering Unit, experiments to explore industrial uses of space, and the Skylab living routine.

KSC-99pp0937

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- Neil Armstrong, former Apollo 11 astronaut, and first man to walk on the moon, talks about his experiences for an enthusiastic audience at the Apollo/Saturn V Center, part of the KSC Visitor Complex. The occasion was a banquet celebrating the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among other guests at the banquet were astronauts Wally Schirra, Edwin "Buzz" Aldrin and Walt Cunningham. Gene Cernan was the last man to walk on the moon

Prelaunch - Apollo X

NASA Image and Video Library

1969-05-18

S69-34482 (18 May 1969) --- Astronaut John W. Young, Apollo 10 command module pilot, jokes with Donald K. Slayton (standing left), director of Flight Crew Operations, Manned Spacecraft Center, during Apollo 10 suiting up operations. On couch in background is astronaut Eugene A. Cernan, lunar module pilot. Astronauts Young; Cernan; and Thomas P. Stafford, commander, rode a transfer van from the Manned Spacecraft Operations Building over to Pad B, Launch Complex 39 where their spacecraft awaited them. Liftoff was at 12:49 p.m. (EDT), May 18, 1969.

Internship at NASA Kennedy Space Center's Cryogenic Test laboratory

NASA Technical Reports Server (NTRS)

Holland, Katherine

2013-01-01

NASA's Kennedy Space Center (KSC) is known for hosting all of the United States manned rocket launches as well as many unmanned launches at low inclinations. Even though the Space Shuttle recently retired, they are continuing to support unmanned launches and modifying manned launch facilities. Before a rocket can be launched, it has to go through months of preparation, called processing. Pieces of a rocket and its payload may come in from anywhere in the nation or even the world. The facilities all around the center help integrate the rocket and prepare it for launch. As NASA prepares for the Space Launch System, a rocket designed to take astronauts beyond Low Earth Orbit throughout the solar system, technology development is crucial for enhancing launch capabilities at the KSC. The Cryogenics Test Laboratory at Kennedy Space Center greatly contributes to cryogenic research and technology development. The engineers and technicians that work there come up with new ways to efficiently store and transfer liquid cryogens. NASA has a great need for this research and technology development as it deals with cryogenic liquid hydrogen and liquid oxygen for rocket fuel, as well as long term space flight applications. Additionally, in this new era of space exploration, the Cryogenics Test Laboratory works with the commercial sector. One technology development project is the Liquid Hydrogen (LH2) Ground Operations Demonstration Unit (GODU). LH2 GODU intends to demonstrate increased efficiency in storing and transferring liquid hydrogen during processing, loading, launch and spaceflight of a spacecraft. During the Shuttle Program, only 55% of hydrogen purchased was used by the Space Shuttle Main Engines. GODU's goal is to demonstrate that this percentage can be increased to 75%. Figure 2 shows the GODU layout when I concluded my internship. The site will include a 33,000 gallon hydrogen tank (shown in cyan) with a heat exchanger inside the hydrogen tank attached to a refrigerator capable of removing 850 Watts at 20 Kelvin (shown in green). The refrigerator and most of its supporting equipment will be kept in a standard shipping container (shown in pink). Currently, GODU is in the fabrication process and some of the large components have already been purchased.

Lunar base launch and landing facilities conceptual design

NASA Technical Reports Server (NTRS)

Phillips, Paul G.; Simonds, Charles H.; Stump, William R.

1992-01-01

The purpose of this study was to perform a first look at the requirements for launch and landing facilities for early lunar bases and to prepared conceptual designs for some of these facilities. The emphasis of the study is on the facilities needed from the first manned landing until permanent occupancy, the Phase 2 lunar base. Factors including surface characteristics, navigation system, engine blast effects, and expected surface operations are used to develop landing pad designs, and definitions fo various other elements of the launch and landing facilities. Finally, the dependence of the use of these elements and the evolution of the facilities are established.

Launch Vehicles Based on Advanced Hybrid Rocket Motors: An Enabling Technology for the Commercial Small and Micro Satellite Planetary Science

NASA Astrophysics Data System (ADS)

Karabeyoglu, Arif; Tuncer, Onur; Inalhan, Gokhan

2016-07-01

Mankind is relient on chemical propulsion systems for space access. Nevertheless, this has been a stagnant area in terms of technological development and the technology base has not changed much almost for the past forty years. This poses a vicious circle for launch applications such that high launch costs constrain the demand and low launch freqencies drive costs higher. This also has been a key limiting factor for small and micro satellites that are geared towards planetary science. Rather this be because of the launch frequencies or the costs, the access of small and micro satellites to orbit has been limited. With today's technology it is not possible to escape this circle. However the emergence of cost effective and high performance propulsion systems such as advanced hybrid rockets can decrease launch costs by almost an order or magnitude. This paper briefly introduces the timeline and research challenges that were overcome during the development of advanced hybrid LOX/paraffin based rockets. Experimental studies demonstrated effectiveness of these advanced hybrid rockets which incorporate fast burning parafin based fuels, advanced yet simple internal balistic design and carbon composite winding/fuel casting technology that enables the rocket motor to be built from inside out. A feasibility scenario is studied using these rocket motors as building blocks for a modular launch vehicle capable of delivering micro satellites into low earth orbit. In addition, the building block rocket motor can be used further solar system missions providing the ability to do standalone small and micro satellite missions to planets within the solar system. This enabling technology therefore offers a viable alternative in order to escape the viscous that has plagued the space launch industry and that has limited the small and micro satellite delivery for planetary science.

The First 500 Registrations to the Research Registry®: Advancing Registration of Under-Registered Study Types.

PubMed

Agha, Riaz; Fowler, Alexander J; Limb, Christopher; Al Omran, Yasser; Sagoo, Harkiran; Koshy, Kiron; Jafree, Daniyal J; Anwar, Mohammed Omer; McCullogh, Peter; Orgill, Dennis Paul

2016-01-01

The Declaration of Helsinki 2013 encourages the registration of all research studies involving human participants. However, emphasis has been placed on prospective clinical trials, and it is estimated that only 10% of observational studies are registered. In response, Research Registry ® was launched in February 2015; a retrospectively curated registry that is free and easy to use. Research Registry ® enables prospective or retrospective registration of studies, including those study types that cannot be registered on existing registries. In this study, we describe the first 500 registrations on Research Registry ® . Since the launch of Research Registry ® in February 2015, data of registrations have been collected, including type of studies registered, country of origin, and data curation activity. Inappropriate registrations, such as duplicates, were identified by the data curation process. These were removed from the database or modified as required. A quality score was assigned for each registration, based on Sir Austin Bradford Hill's criteria on what research studies should convey. Changes in quality scores over time were assessed. A total of 500 studies were registered on Research Registry ® from February 2015 to October 2015, with a total of 1.7 million patients enrolled. The most common study types were retrospective cohort studies (37.2%), case series (14.8%), and first-in-man case reports (10.4%). Registrations were received from 57 different countries; the most submissions were received from Turkey, followed by China and the United Kingdom. Retrospective data curation identified 80 studies that were initially registered as the incorrect study type, and were subsequently correct. The Kruskal-Wallis test identified a significant improvement in quality scores for registrations from February 2015 to October 2015 ( p  < 0.0001). Since its conception in February 2015, Research Registry ® has established itself as a new registry that is free, easy to use, and enables the registration of various study types, including observational studies and first-in-man case reports. Going forward, our plan is to continue developing Research Registry ® in line with user feedback and usability studies. We plan to further promote Research Registry ® to advance the cause of registration of research, to increase compliance with the Declaration of Helsinki 2013.

Cost and Economics for Advanced Launch Vehicles

NASA Technical Reports Server (NTRS)

Whitfield, Jeff

1998-01-01

Market sensitivity and weight-based cost estimating relationships are key drivers in determining the financial viability of advanced space launch vehicle designs. Due to decreasing space transportation budgets and increasing foreign competition, it has become essential for financial assessments of prospective launch vehicles to be performed during the conceptual design phase. As part of this financial assessment, it is imperative to understand the relationship between market volatility, the uncertainty of weight estimates, and the economic viability of an advanced space launch vehicle program. This paper reports the results of a study that evaluated the economic risk inherent in market variability and the uncertainty of developing weight estimates for an advanced space launch vehicle program. The purpose of this study was to determine the sensitivity of a business case for advanced space flight design with respect to the changing nature of market conditions and the complexity of determining accurate weight estimations during the conceptual design phase. The expected uncertainty associated with these two factors drives the economic risk of the overall program. The study incorporates Monte Carlo simulation techniques to determine the probability of attaining specific levels of economic performance when the market and weight parameters are allowed to vary. This structured approach toward uncertainties allows for the assessment of risks associated with a launch vehicle program's economic performance. This results in the determination of the value of the additional risk placed on the project by these two factors.

Environmental Control System Development

NASA Technical Reports Server (NTRS)

Stewart, Raymond

2017-01-01

With the ever-growing desire for mankind to reach destinations whose distances had been deemed impossible to transit, the largest rocket known to man was designed and is being developed. The Space Launch System (SLS), National Aeronautics and Space Administration’s (NASA) solution for deep space travel, will begin its missions with the launch of Exploration Mission 1 (EM-1) and Exploration Mission 2 (EM-2). In order to accommodate the larger rocket, Kennedy Space Center made crucial upgrades to its existing facilities. At Launch Complex 39B, an entirely new Environmental Control System (ECS) was developed to supply the vehicle with the appropriate air or nitrogen gas mixture for launch. The new ECS displays must undergo Validation and Verification (V&V) using testing procedures developed to meet this requirement.

APOLLO XV - (LIFTOFF) - CAPE

NASA Image and Video Library

1971-07-26

S71-41810 (26 July 1971) --- The 363-feet tall Apollo 15 (Spacecraft 112/Lunar Module 10/Saturn 510) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center, Florida, at 9:34:00.79 a.m., July 26, 1971, on a lunar landing mission. Aboard the Apollo 15 spacecraft were astronauts David R. Scott, commander; Alfred M. Worden, commander module pilot; and James B. Irwin, lunar module pilot. Apollo 15 is the National Aeronautics and Space Administration's (NASA) fourth manned lunar landing mission.

n/a

NASA Image and Video Library

1967-11-01

Workmen at the Kennedy Space Center position the nose cone for the 204LM-1, an unmanned Apollo mission that tested the Apollo Lunar Module (LM) in Earth orbit. Also known as Apollo 5, the spacecraft was launched on the fourth Saturn IBC launch vehicle. Developed by the Marshall Space Flight Center (MSFC) as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IBC utilized Saturn I technology to further develop and refine a larger booster and the Apollo spacecraft capabilities required for the manned lunar missions.

Saturn Apollo Program

NASA Image and Video Library

1965-01-01

Workers at the Marshall Space Flight Center's (MSFC) Dynamic Test Stand install S-IB-200D, a dynamic test version of the Saturn IB launch vehicle's first stage, on January 11, 1965. MSFC Test Laboratory persornel assembled a complete Saturn IB to test the launch vehicle's structural soundness. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine the larger boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

Apollo 11 Launched Via Saturn V Rocket - High Angle View

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. The Saturn V vehicle produced a holocaust of flames as it rose from its pad at Launch complex 39. The 363 foot tall, 6,400,000 pound rocket hurled the spacecraft into Earth parking orbit and then placed it on the trajectory to the moon. This high angle view of the launch was provided by a `fisheye' camera mounted on the launch tower. The Saturn V was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun. Aboard the spacecraft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Launch Vehicle Debris Models and Crew Vehicle Ascent Abort Risk

NASA Technical Reports Server (NTRS)

Gee, Ken; Lawrence, Scott

2013-01-01

For manned space launch systems, a reliable abort system is required to reduce the risks associated with a launch vehicle failure during ascent. Understanding the risks associated with failure environments can be achieved through the use of physics-based models of these environments. Debris fields due to destruction of the launch vehicle is one such environment. To better analyze the risk posed by debris, a physics-based model for generating launch vehicle debris catalogs has been developed. The model predicts the mass distribution of the debris field based on formulae developed from analysis of explosions. Imparted velocity distributions are computed using a shock-physics code to model the explosions within the launch vehicle. A comparison of the debris catalog with an existing catalog for the Shuttle external tank show good comparison in the debris characteristics and the predicted debris strike probability. The model is used to analyze the effects of number of debris pieces and velocity distributions on the strike probability and risk.

Apollo Lightcraft Project

NASA Technical Reports Server (NTRS)

Myrabo, Leik N.; Atonison, Mark A. (Editor); Chen, Sammy G. (Editor); Decusatis, Casimer (Editor); Kusche, Karl P. (Editor); Minucci, Marco A. (Editor); Moder, Jeffrey P. (Editor); Morales, Ciro (Editor); Nelson, Caroline V. (Editor); Richard, Jacques C. (Editor)

1989-01-01

The ultimate goal for this NASA/USRA-sponsored Apollo Lightcraft Project is to develop a revolutionary manned launch vehicle technology which can potentially reduce payload transport costs by a factor of 1000 below the Space Shuttle Orbiter. The Rensselaer design team proposes to utilize advanced, highly energetic, beamed-energy sources (laser, microwave) and innovative combined-cycle (airbreathing/rocket) engines to accomplish this goal. The research effort focuses on the concept of a 100 MW-class, laser-boosted Lightcraft Technology Demonstrator (LTD) drone. The preliminary conceptual design of this 1.4 meter diameter microspacecraft involved an analytical performance analysis of the transatmospheric engine in its two modes of operation (including an assessment of propellant and tankage requirements), and a detailed design of internal structure and external aeroshell configuration. The central theme of this advanced propulsion research was to pick a known excellent working fluid (i.e., air or LN sub 2), and then to design a combined-cycle engine concept around it. Also, a structural vibration analysis was performed on the annular shroud pulsejet engine. Finally, the sensor satellite mission was examined to identify the requisite subsystem hardware: e.g., electrical power supply, optics and sensors, communications and attitude control systems.

Biconic cargo return vehicle with an advanced recovery system. Volume 1: Conceptual design

NASA Technical Reports Server (NTRS)

1990-01-01

The conceptual design of the biconic Cargo Return Vehicle (CRV) is presented. The CRV will be able to meet all of the Space Station Freedom (SSF's) resupply needs. Worth note is the absence of a backup recovery chute in case of Advanced Recovery System (ARS) failure. The high reliability of ram-air parachutes does not warrant the penalty weight that such a system would create on successful missions. The CRV will launch vertically integrated with an Liquid Rocket Booster (LRB) vehicle and meets all NASA restrictions on fuel type for all phases of the mission. Because of the downscaled Orbital Maneuvering Vehicle (OMV) program, the CRV has been designed to be able to transfer cargo by docking directly to the Space Station Freedom as well as with OMV assistance. The CRV will cover enough crossrange to reach its primary landing site, Edwards Airforce Base, and all secondary landing sites with the exception of one orbit. Transportation back to KSC will be via the Boeing Super Guppy. Due to difficulties with man-rating the CRV, it will not be used in a CERV role. A brief summary of the CRV's specifications is given.

Orion Launch Abort System Jettison Motor Performance During Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

McCauley, Rachel J.; Davidson, John B.; Winski, Richard G.

2015-01-01

This paper presents an overview of the flight test objectives and performance of the Orion Launch Abort System during Exploration Flight Test-1. Exploration Flight Test-1, the first flight test of the Orion spacecraft, was managed and led by the Orion prime contractor, Lockheed Martin, and launched atop a United Launch Alliance Delta IV Heavy rocket. This flight test was a two-orbit, high-apogee, high-energy entry, low-inclination test mission used to validate and test systems critical to crew safety. This test included the first flight test of the Launch Abort System performing Orion nominal flight mission critical objectives. Although the Orion Program has tested a number of the critical systems of the Orion spacecraft on the ground, the launch environment cannot be replicated completely on Earth. Data from this flight will be used to verify the function of the jettison motor to separate the Launch Abort System from the crew module so it can continue on with the mission. Selected Launch Abort System flight test data is presented and discussed in the paper. Through flight test data, Launch Abort System performance trends have been derived that will prove valuable to future flights as well as the manned space program.

Helicopter lifts Grissom from water

NASA Technical Reports Server (NTRS)

1961-01-01

Marine helicopter has astronaut Virgil I. Grissom in harness and is bringing him up out of the water. The Liberty Bell 7 spacecraft has just sunk below the water. His Mercury-Redstone 4 launch was the second in the U.S. manned space effort.

ASTRONAUT GLENN, JOHN - MERCURY SPACE SUIT

NASA Image and Video Library

1962-02-20

S62-00965 (20 Feb. 1962) --- Astronaut John H. Glenn Jr., finishes suiting up, and prepares for the launch of his Mercury-Atlas 6 (MA-6) spacecraft. The MA-6 ?Friendship 7? mission marks America's first manned Earth-orbiting spaceflight. Photo credit: NASA

Liquid rocket booster study addendum

NASA Technical Reports Server (NTRS)

1990-01-01

Liquid rocket booster study (LRB) addendum to final report is presented in the form of the view-graphs. The following subject areas are covered: LRB launch vehicle concepts; LRB design; propulsion system configurations; LRB boattail for Shuttle-C application; and manned transportation systems.

KSC Vertical Launch Site Evaluation

NASA Technical Reports Server (NTRS)

Phillips, Lynne V.

2007-01-01

RS&H was tasked to evaluate the potential available launch sites for a combined two user launch pad. The Launch sites were to be contained entirely within current Kennedy Space Center property lines. The user launch vehicles to be used for evaluation are in the one million pounds of first stage thrust range. Additionally a second evaluation criterion was added early on in the study. A single user launch site was to be evaluated for a two million pound first stage thrust vehicle. Both scenarios were to be included in the report. To provide fidelity to the study criteria, a specific launch vehicle in the one million pound thrust range was chosen as a guide post or straw-man launch vehicle. The RpK K-1 vehicle is a current Commercial Orbital Transportation System (COTS), contract awardee along with the SpaceX Falcon 9 vehicle. SpaceX, at the time of writing, is planning to launch COTS and possibly other payloads from Cx-40 on Cape Canaveral Air Force Station property. RpK has yet to declare a specific launch site as their east coast US launch location. As such it was deemed appropriate that RpK's vehicle requirements be used as conceptual criteria. For the purposes of this study those criteria were marginally generalized to make them less specifiC.

Solid polymer electrolyte water electrolysis system development. [to generate oxygen for manned space station applications

NASA Technical Reports Server (NTRS)

1975-01-01

Solid polymer electrolyte technology used in a water electrolysis system (WES) to generate oxygen and hydrogen for manned space station applications was investigated. A four-man rated, low pressure breadboard water electrolysis system with the necessary instrumentation and controls was fabricated and tested. A six man rated, high pressure, high temperature, advanced preprototype WES was developed. This configuration included the design and development of an advanced water electrolysis module, capable of operation at 400 psig and 200 F, and a dynamic phase separator/pump in place of a passive phase separator design. Evaluation of this system demonstrated the goal of safe, unattended automated operation at high pressure and high temperature with an accumulated gas generation time of over 1000 hours.

Project APEX: Advanced Phobos Exploration. Manned mission to the Martian moon Phobos

NASA Technical Reports Server (NTRS)

1992-01-01

The manned exploration of Mars is a massive undertaking which requires careful consideration. A mission to the moon of Mars called Phobos as a prelude to manned landings on the Martian surface offers some advantages. One is that the energy requirements, in terms of delta 5, is only slightly higher than going to the Moon's surface. Another is that Phobos is a potential source of water and carbon which could be extracted and processed for life support and cryogenic propellants for use in future missions; thus, Phobos might serve as a base for extended Mars exploration or for exploration of the outer planets. The design of a vehicle for such a mission is the subject of our Aerospace System Design course this year. The materials and equipment needed for the processing plant would be delivered to Phobos in a prior unmanned mission. This study focuses on what it would take to send a crew to Phobos, set up the processing plant for extraction and storage of water and hydrocarbons, conduct scientific experiments, and return safely to Earth. The size, configuration, and subsystems of the vehicle are described in some detail. The spacecraft carries a crew of five and is launched from low Earth orbit in the year 2010. The outbound trajectory to Mars uses a gravitational assisted swing by of Venus and takes eight months to complete. The stay at Phobos is 60 days at which time the crew will be engaged in setting up the processing facility. The crew will then return to Earth orbit after a total mission duration of 656 days. Both stellar and solar observations will be conducted on both legs of the mission. The design of the spacecraft addresses human factors and life science; mission analysis and control; propulsion; power generation and distribution; thermal control; structural analysis; and planetary, solar, and stellar science. A 0.5 g artificial gravity is generated during transit by spinning about the lateral body axis. Nuclear thermal rockets using hydrogen as fuel are selected to reduce total launch mass and to shorten the duration of the mission. The nuclear systems also provide the primary electrical power via dual mode operation. The overall spacecraft length is 110 meters and the total mass departing from low Earth orbit is 900 metric tons.

Project APEX: Advanced Phobos Exploration. Manned mission to the Martian moon Phobos

NASA Astrophysics Data System (ADS)

1992-04-01

The manned exploration of Mars is a massive undertaking which requires careful consideration. A mission to the moon of Mars called Phobos as a prelude to manned landings on the Martian surface offers some advantages. One is that the energy requirements, in terms of delta 5, is only slightly higher than going to the Moon's surface. Another is that Phobos is a potential source of water and carbon which could be extracted and processed for life support and cryogenic propellants for use in future missions; thus, Phobos might serve as a base for extended Mars exploration or for exploration of the outer planets. The design of a vehicle for such a mission is the subject of our Aerospace System Design course this year. The materials and equipment needed for the processing plant would be delivered to Phobos in a prior unmanned mission. This study focuses on what it would take to send a crew to Phobos, set up the processing plant for extraction and storage of water and hydrocarbons, conduct scientific experiments, and return safely to Earth. The size, configuration, and subsystems of the vehicle are described in some detail. The spacecraft carries a crew of five and is launched from low Earth orbit in the year 2010. The outbound trajectory to Mars uses a gravitational assisted swing by of Venus and takes eight months to complete. The stay at Phobos is 60 days at which time the crew will be engaged in setting up the processing facility. The crew will then return to Earth orbit after a total mission duration of 656 days. Both stellar and solar observations will be conducted on both legs of the mission. The design of the spacecraft addresses human factors and life science; mission analysis and control; propulsion; power generation and distribution; thermal control; structural analysis; and planetary, solar, and stellar science. A 0.5 g artificial gravity is generated during transit by spinning about the lateral body axis. Nuclear thermal rockets using hydrogen as fuel are selected to reduce total launch mass and to shorten the duration of the mission. The nuclear systems also provide the primary electrical power via dual mode operation. The overall spacecraft length is 110 meters and the total mass departing from low Earth orbit is 900 metric tons.

Automation Applications in an Advanced Air Traffic Management System : Volume 3. Methodology for Man-Machine Task Allocation

DOT National Transportation Integrated Search

1974-08-01

Volume 3 describes the methodology for man-machine task allocation. It contains a description of man and machine performance capabilities and an explanation of the methodology employed to allocate tasks to human or automated resources. It also presen...

Advanced Aircraft Interfaces: The Machine Side of the Man-Machine Interface (Les Interfaces sur les Avions de Pointe: L’Aspect Machine de l’Interface Homme-Machine)

DTIC Science & Technology

1992-10-01

Manager , Advanced Transport Operating Systems Program Office Langley Research Center Mail Stop 265 Hampton, VA 23665-5225 United States Programme Committee...J.H.Lind, and C.G.Burge Advanced Cockpit - Mission and Image Management 4 by J. Struck Aircrew Acceptance of Automation in the Cockpit 5 by M. Hicks and I...DESIGN CONCEPTS AND TOOLS A Systems Approach to the Advanced Aircraft Man-Machine Interface 23 by F. Armogida Management of Avionics Data in the Cockpit

A Geometric Analysis to Protect Manned Assets from Newly Launched Objects - Cola Gap Analysis

NASA Technical Reports Server (NTRS)

Hametz, Mark E.; Beaver, Brian A.

2013-01-01

A safety risk was identified for the International Space Station (ISS) by The Aerospace Corporation, where the ISS would be unable to react to a conjunction with a newly launched object following the end of the launch Collision Avoidance (COLA) process. Once an object is launched, there is a finite period of time required to track, catalog, and evaluate that new object as part of standard onorbit COLA screening processes. Additionally, should a conjunction be identified, there is an additional period of time required to plan and execute a collision avoidance maneuver. While the computed prelaunch probability of collision with any object is extremely low, NASA/JSC has requested that all US launches take additional steps to protect the ISS during this "COLA gap" period. This paper details a geometric-based COLA gap analysis method developed by the NASA Launch Services Program to determine if launch window cutouts are required to mitigate this risk. Additionally, this paper presents the results of several missions where this process has been used operationally.

MSFC Advanced Concepts Office and the Iterative Launch Vehicle Concept Method

NASA Technical Reports Server (NTRS)

Creech, Dennis

2011-01-01

This slide presentation reviews the work of the Advanced Concepts Office (ACO) at Marshall Space Flight Center (MSFC) with particular emphasis on the method used to model launch vehicles using INTegrated ROcket Sizing (INTROS), a modeling system that assists in establishing the launch concept design, and stage sizing, and facilitates the integration of exterior analytic efforts, vehicle architecture studies, and technology and system trades and parameter sensitivities.

Launch - Apollo XV Space Vehicle - KSC

NASA Image and Video Library

1971-07-26

S71-41356 (26 July 1971) --- The huge, 363-feet tall Apollo 15 (Spacecraft 112/Lunar Module 10/Saturn 510) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), Florida, at 9:34:00:79 a.m. (EDT), July 26, 1971, on a lunar landing mission. Aboard the Apollo 15 spacecraft were astronauts David R. Scott, commander; Alfred M. Worden, command module pilot; and James B. Irwin, lunar module pilot. Apollo 15 is the National Aeronautics and Space Administration's (NASA) fourth manned lunar landing mission. While astronauts Scott and Irwin will descend in the Lunar Module (LM) to explore the moon, astronaut Worden will remain with the Command and Service Modules (CSM) in lunar orbit.

Lunar base launch and landing facility conceptual design, 2nd edition

NASA Technical Reports Server (NTRS)

1988-01-01

This report documents the Lunar Base Launch and Landing Facility Conceptual Design study. The purpose of this study was to examine the requirements for launch and landing facilities for early lunar bases and to prepare conceptual designs for some of these facilities. The emphasis of this study is on the facilities needed from the first manned landing until permanent occupancy. Surface characteristics and flight vehicle interactions are described, and various facility operations are related. Specific recommendations for equipment, facilities, and evolutionary planning are made, and effects of different aspects of lunar development scenarios on facilities and operations are detailed. Finally, for a given scenario, a specific conceptual design is developed and presented.

MERCURY-ATALS (MA)-9 - LIFTOFF - CAPE

NASA Image and Video Library

1963-05-01

S63-07135 (16 May 1963) --- This was the Nation?s sixth manned orbital space flight, and the ?Faith 7? spacecraft was piloted by astronaut L. Gordon Cooper Jr. The launch was originally scheduled for May 14, 1963, but due to a malfunction in the radar tracking system at Bermuda. The launch was ?scrubbed? 12 minutes before countdown would have been completed. At midnight, May 15, 1963, countdown was resumed and liftoff occurred at 8:04 a.m. (EST), May 16, 1963. Astronaut L. Gordon Cooper Jr., completed a total of 22.9 orbits and spent 34 hours, 20 minutes in space flight. The launch and recovery was highly successful and was the last of the Mercury flights.

Gemini Program Mission Report: Gemini IV

NASA Technical Reports Server (NTRS)

1965-01-01

The second manned mission of the Gemini Program, Gemini IV, was launched from Complex 19 at Cape Kennedy, Florida, at 10:16 a.m. e.s.t. on June 3, 1965. The mission was successfully concluded on June 7, 1965, with the recovery of the spacecraft by the prime recovery ship, the aircraft carrier U.S.S. Wasp, at 27 deg 44' N. latitude, 74 deg 11' W. longitude at 2:28 p.m. e.s.t. This manned long-duration flight was accomplished 10 weeks after the three-orbit manned flight which qualified the Gemini spacecraft and systems for orbital flight. The spacecraft was manned by Astronaut James A. McDivitt, command pilot, and Astronaut Edward H. White II, pilot. The flight crew completed the 4-day mission in excellent physical condition, and demonstrated full control of the spacecraft and competent management of all aspects of the mission.

Ariane Transfer Vehicle in service of man in orbit

NASA Astrophysics Data System (ADS)

Deutscher, N.; Schefold, K.; Cougnet, C.

1988-10-01

The Ariane Transfer Vehicle (ATV), an unmanned propulsion system that is designed to be carried by the Ariane 5 launch vehicle, will undertake the logistical support required by the International Space Station and the Man-Tended Free Flyer, carrying both pressurized and unpressurized cargo to these spacecraft and carrying away wastes. The ATV is an expendable vehicle, disposed of by burn-up during reentry, and will be available for initial operations in 1996. In order to minimize development costs and recurrent costs, the ATV design will incorporate existing hardware and software.

View of White Room atop Pad A during Apollo 9 Countdown Demonstration Test

NASA Image and Video Library

1969-02-23

S69-25884 (23 Feb. 1969) --- Interior view of the white room atop Pad A, Launch Complex 39, Kennedy Space Center, during Apollo 9 Countdown Demonstration Test activity. Standing next to spacecraft hatch is astronaut James A. McDivitt, commander. Also, taking part in the training exercise were astronauts David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. The Apollo 9 mission will evaluate spacecraft lunar module systems performance during manned Earth-orbital flight. Apollo 9 will be the second manned Saturn V mission.

Saturn Apollo Program

NASA Image and Video Library

1969-07-27

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. In this photo taken at Pearl Harbor, Hawaii, the inhabited MQF is prepared for loading into an Air Force C-141 jet transport for the flight back to Ellington Air Force Base Texas and then on to the MSC.

Orion: Design of a system for assured low-cost human access to space

NASA Technical Reports Server (NTRS)

Elvander, Josh; Heifetz, Andy; Hunt, Teresa; Zhu, Martin

1994-01-01

In recent years, Congress and the American people have begun to seriously question the role and importance of future manned spaceflight. This is mainly due to two factors: a decline in technical competition caused by the collapse of communism, and the high costs associated with the Space Shuttle transportation system. With these factors in mind, the ORION system was designed to enable manned spaceflight at a low cost, while maintaining the ability to carry out diverse missions, each with a high degree of flexibility. It is capable of performing satellite servicing missions, supporting a space station via crew rotation and resupply, and delivering satellites into geosynchronous orbit. The components of the system are a primary launch module, an upper stage, and a manned spacecraft capable of dynamic reentry. For satellite servicing and space station resupply missions, the ORION system utilizes three primary modules, an upper stage, and the spacecraft, which is delivered to low earth orbit and used to rendezvous, transfer materials, and make repairs. For launching a geosynchronous satellite, one primary module and an upper stage are used to deliver the satellite, along with an apogee kick motor, into orbit. The system is designed with reusability and modularity in mind in an attempt to lower cost.

n/a

NASA Image and Video Library

1969-07-27

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. (Buzz) Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. On arrival at Ellington Air Force base near the MSC, the crew, still under a 21 day quarantine in the MQF, were greeted by their wives. Pictured here is Joan Aldrin, wife of Buzz Aldrin, speaking with her husband via telephone patch.

Saturn Apollo Program

NASA Image and Video Library

1969-08-03

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. The three are seen here at the MSC, still inside the MQF, undergoing their first debriefing on Sunday, August 3, 1969. Behind the glass are (L-R): Edwin Aldrin, Michael Collins, and Neil Armstrong.

Quarantined Apollo 11 Astronauts Address by Hawaiian Governor

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named 'Eagle'', carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet recovery ship, where they were quartered in a Mobile Quarantine Facility (MQF) for 21 days. The recovery vessel docked in Pearl Harbor Hawaii, where the occupied MQF was transferred for transport to the to NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. In this photo the quarantined astronauts are addressed by Hawaiian Governor John Burns upon their arrival at Pearl Harbor.

Saturn Apollo Program

NASA Image and Video Library

1969-07-27

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet recovery ship, where they were quartered in a Mobile Quarantine Facility (MQF) for 21 days. The recovery vessel docked in Pearl Harbor Hawaii, where the occupied MQF was transferred for transport to the to NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. In this photo the quarantined astronauts are addressed by Hawaiian Governor John Burns upon their arrival at Pearl Harbor.

Flight Testing of the Space Launch System (SLS) Adaptive Augmenting Control (AAC) Algorithm on an F/A-18

NASA Technical Reports Server (NTRS)

Dennehy, Cornelius J.; VanZwieten, Tannen S.; Hanson, Curtis E.; Wall, John H.; Miller, Chris J.; Gilligan, Eric T.; Orr, Jeb S.

2014-01-01

The Marshall Space Flight Center (MSFC) Flight Mechanics and Analysis Division developed an adaptive augmenting control (AAC) algorithm for launch vehicles that improves robustness and performance on an as-needed basis by adapting a classical control algorithm to unexpected environments or variations in vehicle dynamics. This was baselined as part of the Space Launch System (SLS) flight control system. The NASA Engineering and Safety Center (NESC) was asked to partner with the SLS Program and the Space Technology Mission Directorate (STMD) Game Changing Development Program (GCDP) to flight test the AAC algorithm on a manned aircraft that can achieve a high level of dynamic similarity to a launch vehicle and raise the technology readiness of the algorithm early in the program. This document reports the outcome of the NESC assessment.

Assessment of candidate-expendable launch vehicles for large payloads

NASA Technical Reports Server (NTRS)

1984-01-01

In recent years the U.S. Air Force and NASA conducted design studies of 3 expendable launch vehicle configurations that could serve as a backup to the space shuttle--the Titan 34D7/Centaur, the Atlas II/Centaur, and the shuttle-derived SRB-X--as well as studies of advanced shuttle-derived launch vehicles with much larger payload capabilities than the shuttle. The 3 candidate complementary launch vehicles are judged to be roughly equivalent in cost, development time, reliability, and payload-to-orbit performance. Advanced shuttle-derived vehicles are considered viable candidates to meet future heavy lift launch requirements; however, they do not appear likely to result in significant reduction in cost-per-pound to orbit.

Automated Rendezvous and Capture System Development and Simulation for NASA

NASA Technical Reports Server (NTRS)

Roe, Fred D.; Howard, Richard T.; Murphy, Leslie

2004-01-01

The United States does not have an Automated Rendezvous and Capture Docking (AR&C) capability and is reliant on manned control for rendezvous and docking of orbiting spacecraft. T h i s reliance on the labor intensive manned interface for control of rendezvous and docking vehicles has a significant impact on the cost of the operation of the International Space Station (ISS) and precludes the use of any U.S. expendable launch capabilities for Space Station resupply. The Marshall Space Flight Center (MSFC) has conducted pioneering research in the development of an automated rendezvous and capture (or docking) (AR&C) system for U.S. space vehicles. This A M C system was tested extensively using hardware-in-the-loop simulations in the Flight Robotics Laboratory, and a rendezvous sensor, the Video Guidance Sensor was developed and successfully flown on the Space Shuttle on flights STS-87 and STS-95, proving the concept of a video- based sensor. Further developments in sensor technology and vehicle and target configuration have lead to continued improvements and changes in AR&C system development and simulation. A new Advanced Video Guidance Sensor (AVGS) with target will be utilized as the primary navigation sensor on the Demonstration of Autonomous Rendezvous Technologies (DART) flight experiment in 2004. Realtime closed-loop simulations will be performed to validate the improved AR&C systems prior to flight.

Saturn Apollo Program

NASA Image and Video Library

1969-11-24

Aboard the recovery ship, USS Hornet, Apollo 12 astronauts wave to the crowd as they enter the mobile quarantine facility. The recovery operation took place in the Pacific Ocean after the splashdown of the Command Module capsule. Navy para-rescue men recovered the capsule housing the 3-man Apollo 12 crew. The second manned lunar landing mission, Apollo 12 launched from launch pad 39-A at Kennedy Space Center in Florida on November 14, 1969 via a Saturn V launch vehicle. The Saturn V was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun. Aboard Apollo 12 was a crew of three astronauts: Alan L. Bean, pilot of the Lunar Module (LM), Intrepid; Richard Gordon, pilot of the Command Module (CM), Yankee Clipper; and Spacecraft Commander Charles Conrad. The LM, Intrepid, landed astronauts Conrad and Bean on the lunar surface in what’s known as the Ocean of Storms while astronaut Richard Gordon piloted the CM, Yankee Clipper, in a parking orbit around the Moon. Lunar soil activities included the deployment of the Apollo Lunar Surface Experiments Package (ALSEP), finding the unmanned Surveyor 3 that landed on the Moon on April 19, 1967, and collecting 75 pounds (34 kilograms) of rock samples. Apollo 12 safely returned to Earth on November 24, 1969.

Small Solar Electric Propulsion Spacecraft Concept for Near Earth Object and Inner Solar System Missions

NASA Technical Reports Server (NTRS)

Lang, Jared J.; Randolph, Thomas M.; McElrath, Timothy P.; Baker, John D.; Strange, Nathan J.; Landau, Damon; Wallace, Mark S.; Snyder, J. Steve; Piacentine, Jamie S.; Malone, Shane;

Skylab

NASA Image and Video Library

1974-01-01

This image is an artist's concept of the Skylab in orbit. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Skylab

NASA Image and Video Library

1971-01-01

This image illustrates major areas of emphasis of the Skylab Program. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab Program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Log of Apollo 11.

ERIC Educational Resources Information Center

National Aeronautics and Space Administration, Washington, DC.

The major events of the first manned moon landing mission, Apollo 11, are presented in chronological order from launch time until arrival of the astronauts aboard the U.S.S. Hornet. The log is descriptive, non-technical, and includes numerous color photographs of the astronauts on the moon. (PR)

Apollo 14 Crew Receive Greetings Inside the Mobile Quarantine Facility

NASA Technical Reports Server (NTRS)

1971-01-01

Apollo 14 astronauts listen to official greetings from the Mobile Quarantine Facility aboard the USS New Orleans following their safe return from the third manned lunar landing mission. Pictured (from left to right) are Stuart A. Roosa, Command Module pilot ; Alan B. Shepard, Jr., Mission commander; and Edgar D. Mitchell, Lunar Module pilot. The Apollo 14 crew launched from launch complex 39A at the Kennedy Space Center on January 31, 1971 and safely returned to Earth on February 9, 1971. It was the first manned landing in exploration of the lunar highlands, and it demonstrated pinpoint landing capability. The major goal of Apollo 14 was the scientific exploration of the Moon in the foothills of the rugged Fra Mauro region. The extravehicular activity (EVA) of astronauts Shepard and Mitchell included setting up an automated scientific laboratory called Apollo Lunar Scientific Experiments Package (ALSEP), and collecting a total of about 95 pounds (43 kilograms) of Moon rock and soil for a geological investigation back on the Earth.

Saturn Apollo Program

NASA Image and Video Library

1969-06-24

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard he space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. Splashdown occurred in the Pacific Ocean on July 24, 1969. This overall view of the Mission Operations Control Room in the Mission Control Center at the NASA Manned Spacecraft Center (MSC) in Houston Texas shows the jubilation of the celebration of mission success. Mission controllers wave their American flags just after Apollo 11 had been recovered from the Pacific Ocean.

Saturn Apollo Program

NASA Image and Video Library

1969-07-09

In this photograph, laboratory technician Bart Ruark visually inspects a Japanese Qail confined within a class III cabinet in the Intervertebrae, Aves, and Fish Laboratory of the Lunar Receiving Laboratory, Building 37 of the Manned Spacecraft Center (MSC) in Houston, Texas. This laboratory was part of the overall physical, chemical, and biological test program of the Apollo 11 returned lunar samples. Aboard the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle, the Apollo 11 mission launched from The Kennedy Space Center, Florida on July 16, 1969 and safely returned to Earth on July 24, 1969. The 3-man crew aboard the flight consisted of astronauts Neil A. Armstrong, commander; Edwin Aldrin, Lunar Module (LM) pilot; and Michael Collins, Command Module (CM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. In 2 1/2 hours, the crew collected 47 pounds of lunar surface material which was returned to Earth for analysis.

Saturn Apollo Program

NASA Image and Video Library

1969-07-09

In this photograph, a laboratory technician handles a portion of the more than 20 different plant lines that were used within the Lunar Receiving Laboratory, Building 37 of the Manned Spacecraft Center (MSC) in Houston, Texas. This laboratory was part of the overall physical, chemical, and biological test program of the Apollo 11 returned lunar samples. Aboard the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle, the Apollo 11 mission launched from The Kennedy Space Center, Florida on July 16, 1969 and safely returned to Earth on July 24, 1969. The 3-man crew aboard the flight consisted of astronauts Neil A. Armstrong, commander; Edwin Aldrin, Lunar Module (LM) pilot; and Michael Collins, Command Module (CM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. In 2 1/2 hours, the crew collected 47 pounds of lunar surface material which was returned to Earth for analysis.

The space shuttle launch vehicle aerodynamic verification challenges

NASA Technical Reports Server (NTRS)

Wallace, R. O.; Austin, L. D.; Hondros, J. G.; Surber, T. E.; Gaines, L. M.; Hamilton, J. T.

1985-01-01

The Space Shuttle aerodynamics and performance communities were challenged to verify the Space Shuttle vehicle (SSV) aerodynamics and system performance by flight measurements. Historically, launch vehicle flight test programs which faced these same challenges were unmanned instrumented flights of simple aerodynamically shaped vehicles. However, the manned SSV flight test program made these challenges more complex because of the unique aerodynamic configuration powered by the first man-rated solid rocket boosters (SRB). The analyses of flight data did not verify the aerodynamics or performance preflight predictions of the first flight of the Space Transportation System (STS-1). However, these analyses have defined the SSV aerodynamics and verified system performance. The aerodynamics community also was challenged to understand the discrepancy between the wind tunnel and flight defined aerodynamics. The preflight analysis challenges, the aerodynamic extraction challenges, and the postflight analyses challenges which led to the SSV system performance verification and which will lead to the verification of the operational ascent aerodynamics data base are presented.

Mars Mission Concepts: SAR and Solar Electric Propulsion

NASA Astrophysics Data System (ADS)

Elsperman, M.; Klaus, K.; Smith, D. B.; Clifford, S. M.; Lawrence, S. J.

2012-12-01

Introduction: The time has come to leverage technology advances (including advances in autonomous operation and propulsion technology) to reduce the cost and increase the flight rate of planetary missions, while actively developing a scientific and engineering workforce to achieve national space objectives. Mission Science at Mars: A SAR imaging radar offers an ability to conduct high resolution investigations of the shallow (<10 m depth) subsurface of Mars, enabling identification of fine-scale layering within the Martian polar layered deposits (PLD), as well as the identification of pingos, investigations of polygonal terrain, and measurements of the thickness of mantling layers at non-polar latitudes. It would allow systematic near-surface prospecting, which is tremendously useful for human exploration purposes (in particular, the identification of accessible ice deposits and quantification of Martian regolith properties). Limited color capabilities in a notional high-resolution stereo imaging system would enable the generation of false color images, resulting in useful science results, and the stereo data could be reduced into high-resolution Digital Elevation Models uniquely useful for exploration planning and science purposes. Since the SAR and the notional high-resolution stereo imaging system would be huge data volume producers - to maximize the science return we are currently considering the usage of laser communications systems; this notional spacecraft represents one pathway to evaluate the utility of laser communications in planetary exploration while providing useful science return.. Mission Concept: Using a common space craft for multiple missions reduces costs. Solar electric propulsion (SEP) provides the flexibility required for multiple mission objectives. SEP provides the greatest payload advantage albeit at the sacrifice of mission time. Our concept involves using a SEP enabled space craft (Boeing 702SP) with a highly capable SAR imager that also conducts autonomous rendezvous and docking experiments accomplished from Mars orbit. Our concept of operations is to launch on May 5, 2018 using a launch vehicle with 2000kg launch capacity with a C3 of 7.4. After reaching Mars it takes 145 days to spiral down to a 250 km orbit above the surface of Mars when Mars SAR operations begin. Summary/Conclusions: A robust and compelling Mars mission can be designed to meet the 2018 Mars launch window opportunity. Using advanced in-space power and propulsion technologies like High Power Solar Electric Propulsion provides enormous mission flexibility to execute the baseline science mission and conduct necessary Mars Sample Return Technology Demonstrations in Mars orbit on the same mission. An observation spacecraft platform like the high power (~5Kw) 702SP at Mars also enables the use of a SAR instrument to reveal new insights and understanding of the Mars regolith for both science and future manned exploration and utilization.

Advanced Welding Applications

NASA Technical Reports Server (NTRS)

Ding, Robert J.

2010-01-01

Some of the applications of advanced welding techniques are shown in this poster presentation. Included are brief explanations of the use on the Ares I and Ares V launch vehicle and on the Space Shuttle Launch vehicle. Also included are microstructural views from four advanced welding techniques: Variable Polarity Plasma Arc (VPPA) weld (fusion), self-reacting friction stir welding (SR-FSW), conventional FSW, and Tube Socket Weld (TSW) on aluminum.

Lowest cost, nearest term options for a manned Mars mission

NASA Technical Reports Server (NTRS)

Sauls, Bob; Mortensen, Michael; Myers, Renee; Guacci, Giovanni; Montes, Fred

1992-01-01

This study is part of a NASA/USRA Advanced Design Program project executed for the purpose of examining the requirements of a first manned Mars mission. The mission, classified as a split/sprint mission, has been designed for a crew of six with a total manned trip time of one year.

Launch vehicle flight control augmentation using smart materials and advanced composites (CDDF Project 93-05)

NASA Technical Reports Server (NTRS)

Barret, C.

1995-01-01

The Marshall Space Flight Center has a rich heritage of launch vehicles that have used aerodynamic surfaces for flight stability such as the Saturn vehicles and flight control such as on the Redstone. Recently, due to aft center-of-gravity locations on launch vehicles currently being studied, the need has arisen for the vehicle control augmentation that is provided by these flight controls. Aerodynamic flight control can also reduce engine gimbaling requirements, provide actuator failure protection, enhance crew safety, and increase vehicle reliability, and payload capability. In the Saturn era, NASA went to the Moon with 300 sq ft of aerodynamic surfaces on the Saturn V. Since those days, the wealth of smart materials and advanced composites that have been developed allow for the design of very lightweight, strong, and innovative launch vehicle flight control surfaces. This paper presents an overview of the advanced composites and smart materials that are directly applicable to launch vehicle control surfaces.

Study of solid rocket motors for a space shuttle booster. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1972-01-01

The design, development, production, and launch support analysis for determining the solid propellant rocket engine to be used with the space shuttle are discussed. Specific program objectives considered were: (1) definition of engine designs to satisfy the performance and configuration requirements of the various vehicle/booster concepts, (2) definition of requirements to produce booster stages at rates of 60, 40, 20, and 10 launches per year in a man-rated system, and (3) estimation of costs for the defined SRM booster stages.

Conceptual designs study for a Personnel Launch System (PLS)

NASA Technical Reports Server (NTRS)

Wetzel, E. D.

1990-01-01

A series of conceptual designs for a manned, Earth to Low Earth Orbit transportation system was developed. Non-winged, low L/D vehicle shapes are discussed. System and subsystem trades emphasized safety, operability, and affordability using near-term technology. The resultant conceptual design includes lessons learned from commercial aviation that result in a safe, routine, operationally efficient system. The primary mission for this Personnel Launch System (PLS) would be crew rotation to the SSF; other missions, including satellite servicing, orbital sortie, and space rescue were also explored.

International Space Station (ISS)

NASA Image and Video Library

2003-10-16

The Soyuz TMA-3 spacecraft and its booster rocket (rear view) is shown on a rail car for transport to the launch pad where it was raised to a vertical launch position at the Baikonur Cosmodrome, Kazakhstan on October 16, 2003. Liftoff occurred on October 18th, transporting a three man crew to the International Space Station (ISS). Aboard were Michael Foale, Expedition-8 Commander and NASA science officer; Alexander Kaleri, Soyuz Commander and flight engineer, both members of the Expedition-8 crew; and European Space agency (ESA) Astronaut Pedro Duque of Spain. Photo Credit: "NASA/Bill Ingalls"

International Space Station (ISS)

NASA Image and Video Library

2003-10-16

The Soyuz TMA-3 spacecraft and its booster rocket (front view) is shown on a rail car for transport to the launch pad where it was raised to a vertical launch position at the Baikonur Cosmodrome, Kazakhstan on October 16, 2003. Liftoff occurred on October 18th, transporting a three man crew to the International Space Station (ISS). Aboard were Michael Foale, Expedition-8 Commander and NASA science officer; Alexander Kaleri, Soyuz Commander and flight engineer, both members of the Expedition-8 crew; and European Space agency (ESA) Astronaut Pedro Duque of Spain. Photo Credit: "NASA/Bill Ingalls"

Apollo 9 crew leaves Spacecraft Operations Building during countdown

NASA Image and Video Library

1969-03-03

S69-25883 (3 March 1969) --- The Apollo 9 crew leaves the Kennedy Space Center's Manned Spacecraft Operations Building during the Apollo 9 prelaunch countdown. Leading is astronaut James A. McDivitt, commander; followed by astronaut David R. Scott, command module pilot; and Russell L. Schweickart, lunar module pilot. Moments later they entered the special transfer van which transported them to their waiting spacecraft at Pad A, Launch Complex 39. Apollo 9 was launched at 11 a.m. (EST), March 3, 1969, on a 10-day Earth-orbital mission.

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

Marshall Space Flight Center (MSFC) workers hoist a dynamic test version of the S-IVB stage, the Saturn IB launch vehicle's second stage, into the Center's Dynamic Test Stand on January 18, 1965. MSFC Test Laboratory persornel assembled a complete Saturn IB to test the launch vehicle's structural soundness. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine the larger boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

Saturn Apollo Program

NASA Image and Video Library

1965-01-01

Marshall Space Flight Center (MSFC) workers lower S-IB-200D, a dynamic test version of the Saturn IB launch vehicle's first stage (S-IB stage), into the Center's Dynamic Test Stand on January 12, 1965. Test Laboratory persornel assembled a complete Saturn IB to test the structural soundness of the launch vehicle. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine large boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

n/a

NASA Image and Video Library

1967-11-01

Workmen at the Kennedy Space Center hoist the Saturn Lunar Module (LM) Adapter into position during assembly of the 204LM-1, an unmanned Apollo mission that tested the Apollo Lunar Module in Earth orbit. Also known as Apollo 5, the spacecraft was launched on the fourth Saturn IB launch vehicle. Developed by the Marshall Space Flight Center (MSFC) as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine a larger booster and the Apollo spacecraft capabilities required for the manned lunar missions.

Smart sensor technology for advanced launch vehicles

NASA Astrophysics Data System (ADS)

Schoess, Jeff

1989-07-01

Next-generation advanced launch vehicles will require improved use of sensor data and the management of multisensor resources to achieve automated preflight checkout, prelaunch readiness assessment and vehicle inflight condition monitoring. Smart sensor technology is a key component in meeting these needs. This paper describes the development of a smart sensor-based condition monitoring system concept referred to as the Distributed Sensor Architecture. A significant event and anomaly detection scheme that provides real-time condition assessment and fault diagnosis of advanced launch system rocket engines is described. The design and flight test of a smart autonomous sensor for Space Shuttle structural integrity health monitoring is presented.

Launch Vehicle Demonstrator Using Shuttle Assets

NASA Technical Reports Server (NTRS)

Threet, Grady E., Jr.; Creech, Dennis M.; Philips, Alan D.; Water, Eric D.

2011-01-01

The Marshall Space Flight Center Advanced Concepts Office (ACO) has the leading role for NASA s preliminary conceptual launch vehicle design and performance analysis. Over the past several years the ACO Earth-to-Orbit Team has evaluated thousands of launch vehicle concept variations for a multitude of studies including agency-wide efforts such as the Exploration Systems Architecture Study (ESAS), Constellation, Heavy Lift Launch Vehicle (HLLV), Heavy Lift Propulsion Technology (HLPT), Human Exploration Framework Team (HEFT), and Space Launch System (SLS). NASA plans to continue human space exploration and space station utilization. Launch vehicles used for heavy lift cargo and crew will be needed. One of the current leading concepts for future heavy lift capability is an inline one and a half stage concept using solid rocket boosters (SRB) and based on current Shuttle technology and elements. Potentially, the quickest and most cost-effective path towards an operational vehicle of this configuration is to make use of a demonstrator vehicle fabricated from existing shuttle assets and relying upon the existing STS launch infrastructure. Such a demonstrator would yield valuable proof-of-concept data and would provide a working test platform allowing for validated systems integration. Using shuttle hardware such as existing RS-25D engines and partial MPS, propellant tanks derived from the External Tank (ET) design and tooling, and four-segment SRB s could reduce the associated upfront development costs and schedule when compared to a concept that would rely on new propulsion technology and engine designs. There are potentially several other additional benefits to this demonstrator concept. Since a concept of this type would be based on man-rated flight proven hardware components, this demonstrator has the potential to evolve into the first iteration of heavy lift crew or cargo and serve as a baseline for block upgrades. This vehicle could also serve as a demonstration and test platform for the Orion Program. Critical spacecraft systems, re-entry and recovery systems, and launch abort systems of Orion could also be demonstrated in early test flights of the launch vehicle demo. Furthermore, an early demonstrator of this type would provide a stop-gap for retaining critical human capital and infrastructure while affording the current emerging generation of young engineers opportunity to work with and capture lessons learned from existing STS program offices and personnel, who were integral in the design and development of the Space Shuttle before these resources are no longer available. The objective of this study is to define candidate launch vehicle demonstration concepts that are based on Space Shuttle assets and determine their performance capabilities and how these demonstration vehicles could evolve to a heavy lift capability to low earth orbit.

The Advanced Composition Explorer is placed atop its Delta II launcher at Pad 17A, CCAS

NASA Technical Reports Server (NTRS)

1997-01-01

The Advanced Composition Explorer (ACE) spacecraft is placed atop its launch vehicle at Launch Complex 17A. Scheduled for launch on a Delta II rocket from Cape Canaveral Air Station on Aug. 24, ACE will study low-energy particles of solar origin and high-energy galactic particles. The collecting power of instruments aboard ACE is 10 to 1,000 times greater than anything previously flown to collect similar data by NASA.

KSC-75PC-0330

NASA Image and Video Library

1975-07-03

CAPE CANAVERAL, Fla. – ASTP prime crewmen Donald Slayton, Thomas Stafford and Vance Brand pose with their Saturn IB launch vehicle following the Countdown Demonstration Test [CDDT], a step-by-step dress rehearsal for their July 15 launch. During the “wet” portion of the test, conducted yesterday, the stages of the launch vehicle were fueled as they will be on launch day. The fuels were off loaded and the terminal portion of the count repeated today with the astronauts aboard the vehicle. The first international crewed spaceflight was a joint U.S.-U.S.S.R. rendezvous and docking mission. The Apollo-Soyuz Test Project, or ASTP, took its name from the spacecraft employed: the American Apollo and the Soviet Soyuz. The three-man Apollo crew lifted off from Kennedy Space Center aboard a Saturn IB rocket on July 15, 1975, to link up with the Soyuz that had launched a few hours earlier. A cylindrical docking module served as an airlock between the two spacecraft for transfer of the crew members. Photo credit: NASA

KSC-108-75PC-0388

NASA Image and Video Library

1975-07-15

CAPE CANAVERAL, Fla. – The Apollo Soyuz Test Project Saturn IB launch vehicle thundered away from KSC’s Launch Complex 39B at 3:50 p.m. today. Aboard the Apollo Command Module were ASTP Astronauts Thomas Stafford, Vance Brand and Donald Slayton. The astronauts will rendezvous and dock with a Soyuz spacecraft, launched this morning from the Baikonur launch facility in the Soviet Union, carrying Soviet cosmonauts Aleksey Leonov and Valeriy Kubasov. The first international crewed spaceflight was a joint U.S.-U.S.S.R. rendezvous and docking mission. The Apollo-Soyuz Test Project, or ASTP, took its name from the spacecraft employed: the American Apollo and the Soviet Soyuz. The three-man Apollo crew lifted off from Kennedy Space Center aboard a Saturn IB rocket on July 15, 1975, to link up with the Soyuz that had launched a few hours earlier. A cylindrical docking module served as an airlock between the two spacecraft for transfer of the crew members. Photo credit: NASA

Next generation solid boosters

NASA Technical Reports Server (NTRS)

Lund, R. K.

1991-01-01

Space transportation solid rocket motor systems; Shuttle derived heavy lift launch vehicles; advanced launch system (ALS) derived heavy lift launch vehicles; large launch solid booster vehicles are outlined. Performance capabilities and concept objectives are presented. Small launch vehicle concepts; enabling technologies; reusable flyback booster system; and high-performance solid motors for space are briefly described. This presentation is represented by viewgraphs.

The Economics of Advanced In-Space Propulsion

NASA Technical Reports Server (NTRS)

Bangalore, Manju; Dankanich, John

2016-01-01

The cost of access to space is the single biggest driver is commercial space sector. NASA continues to invest in both launch technology and in-space propulsion. Low-cost launch systems combined with advanced in-space propulsion offer the greatest potential market capture. Launch market capture is critical to national security and has a significant impact on domestic space sector revenue. NASA typically focuses on pushing the limits on performance. However, the commercial market is driven by maximum net revenue (profits). In order to maximum the infusion of NASA investments, the impact on net revenue must be known. As demonstrated by Boeing's dual launch, the Falcon 9 combined with all Electric Propulsion (EP) can dramatically shift the launch market from foreign to domestic providers.

KSC-2009-2935

NASA Image and Video Library

2009-05-05

VANDENBERG AIR FORCE BASE, Calif. -- A United Launch Alliance Delta II rocket, on behalf of the NASA Launch Services Program, is poised on its Space Launch Complex-2 launch pad at Vandenberg AFB, Calif., ready for launch. The Delta II will carry the Missile Defense Agency's Space Tracking and Surveillance System (STSS) Advanced Technology Risk Reduction (ATRR) payload into orbit. The launch is scheduled for 1:24 p.m. PDT. Photo by Carleton Bailie, United Launch Alliance.

Man-machine interface requirements - advanced technology

NASA Technical Reports Server (NTRS)

Remington, R. W.; Wiener, E. L.

1984-01-01

Research issues and areas are identified where increased understanding of the human operator and the interaction between the operator and the avionics could lead to improvements in the performance of current and proposed helicopters. Both current and advanced helicopter systems and avionics are considered. Areas critical to man-machine interface requirements include: (1) artificial intelligence; (2) visual displays; (3) voice technology; (4) cockpit integration; and (5) pilot work loads and performance.

Software and Human-Machine Interface Development for Environmental Controls Subsystem Support

NASA Technical Reports Server (NTRS)

Dobson, Matthew

2018-01-01

The Space Launch System (SLS) is the next premier launch vehicle for NASA. It is the next stage of manned space exploration from American soil, and will be the platform in which we push further beyond Earth orbit. In preparation of the SLS maiden voyage on Exploration Mission 1 (EM-1), the existing ground support architecture at Kennedy Space Center required significant overhaul and updating. A comprehensive upgrade of controls systems was necessary, including programmable logic controller software, as well as Launch Control Center (LCC) firing room and local launch pad displays for technician use. Environmental control acts as an integral component in these systems, being the foremost system for conditioning the pad and extremely sensitive launch vehicle until T-0. The Environmental Controls Subsystem (ECS) required testing and modification to meet the requirements of the designed system, as well as the human factors requirements of NASA software for Validation and Verification (V&V). This term saw significant strides in the progress and functionality of the human-machine interfaces used at the launch pad, and improved integration with the controller code.

Contribution of TOMS to Earth Science- An Overview

NASA Technical Reports Server (NTRS)

Bhartia, P. K.

2004-01-01

The TOMS instrument was launched on the Nimbus-7 satellite in Oct 1978 with the goal of understanding the meteorological influences on the ozone column. The nominal lifetime of the instrument was 1 year. However, in response to the concern over possible man-made influences on the ozone layer NASA continued to nurse the instrument for 13.5 years and launched a major program to produce accurate trend quality dataset of ozone. Despite severe optical degradation and other significant anomalies that developed in the instrument over its lifetime, the effort turned out to be a tremendous success. In 1984, TOMS took center stage as the primary provider of Antarctic ozone hole maps to the world community; it continues to play that role until today. An unexpected benefit of the close attention paid to improving the TOMS data quality was that several atmospheric constituents that interfere with ozone measurement were also identified and meticulously converted into long-term datasets of their own. These constituents include clouds, volcanic S02, aerosols, and ocean phytoplankton. In addition, the high quality of the basic datasets made it possible to produce global maps of surface UV and tropospheric ozone. In most cases there are no other sources of these data sets. Advanced UV instruments currently under development in the US and Europe will continue to exploit the TOMS-developed techniques for several decades.

Mercury Project

NASA Image and Video Library

1959-04-27

Astronaut John H. Glenn, one of the original seven astronauts for Mercury Project selected by NASA on April 27, 1959. The MA-6 mission, boosted by the Mercury-Atlas vehicle, was the first manned orbital launch by the United States, and carried Astronaut Glenn aboard the Friendship 7 spacecraft to orbit the Earth.

Saturn Apollo Program

NASA Image and Video Library

1969-03-30

This is the official crew portrait of the Apollo 11 astronauts. Pictured from left to right are: Neil A. Armstrong, Commander; Michael Collins, Module Pilot; Edwin E. "Buzz" Aldrin, Lunar Module Pilot. Apollo 11 was the first marned lunar landing mission that placed the first humans on the surface of the moon and returned them back to Earth. Astronaut Armstrong became the first man on the lunar surface, and astronaut Aldrin became the second. Astronaut Collins piloted the Command Module in a parking orbit around the Moon. Launched aboard the Saturn V launch vehicle (SA-506), the three astronauts began their journey to the moon with liftoff from launch complex 39A at the Kennedy Space Center at 8:32 am CDT, July 16, 1969.

Gun Launch System: efficient and low-cost means of research and real-time monitoring

NASA Astrophysics Data System (ADS)

Degtyarev, Alexander; Ventskovsky, Oleg; Korostelev, Oleg; Yakovenko, Peter; Kanevsky, Valery; Tselinko, Alexander

2005-08-01

The Gun Launch System with a reusable sub-orbital launch vehicle as a central element is proposed by a consortium of several Ukrainian high-tech companies as an effective, fast-response and low-cost means of research and real-time monitoring. The system is described in details, with the emphasis on its most important advantages. Multiple applications of the system are presented, including ones for the purposes of microgravity research; chemical, bacteriological and radiation monitoring and research of atmosphere and ionosphere; operational monitoring of natural and man-made disasters, as well as for some other areas of great practical interest. The current level of the system development is given, and the way ahead towards full system's implementation is prescribed.

Distribution of man-machine controls in space teleoperation

NASA Technical Reports Server (NTRS)

Bejczy, A. K.

1982-01-01

The distribution of control between man and machine is dependent on the tasks, available technology, human performance characteristics and control goals. This dependency has very specific projections on systems designed for teleoperation in space. This paper gives a brief outline of the space-related issues and presents the results of advanced teleoperator research and development at the Jet Propulsion Laboratory (JPL). The research and development work includes smart sensors, flexible computer controls and intelligent man-machine interface devices in the area of visual displays and kinesthetic man-machine coupling in remote control of manipulators. Some of the development results have been tested at the Johnson Space Center (JSC) using the simulated full-scale Shuttle Remote Manipulator System (RMS). The research and development work for advanced space teleoperation is far from complete and poses many interdisciplinary challenges.

Estimating the Effects of Astronaut Career Ionizing Radiation Dose Limits on Manned Interplanetary Flight Programs

NASA Technical Reports Server (NTRS)

Koontz, Steven L.; Rojdev, Kristina; Valle, Gerard D.; Zipay, John J.; Atwell, William S.

2013-01-01

The Hybrid Inflatable DSH combined with electric propulsion and high power solar-electric power systems offer a near TRL-now solution to the space radiation crew dose problem that is an inevitable aspect of long term manned interplanetary flight. Spreading program development and launch costs over several years can lead to a spending plan that fits with NASA's current and future budgetary limitations, enabling early manned interplanetary operations with space radiation dose control, in the near future while biomedical research, nuclear electric propulsion and active shielding research and development proceed in parallel. Furthermore, future work should encompass laboratory validation of HZETRN calculations, as previous laboratory investigations have not considered large shielding thicknesses and the calculations presented at these thicknesses are currently performed via extrapolation.

Biosputniks: The use by the Soviet Union and Russia of dogs, monkeys and other animals in the exploration of space, 1949-93

NASA Astrophysics Data System (ADS)

Harvey, B.

1993-10-01

The Soviet Union used animals in the exploration of space from 1949 onwards. Russia has continued the use of animals in the exploration of space with the launch on 30 December 1992 of Bion-10 (Cosmos 2229). Animals in the space program is an important theme in the Soviet exploration of space. The use of animals in the exploration of space has four main phases: (1) Suborbital missions 1949-1959; (2) Preparation for man's first flight into space 1960-1; (3) Preparation for man's flight to the Moon 1968-1970; (4) The international biomedical program 1962- . Each is dealt with in turn. The use of animals or biological specimens on board manned orbital space stations is not discussed.

Saturn Apollo Program

NASA Image and Video Library

1969-07-16

Aboard a Saturn V launch vehicle, the Apollo 11 mission launched from The Kennedy Space Center, Florida on July 16, 1969 and safely returned to Earth on July 24, 1969. The space vehicle is shown here during the rollout for launch preparation. The 3-man crew aboard the flight consisted of Neil A. Armstrong, commander; Michael Collins, Command Module pilot; and Edwin E. Aldrin Jr., Lunar Module pilot. Armstrong was the first human to ever stand on the lunar surface, followed by Edwin (Buzz) Aldrin. The crew collected 47 pounds of lunar surface material which was returned to Earth for analysis. The surface exploration was concluded in 2½ hours. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished. The Saturn V launch vehicle was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun.

Orbit on demand - Will cost determine best design?

NASA Technical Reports Server (NTRS)

Macconochie, J. O.; Mackley, E. A.; Morris, S. J.; Phillips, W. P.; Breiner, C. A.; Scotti, S. J.

1985-01-01

Eleven design concepts for vertical (V) and horizontal (H) take-off launch-on-demand manned orbital vehicles are discussed. Attention is given to up to three stages, Mach numbers (sub-, 2, or 3), expendable boosters, drop tanks (DT), and storable (S) or cryogenic fuels. All the concepts feature lifting bodies with circular cross-section and most have a 7 ft diam, 15 ft long payload bay as well as a crew compartment. Expendable elements impose higher costs and in some cases reduce all-azimuth launch capabilities. Single-stage vehicles simplify the logistics whether in H or V configuration. A two-stage H vehicle offers launch offset for the desired orbital plane before firing the rocket engines after take-off and subsonic acceleration. A two-stage fully reusable V form has the second lowest weight of the vehicles studied and an all-azimuth launch capability. Better definition of the prospective mission requirements is needed before choosing among the alternatives.

Crew transportation for the 1990s. I - Commercializing manned flight with today's propulsion

NASA Astrophysics Data System (ADS)

Staehle, Robert; French, J. R.

Two commercial space transport concepts that have been developed employing reusable production engines are discussed. A winged space transport (WST) launched from a Boeing 747 was sized to carry six people to low orbit. With no margin for performance growth, it is not favored for development. A vertical launch/landing space transport was designed with capabilities and propulsion similar to the WST, but launched from the ground. A small launch mass penalty is offset by improved performance margins and by eliminating carrier aircraft costs. The two-pilot plus five-passenger vehicle is designed for short-duration trips to low earth orbit, or for docking up to 10 d at an orbiting station. Market applications include space station crew rotation, equipment delivery and product return, short-duration experiments, satellite servicing, reconnaissance, and tourism. Profitable per-mission prices are projected at $10-15 million, with development costs approaching $400 million.

The Scientific-Technological Revolution and the Formation of the New Man

ERIC Educational Resources Information Center

Soviet Education, 1976

1976-01-01

This issue contains the proceedings of a round table discussion by Ukranian educators, philosophers, and social scientists on the education of the new Soviet man in the era of scientific-technological revolution. The "new man" is defined as the builder of communism, the participant in the transition to an advanced industrial economy.…

Robust flight design for an advanced launch system vehicle

NASA Astrophysics Data System (ADS)

Dhand, Sanjeev K.; Wong, Kelvin K.

Current launch vehicle trajectory design philosophies are generally based on maximizing payload capability. This approach results in an expensive trajectory design process for each mission. Two concepts of robust flight design have been developed to significantly reduce this cost: Standardized Trajectories and Command Multiplier Steering (CMS). These concepts were analyzed for an Advanced Launch System (ALS) vehicle, although their applicability is not restricted to any particular vehicle. Preliminary analysis has demonstrated the feasibility of these concepts at minimal loss in payload capability.

Mars exploration advances: Missions to Mars - Mars base

NASA Technical Reports Server (NTRS)

Dejarnette, Fred R.; Mckay, Christopher P.

1992-01-01

An overview is presented of Mars missions and related planning with attention given to four mission architectures in the light of significant limitations. Planned unpiloted missions are discussed including the Mars Orbital Mapping Mission, the Mars Rover Sample Return, the Mars Aeronomy Orbiter, and the Mars Environmental Survey. General features relevant to the missions are mentioned including launch opportunities, manned-mission phases, and propulsion options. The four mission architectures are set forth and are made up of: (1) the Mars-exploration infrastructures; (2) science emphasis for the moon and Mars; (3) the moon to stay and Mars exploration; and (4) space resource utilization. The possibility of robotic missions to the moon and Mars is touched upon and are concluded to be possible by the end of the century. The ramifications of a Mars base are discussed with specific reference to habitability and base activities, and the human missions are shown to require a heavy-lift launcher and either chemical/aerobrake or nuclear-thermal propulsion system.

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.

Advanced Launch System (ALS) actuation and power systems impact operability and cost

NASA Technical Reports Server (NTRS)

Sundberg, Gale R.

1990-01-01

To obtain the Advanced Launch System (ALS) primary goals of reduced costs and improved operability, there must be significant reductions in the launch operations and servicing requirements relative to current vehicle designs and practices. One of the primary methods for achieving these goals is by using vehicle electrical power system and controls for all actuation and avionics requirements. A brief status review of the ALS and its associated Advanced Development Program is presented to demonstrate maturation of those technologies that will help meet the overall operability and cost goals. The electric power and actuation systems are highlighted as a specific technology ready not only to meet the stringent ALS goals (cryogenic field valves and thrust vector controls with peak power demands to 75 hp), but also those of other launch vehicles, military and civilian aircraft, lunar/Martian vehicles, and a multitude of commercial applications.

Advanced Launch System (ALS): Electrical actuation and power systems improve operability and cost picture

NASA Technical Reports Server (NTRS)

Sundberg, Gale R.

1990-01-01

To obtain the Advanced Launch System (ALS) primary goals of reduced costs and improved operability, there must be significant reductions in the launch operations and servicing requirements relative to current vehicle designs and practices. One of the primary methods for achieving these goals is by using vehicle electrical power system and controls for all actuation and avionics requirements. A brief status review of the ALS and its associated Advanced Development Program is presented to demonstrate maturation of those technologies that will help meet the overall operability and cost goals. The electric power and actuation systems are highlighted as a specific technology ready not only to meet the stringent ALS goals (cryogenic field valves and thrust vector controls with peak power demands to 75 hp), but also those of other launch vehicles, military and civilian aircraft, lunar/Martian vehicles, and a multitude of commercial applications.

Advanced launch system (ALS) - Electrical actuation and power systems improve operability and cost picture

NASA Technical Reports Server (NTRS)

Sundberg, Gale R.

1990-01-01

To obtain the Advanced Launch System (ALS) primary goals of reduced costs and improved operability, there must be significant reductions in the launch operations and servicing requirements relative to current vehicle designs and practices. One of the primary methods for achieving these goals is by using vehicle electrrical power system and controls for all aviation and avionics requirements. A brief status review of the ALS and its associated Advanced Development Program is presented to demonstrate maturation of those technologies that will help meet the overall operability and cost goals. The electric power and actuation systems are highlighted as a sdpecific technology ready not only to meet the stringent ALS goals (cryogenic field valves and thrust vector controls with peak power demands to 75 hp), but also those of other launch vehicles, military ans civilian aircraft, lunar/Martian vehicles, and a multitude of comercial applications.

Space Station

NASA Image and Video Library

1981-12-01

During 1980 and the first half of 1981, the Marshall Space Flight Center conducted studies concerned with a relatively low-cost, near-term, manned space platform to satisfy current user needs, yet capable of evolutionary growth to meet future needs. The Science and Application Manned Space Platform (SAMSP) studies were to serve as a test bed for developing scientific and operational capabilities required by later, more advanced manned platforms while accomplishing early science and operations. This concept illustrates a manned space platform.

Google Moon Press Conference

NASA Image and Video Library

2009-07-19

Andrew Chaikin, author of "A Man on the Moon" speaks during a press conference, Monday, July 20, 2009, announcing the launch of Moon in Google Earth, an immersive 3D atlas of the Moon, accessible within Google Earth 5.0, Monday, July 20, 2009, at the Newseum in Washington. Photo Credit: (NASA/Bill Ingalls)

Google Moon Press Conference

NASA Image and Video Library

2009-07-19

Buzz Aldrin, the second man to walk on the moon, speaks during a press conference, Monday, July 20, 2009, announcing the launch of Moon in Google Earth, an immersive 3D atlas of the Moon, accessible within Google Earth 5.0, Monday, July 20, 2009, at the Newseum in Washington. Photo Credit: (NASA/Bill Ingalls)

Astronaut John H. Glenn

NASA Technical Reports Server (NTRS)

1959-01-01

Astronaut John H. Glenn, one of the original seven astronauts for Mercury Project selected by NASA on April 27, 1959. The MA-6 mission, boosted by the Mercury-Atlas vehicle, was the first manned orbital launch by the United States, and carried Astronaut Glenn aboard the Friendship 7 spacecraft to orbit the Earth.

Development of Precision Pointing Controllers with and Without Vibration Suppression for the NPS Precision Pointing Hexapod

DTIC Science & Technology

2002-12-01

applications, vibration sources are numerous such as: ! Launch Loading ! Man-induced accelerations like on the Shuttle or space station ! Solar ...However, the lack of significant tracking errors during times when other actuators were stationary, and the fact that the local maximum tracking...

Clifford Charlesworth seated at his console in Mission Control Room

NASA Image and Video Library

1968-12-21

S68-55742 (21 Dec. 1968) --- Clifford E. Charlesworth, Apollo 8 "Green Team" flight director, is seated at his console in the Mission Operations Control Room in the Mission Control Center, Building 30, during the launch of the Apollo 8 (Spacecraft 103/Saturn 503) manned lunar orbit space mission.

Saturn Apollo Program

NASA Image and Video Library

1968-06-03

Pictured left to right, in the Apollo 7 Crew Portrait, are astronauts R. Walter Cunningham, Lunar Module pilot; Walter M. Schirra, Jr., commander; and Donn F. Eisele, Command Module Pilot. The Apollo 7 mission, boosted by a Saturn IB launch vehicle on October 11, 1968, was the first manned flight of the Apollo spacecraft.

Advanced protein crystal growth programmatic sensitivity study

NASA Technical Reports Server (NTRS)

1992-01-01

The purpose of this study is to define the costs of various APCG (Advanced Protein Crystal Growth) program options and to determine the parameters which, if changed, impact the costs and goals of the programs and to what extent. This was accomplished by developing and evaluating several alternate programmatic scenarios for the microgravity Advanced Protein Crystal Growth program transitioning from the present shuttle activity to the man tended Space Station to the permanently manned Space Station. These scenarios include selected variations in such sensitivity parameters as development and operational costs, schedules, technology issues, and crystal growth methods. This final report provides information that will aid in planning the Advanced Protein Crystal Growth Program.

Advanced water iodinating system. [for potable water aboard manned spacecraft

NASA Technical Reports Server (NTRS)

Davenport, R. J.; Schubert, F. H.; Wynveen, R. A.

1975-01-01

Potable water stores aboard manned spacecraft must remain sterile. Suitable sterilization techniques are needed to prevent microbial growth. The development of an advanced water iodinating system for possible application to the shuttle orbiter and other advanced spacecraft, is considered. The AWIS provides a means of automatically dispensing iodine and controlling iodination levels in potable water stores. In a recirculation mode test, simulating application of the AWIS to a water management system of a long term six man capacity space mission, noniodinated feed water flowing at 32.2 cu cm min was iodinated to 5 + or - ppm concentrations after it was mixed with previously iodinated water recirculating through a potable water storage tank. Also, the AWIS was used to successfully demonstrate its capability to maintain potable water at a desired I2 concentration level while circulating through the water storage tank, but without the addition of noniodinated water.

A Brief History of Meteoroid and Orbital Debris Shielding Technology for US Manned Spacecraft

NASA Technical Reports Server (NTRS)

Bjorkman, Michael D.; Hyde, James L.

2008-01-01

Meteoroid and orbital debris shielding has played an important role from the beginning of manned spaceflight. During the early 60 s, meteoroid protection drove requirements for new meteor and micrometeoroid impact science. Meteoroid protection also stimulated advances in the technology of hypervelocity impact launchers and impact damage assessment methodologies. The first phase of meteoroid shielding assessments closed in the early 70 s with the end of the Apollo program. The second phase of meteoroid protection technology began in the early 80 s when it was determined that there is a manmade Earth orbital debris belt that poses a significant risk to LEO manned spacecraft. The severity of the Earth orbital debris environment has dictated changes in Space Shuttle and ISS operations as well as driven advances in shielding technology and assessment methodologies. A timeline of shielding technology and assessment methodology advances is presented along with a summary of risk assessment results.

n/a

NASA Image and Video Library

1969-07-27

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet recovery ship, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home for 21 days. In this photo taken at Pearl Harbor, Hawaii, the quarantined housing facility is being lowered from the U.S.S. Hornet, onto a trailer for transport to Hickam Field. From there, it was loaded aboard an Air Force C-141 jet and flown back to Ellington Air Force Base Texas, and then on to the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas.

Saturn Apollo Program

NASA Image and Video Library

1969-07-20

This is a close-up view of an astronaut’s footprint in the lunar soil, photographed by a 70 mm lunar surface camera during the Apollo 11 lunar surface extravehicular activity. The first manned lunar mission, the Apollo 11 launched aboard a Saturn V launch vehicle from the Kennedy Space Center, Florida on July 16, 1969 and safely returned to Earth on July 24, 1969. The 3-man crew aboard the flight consisted of Neil A, Armstrong, mission commander; Edwin E. Aldrin, Jr., Lunar Module Pilot; and Michael Collins, Command Module pilot. The LM landed on the moon’s surface on July 20, 1969 in the region known as Mare Tranquilitatis (the Sea of Tranquility). Armstrong was the first human to ever stand on the lunar surface. As he stepped off the LM, Armstrong proclaimed, “That’s one small step for man, one giant leap for mankind”. He was followed by Edwin (Buzz) Aldrin, describing the lunar surface as Magnificent desolation. Astronaut Collins piloted the Command Module in a parking orbit around the Moon. The crew collected 47 pounds of lunar surface material which was returned to Earth for analysis. The surface exploration was concluded in 2½ hours. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished. The Saturn V vehicle was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. von Braun.

Saturn Apollo Program

NASA Image and Video Library

1969-07-25

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. This photograph was taken as the mission’s first loaded sample return container arrived at Ellington Air Force Base by air from the Pacific recovery area. The rock box was immediately taken to the Lunar Receiving Laboratory at the Manned Spacecraft Center (MSC) in Houston, Texas. Happily posing for the photograph with the rock container are (L-R) Richard S. Johnston (back), special assistant to the MSC Director; George M. Low, MSC Apollo Spacecraft Program manager; George S. Trimble (back), MSC Deputy Director; Lt. General Samuel C. Phillips, Apollo Program Director, Office of Manned Spaceflight at NASA headquarters; Eugene G. Edmonds, MSC Photographic Technology Laboratory; Dr. Thomas O. Paine, NASA Administrator; and Dr. Robert R. Gilruth, MSC Director.

Saturn Apollo Program

NASA Image and Video Library

1969-07-27

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. On arrival at Ellington Air Force base near the MSC, the crew, still under a 21 day quarantine in the MQF are greeted by their wives. Looking out of the facility are (L-R) Armstrong, Aldrin, and Collins. Wives are (L-R) Pat Collins, Jan Armstrong, and Joan Aldrin.

Proposal for a remotely manned space station

NASA Technical Reports Server (NTRS)

Minsky, Marvin

1990-01-01

The United States is in trouble in space. The costs of the proposed Space Station Freedom have grown beyond reach, and the present design is obsolete. The trouble has come from imagining that there are only two alternatives: manned vs. unmanned. Both choices have led us into designs that do not appear to be practical. On one side, the United States simply does not possess the robotic technology needed to operate or assemble a sophisticated unmanned space station. On the other side, the manned designs that are now under way seem far too costly and dangerous, with all of its thousands of extravehicular activity (EVA) hours. More would be accomplished at far less cost by proceeding in a different way. The design of a space station made of modular, Erector Set-like parts is proposed which is to be assembled using earth-based remotely-controlled binary-tree telerobots. Earth-based workers could be trained to build the station in space using simulators. A small preassembled spacecraft would be launched with a few telerobots, and then, telerobots could be ferried into orbit along with stocks of additional parts. Trained terrestrial workers would remotely assemble a larger station, and materials for additional power and life support systems could be launched. Finally, human scientists and explorers could be sent to the space station. Other aspects of such a space station program are discussed.

Apollo 11 Quarantine Facility Prepared for Loading Onto Jet Transport

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named 'Eagle'', carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. In this photo taken at Pearl Harbor, Hawaii, the inhabited MQF is prepared for loading into an Air Force C-141 jet transport for the flight back to Ellington Air Force Base Texas and then on to the MSC.

Quarantined Apollo 11 Astronaut Aldrin Speaks With Wife Joan

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. (Buzz) Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named 'Eagle'', carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. On arrival at Ellington Air Force base near the MSC, the crew, still under a 21 day quarantine in the MQF, were greeted by their wives. Pictured here is Joan Aldrin, wife of Buzz Aldrin, speaking with her husband via telephone patch.

Wash water reclamation technology for advanced manned spacecraft

NASA Technical Reports Server (NTRS)

Putnam, D. F.

1977-01-01

The results of an analytical study and assessment of state-of-the-art wash water reclamation technology for advanced manned spacecraft is presented. All non-phase-change unit operations, unit processes, and subsystems currently under development by NASA are considered. Included among these are: filtration, ultrafiltration, carbon adsorption, ion exchange, chemical pretreatment, reverse osmosis, hyperfiltration, and certain urea removal techniques. Performance data are given together with the projected weights and sizes of key components and subsystems. In the final assessment, a simple multifiltration approach consisting of surface-type cartridge filters, carbon adsorption and ion exchange resins receives the highest rating for six-man orbital missions of up to 10 years in duration.

Advanced Transportation System Studies Technical Area 2 (TA-2) Heavy Lift Launch Vehicle Development Contract. Volume 2; Technical Results

NASA Technical Reports Server (NTRS)

1995-01-01

The purpose of the Advanced Transportation System Studies (ATSS) Technical Area 2 (TA-2) Heavy Lift Launch Vehicle Development contract was to provide advanced launch vehicle concept definition and analysis to assist NASA in the identification of future launch vehicle requirements. Contracted analysis activities included vehicle sizing and performance analysis, subsystem concept definition, propulsion subsystem definition (foreign and domestic), ground operations and facilities analysis, and life cycle cost estimation. This document is Volume 2 of the final report for the contract. It provides documentation of selected technical results from various TA-2 analysis activities, including a detailed narrative description of the SSTO concept assessment results, a user's guide for the associated SSTO sizing tools, an SSTO turnaround assessment report, an executive summary of the ground operations assessments performed during the first year of the contract, a configuration-independent vehicle health management system requirements report, a copy of all major TA-2 contract presentations, a copy of the FLO launch vehicle final report, and references to Pratt & Whitney's TA-2 sponsored final reports regarding the identification of Russian main propulsion technologies.

EMMI-Electric solar wind sail facilitated Manned Mars Initiative

NASA Astrophysics Data System (ADS)

Janhunen, Pekka; Merikallio, Sini; Paton, Mark

2015-08-01

The novel propellantless electric solar wind sail concept promises efficient low thrust transportation in the Solar System outside Earth's magnetosphere. Combined with asteroid mining to provide water and synthetic cryogenic rocket fuel in orbits of Earth and Mars, possibilities for affordable continuous manned presence on Mars open up. Orbital fuel and water enable reusable bidirectional Earth-Mars vehicles for continuous manned presence on Mars and allow smaller fuel fraction of spacecraft than what is achievable by traditional means. Water can also be used as radiation shielding of the manned compartment, thus reducing the launch mass further. In addition, the presence of fuel in the orbit of Mars provides the option for an all-propulsive landing, thus potentially eliminating issues of heavy heat shields and augmenting the capability of pinpoint landing. With this E-sail enabled scheme, the recurrent cost of continuous bidirectional traffic between Earth and Mars might ultimately approach the recurrent cost of running the International Space Station, ISS.

Advanced photovoltaic power system technology for lunar base applications

NASA Astrophysics Data System (ADS)

Brinker, David J.; Flood, Dennis J.

1992-09-01

The development of an advanced photovoltaic power system that would have application for a manned lunar base is currently planned under the Surface Power element of Pathfinder. Significant mass savings over state-of-the-art photovoltaic/battery systems are possible with the use of advanced lightweight solar arrays coupled with regenerative fuel cell storage. The solar blanket, using either ultrathin GaAs or amorphous silicon solar cells, would be integrated with a reduced-g structure. Regenerative fuel cells with high-pressure gas storage in filament-wound tanks are planned for energy storage. An advanced PV/RFC power system is a leading candidate for a manned lunar base as it offers a tremendous weight advantage over state-of-the-art photovoltaic/battery systems and is comparable in mass to other advanced power generation technologies.

Recent Advances in Bathymetric Surveying of Continental Shelf Regions Using Autonomous Vehicles

NASA Astrophysics Data System (ADS)

Holland, K. T.; Calantoni, J.; Slocum, D.

2016-02-01

Obtaining bathymetric observations within the continental shelf in areas closer to the shore is often time consuming and dangerous, especially when uncharted shoals and rocks present safety concerns to survey ships and launches. However, surveys in these regions are critically important to numerical simulation of oceanographic processes, as bathymetry serves as the bottom boundary condition in operational forecasting models. We will present recent progress in bathymetric surveying using both traditional vessels retrofitted for autonomous operations and relatively inexpensive, small team deployable, Autonomous Underwater Vehicles (AUV). Both systems include either high-resolution multibeam echo sounders or interferometric sidescan sonar sensors with integrated inertial navigation system capabilities consistent with present commercial-grade survey operations. The advantages and limitations of these two configurations employing both unmanned and autonomous strategies are compared using results from several recent survey operations. We will demonstrate how sensor data collected from unmanned platforms can augment or even replace traditional data collection technologies. Oceanographic observations (e.g., sound speed, temperature and currents) collected simultaneously with bathymetry using autonomous technologies provide additional opportunities for advanced data assimilation in numerical forecasts. Discussion focuses on our vision for unmanned and autonomous systems working in conjunction with manned or in-situ systems to optimally and simultaneously collect data in environmentally hostile or difficult to reach areas.

Antimatter propulsion, status and prospects

NASA Technical Reports Server (NTRS)

Howe, Steven D.; Hynes, Michael V.

1986-01-01

The use of advanced propulsion techniques must be considered if the currently envisioned launch date of the manned Mars mission were delayed until 2020 or later. Within the next thirty years, technological advances may allow such methods as beaming power to the ship, inertial-confinement fusion, or mass-conversion of antiprotons to become feasible. A propulsion system with an ISP of around 5000 s would allow the currently envisioned mission module to fly to Mars in 3 months and would require about one million pounds to be assembled in Earth orbit. Of the possible methods to achieve this, the antiproton mass-conversion reaction offers the highest potential, the greatest problems, and the most fascination. Increasing the production rates of antiprotons is a high priority task at facilities around the world. The application of antiprotons to propulsion requires the coupling of the energy released in the mass-conversion reaction to thrust-producing mechanisms. Recent proposals entail using the antiprotons to produce inertial confinement fusion or to produce negative muons which can catalyze fusion. By increasing the energy released per antiproton, the effective cost, (dollars/joule) can be reduced. These proposals and other areas of research can be investigated now. These short term results will be important in assessing the long range feasibility of an antiproton powered engine.

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.

Atomic hydrogen as a launch vehicle propellant

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan A.

1990-01-01

An analysis of several atomic hydrogen launch vehicles was conducted. A discussion of the facilities and the technologies that would be needed for these vehicles is also presented. The Gross Liftoff Weights (GLOW) for two systems were estimated; their specific impulses (I sub sp) were 750 and 1500 lb (sub f)/s/lb(sub m). The atomic hydrogen launch vehicles were also compared to the currently planned Advanced Launch System design concepts. Very significant GLOW reductions of 52 to 58 percent are possible over the Advanced Launch System designs. Applying atomic hydrogen propellants to upper stages was also considered. Very high I(sub sp) (greater than 750 1b(sub f)/s/lb(sub m) is needed to enable a mass savings over advanced oxygen/hydrogen propulsion. Associated with the potential benefits of high I(sub sp) atomic hydrogen are several challenging problems. Very high magnetic fields are required to maintain the atomic hydrogen in a solid kilogauss (3 Tesla). Also the storage temperature of the propellant is 4 K. This very low temperature will require a large refrigeration facility for the launch vehicle. The design considerations for a very high recombination rate for the propellant are also discussed. A recombination rate of 210 cm/s is predicted for atomic hydrogen. This high recombination rate can produce very high acceleration for the launch vehicle. Unique insulation or segmentation to inhibit the propellant may be needed to reduce its recombination rate.

Studies of Fission Fragment Rocket Engine Propelled Spacecraft

NASA Technical Reports Server (NTRS)

Werka, Robert O.; Clark, Rodney; Sheldon, Rob; Percy, Thomas K.

2014-01-01

The NASA Office of Chief Technologist has funded from FY11 through FY14 successive studies of the physics, design, and spacecraft integration of a Fission Fragment Rocket Engine (FFRE) that directly converts the momentum of fission fragments continuously into spacecraft momentum at a theoretical specific impulse above one million seconds. While others have promised future propulsion advances if only you have the patience, the FFRE requires no waiting, no advances in physics and no advances in manufacturing processes. Such an engine unequivocally can create a new era of space exploration that can change spacecraft operation. The NIAC (NASA Institute for Advanced Concepts) Program Phase 1 study of FY11 first investigated how the revolutionary FFRE technology could be integrated into an advanced spacecraft. The FFRE combines existent technologies of low density fissioning dust trapped electrostatically and high field strength superconducting magnets for beam management. By organizing the nuclear core material to permit sufficient mean free path for escape of the fission fragments and by collimating the beam, this study showed the FFRE could convert nuclear power to thrust directly and efficiently at a delivered specific impulse of 527,000 seconds. The FY13 study showed that, without increasing the reactor power, adding a neutral gas to the fission fragment beam significantly increased the FFRE thrust through in a manner analogous to a jet engine afterburner. This frictional interaction of gas and beam resulted in an engine that continuously produced 1000 pound force of thrust at a delivered impulse of 32,000 seconds, thereby reducing the currently studied DRM 5 round trip mission to Mars from 3 years to 260 days. By decreasing the gas addition, this same engine can be tailored for much lower thrust at much higher impulse to match missions to more distant destinations. These studies created host spacecraft concepts configured for manned round trip journeys. While the vehicles are very large, they are primarily made up of a habitat payload on one end, the engine on the opposite end and a connecting spine containing radiator acreage needed to reject the heat of this powerful, but inefficient engine. These studies concluded that the engine and spacecraft are within today's technology, could be built, tested, launched on several SLS launchers, integrated, checked out, maintained at an in-space LEO base, and operated for decades just as Caribbean cruise ships operate today. The nuclear issues were found to be far less daunting that [than for] current nuclear engines. The FFRE produces very small amounts of radioactive efflux compared to their impulse, easily contained in an evacuated "bore-hole" test site. The engine poses no launch risk since it is simply a structure containing no fissionable material. The nuclear fuel is carried to orbit in containers highly crash-proofed for launch accidents from which it, in a liquid medium, is injected into the FFRE. The radioactive exhaust, with a velocity above 300 kilometers per second rapidly leaves the solar system.

Spaceport Command and Control System Automated Testing

NASA Technical Reports Server (NTRS)

Stein, Meriel

2017-01-01

The Spaceport Command and Control System (SCCS) is the National Aeronautics and Space Administrations (NASA) launch control system for the Orion capsule and Space Launch System, the next generation manned rocket currently in development. This large system requires high quality testing that will properly measure the capabilities of the system. Automating the test procedures would save the project time and money. Therefore, the Electrical Engineering Division at Kennedy Space Center (KSC) has recruited interns for the past two years to work alongside full-time engineers to develop these automated tests, as well as innovate upon the current automation process.

Booster propulsion/vehicle impact study

NASA Technical Reports Server (NTRS)

Weldon, Vincent; Dunn, Michael; Fink, Lawrence; Phillips, Dwight; Wetzel, Eric

1988-01-01

The use of hydrogen RP-1, propane, and methane as fuels for booster engines of launch vehicles is discussed. An automated procedure for integrated launch vehicle, engine sizing, and design optimization was used to define two stage and single stage concepts for minimum dry weight. The two stage vehicles were unmanned and used a flyback booster and partially reusable orbiter. The single stage designs were fully reusable, manned flyback vehicles. Comparisons of these vehicle designs, showing the effects of using different fuels, as well as sensitivity and trending data, are presented. In addition, the automated design technique utilized for the study is described.

KSC-99pp0843

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- In the Apollo/Saturn V Center, Lisa Malone (left), chief of KSC's Media Services branch, identifies a reporter to pose a question to one of the former Apollo astronauts seated next to her. From left, they are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch to the moon; Gene Cernan, who flew on Apollo 10 and 17; and Walt Cunningham, who flew on Apollo 7. This is the 30th anniversary of the launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon

Spaceport Command and Control System Automation Testing

NASA Technical Reports Server (NTRS)

Hwang, Andrew

2017-01-01

The Spaceport Command and Control System (SCCS) is the National Aeronautics and Space Administrations (NASA) launch control system for the Orion capsule and Space Launch System, the next generation manned rocket currently in development. This large system requires high quality testing that will properly measure the capabilities of the system. Automating the test procedures would save the project time and money. Therefore, the Electrical Engineering Division at Kennedy Space Center (KSC) has recruited interns for the past two years to work alongside full-time engineers to develop these automated tests, as well as innovate upon the current automation process.

Performance Analysis and Design Synthesis (PADS) computer program. Volume 1: Formulation

NASA Technical Reports Server (NTRS)

1972-01-01

The program formulation for PADS computer program is presented. It can size launch vehicles in conjunction with calculus-of-variations optimal trajectories and can also be used as a general-purpose branched trajectory optimization program. In the former use, it has the Space Shuttle Synthesis Program as well as a simplified stage weight module for optimally sizing manned recoverable launch vehicles. For trajectory optimization alone or with sizing, PADS has two trajectory modules. The first trajectory module uses the method of steepest descent; the second employs the method of quasilinearization, which requires a starting solution from the first trajectory module.

Natural environment analysis

NASA Technical Reports Server (NTRS)

Frost, W.

1985-01-01

The influence of terrain features on wind loading of the space shuttle while on the launch pad, or during early liftoff, was investigated both qualitatively and quantitatively. The climatology and meteorology producing macroscale wind patterns and characteristics for the Vandenburg Air Force Base launch site are described. Field test data are analyzed, and the nature and characteristic of flow disturbances due to the various terrain features, both natural and man-made, are reviewed. The magnitude of these wind loads are estimated. Finally, effects of turbulence are discussed. It is concluded that the influence of complex terrain can create significant wind loading on the vehicle.

Saturn Apollo Program

NASA Image and Video Library

1965-01-01

S-IB-200D, a dynamic test version of the Saturn IB launch vehicle's first stage (S-IB), makes its way to the Marshall Space Flight Center (MSFC) East Test Area on January 4, 1965. Test Laboratory persornel assembled a complete Saturn IB to test the structural soundness of the launch vehicle in the Dynamic Test Stand. Developed by the MSFC as an interim vehicle in MSFC's "building block" approach to the Saturn rocket development, the Saturn IB utilized Saturn I technology to further develop and refine the larger boosters and the Apollo spacecraft capabilities required for the manned lunar missions.

Solar dynamic power for Space Station Freedom

NASA Technical Reports Server (NTRS)

Labus, Thomas L.; Secunde, Richard R.; Lovely, Ronald G.

1989-01-01

The Space Station Freedom Program is presently planned to consist of two phases. At the completion of Phase 1, Freedom's manned base will consist of a transverse boom with attached manned modules and 75 kW of available electric power supplied by photovoltaic (PV) power sources. In Phase 2, electric power available to the manned base will be increased to 125 kW by the addition of two solar dynamic (SD) power modules, one at each end of the transverse boom. Power for manned base growth beyond Phase 2 will be supplied by additional SD modules. Studies show that SD power for the growth eras will result in life cycle cost savings of $3 to $4 billion when compared to PV-supplied power. In the SD power modules for Space Station Freedom, an offset parabolic concentrator collects and focuses solar energy into a heat receiver. To allow full power operation over the entire orbit, the receiver includes integral thermal energy storage by means of the heat of fusion of a salt mixture. Thermal energy is removed from the receiver and converted to electrical energy by a power conversion unit (PCU) which includes a closed brayton cycle (CBC) heat engine and an alternator. The receiver/PCU/radiator combination will be completely assembled and charged with gas and cooling fluid on earth before launch to orbit. The concentrator subassemblies will be pre-aligned and stowed in the orbiter bay before launch. On orbit, the receiver/PCU/radiator assembly will be installed as a unit. The pre-aligned concentrator panels will then be latched together and the total concentrator attached to the receiver/PCU/radiator by the astronauts. After final electric connections are made and checkout is complete, the SD power module will be ready for operation.

Solar dynamic power for space station freedom

NASA Technical Reports Server (NTRS)

Labus, Thomas L.; Secunde, Richard R.; Lovely, Ronald G.

1989-01-01

The Space Station Freedom Program is presently planned to consist of two phases. At the completion of Phase 1, Freedom's manned base will consist of a transverse boom with attached manned modules and 75 kW of available electric power supplied by photovoltaic (PV) power sources. In Phase 2, electric power available to the manned base will be increased to 125 kW by the addition of two solar dynamic (SD) power modules, one at each end of the transverse boom. Power for manned base growth beyond Phase 2 will be supplied by additional SD modules. Studies show that SD power for the growth eras will result in life cycle cost savings of $3 to $4 billion when compared to PV-supplied power. In the SD power modules for Space Station Freedom, an offset parabolic concentrator collects and focuses solar energy into a heat receiver. To allow full power operation over the entire orbit, the receiver includes integral thermal energy storage by means of the heat of fusion of a salt mixture. Thermal energy is removed from the receiver and converted to electrical energy by a power conversion unit (PCU) which includes a closed brayton cycle (CBC) heat engine and an alternator. The receiver/PCU/radiator combination will be completely assembled and charged with gas and cooling fluid on Earth before launch to orbit. The concentrator subassemblies will be pre-aligned and stowed in the orbiter bay before launch. On orbit, the receiver/PCU/radiator assembly will be installed as a unit. The pre-aligned concentrator panels will then be latched together and the total concentrator attached to the receiver/PCU/radiator by the astronauts. After final electric connections are made and checkout is complete, the SD power module will be ready for operation.

Skylab

NASA Image and Video Library

1972-01-01

This artist's concept is a cutaway illustration of the Skylab with the Command/Service Module being docked to the Multiple Docking Adapter. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab Program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Skylab

NASA Image and Video Library

1970-01-01

This illustration shows general characteristics of the Skylab with callouts of its major components. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab Program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Skylab

NASA Image and Video Library

1967-01-01

This photograph is of a model of the Skylab with the Command/Service Module being docked. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab Program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

Skylab

NASA Image and Video Library

1974-01-01

This image is an artist's concept of the Skylab in orbit with callouts of its major components. In an early effort to extend the use of Apollo for further applications, NASA established the Apollo Applications Program (AAP) in August of 1965. The AAP was to include long duration Earth orbital missions during which astronauts would carry out scientific, technological, and engineering experiments in space by utilizing modified Saturn launch vehicles and the Apollo spacecraft. Established in 1970, the Skylab Program was the forerurner of the AAP. The goals of the Skylab were to enrich our scientific knowledge of the Earth, the Sun, the stars, and cosmic space; to study the effects of weightlessness on living organisms, including man; to study the effects of the processing and manufacturing of materials utilizing the absence of gravity; and to conduct Earth resource observations. The Skylab also conducted 19 selected experiments submitted by high school students. Skylab's 3 different 3-man crews spent up to 84 days in Earth orbit. The Marshall Space Flight Center (MSFC) had responsibility for developing and integrating most of the major components of the Skylab: the Orbital Workshop (OWS), Airlock Module (AM), Multiple Docking Adapter (MDA), Apollo Telescope Mount (ATM), Payload Shroud (PS), and most of the experiments. MSFC was also responsible for providing the Saturn IB launch vehicles for three Apollo spacecraft and crews and a Saturn V launch vehicle for the Skylab.

An Advanced Neutron Spectrometer for Future Manned Exploration Missions

NASA Technical Reports Server (NTRS)

Christl, Mark; Apple, Jeffrey A.; Cox, Mark D.; Dietz, Kurtis L.; Dobson, Christopher C.; Gibson, Brian F.; Howard, David E.; Jackson, Amanda C.; Kayatin, Mathew J.; Kuznetsov, Evgeny N.;

View of Apollo 15 space vehicle on way from VAB to Pad A, Launch Complex 39

NASA Image and Video Library

1971-05-11

S71-33781 (11 May 1971) --- High angle view showing the Apollo 15 (Spacecraft 112/Lunar Module 10/Saturn 510) space vehicle on the way from the Vehicle Assembly Building (VAB) to Pad A, Launch Complex 39, Kennedy Space Center (KSC). The Saturn V stack and its mobile launch tower are atop a huge crawler-transporter. Apollo 15 is scheduled as the fourth manned lunar landing mission by the National Aeronautics and Space Administration (NASA). The crew men will be astronauts David R. Scott, commander; Alfred M. Worden, command module pilot; and James B. Irwin, lunar module pilot. While astronauts Scott and Irwin descend in the Lunar Module (LM) to explore the moon, astronaut Worden will remain with the Command and Service Modules (CSM) in lunar orbit.

Wernher von Braun

NASA Image and Video Library

1971-07-26

During the Apollo 15 launch activities in the launch control center's firing room 1 at Kennedy Space Center, Dr. Wernher von Braun, NASA's Deputy Associate Administrator for planning, takes a closer look at the launch pad through binoculars. The fifth manned lunar landing mission, Apollo 15 (SA-510), carrying a crew of three astronauts: Mission commander David R. Scott, Lunar Module pilot James B. Irwin, and Command Module pilot Alfred M. Worden Jr., lifted off on July 26, 1971. Astronauts Scott and Irwin were the first to use a wheeled surface vehicle, the Lunar Roving Vehicle, or the Rover, which was designed and developed by the Marshall Space Flight Center, and built by the Boeing Company. Astronauts spent 13 days, nearly 67 hours, on the Moon's surface to inspect a wide variety of its geological features.

ASCANS Class of 2013 Tour the O&C with Cabana

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. -- In the Operations and Checkout Building of NASA's Kennedy Space Center in Florida, associate center director Kelvin Manning, left, briefs astronaut candidates Nicole Mann, center, and Tyler Nick Hague on preparations for the launch the Orion spacecraft on Exploration Flight Test EFT-1. Plans call for the Lockheed Martin-built Orion to launch atop a United Launch Alliance Delta IV Heavy rocket from Cape Canaveral Air Force Station. The astronaut class of 2013 was selected by NASA after an extensive year-and-a-half search. The new group will help the agency push the boundaries of exploration and travel to new destinations in the solar system. To learn more about the astronaut class of 2013, visit: http://www.nasa.gov/astronauts/2013astroclass.html Photo credit: NASA/Kim Shiflett

Emmonsia helica Infection in HIV-Infected Man, California, USA.

PubMed

Rofael, Martin; Schwartz, Ilan S; Sigler, Lynne; Kong, Li K; Nelson, Nicholas

2018-01-01

Emmonsia-like fungi have rarely been reported from North America. We report a fatal case of E. helica infection in a man with advanced HIV infection from California, USA, who had progressive respiratory failure and a brain abscess.

The Vehicle Control Systems Branch at the Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

Barret, Chris

1990-01-01

This paper outlines the responsibility of the Vehicle Control Systems Branch at the Marshall Space Flight Center (MSFC) to analyze, evaluate, define, design, verify, and specify requirements for advanced launch vehicles and related space projects, and to conduct research in advanced flight control concepts. Attention is given to branch responsibilities which include Shuttle-C, Shuttle-C Block II, Shuttle-Z, lunar cargo launch vehicles, Mars cargo launch vehicles, orbital maneuvering vehicle, automatic docking, tethered satellite, aeroassisted flight experiment, and solid rocket booster parachute recovery system design.

The humanation of Mars

NASA Astrophysics Data System (ADS)

David, L. W.

Early developments related to human excursions to Mars are examined, taking into account plans considered by von Braun, and the 'ambitious goal of a manned flight to Mars by the end of the century', proposed at the launch of Apollo 11. In response to public reaction, plans for manned flights to Mars in the immediate future were given up, and unmanned reconnaissance of Mars was continued. An investigation is conducted concerning the advantages of manned exploration of Mars in comparison to a study by unmanned space probes, and arguments regarding a justification for interplanetary flight to Mars are discussed. Attention is given to the possibility to consider Mars as a 'back-up' planet for preserving earth life, an international Mars expedition as a world peace project, the role of Mars in connection with resource utilization considerations, and questions of exploration ethics.

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 station support of manned Mars missions

NASA Technical Reports Server (NTRS)

Holt, Alan C.

1986-01-01

The assembly of a manned Mars interplanetary spacecraft in low Earth orbit can be best accomplished with the support of the space station. Station payload requirements for microgravity environments of .001 g and pointing stability requirements of less than 1 arc second could mean that the spacecraft may have to be assembled at a station-keeping position about 100 meters or more away from the station. In addition to the assembly of large modules and connective structures, the manned Mars mission assembly tasks may include the connection of power, fluid, and data lines and the handling and activation of components for chemical or nuclear power and propulsion systems. These assembly tasks will require the use of advanced automation and robotics in addition to Orbital Maneuvering Vehicle and Extravehicular Activity (EVA) crew support. Advanced development programs for the space station, including on-orbit demonstrations, could also be used to support manned Mars mission technology objectives. Follow-on studies should be conducted to identify space station activities which could be enhanced or expanded in scope (without significant cost and schedule impact) to help resolve key technical and scientific questions relating to manned Mars missions.

KSC-2009-2946

NASA Image and Video Library

2009-05-05

VANDENBERG AIR FORCE BASE, Calif. – A United Launch Alliance Delta II rocket blasts off from Space Launch Complex-2 launch pad at Vandenberg AFB, Calif., at 1:24 p.m. PDT. The Delta II successfully carried the Missile Defense Agency's Space Tracking and Surveillance System (STSS) Advanced Technology Risk Reduction (ATRR) payload into orbit. Photo by Carleton Bailie, United Launch Alliance.

Google Moon Press Conference

NASA Image and Video Library

2009-07-19

Apollo 11 astronaut Buzz Aldrin, the second man to walk on the Moon, speaks during a press conference, Monday, July 20, 2009, announcing the launch of Moon in Google Earth, an immersive 3D atlas of the Moon, accessible within Google Earth 5.0, Monday, July 20, 2009, at the Newseum in Washington. Photo Credit: (NASA/Bill Ingalls)

Backgrounder: The MAB Programme.

ERIC Educational Resources Information Center

United Nations Educational, Scientific, and Cultural Organization, Paris (France). Office of Public Information.

The Man and the Biosphere Programme (MAB) was launched in November 1971 under the auspices of Unesco. Its aim is to help to develop scientific knowledge with a view to the rational management and conservation of natural resources, to train qualified personnel in this field, and to disseminate the knowledge acquired both to the decision-makers and…

Expedition 40 Press Conference

NASA Image and Video Library

2014-05-27

A man taking a picture with a cell phone is seen reflected in the glass separating the quarantined crew during a press conference on Tuesday, May 27, 2014, at the Cosmonaut Hotel in Baikonur, Kazakhstan. The mission to the International Space Station is set to launch May 29 from the Baikonur Cosmodrome. Photo Credit: (NASA/Joel Kowsky)

11. Photographic copy of photograph (original print in possession of ...

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

11. Photographic copy of photograph (original print in possession of CSSD-HO, Huntsville, AL). Photographer unknown. View of rocket models, allowing a comparison of the Spartan, galosh (USSR), minute man III, and SS-9 (USSR) missiles - Stanley R. Mickelsen Safeguard Complex, Missile Launch Area, Within Exclusion Area, Nekoma, Cavalier County, ND

Saturn Apollo Program

NASA Image and Video Library

1968-12-20

Searchlights penetrate the darkness surrounding Apollo 8 on Pad 39-A at Kennedy Space Center. This mission was the first manned flight using the Saturn V. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

A mockup of a solid rocket booster nozzle is lowered into the waters of the Atlantic during a test of a new booster retrieval method. A one-man submarine known as DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

From the deck of Liberty Star, one of two KSC solid rocket booster recovery ships, a crane lowers a one-man submarine into the ocean near Cape Canaveral, Fla. Called DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

- The one-man submarine known as DeepWorker 2000 is tested in Atlantic waters near Cape Canaveral, Fla. Nearby are divers; inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

Saturn Apollo Program

NASA Image and Video Library

1969-07-09

In this photograph, technicians are transferring mice from a support germ free isolator, through a hypochlorite dunk tank, into the class III cabinetry in the Germ-free and Conventional Animal Laboratories of the Lunar Receiving Laboratory, building 37, of the Manned Spacecraft Center in Houston, Texas. This laboratory was part of the overall physical, chemical, and biological test program of the Apollo 11 returned lunar samples. Aboard the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle, the Apollo 11 mission launched from The Kennedy Space Center, Florida on July 16, 1969 and safely returned to Earth on July 24, 1969. The 3-man crew aboard the flight consisted of astronauts Neil A. Armstrong, commander; Edwin Aldrin, Lunar Module (LM) pilot; and Michael Collins, Command Module (CM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. In 2 1/2 hours, the crew collected 47 pounds of lunar surface material which was returned to Earth for analysis.

CELSS and regenerative life support for manned missions to MARS

NASA Technical Reports Server (NTRS)

Mcelroy, R. D.

1986-01-01

In the mid 1990's, the space station will become a point from which inter-planetary vehicles can be launched. The practicalities of a manned Mars mission are now being studied, along with some newer concepts for human life support. Specifically, the use of organisms such as plants and algae as the basis for life support systems is now being actively considered. A Controlled Ecological Life Support System (CELSS) is composed of several facilities: (1) to grow photosynthetic plants or algae which will produce food, oxygen and potable water, and remove carbon dioxide exhaled by a crew; (2) to process biomass into food; (3) to oxidize organic wastes into CO2; and (4) to maintain system operation and stability. Such a system, when compared to using materials stored at launch, may have distinct weight and cost advantages, depending upon crew size and mission duration, as well as psychological benefits for the crew. The use of the system during transit, as well as in establishing a re-visitable surface camp, will increase the attractiveness of the CELSS concept for life support on interplanetary missions.

Scientific Objectives of China-Russia Joint Mars Exploration Program YH-1

NASA Astrophysics Data System (ADS)

Wu, Ji; Zhu, Guang-Wu; Zhao, Hua; Wang, Chi; Li, Lei; Sun, Yue-Qiang; Guo, Wei; Huang, Cheng-Li

2010-04-01

Compared with other planets, Mars is a planet most similar with the earth and most possible to find the extraterrestrial life on it, and therefore especially concerned about by human beings. In recent years, some countries have launched Mars probes and announced their manned Mars exploration programs. China has become the fifth country in the world to launch independently artificial satellites, and the third country able to carry out an independent manned space program. However, China is just at the beginning of deep space explorations. In 2007, China and Russia signed an agreement on a joint Mars exploration program by sending a Chinese micro-satellite Yinghuo-1 (YH-1) to the Mars orbit. Once YH-1 enters its orbit, it will carry out its own exploration, as well as the joint exploration with the Russian Phobos-Grunt probe. This paper summarizes the scientific background and objectives of YH-1 and describes briefly its payloads for realizing these scientific objectives. In addition, the main exploration tasks of YH-1 and a preliminary prospect on its exploration results are also given.

Key technologies for expeditions to Mars.

NASA Astrophysics Data System (ADS)

French, J. R., Jr.

A round-trip manned Mars landing mission, while difficult, is within the realm of today's technology. However, better understood and more practical advanced technologies offer promising improvements in mass performance, and some also enhance certain aspects of self-reliance for manned missions.

Image understanding and the man-machine interface II; Proceedings of the Meeting, Los Angeles, CA, Jan. 17, 18, 1989

NASA Technical Reports Server (NTRS)

Barrett, Eamon B. (Editor); Pearson, James J. (Editor)

1989-01-01

Image understanding concepts and models, image understanding systems and applications, advanced digital processors and software tools, and advanced man-machine interfaces are among the topics discussed. Particular papers are presented on such topics as neural networks for computer vision, object-based segmentation and color recognition in multispectral images, the application of image algebra to image measurement and feature extraction, and the integration of modeling and graphics to create an infrared signal processing test bed.

Space station: Cost and benefits

NASA Technical Reports Server (NTRS)

1983-01-01

Costs for developing, producing, operating, and supporting the initial space station, a 4 to 8 man space station, and a 4 to 24 man space station are estimated and compared. These costs include contractor hardware; space station assembly and logistics flight costs; and payload support elements. Transportation system options examined include orbiter modules; standard and extended duration STS fights; reusable spacebased perigee kick motor OTV; and upper stages. Space station service charges assessed include crew hours; energy requirements; payload support module storage; pressurized port usage; and OTV service facility. Graphs show costs for science missions, space processing research, small communication satellites; large GEO transportation; OVT launch costs; DOD payload costs, and user costs.

EELV Booster Assist Options for CEV

NASA Technical Reports Server (NTRS)

McNeal, Curtis, Jr.

2005-01-01

Medium lift EELVs may still play a role in manned space flight. To be considered for manned flight, medium lift EELVs must address the short comings in their current boost assist motors. Two options exist: redesign and requalify the solid rocket motors. Replace solid rocket motors (SRMs) with hybrid rocket motors. Hybrid rocket motors are an attractive alternative. They are safer than SRMs. The TRL's Lockheed Martin Small Launch Vehicle booster development substantially lowers the development risk, cost risk, and the schedule risk for developing hybrid boost assist for EELVs. Hybrid boosters testability offsets SRMs higher inherent reliability.Hybrid booster development and recurring costs are lower than SRMs. Performance gains are readily achieved.

The Application of the NASA Advanced Concepts Office, Launch Vehicle Team Design Process and Tools for Modeling Small Responsive Launch Vehicles

NASA Technical Reports Server (NTRS)

Threet, Grady E.; Waters, Eric D.; Creech, Dennis M.

2012-01-01

The Advanced Concepts Office (ACO) Launch Vehicle Team at the NASA Marshall Space Flight Center (MSFC) is recognized throughout NASA for launch vehicle conceptual definition and pre-phase A concept design evaluation. The Launch Vehicle Team has been instrumental in defining the vehicle trade space for many of NASA s high level launch system studies from the Exploration Systems Architecture Study (ESAS) through the Augustine Report, Constellation, and now Space Launch System (SLS). The Launch Vehicle Team s approach to rapid turn-around and comparative analysis of multiple launch vehicle architectures has played a large role in narrowing the design options for future vehicle development. Recently the Launch Vehicle Team has been developing versions of their vetted tools used on large launch vehicles and repackaged the process and capability to apply to smaller more responsive launch vehicles. Along this development path the LV Team has evaluated trajectory tools and assumptions against sounding rocket trajectories and air launch systems, begun altering subsystem mass estimating relationships to handle smaller vehicle components, and as an additional development driver, have begun an in-house small launch vehicle study. With the recent interest in small responsive launch systems and the known capability and response time of the ACO LV Team, ACO s launch vehicle assessment capability can be utilized to rapidly evaluate the vast and opportune trade space that small launch vehicles currently encompass. This would provide a great benefit to the customer in order to reduce that large trade space to a select few alternatives that should best fit the customer s payload needs.

Advanced transportation system studies technical area 2(TA-2): Heavy lift launch vehicle development. volume 1; Executive summary

NASA Technical Reports Server (NTRS)

McCurry, J.

1995-01-01

The purpose of the TA-2 contract was to provide advanced launch vehicle concept definition and analysis to assist NASA in the identification of future launch vehicle requirements. Contracted analysis activities included vehicle sizing and performance analysis, subsystem concept definition, propulsion subsystem definition (foreign and domestic), ground operations and facilities analysis, and life cycle cost estimation. This document is part of the final report for the TA-2 contract. The final report consists of three volumes: Volume 1 is the Executive Summary, Volume 2 is Technical Results, and Volume 3 is Program Cost Estimates. The document-at-hand, Volume 1, provides a summary description of the technical activities that were performed over the entire contract duration, covering three distinct launch vehicle definition activities: heavy-lift (300,000 pounds injected mass to low Earth orbit) launch vehicles for the First Lunar Outpost (FLO), medium-lift (50,000-80,000 pounds injected mass to low Earth orbit) launch vehicles, and single-stage-to-orbit (SSTO) launch vehicles (25,000 pounds injected mass to a Space Station orbit).

76 FR 72686 - 36(b)(1) Arms Sales Notification

Federal Register 2010, 2011, 2012, 2013, 2014

2011-11-25

... Electromagnetic Aircraft Launch System/Advanced Arresting Gear (EMALS/AAG). The EMALS long lead sub-assemblies... United Kingdom--Electromagnetic Aircraft Launch System Long Lead Sub- Assemblies The Government of the United Kingdom (UK) has requested the long lead sub-assemblies for the Electromagnetic Aircraft Launch...

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.

Atomic hydrogen as a launch vehicle propellant

NASA Technical Reports Server (NTRS)

Palaszewski, Bryan A.

1990-01-01

An analysis of several atomic hydrogen launch vehicles was conducted. A discussion of the facilities and the technologies that would be needed for these vehicles is also presented. The Gross Liftoff Weights (GLOW) for two systems were estimated; their specific impulses (I sub sp) were 750 and 1500 lb(sub f)/s/lb(sub m). The atomic hydrogen launch vehicles were also compared to the currently planned Advanced Launch System design concepts. Very significant GLOW reductions of 52 to 58 percent are possible over the Advanced Launch System designs. Applying atomic hydrogen propellants to upper stages was also considered. Very high I(sub sp) (greater than 750 lb(sub f)/s/lb(sub m)) is needed to enable a mass savings over advanced oxygen/hydrogen propulsion. Associated with the potential benefits of high I(sub sp) atomic hydrogen are several challenging problems. Very high magnetic fields are required to maintain the atomic hydrogen in a solid hydrogen matrix. The magnetic field strength was estimated to be 30 kilogauss (3 Tesla). Also the storage temperature of the propellant is 4 K. This very low temperature will require a large refrigeration facility for the launch vehicle. The design considerations for a very high recombination rate for the propellant are also discussed. A recombination rate of 210 cm/s is predicted for atomic hydrogen. This high recombination rate can produce very high acceleration for the launch vehicle. Unique insulation or segmentation to inhibit the propellant may be needed to reduce its recombination rate.

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Advanced information processing system for advanced launch system: Hardware technology survey and projections

NASA Technical Reports Server (NTRS)

Cole, Richard

1991-01-01

The major goals of this effort are as follows: (1) to examine technology insertion options to optimize Advanced Information Processing System (AIPS) performance in the Advanced Launch System (ALS) environment; (2) to examine the AIPS concepts to ensure that valuable new technologies are not excluded from the AIPS/ALS implementations; (3) to examine advanced microprocessors applicable to AIPS/ALS, (4) to examine radiation hardening technologies applicable to AIPS/ALS; (5) to reach conclusions on AIPS hardware building blocks implementation technologies; and (6) reach conclusions on appropriate architectural improvements. The hardware building blocks are the Fault-Tolerant Processor, the Input/Output Sequencers (IOS), and the Intercomputer Interface Sequencers (ICIS).

Space Launch System Advanced Development Office, FY 2013 Annual Report

NASA Technical Reports Server (NTRS)

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

2013-01-01

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 34 separate tasks were funded by ADO in FY 2013.

Recommended Screening Practices for Launch Collision Aviodance

NASA Technical Reports Server (NTRS)

Beaver, Brian A.; Hametz, Mark E.; Ollivierre, Jarmaine C.; Newman, Lauri K.; Hejduk, Matthew D.

2015-01-01

The objective of this document is to assess the value of launch collision avoidance (COLA) practices and provide recommendations regarding its implementation for NASA robotic missions. The scope of this effort is limited to launch COLA screens against catalog objects that are either spacecraft or debris. No modifications to manned safety COLA practices are considered in this effort. An assessment of the value of launch COLA can be broken down into two fundamental questions: 1) Does collision during launch represent a significant risk to either the payload being launched or the space environment? 2) Can launch collision mitigation be performed in a manner that provides meaningful risk reduction at an acceptable level of operational impact? While it has been possible to piece together partial answers to these questions for some time, the first attempt to comprehensively address them is documented in reference (a), Launch COLA Operations: an Examination of Data Products, Procedures, and Thresholds, Revision A. This report is the product of an extensive study that addressed fundamental technical questions surrounding launch collision avoidance analysis and practice. The results provided in reference (a) will be cited throughout this document as these two questions are addressed. The premise of this assessment is that in order to conclude that launch COLA is a value-added activity, the answer to both of these questions must be affirmative. A "no" answer to either of these questions points toward the conclusion that launch COLA provides little or no risk mitigation benefit. The remainder of this assessment will focus on addressing these two questions.

Launch Vehicle Design and Optimization Methods and Priority for the Advanced Engineering Environment

NASA Technical Reports Server (NTRS)

Rowell, Lawrence F.; Korte, John J.

2003-01-01

NASA's Advanced Engineering Environment (AEE) is a research and development program that will improve collaboration among design engineers for launch vehicle conceptual design and provide the infrastructure (methods and framework) necessary to enable that environment. In this paper, three major technical challenges facing the AEE program are identified, and three specific design problems are selected to demonstrate how advanced methods can improve current design activities. References are made to studies that demonstrate these design problems and methods, and these studies will provide the detailed information and check cases to support incorporation of these methods into the AEE. This paper provides background and terminology for discussing the launch vehicle conceptual design problem so that the diverse AEE user community can participate in prioritizing the AEE development effort.

Observation of rocket pollution with overhead sensors

NASA Astrophysics Data System (ADS)

Fisher, Annette

2011-12-01

The objective of this thesis is to study the dispersal of rocket pollution through remote sensing techniques. Substantial research with remote sensors has been dedicated to observation of volcanic plumes, particulate dispersion, and aircraft contrails with less emphasis on observing rocket launches and the effects on the surrounding environment. This research focuses on observation of rocket exhaust constituents, particularly carbon soot, alumina, and water vapor. The sensors utilized in this thesis have unique capabilities that provide measurements that are likely capable of detecting the rocket exhaust constituents. Methodology and analysis included choosing an appropriate launch vehicle with obtainable launch data and various booster combinations of liquid propellant only or a combination of liquid and solid propellant, prioritizing the data based on launch time versus sensor passing, processing the data, and applying known constituent properties to the data sets where key areas of work in this endeavor. Results of this work demonstrate a unique capability in monitoring man-made pollution and the extent the pollution can spread to surrounding areas.

Discovery: Under the Microscope at Kennedy Space Center

NASA Technical Reports Server (NTRS)

Howard, Philip M.

2013-01-01

The National Aeronautics & Space Administration (NASA) is known for discovery, exploration, and advancement of knowledge. Since the days of Leeuwenhoek, microscopy has been at the forefront of discovery and knowledge. No truer is that statement than today at Kennedy Space Center (KSC), where microscopy plays a major role in contamination identification and is an integral part of failure analysis. Space exploration involves flight hardware undergoing rigorous "visually clean" inspections at every step of processing. The unknown contaminants that are discovered on these inspections can directly impact the mission by decreasing performance of sensors and scientific detectors on spacecraft and satellites, acting as micrometeorites, damaging critical sealing surfaces, and causing hazards to the crew of manned missions. This talk will discuss how microscopy has played a major role in all aspects of space port operations at KSC. Case studies will highlight years of analysis at the Materials Science Division including facility and payload contamination for the Navigation Signal Timing and Ranging Global Positioning Satellites (NA VST AR GPS) missions, quality control monitoring of monomethyl hydrazine fuel procurement for launch vehicle operations, Shuttle Solids Rocket Booster (SRB) foam processing failure analysis, and Space Shuttle Main Engine Cut-off (ECO) flight sensor anomaly analysis. What I hope to share with my fellow microscopists is some of the excitement of microscopy and how its discoveries has led to hardware processing, that has helped enable the successful launch of vehicles and space flight missions here at Kennedy Space Center.

Space transfer vehicle concepts and requirements. Volume 4: Summary of special studies

NASA Technical Reports Server (NTRS)

1993-01-01

Our final report for Phase 1 addressed the future space transportation needs and requirements based on the current assets, at the time, and their evolution through technology/advanced development using a path and schedule that supported the world leadership role of the United States in a responsible and realistic financial forecast. Always, and foremost, the recommendations placed high values on the safety and success of missions both manned and unmanned through a total quality management philosophy at Martin Marietta. The second phase of the STV contract involved the use of Technical Directives (TD) to provide short-term support for specialized tasks as required by the COTR. Three of these tasks were performed in parallel with Phase 1. These tasks were the Liquid Acquisition Experiment (LACE), Liquid Reorientation Experiment (LIRE), and Expert System for Design, Operation, and Technology Studies (ESDOTS). The results of these TD's were reported in conjunction with the Phase 1 Final Report. Cost analysis of existing launch systems has demonstrated a need for a new upper stage that will increase America's competitiveness in the global launch services market. To provide a growth path of future exploration class STV's, near-term low-cost upper stages featuring modularity, portability, scalability, and evolvability must be developed. These recommendations define a program that: leverages ongoing activities to establish a new development environment, develop technologies that benefit the entire life cycle of a system, and result in a scalable hardware platform that provides a growth path to future upper stages.

KSC-99pp0875

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- NASA Administrator Daniel S. Goldin (right) addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex, with seating under an unused Saturn V rocket like those that powered the Apollo launches . This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

View of Apollo 15 space vehicle leaving VAB to Pad A, Launch Complex 39

NASA Image and Video Library

1971-05-11

S71-33786 (11 May 1971) --- The 363-feet tall Apollo (Spacecraft 112/Lunar Module 10/Saturn 510) space vehicle which leaves the Vehicle Assembly Building (VAB) to Pad A, Launch Complex 39, Kennedy Space Center (KSC). The Saturn V stack and its mobile launch tower are atop a huge crawler-transporter. Apollo 15 is scheduled as the fourth manned lunar landing mission by the National Aeronautics and Space Administration (NASA) and is scheduled to lift off on July 26, 1971. The crew men will be astronauts David R. Scott, commander; Alfred M. Worden, command module pilot; and James B. Irwin, lunar module pilot. While astronaut Scott and Irwin will descend in the Lunar Module (LM) to explore the moon, astronaut Worden will remain with the Command and Service Modules (CSM) in lunar orbit.

Saturn V Arrives at Launch Pad Complex 39

NASA Technical Reports Server (NTRS)

1969-01-01

The Saturn V launch vehicle (AS-506) carrying the Apollo 11 spacecraft, arrived at the launch pad complex 39 at the Kennedy Space Center (KSC) on May 20, 1969. On July 16, 1969, the 363 foot tall, 6,400,000 pound rocket, developed by the Marshall Space Flight Center (MSFC) under the direction of Werner von Braun, hurled the spacecraft into Earth parking orbit and then placed it on the trajectory to the moon for man's first lunar landing. Aboard the spacecraft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The crew safely splashed down into the Pacific Ocean on July 24, 1969. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

NASA Administrator Dan Goldin speaks at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

NASA Administrator Daniel S. Goldin (right) addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex, with seating under an unused Saturn V rocket like those that powered the Apollo launches . This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Saturn Apollo Program

NASA Image and Video Library

1969-07-27

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet recovery ship, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. The occupied MQF was unloaded from the U.S.S. Hornet in Pearl Harbor, Hawaii. In this photo, the facility is moved from the Hornet’s dock enroute to Hickam Field where it was loaded aboard an Air Force C-141 jet transport for the flight back to Ellington Air Force Base Texas, and then on to the MSC.

Quarantined Apollo 11 Astronauts Loaded Onto Trailer For Transport

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named 'Eagle'', carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet recovery ship, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home for 21 days. In this photo taken at Pearl Harbor, Hawaii, the quarantined housing facility is being lowered from the U.S.S. Hornet, onto a trailer for transport to Hickam Field. From there, it was loaded aboard an Air Force C-141 jet and flown back to Ellington Air Force Base Texas, and then on to the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas.

Apollo 11 Occupied Mobile Quarantine Facility (MQF) Moved For Transport

NASA Technical Reports Server (NTRS)

1969-01-01

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Marshall Space Flight Center (MSFC) developed Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard the space craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named 'Eagle'', carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet recovery ship, where they were quartered in a Mobile Quarantine Facility (MQF) which served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. The occupied MQF was unloaded from the U.S.S. Hornet in Pearl Harbor, Hawaii. In this photo, the facility is moved from the Hornet's dock enroute to Hickam Field where it was loaded aboard an Air Force C-141 jet transport for the flight back to Ellington Air Force Base Texas, and then on to the MSC.

Project Minerva: A low cost manned Mars mission based on indigenous propellant production

NASA Technical Reports Server (NTRS)

Beder, David; Bryan, Richard; Bui, Tuyen; Caviezel, Kelly; Cinnamon, Mark; Daggert, Todd; Folkers, Mike; Fornia, Mark; Hanks, Natasha; Hamilton, Steve

1992-01-01

Project Minerva is a low-cost manned Mars mission designed to deliver a crew of four to the Martian surface using only two sets of two launches from the Kennedy Space Center. Key concepts which make this mission realizable are the use of near-term technologies and in-situ propellant production, following the scenario originally proposed by R. Zubrin. The first set of launches delivers two unmanned payloads into low Earth orbit (LEO): the first payload consists of an Earth Return Vehicle (ERV), a propellant production plant, and a set of robotic vehicles; the second payload consists of the trans-Mars injection (TMI) upper stage. In LEO, the two payloads are docked and the configuration is injected into a Mars transfer orbit. The landing on Mars is performed with the aid of multiple aerobraking maneuvers. On the Martian surface, the propellant production plant uses a Sabatier/electrolysis type process to combine nine tons of hydrogen with carbon dioxide from the Martian atmosphere to produce over a hundred tons of liquid oxygen and liquid methane, which are later used as the propellants for the rover expeditions and the manned return journey of the ERV. The systems necessary for the flights to and from Mars, as well as those needed for the stay on Mars, are discussed. These systems include the transfer vehicle design, life support, guidance and communications, rovers and telepresence, power generation, and propellant manufacturing. Also included are the orbital mechanics, the scientific goals, and the estimated mission costs.

An overview of Korean astronaut’s space experiments

NASA Astrophysics Data System (ADS)

Lee, J. H.; Kim, Y. K.; Yi, S. Y.; Kim, K. S.; Kang, S. W.; Choi, G. H.; Sim, E. S.

2010-10-01

The paper presents an overview of the scientific space experiments in the Korean Astronaut Program (KAP) that were conducted on the International Space Station (ISS), beginning with launch of the Soyuz TMA-12 spacecraft with the first Korean astronaut and two Russian astronauts on April 8, 2008 and returning to Earth on April 19, 2008. During the 10 days aboard the ISS, the Korean astronaut successfully completed thirteen scientific experiments in biology, life science, material science, earth science, and system engineering, five educational space experiments, and three kinds of international collaboration experiments. These experiments were the first Korean manned space experiments and these missions were the first steps toward the manned space exploration by Korea. In this paper, we briefly discuss the descriptions, conduct, and results of the space experiments and discuss future plans. In addition, the lessons learned with respect to the performing of these manned space experiments on the ISS are presented.

Manned Venus Flyby

NASA Technical Reports Server (NTRS)

Feldman, M. S.; Ferrara, L. A.; Havenstein, P. L.; Volonte, J. E.; Whipple, P. H.

1967-01-01

This study is one of several being conducted at Bellcomm and in Manned Space Flight whose purpose is to give guidance to the Apollo Applications Program's technical objectives by focusing on a longer range goal. The assumed mission in this case is a three-man flyby of Venus launched in November, 1973 on a single standard Saturn V. The selected flight configuration includes a Command and Service Module similar in some respects to Apollo, an Environmental Support Module which occupies the adapter area and a spent S-IVB stage which is utilized for habitable volume and structural support of a solar cell electrical power system. The total injected weight, 106,775 lbs., is within the capability of a single Saturn V of the early 1970's. The study is focused on the selection of subsystem technologies appropriate to long duration flight. The conclusions are reported in terms of the technical characteristics to be achieved as part of the Apollo Applications Program's long duration objectives.

Integrated Vehicle Ground Vibration Testing in Support of Launch Vehicle Loads and Controls Analysis

NASA Technical Reports Server (NTRS)

Askins, Bruce R.; Davis, Susan R.; Salyer, Blaine H.; Tuma, Margaret L.

2008-01-01

All structural systems possess a basic set of physical characteristics unique to that system. These unique physical characteristics include items such as mass distribution and damping. When specified, they allow engineers to understand and predict how a structural system behaves under given loading conditions and different methods of control. These physical properties of launch vehicles may be predicted by analysis or measured by certain types of tests. Generally, these properties are predicted by analysis during the design phase of a launch vehicle and then verified by testing before the vehicle becomes operational. A ground vibration test (GVT) is intended to measure by test the fundamental dynamic characteristics of launch vehicles during various phases of flight. During the series of tests, properties such as natural frequencies, mode shapes, and transfer functions are measured directly. These data will then be used to calibrate loads and control systems analysis models for verifying analyses of the launch vehicle. NASA manned launch vehicles have undergone ground vibration testing leading to the development of successful launch vehicles. A GVT was not performed on the inaugural launch of the unmanned Delta III which was lost during launch. Subsequent analyses indicated had a GVT been performed, it would have identified instability issues avoiding loss of the vehicle. This discussion will address GVT planning, set-up, execution and analyses, for the Saturn and Shuttle programs, and will also focus on the current and on-going planning for the Ares I and V Integrated Vehicle Ground Vibration Test (IVGVT).

17. INTERIOR VIEW INSIDE BUNKER. MAN SEATED AT LEFT LOOKS ...

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

17. INTERIOR VIEW INSIDE BUNKER. MAN SEATED AT LEFT LOOKS AT OPENING TO CABLE CHASE, HIS HANDS ON MANUALLY-OPERATED PULLEY. INEL PHOTO NUMBER 65-6179, TAKEN NOVEMBER 10, 1965. - Idaho National Engineering Laboratory, Advanced Reentry Vehicle Fusing System, Scoville, Butte County, ID

Advanced transportation system studies. Technical area 2: Heavy lift launch vehicle development. Volume 2; Technical Results

NASA Technical Reports Server (NTRS)

1995-01-01

Sections 10 to 13 of the Advanced Transportation System Studies final report are included in this volume. Section 10 contains a copy of an executive summary that was prepared by Lockheed Space Operations Company (LSOC) to document their support to the TA-2 contract during the first-year period of performance of the contract, May 1992 through May 1993. LSOC participated on the TA-2 contract as part of the concurrent engineering launch system definition team, and provided outstanding heavy lift launch vehicle (HLLV) ground operations requirements and concept assessments for Lockheed Missiles and Space Company (LMSC) through an intercompany work transfer as well as providing specific HLLV ground operations assessments at the direction of NASA KSC through KSC funding that was routed to the TA-2 contract. Section 11 contains a copy of a vehicle-independent, launch system health management requirements assessment. The purpose of the assessment was to define both health management requirements and the associated interfaces between a generic advanced transportation system launch vehicle and all related elements of the entire transportation system, including the ground segment. Section 12 presents the major TA-2 presentations provided to summarize the significant results and conclusions that were developed over the course of the contract. Finally, Section 13 presents the design and assessment report on the first lunar outpost heavy lift launch vehicle.

NASA's Integrated Space Transportation Plan — 3 rd generation reusable launch vehicle technology update

NASA Astrophysics Data System (ADS)

Cook, Stephen; Hueter, Uwe

2003-08-01

NASA's Integrated Space Transportation Plan (ISTP) calls for investments in Space Shuttle safety upgrades, second generation Reusable Launch Vehicle (RLV) advanced development and third generation RLV and in-space research and technology. NASA's third generation launch systems are to be fully reusable and operation by 2025. The goals for third generation launch systems are to reduce cost by a factor of 100 and improve safety by a factor of 10,000 over current systems. The Advanced Space Transportation Program Office (ASTP) at NASA's Marshall Space Flight Center in Huntsville, AL has the agency lead to develop third generation space transportation technologies. The Hypersonics Investment Area, part of ASTP, is developing the third generation launch vehicle technologies in two main areas, propulsion and airframes. The program's major investment is in hypersonic airbreathing propulsion since it offers the greatest potential for meeting the third generation launch vehicles. The program will mature the technologies in three key propulsion areas, scramjets, rocket-based combined cycle and turbine-based combination cycle. Ground and flight propulsion tests are being planned for the propulsion technologies. Airframe technologies will be matured primarily through ground testing. This paper describes NASA's activities in hypersonics. Current programs, accomplishments, future plans and technologies that are being pursued by the Hypersonics Investment Area under the Advanced Space Transportation Program Office will be discussed.

Chronology of KSC and KSC related events for 1984

NASA Technical Reports Server (NTRS)

Nail, K., Jr.

1985-01-01

In his third State of the Union address, President Reagan told NASA to develop a permanent manned space station in 10 years. The President also ordered the Department of Transportation to help private firms launch rockets, thus introducing the commercialization of space. There were five space shuttle and six expendable vehicle launches in 1984. Materials were selected from a number of published sources. The document records KSC events of interest to historians and other researchers. Arrangement is by month; items are by date of the published sources. Actual date of the event may be indicated in parenthesis, when the article itself does not make that information explicit.

Developmental Testing of Electric Thrust Vector Control Systems for Manned Launch Vehicle Applications

NASA Technical Reports Server (NTRS)

Bates, Lisa B.; Young, David T.

2012-01-01

This paper describes recent developmental testing to verify the integration of a developmental electromechanical actuator (EMA) with high rate lithium ion batteries and a cross platform extensible controller. Testing was performed at the Thrust Vector Control Research, Development and Qualification Laboratory at the NASA George C. Marshall Space Flight Center. Electric Thrust Vector Control (ETVC) systems like the EMA may significantly reduce recurring launch costs and complexity compared to heritage systems. Electric actuator mechanisms and control requirements across dissimilar platforms are also discussed with a focus on the similarities leveraged and differences overcome by the cross platform extensible common controller architecture.

Feasibility of Space Disposal of Radioactive Nuclear Waste. 1: Executive Summary

NASA Technical Reports Server (NTRS)

1973-01-01

This NASA study, performed at the request of the AEC, concludes that transporting radioactive waste (primarily long-lived isotopes) into space is feasible. Tentative solutions are presented for technical problems involving safe packaging. Launch systems (existing and planned), trajectories, potential hazards, and various destinations were evaluated. Solar system escape is possible and would have the advantage of ultimate removal of the radioactive waste from man's environment. Transportation costs would be low (comparable to less than a 5 percent increase in the cost of electricity) even though more than 100 space shuttle launches per year would be required by the year 2000.

KSC-04pd1226

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operator Rick Wetherington checks out one of the recently acquired Contraves-Goerz Kineto Tracking Mounts (KTM). There are 10 KTMs certified for use on the Eastern Range. The KTM, which is trailer-mounted with an electric drive tracking mount, includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff.

KSC-04pd1220

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operator Kenny Allen works on the recently acquired Contraves-Goerz Kineto Tracking Mount (KTM). Trailer-mounted with a center console/seat and electric drive tracking mount, the KTM includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff. There are 10 KTMs certified for use on the Eastern Range.

KSC-04pd1219

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operator Kenny Allen works on the recently acquired Contraves-Goerz Kineto Tracking Mount (KTM). Trailer-mounted with a center console/seat and electric drive tracking mount, the KTM includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff. There are 10 KTMs certified for use on the Eastern Range.

KSC-04pd1227

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operator Kenny Allen checks out one of the recently acquired Contraves-Goerz Kineto Tracking Mounts (KTM). There are 10 KTMs certified for use on the Eastern Range. The KTM, which is trailer-mounted with an electric drive tracking mount, includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff.

KSC-99pp0844

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- In the Apollo/Saturn V Center, Lisa Malone (left), chief of KSC's Media Services branch, laughs at a humorous comment along with former Apollo astronauts Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch to the moon; Gene Cernan, who flew on Apollo 10 and 17; and Walt Cunningham, who flew on Apollo 7. The four met with the media before an anniversary banquet celebrating the accomplishments of the Apollo program team. This is the 30th anniversary of the launch and moon landing, July 16 and July 20, 1969. Neil Armstrong was the first man to set foot on the moon

Vehicle for Space Transfer and Recovery (VSTAR), volume 1

NASA Technical Reports Server (NTRS)

1988-01-01

The Vehicle Space Transfer and Recovery (VSTAR) system is designed as a manned orbital transfer vehicle (MOTV) with the primary mission of Satellite Launch and Repair (SLR). VSTAR will provide for economic use of high altitude spaceflight for both the public and private sector. VSTAR components will be built and tested using earth based facilities. These components will then be launched using the space shuttle, into low earth orbit (LEO) where it will be constructed on a U.S. built space station. Once in LEO the vehicle components will be assembled in modules which can then be arranged in various configurations to perform the required missions.

s27-s-071

NASA Image and Video Library

2009-06-30

STS027-S-071 (2 Dec. 1988) --- The Space Shuttle Atlantis and its five-man crew of astronauts are launched from Kennedy Space Center?s Pad 39B at 9:30 a.m. (EST), Dec. 2, 1988. Onboard the Department of Defense?dedicated mission are astronauts Robert L. Gibson, Guy S. Gardner, Jerry L. Ross, Richard M. (Mike) Mullane and Williams M. Shepherd.

s27-s-003

NASA Image and Video Library

2009-06-30

STS027-S-003 (2 Dec. 1988) --- The Space Shuttle Atlantis and its five-man crew of astronauts are launched from Kennedy Space Center?s Pad 39B at 9:30 a.m. (EST), Dec. 2, 1988. Onboard the Department of Defense ? dedicated mission are astronauts Robert L. Gibson, Guy S. Gardner, Jerry L. Ross, Richard M. (Mike) Mullane and Williams M. Shepherd.

Mercury Project

NASA Image and Video Library

1962-02-20

Astronaut John Glenn enters the Mercury spacecraft, Friendship 7, prior to the launch of MA-6 on February 20, 1961 and became the first American who orbited the Earth. The MA-6 mission was the first manned orbital flight boosted by the Mercury-Atlas vehicle, a modified Atlas ICBM (Intercontinental Ballistic Missile), lasted for five hours, and orbited the Earth three times.

Astronaut Curtis Brown on flight deck mockup during training

NASA Technical Reports Server (NTRS)

1994-01-01

Astronaut Curtis L. Brown, STS-66 pilot, mans the pilot's station during a rehearsal of procedures to be followed during the launch and entry phases of their scheduled November 1994 flight. This rehearsal, held in the crew compartment trainer (CCT) of JSC's Shuttle mockup and integration laboratory, was followed by a training session on emergency egress procedures.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members prepare the Advanced Base Line Imager, the primary optical instrument, for installation on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members install the Advanced Base Line Imager, the primary optical instrument, on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

The Advanced Base Line Imager, the primary optical instrument, has been installed on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

Advanced missions safety. Volume 3: Appendices. Part 1: Space shuttle rescue capability

NASA Technical Reports Server (NTRS)

1972-01-01

The space shuttle rescue capability is analyzed as a part of the advanced mission safety study. The subjects discussed are: (1) mission evaluation, (2) shuttle configurations and performance, (3) performance of shuttle-launched tug system, (4) multiple pass grazing reentry from lunar orbit, (5) ground launched ascent and rendezvous time, (6) cost estimates, and (7) parallel-burn space shuttle configuration.

The FLECS expandable module concept for future space missions and an overall description on the material validation

NASA Astrophysics Data System (ADS)

Mileti, Sandro; Guarrera, Giuseppe; Marchetti, Mario; Ferrari, Giorgio; Nebiolo, Marco; Augello, Gerlando; Bitetti, Grazia; Carnà, Emiliano; Marranzini, Andrea; Mazza, Fabio

2006-07-01

The future space exploration missions aim to reduce the costs associated with design, fabrication and launch for ISS, Moon and Mars modules, while simultaneously increasing the useful volume. Flexible and inflatable structures offer many advantages over conventional structures for space applications. Principal among the advantages is the ability to package these structures into small volumes for launch. Design maturation and the development of advanced materials and fabrication processes have made the concept of an inflatable module achievable in the near future. The Multipurpose Expandable Module (FLECS) Project sponsored by ASI (Italian Space Agency) whose prime contractor is Alcatel Alenia Space Italia, links the conventional and traditional technology of modules with the innovative solutions of inflatable technology. This project emphasizes on demonstrating the capability in using inflatable technology on space structures aiming to substitute the conventional modules in future manned missions. FLECS has been designed using advanced textiles and films in order to guarantee the structural reliability necessary for the deployment and packaging configurations. A non-linear structural analysis has been conducted using several numerical codes that simulate the deployed structural characteristics achieving also the damping resistance during the packaging. All the materials used for the flexible parts have been selected through a series of mechanical tests in order to validate the more appropriate ones for the mission. The multi-layer pneumatic retention bladder and the intermediate restraint layer are composed of polymer sheets, ortho-fabrics and elastomers like polyurethanes. The External protection shield is configured using several layers of impact absorption materials and also several layers of space environment (UV, IR, atomic oxygen) protection materials such as Kapton, Mylar and Nextel. The validation of the fabrics, the films and the final prototype assembly are tested in the Space Environment Simulator (SAS), located in the SASLab laboratory of the Aerospace Engineering Department of the “La Sapienza” University of Rome.

Kennedy Space Center: Apollo to Multi-User Spaceport

NASA Technical Reports Server (NTRS)

Weber, Philip J.; Kanner, Howard S.

2017-01-01

NASA Kennedy Space Center (KSC) was established as the gateway to exploring beyond earth. Since the establishment of KSC in December 1963, the Center has been critical in the execution of the United States of Americas bold mission to send astronauts beyond the grasp of the terra firma. On May 25, 1961, a few weeks after a Soviet cosmonaut became the first person to fly in space, President John F. Kennedy laid out the ambitious goal of landing a man on the moon and returning him safely to the Earth by the end of the decade. The resultant Apollo program was massive endeavor, driven by the Cold War Space Race, and supported with a robust budget. The Apollo program consisted of 18 launches from newly developed infrastructure, including 12 manned missions and six lunar landings, ending with Apollo 17 that launched on December 7, 1972. Continuing to use this infrastructure, the Skylab program launched four missions. During the Skylab program, KSC infrastructure was redesigned to meet the needs of the Space Shuttle program, which launched its first vehicle (STS-1) on April 12, 1981. The Space Shuttle required significant modifications to the Apollo launch pads and assembly facilities, as well as new infrastructure, such as Orbiter and Payload Processing Facilities, as well as the Shuttle Landing Facility. The Space Shuttle was a workhorse that supported many satellite deployments, but was key for the construction and maintenance of the International Space Station, which required additional facilities at KSC to support processing of the flight hardware. After reaching the new Millennium, United States policymakers searched for new ways to reduce the cost of space exploration. The Constellation Program was initiated in 2005 with a goal of providing a crewed lunar landing with a much smaller budget. The very successful Space Shuttle made its last launch on July 8, 2011, after 135 missions. In the subsequent years, KSC continues to evolve, and this paper will address past and future efforts of the transformation of the KSC Apollo and Space Shuttle heritage infrastructure into a more versatile, multi-user spaceport. The paper will also discuss the US Congressional and NASA initiatives for developing and supporting multiple commercial partners, while simultaneously supporting NASAs human exploration initiative, consisting of Space Launch System (SLS), Orion spacecraft and associated ground launch systems. In addition, the paper explains the approach with examples for NASA KSC to leverage new technologies and innovative capabilities developed to reduce the cost to individual users.

The effect of interplanetary trajectory options on a manned Mars aerobrake configuration

NASA Technical Reports Server (NTRS)

Braun, Robert D.; Powell, Richard W.; Hartung, Lin C.

1990-01-01

Manned Mars missions originating in low Earth orbit (LEO) in the time frame 2010 to 2025 were analyzed to identify preferred mission opportunities and their associated vehicle and trajectory characteristics. Interplanetary and Mars atmospheric trajectory options were examined under the constraints of an initial manned exploration scenario. Two chemically propelled vehicle options were considered: (1) an all propulsive configuration, and (2) a configuration which employs aerobraking at Earth and Mars with low lift/drag (L/D) shapes. Both the interplanetary trajectory options as well as the Mars atmospheric passage are addressed to provide a coupled trajectory simulation. Direct and Venus swingby interplanetary transfers with a 60 day Mars stopover are considered. The range and variation in both Earth and Mars entry velocity are also defined. Two promising mission strategies emerged from the study: (1) a 1.0 to 2.0 year Venus swingby mission, and (2) a 2.0 to 2.5 year direct mission. Through careful trajectory selection, 11 mission opportunities are identified in which the Mars entry velocity is between 6 and 10 km/sec and Earth entry velocity ranges from 11.5 to 12.5 km/sec. Simulation of the Earth return aerobraking maneuver is not performed. It is shown that a low L/D configuration is not feasible for Mars aerobraking without substantial improvements in the interplanetary navigation system. However, even with an advanced navigation system, entry corridor and aerothermal requirements restrict the number of potential mission opportunities. It is also shown that for a large blunt Mars aerobrake configuration, the effects of radiative heating can be significant at entry velocities as low as 6.2 km/sec and will grow to dominate the aerothermal environment at entry velocities above 8.5 km/sec. Despite the additional system complexity associated with an aerobraking vehicle, the use of aerobraking was shown to significantly lower the required initial LEO weight. In comparison with an all propulsive mission, savings between 19 and 59 percent were obtained depending upon launch date.

EMERGING MOLECULAR COMPUTATIONAL APPROACHES FOR CROSS-SPECIES EXTRAPOLATIONS: A WORKSHOP SUMMARY

EPA Science Inventory

Advances in molecular technology have led to the elucidation of full genomic sequences of several multicellular organisms, ranging from nematodes to man. The related molecular field of proteomics and metabolomics are now beginning to advance rapidly as well. In addition, advances...

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.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members assist as a crane lifts the Advanced Base Line Imager, the primary optical instrument, for installation on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

GOES-R Advanced Base Line Imager Installation

NASA Image and Video Library

2016-08-30

Team members assist as a crane moves the Advanced Base Line Imager, the primary optical instruments, for installation on the Geostationary Operational Environmental Satellite (GOES-R) inside the Astrotech payload processing facility in Titusville, Florida near NASA’s Kennedy Space Center. GOES-R will be the first satellite in a series of next-generation NOAA GOES Satellites. The spacecraft is to launch aboard a United Launch Alliance Atlas V rocket in November.

Apollo 8 Mission Report

NASA Technical Reports Server (NTRS)

1969-01-01

Postflight analysis of Apollo 8 mission. Apollo 8 was the second manned flight in the program and the first manned lunar orbit mission. The crew were Frank Borman, Commander; James A. Lovell, Command Module Pilot; and William A. Anders, Lunar Module Pilot. The Apollo 8 space vehicle was launched on time from Kennedy Space Center, Florida, at 7:51:00 AM, EST, on December 21, 1968. Following a nominal boost phase, the spacecraft and S-IVB combination was inserted - into a parking orbit of 98 by 103 nautical miles. After a post-insertion checkout of spacecraft systems, the 319-second translunar injection maneuver was initiated at 2:50:37 by reignition of the S-IVB engine.

Skylab (SL)-3 Crew - KSC

NASA Image and Video Library

2006-03-21

S73-31800 (28 July 1973) --- The three crewmen of the second manned Skylab mission (Skylab 3) participate in prelaunch suiting up activities in the Manned Spacecraft Operations Building at the Kennedy Space Center on the morning of the Skylab 3 launch. They are (from foreground) astronaut Alan L. Bean, commander; scientist-astronaut Owen K. Garriott, science pilot; and astronaut Jack R. Lousma, pilot. Dr. Donald K. Slayton (left foreground), Director of Flight Crew Operations, Johnson Space Center, monitors the prelaunch activities. Skylab 3 lifted off at 7:11 a.m. (EDT), Saturday, July 28, 1973. The three astronauts were scheduled to spend 59 days at the Skylab space station in Earth orbit. Photo credit: NASA

Structural Analysis of Lightning Protection System for New Launch Vehicle

NASA Technical Reports Server (NTRS)

Cope, Anne; Moore, Steve; Pruss, Richard

2008-01-01

This project includes the design and specification of a lightning protection system for Launch Complex 39 B (LC39B) at Kennedy Space Center, FL in support of the Constellation Program. The purpose of the lightning protection system is to protect the Crew Launch Vehicle (CLV) or Cargo Launch Vehicle (CaLV) and associated launch equipment from direct lightning strikes during launch processing and other activities prior to flight. The design includes a three-tower, overhead catenary wire system to protect the vehicle and equipment on LC39B as described in the study that preceded this design effort: KSC-DX-8234 "Study: Construct Lightning Protection System LC3 9B". The study was a collaborative effort between Reynolds, Smith, and Hills (RS&H) and ASRC Aerospace (ASRC), where ASRC was responsible for the theoretical design and risk analysis of the lightning protection system and RS&H was responsible for the development of the civil and structural components; the mechanical systems; the electrical and grounding systems; and the siting of the lightning protection system. The study determined that a triangular network of overhead catenary cables and down conductors supported by three triangular free-standing towers approximately 594 ft tall (each equipped with a man lift, ladder, electrical systems, and communications systems) would provide a level of lightning protection for the Constellation Program CLV and CaLV on Launch Pad 39B that exceeds the design requirements.

Advanced Information Processing System (AIPS)-based fault tolerant avionics architecture for launch vehicles

NASA Technical Reports Server (NTRS)

Lala, Jaynarayan H.; Harper, Richard E.; Jaskowiak, Kenneth R.; Rosch, Gene; Alger, Linda S.; Schor, Andrei L.

1990-01-01

An avionics architecture for the advanced launch system (ALS) that uses validated hardware and software building blocks developed under the advanced information processing system program is presented. The AIPS for ALS architecture defined is preliminary, and reliability requirements can be met by the AIPS hardware and software building blocks that are built using the state-of-the-art technology available in the 1992-93 time frame. The level of detail in the architecture definition reflects the level of detail available in the ALS requirements. As the avionics requirements are refined, the architecture can also be refined and defined in greater detail with the help of analysis and simulation tools. A useful methodology is demonstrated for investigating the impact of the avionics suite to the recurring cost of the ALS. It is shown that allowing the vehicle to launch with selected detected failures can potentially reduce the recurring launch costs. A comparative analysis shows that validated fault-tolerant avionics built out of Class B parts can result in lower life-cycle-cost in comparison to simplex avionics built out of Class S parts or other redundant architectures.

Man/computer communication in a space environment

NASA Technical Reports Server (NTRS)

Hodges, B. C.; Montoya, G.

1973-01-01

The present work reports on a study of the technology required to advance the state of the art in man/machine communications. The study involved the development and demonstration of both hardware and software to effectively implement man/computer interactive channels of communication. While tactile and visual man/computer communications equipment are standard methods of interaction with machines, man's speech is a natural media for inquiry and control. As part of this study, a word recognition unit was developed capable of recognizing a minimum of one hundred different words or sentences in any one of the currently used conversational languages. The study has proven that efficiency in communication between man and computer can be achieved when the vocabulary to be used is structured in a manner compatible with the rigid communication requirements of the machine while at the same time responsive to the informational needs of the man.

Space Fission Propulsion System Development Status

NASA Technical Reports Server (NTRS)

Houts, Mike; VanDyke, Melissa; Godfroy, Tom; Pedersen, Kevin; Martin, James; Dickens, Ricky; Williams, Eric; Harper, Roger; Salvail, Pat; Hrbud, Ivana;

Structural Concepts and Materials for Lunar Exploration Habitats

NASA Technical Reports Server (NTRS)

Belvin, W. Keith; Watson, Judith J.; Singhal, Surendra N.

2006-01-01

A new project within the Exploration Systems Mission Directorate s Technology Development Program at NASA involves development of lightweight structures and low temperature mechanisms for Lunar and Mars missions. The Structures and Mechanisms project is to develop advanced structure technology for the primary structure of various pressurized elements needed to implement the Vision for Space Exploration. The goals are to significantly enhance structural systems for man-rated pressurized structures by 1) lowering mass and/or improving efficient volume for reduced launch costs, 2) improving performance to reduce risk and extend life, and 3) improving manufacturing and processing to reduce costs. The targeted application of the technology is to provide for the primary structure of the pressurized elements of the lunar lander for both sortie and outpost missions, and surface habitats for the outpost missions. The paper presents concepts for habitats that support six month (and longer) lunar outpost missions. Both rigid and flexible habitat wall systems are discussed. The challenges of achieving a multi-functional habitat that provides micro-meteoroid, radiation, and thermal protection for explorers are identified.

The Next Great Ship: NASA's Space Launch System

NASA Technical Reports Server (NTRS)

May, Todd A.

2013-01-01

Topics covered include: Most Capable U.S. Launch Vehicle; Liquid engines Progress; Boosters Progress; Stages and Avionics Progress; Systems Engineering and Integration Progress; Spacecraft and Payload Integration Progress; Advanced Development Progress.

Reliability and Crew Safety Assessment for a Solid Rocket Booster/J-2S Launcher

NASA Astrophysics Data System (ADS)

Fragola, Joseph; Baum, J. D.; Sauvageau, Don; Horowitz, Scott J.

2005-12-01

NASA's Exploration Mission Directorate is currently developing plans to carry out the President's Vision for Space Exploration. This plan includes retiring the Space Shuttle by 2010 and developing the Crew Exploration Vehicle (CEV) to transport astronauts to/from Low Earth Orbit (LEO). There are several alternatives to launch the CEV, including Evolved Expendable Launch Vehicles (EELVs) and launch vehicles derived from new and existing propulsion elements. In May, 2003 the astronaut office made clear its position on the need and feasibility of improving crew safety for future NASA manned missions indicating their "consensus that an order of magnitude reduction in the risk of human life during ascent, compared to the Space Shuttle, is both achievable with current technology and consistent with NASA's focus on steadily improving rocket reliability". The astronaut office set a goal for the Probability of Loss of Crew (PLOC) to be better than 1 in 1,000. This paper documents the evolution of a launch vehicle deign to meet the needs for launching the crew aboard a CEV. The process implemented and the results obtained from, a top-down evaluation performed on the proposed design are presented.

Development of a Refined Space Vehicle Rollout Forcing Function

NASA Technical Reports Server (NTRS)

James, George; Tucker, Jon-Michael; Valle, Gerard; Grady, Robert; Schliesing, John; Fahling, James; Emory, Benjamin; Armand, Sasan

2016-01-01

For several decades, American manned spaceflight vehicles and the associated launch platforms have been transported from final assembly to the launch pad via a pre-launch phase called rollout. The rollout environment is rich with forced harmonics and higher order effects can be used for extracting structural dynamics information. To enable this utilization, processing tools are needed to move from measured and analytical data to dynamic metrics such as transfer functions, mode shapes, modal frequencies, and damping. This paper covers the range of systems and tests that are available to estimate rollout forcing functions for the Space Launch System (SLS). The specific information covered in this paper includes: the different definitions of rollout forcing functions; the operational and developmental data sets that are available; the suite of analytical processes that are currently in-place or in-development; and the plans and future work underway to solve two immediate problems related to rollout forcing functions. Problem 1 involves estimating enforced accelerations to drive finite element models for developing design requirements for the SLS class of launch vehicles. Problem 2 involves processing rollout measured data in near real time to understand structural dynamics properties of a specific vehicle and the class to which it belongs.

Non-Axisymmetric Inflatable Pressure Structure (NAIPS) Concept that Enables Mass Efficient Packageable Pressure Vessels with Sealable Openings

NASA Technical Reports Server (NTRS)

Doggett, William R.; Jones, Thomas C.; Kenner, Winfred S.; Moore, David F.; Watson, Judith J.; Warren, Jerry E.; Makino, Alberto; Yount, Bryan; Selig, Molly; Shariff, Khadijah;

Trial by Fire

NASA Technical Reports Server (NTRS)

Covault, Craig

2005-01-01

Boeing is preparing a range of Delta IV Heavy launcher options for NASA Crew Exploration Vehicle (CEV) and unmanned cargo transportation architectures to the Moon and Mars, now that the massive new rocket has been flight tested. The December 21 launch of the 232-ft. vehicle on 2 million lb. thrust marked the largest all-liquid expendable booster flown since the last Saturn V in 1973. A second Delta IV Heavy mission is scheduled for this summer carrying a U.S. Air Force missile warning satellite. The first launch carried a dummy payload. Boeing wants NASA to consider the Delta IV Heavy for manned CEV missions, but is also pushing the Heavy for unmanned exploration launch roles. One Delta IV Medium version could also be a CEV player. Boeing says even modest upgrades could double the Delta Heavy's Earth orbit capability to more than 50 metric tons, including being able to fire up to 20 metric tons on escape trajectories to Mars.

A Quantitative Reliability, Maintainability and Supportability Approach for NASA's Second Generation Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Safie, Fayssal M.; Daniel, Charles; Kalia, Prince; Smith, Charles A. (Technical Monitor)

2002-01-01

The United States National Aeronautics and Space Administration (NASA) is in the midst of a 10-year Second Generation Reusable Launch Vehicle (RLV) program to improve its space transportation capabilities for both cargo and crewed missions. The objectives of the program are to: significantly increase safety and reliability, reduce the cost of accessing low-earth orbit, attempt to leverage commercial launch capabilities, and provide a growth path for manned space exploration. The safety, reliability and life cycle cost of the next generation vehicles are major concerns, and NASA aims to achieve orders of magnitude improvement in these areas. To get these significant improvements, requires a rigorous process that addresses Reliability, Maintainability and Supportability (RMS) and safety through all the phases of the life cycle of the program. This paper discusses the RMS process being implemented for the Second Generation RLV program.

Design for Reliability and Safety Approach for the New NASA Launch Vehicle

NASA Technical Reports Server (NTRS)

Safie, Fayssal M.; Weldon, Danny M.

2007-01-01

The United States National Aeronautics and Space Administration (NASA) is in the midst of a space exploration program intended for sending crew and cargo to the international Space Station (ISS), to the moon, and beyond. This program is called Constellation. As part of the Constellation program, NASA is developing new launch vehicles aimed at significantly increase safety and reliability, reduce the cost of accessing space, and provide a growth path for manned space exploration. Achieving these goals requires a rigorous process that addresses reliability, safety, and cost upfront and throughout all the phases of the life cycle of the program. This paper discusses the "Design for Reliability and Safety" approach for the NASA new launch vehicles, the ARES I and ARES V. Specifically, the paper addresses the use of an integrated probabilistic functional analysis to support the design analysis cycle and a probabilistic risk assessment (PRA) to support the preliminary design and beyond.

Application of Probabilistic Risk Assessment (PRA) During Conceptual Design for the NASA Orbital Space Plane (OSP)

NASA Technical Reports Server (NTRS)

Rogers, James H.; Safie, Fayssal M.; Stott, James E.; Lo, Yunnhon

2004-01-01

In order to meet the space transportation needs for a new century, America's National Aeronautics and Space Administration (NASA) has implemented an Integrated Space Transportation Plan to produce safe, economical, and reliable access to space. One near term objective of this initiative is the design and development of a next-generation vehicle and launch system that will transport crew and cargo to and from the International Space Station (ISS), the Orbital Space Plane (OSP). The OSP system is composed of a manned launch vehicle by an existing Evolved Expendable Launch Vehicle (EELV). The OSP will provide emergency crew rescue from the ISS by 2008, and provide crew and limited cargo transfer to and from the ISS by 2012. A key requirement is for the OSP to be safer and more reliable than the Soyuz and Space Shuttle, which currently provide these capabilities.

Structural design, analysis, and modal testing of the petite amateur navy satellite (PANSAT)

NASA Astrophysics Data System (ADS)

Sakoda, Daniel J.

1992-09-01

The Naval Postgraduate School's (NPS) Space Systems Academic Group is developing the Petite Amateur Navy Satellite (PANSAT), a small satellite for digital store-and-forward communication in the amateur frequency band. PANSAT is intended to be a payload of opportunity amendable to a number of launch vehicles. The Shuttle Small Self-Contained Payload (SSCP) program was chosen as a design baseline because of its high margins of safety as a manned system. The PANSAT structure design is presented for the launch requirements of a Shuttle SSCP. A finite element model was developed and studied for the design loads of a SSCP. The results showed the structure to be very robust and likely to accommodate the requirements of other launch vehicles. The finite element analysis was verified by model testing, correlating the fundamental mode of the finite element model with that of an engineering test structure.

Saturn Apollo Program

NASA Image and Video Library

1969-07-16

At the press site, thousands of news reporters from the world over watched, taking many pictures, as the Saturn V launch vehicle (AS-506) lifted off to start Apollo 11 on its historic mission to land on the Moon. The total number of news people officially registered to cover the launch was 3,497. The craft lifted off from launch pad 39 at Kennedy Space Flight Center (KSC) on July 16, 1969. A three man crew included astronauts Neil A. Armstrong, commander; Michael Collins, Command Module(CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The mission finalized with splashdown into the Pacific Ocean on July 24, 1969. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished. The Saturn V was developed by the Marshall Space Flight Center (MSFC) under the direction of Werher von Braun.

NASA Medical Response to Human Spacecraft Accidents

NASA Technical Reports Server (NTRS)

Patlach, Robert

2010-01-01

Manned space flight is risky business. Accidents have occurred and may occur in the future. NASA's manned space flight programs, with all their successes, have had three fatal accidents, one at the launch pad and two in flight. The Apollo fire and the Challenger and Columbia accidents resulted in a loss of seventeen crewmembers. Russia's manned space flight programs have had three fatal accidents, one ground-based and two in flight. These accidents resulted in the loss of five crewmembers. Additionally, manned spacecraft have encountered numerous close calls with potential for disaster. The NASA Johnson Space Center Flight Safety Office has documented more than 70 spacecraft incidents, many of which could have become serious accidents. At the Johnson Space Center (JSC), medical contingency personnel are assigned to a Mishap Investigation Team. The team deploys to the accident site to gather and preserve evidence for the Accident Investigation Board. The JSC Medical Operations Branch has developed a flight surgeon accident response training class to capture the lessons learned from the Columbia accident. This presentation will address the NASA Mishap Investigation Team's medical objectives, planned response, and potential issues that could arise subsequent to a manned spacecraft accident. Educational Objectives are to understand the medical objectives and issues confronting the Mishap Investigation Team medical personnel subsequent to a human space flight accident.

Astronauts Grissom and Young in Gemini Mission Simulator

NASA Image and Video Library

1964-05-22

S64-25295 (March 1964) --- Astronauts Virgil I. (Gus) Grissom (right) and John W. Young, prime crew for the first manned Gemini mission (GT-3), are shown inside a Gemini mission simulator at McDonnell Aircraft Corp., St. Louis, MO. The simulator will provide Gemini astronauts and ground crews with realistic mission simulation during intensive training prior to actual launch.

Astronaut John Glenn Enters Friendship 7

NASA Technical Reports Server (NTRS)

1962-01-01

Astronaut John Glenn enters the Mercury spacecraft, Friendship 7, prior to the launch of MA-6 on February 20, 1961 and became the first American who orbited the Earth. The MA-6 mission was the first manned orbital flight boosted by the Mercury-Atlas vehicle, a modified Atlas ICBM (Intercontinental Ballistic Missile), lasted for five hours, and orbited the Earth three times.

Man-rating of a launch vehicle

NASA Astrophysics Data System (ADS)

Soeffker, D.

Analysis techniques for hazard identification, classification, and control, developed for Spacelab, are presented. Hazards were classified as catastrophic (leading to crew or vehicle loss) critical (could lead to serious injury or damage) and controlled (counteracted by design). All nonmetallic materials were rated for flammability in oxygen enriched atmospheres, toxic offgassing, and odor. Any element with less than 200 mission capability was rated life limited.

The 1994 NASA/USRA/ADP Design Projects

NASA Technical Reports Server (NTRS)

Cruse, Thomas; Richardson, Joseph; Tryon, Robert

1994-01-01

The NASA/USRA/ADP Design Projects from Vanderbilt University, Department of Mechanical Engineering (1994) are enclosed in this final report. Design projects include: (1) Protein Crystal Growth, both facilities and methodology; (2) ACES Deployable Space Boom; (3) Hybrid Launch System designs for both manned and unmanned systems; (4) LH2 Fuel Tank design (SSTO); (5) SSTO design; and (6) Pressure Tank Feed System design.

(GT-6 PRIME CREW((PREFLIGHT ACTIVITY) - ASTRONAUT THOMAS P. STAFFORD - MISC.

NASA Image and Video Library

1965-12-12

S65-59977 (15 Dec. 1965) --- Astronauts Thomas P. Stafford (foreground), Gemini-6 prime crew pilot; and Alan B. Shepard Jr., chief, Astronaut Office, Manned Spacecraft Center, look over a Gemini mission chart in the suiting trailer at Launch Complex 16 during the Gemini-6 prelaunch countdown at Cape Kennedy, Florida. Photo credit: NASA or National Aeronautics and Space Administration

Searchlights Illuminate Apollo 8 on Pad 39-A

NASA Technical Reports Server (NTRS)

1968-01-01

Searchlights penetrate the darkness surrounding Apollo 8 on Pad 39-A at Kennedy Space Center. This mission was the first manned flight using the Saturn V. The towering 363-foot Saturn V was a multi-stage, multi-engine launch vehicle standing taller than the Statue of Liberty. Altogether, the Saturn V engines produced as much power as 85 Hoover Dams.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

A Diver Operator Plug (DOP) is being pulled down into the ocean by a newly designed one-man submarine known as DeepWorker 2000. The activity is part of an operation to attach the plug to a mockup of a solid rocket booster nozzle. DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

After a successful dive, the one-man submarine known as DeepWorker 2000 is lifted from Atlantic waters near Cape Canaveral, Fla., onto the deck of the Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

At left, a manipulator arm on a one-man submarine demonstrates its ability to cut tangled parachute riser lines and place a Diver Operator Plug (top right) inside a mock solid rocket booster nozzle (center). Known as DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

n/a

NASA Image and Video Library

1969-07-25

The Apollo 11 mission, the first manned lunar mission, launched aboard the Saturn V launch vehicle from the Kennedy Space Center, Florida on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins, remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. Armstrong was the first human to ever stand on the lunar surface, followed by Edwin (Buzz) Aldrin. The surface exploration was concluded in 2½ hours. Once the crew collected 47 pounds of lunar surface material for analysis back on Earth, the LM redocked with the CM for the crew’s return to Earth. Following splash down in the Pacific Ocean, Navy para-rescue men recovered the capsule housing the 3-man crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF). Astronaut Collins took this snapshot of astronauts Armstrong (center) and Aldrin inside of the MQF.

Saturn Apollo Program

NASA Image and Video Library

1969-07-20

This is a detailed view of the back side of Moon in the vicinity of Crater No. 308 taken during the Apollo 11 mission. Apollo 11, the first manned lunar mission, launched from The Kennedy Space Center, Florida via a Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. The Saturn V vehicle was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun. The 3-man crew aboard the flight consisted of Neil A. Armstrong, commander; Michael Collins, Command Module pilot; and Edwin E. Aldrin Jr., Lunar Module pilot. The Lunar Module (LM), named “Eagle, carrying astronauts Neil Armstrong and Edwin Aldrin, was the first crewed vehicle to land on the Moon. Meanwhile, astronaut Collins piloted the Command Module in a parking orbit around the Moon. Armstrong was the first human to ever stand on the lunar surface, followed by Edwin (Buzz) Aldrin. The crew collected 47 pounds of lunar surface material which was returned to Earth for analysis. The surface exploration was concluded in 2½ hours. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Space reliability technology - A historical perspective

NASA Technical Reports Server (NTRS)

Cohen, H.

1984-01-01

The progressive improvements in reliability of launch vehicles is traced from the Vanguard rocket to the STS. The Vanguard, built with minimal redundancy and a high mass ratio, was used as an operational vehicle midway through its test program in an attempt to meet the perceived challenge represented by the Sputnik. The fourth Vanguard failed due to inadequate contamination prevention and lack of inspection ports. Automatic firing sequences were adopted for the Titan rockets, which were an order of magnitude larger than the Vanguard and therefore had room for interior inspections. Qualification testing and reporting were introduced for components, along with X ray inspection of fuel tank welds. Dual systems were added for flight critical components when the Titan became man-rated for the Gemini program. Designs incorporated full failure mode effects and criticality analyses for the Apollo program, which exposed the limits of applicability of numerical reliability models. Fault tree analyses and program milestone reviews were initiated. The worth of man-in-the-loop in space activities for reliability was demonstrated with the rescue of Skylab after solar panel and meteoroid shield failures. It is now the reliability of the payload, rather than the vehicle, that is questioned for Shuttle launches.

Strategies for Ground Testing of Manned Lunar Surface Systems

NASA Technical Reports Server (NTRS)

Beyer, Jeff; Gill, Tracy; Peacock, Mike

2009-01-01

One of the primary objectives of NASA's Vision for Space Exploration is the creation of a permanently manned lunar outpost. Facing the challenge of establishing a human presence on the moon will require new innovations and technologies that will be critical to expanding this exploration to Mars and beyond. However, accomplishing this task presents an unprecedented set of obstacles, one of the more significant of which is the development of new strategies for ground test and verification. Present concepts for the Lunar Surface System (LSS) architecture call for the construction of a series of independent yet tightly coupled modules and elements to be launched and assembled in incremental stages. Many of these will be fabricated at distributed locations and delivered shortly before launch, precluding any opportunity for testing in an actual integrated configuration. Furthermore, these components must operate flawlessly once delivered to the lunar surface since there is no possibility for returning a malfunctioning module to Earth for repair or modification. Although undergoing continual refinement, this paper will present the current state of the plans and models that have been devised for meeting the challenge of ground based testing for Constellation Program LSS as well as the rationale behind their selection.

Modelling an advanced ManPAD with dual band detectors and a rosette scanning seeker head

NASA Astrophysics Data System (ADS)

Birchenall, Richard P.; Richardson, Mark A.; Butters, Brian; Walmsley, Roy

2012-01-01

Man Portable Air Defence Systems (ManPADs) have been a favoured anti aircraft weapon since their appearance on the military proliferation scene in the mid 1960s. Since this introduction there has been a 'cat and mouse' game of Missile Countermeasures (CMs) and the aircraft protection counter counter measures (CCMs) as missile designers attempt to defeat the aircraft platform protection equipment. Magnesium Teflon Viton (MTV) flares protected the target aircraft until the missile engineers discovered the art of flare rejection using techniques including track memory and track angle bias. These early CCMs relied upon CCM triggering techniques such as the rise rate method which would just sense a sudden increase in target energy and assume that a flare CM had been released by the target aircraft. This was not as reliable as was first thought as aspect changes (bringing another engine into the field of view) or glint from the sun could inadvertently trigger a CCM when not needed. The introduction of dual band detectors in the 1980s saw a major advance in CCM capability allowing comparisons between two distinct IR bands to be made thus allowing the recognition of an MTV flare to occur with minimal false alarms. The development of the rosette scan seeker in the 1980s complemented this advancement allowing the scene in the missile field of view (FOV) to be scanned by a much smaller (1/25) instantaneous FOV (IFOV) with the spectral comparisons being made at each scan point. This took the ManPAD from a basic IR energy detector to a pseudo imaging system capable of analysing individual elements of its overall FOV allowing more complex and robust CCM to be developed. This paper continues the work published in [1,2] and describes the method used to model an advanced ManPAD with a rosette scanning seeker head and robust CCMs similar to the Raytheon Stinger RMP.

Advanced Concept

NASA Image and Video Library

2008-02-15

Shown is a concept illustration of the Ares I crew launch vehicle during launch and the Ares V cargo launch vehicle on the launch pad. Ares I will carry the Orion Crew Exploration Vehicle with an astronaut crew to Earth orbit. Ares V will deliver large-scale hardware to space. This includes the Altair Lunar Lander, materials for establishing an outpost on the moon, and the vehicles and hardware needed to extend a human presence beyond Earth orbit.

Comparison of Two Recent Launch Abort Platforms

NASA Technical Reports Server (NTRS)

Dittemore, Gary D.; Harding, Adam

2011-01-01

The development of new and safer manned space vehicles is a top priority at NASA. Recently two different approaches of how to accomplish this mission of keeping astronauts safe was successfully demonstrated. With work already underway on an Apollo-like launch abort system for the Orion Crew Exploration Vehicle (CEV), an alternative design concept named the Max Launch Abort System, or MLAS, was developed as a parallel effort. The Orion system, managed by the Constellation office, is based on the design of a single solid launch abort motor in a tower positioned above the capsule. The MLAS design takes a different approach placing the solid launch abort motor underneath the capsule. This effort was led by the NASA Engineering and Safety Center (NESC). Both escape systems were designed with the Ares I Rocket as the launch vehicle and had the same primary requirement to safely propel a crew module away from any emergency event either on the launch pad or during accent. Beyond these two parameters, there was little else in common between the two projects, except that they both concluded in successful launches that will further promote the development of crew launch abort systems. A comparison of these projects from the standpoint of technical requirements; program management and flight test objectives will be done to highlight the synergistic lessons learned by two engineers who worked on each program. This comparison will demonstrate how the scope of the project architecture and management involvement in innovation should be tailored to meet the specific needs of the system under development.

Task 4 supporting technology. Part 2: Detailed test plan for thermal seals. Thermal seals evaluation, improvement and test. CAN8-1, Reusable Launch Vehicle (RLV), advanced technology demonstrator: X-33. Leading edge and seals thermal protection system technology demonstration

NASA Technical Reports Server (NTRS)

Hogenson, P. A.; Lu, Tina

1995-01-01

The objective is to develop the advanced thermal seals to a technology readiness level (TRL) of 6 to support the rapid turnaround time and low maintenance requirements of the X-33 and the future reusable launch vehicle (RLV). This program is divided into three subtasks: (1) orbiter thermal seals operation history review; (2) material, process, and design improvement; and (3) fabrication and evaluation of the advanced thermal seals.

Satellite Ocean Aerosol Retrieval (SOAR) Algorithm Extension to S-NPP VIIRS as Part of the "Deep Blue" Aerosol Project

NASA Astrophysics Data System (ADS)

Sayer, A. M.; Hsu, N. C.; Lee, J.; Bettenhausen, C.; Kim, W. V.; Smirnov, A.

2018-01-01

The Suomi National Polar-Orbiting Partnership (S-NPP) satellite, launched in late 2011, carries the Visible Infrared Imaging Radiometer Suite (VIIRS) and several other instruments. VIIRS has similar characteristics to prior satellite sensors used for aerosol optical depth (AOD) retrieval, allowing the continuation of space-based aerosol data records. The Deep Blue algorithm has previously been applied to retrieve AOD from Sea-viewing Wide Field-of-view Sensor (SeaWiFS) and Moderate Resolution Imaging Spectroradiometer (MODIS) measurements over land. The SeaWiFS Deep Blue data set also included a SeaWiFS Ocean Aerosol Retrieval (SOAR) algorithm to cover water surfaces. As part of NASA's VIIRS data processing, Deep Blue is being applied to VIIRS data over land, and SOAR has been adapted from SeaWiFS to VIIRS for use over water surfaces. This study describes SOAR as applied in version 1 of NASA's S-NPP VIIRS Deep Blue data product suite. Several advances have been made since the SeaWiFS application, as well as changes to make use of the broader spectral range of VIIRS. A preliminary validation against Maritime Aerosol Network (MAN) measurements suggests a typical uncertainty on retrieved 550 nm AOD of order ±(0.03+10%), comparable to existing SeaWiFS/MODIS aerosol data products. Retrieved Ångström exponent and fine-mode AOD fraction are also well correlated with MAN data, with small biases and uncertainty similar to or better than SeaWiFS/MODIS products.

Advanced Control Surface Seal Development at NASA GRC for Future Space Launch Vehicles

NASA Technical Reports Server (NTRS)

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.; DeMange, Jeffrey J.

2003-01-01

NASA s Glenn Research Center (GRC) is developing advanced control surface seal technologies for future space launch vehicles as part of the Next Generation Launch Technology project (NGLT). New resilient seal designs are currently being fabricated and high temperature seal preloading devices are being developed as a means of improving seal resiliency. GRC has designed several new test rigs to simulate the temperatures, pressures, and scrubbing conditions that seals would have to endure during service. A hot compression test rig and hot scrub test rig have been developed to perform tests at temperatures up to 3000 F. Another new test rig allows simultaneous seal flow and scrub tests at room temperature to evaluate changes in seal performance with scrubbing. These test rigs will be used to evaluate the new seal designs. The group is also performing tests on advanced TPS seal concepts for Boeing using these new test facilities.

Advanced Propulsion for Gun Launched Projectiles and Missiles: Phase 1 - Low Cost Flight Test Platform Development

DTIC Science & Technology

2009-11-30

Son blueberry fields as shown in Figure 113. All FAA and Maine DOT permits were acquired. Richard Willey was the designated LSO (Launch Safety...The launch area is on the Jasper Wyman & Son blueberry fields as shown in Figure 113. FAA and Maine DOT permits are required for flight testing

Proceedings of the 1986 IEEE international conference on systems, man and cybernetics

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

Not Available

1986-01-01

This book presents the papers given at a conference on man-machine systems. Topics considered at the conference included neural model-based cognitive theory and engineering, user interfaces, adaptive and learning systems, human interaction with robotics, decision making, the testing and evaluation of expert systems, software development, international conflict resolution, intelligent interfaces, automation in man-machine system design aiding, knowledge acquisition in expert systems, advanced architectures for artificial intelligence, pattern recognition, knowledge bases, and machine vision.

Manned Mars mission communication and data management systems

NASA Technical Reports Server (NTRS)

White, Ronald E.

1986-01-01

A manned Mars mission will involve a small crew and many complex tasks. The productivity of the crew and the entire mission will depend significantly on effective automation of these tasks and the ease with which the crew can interface with them. The technology to support a manned Mars mission is available today; however, evolving software and electronic technology are enabling many interesting possibilities for increasing productivity and safety while reducing life cycle cost. Some of these advanced technologies are identified.

Performance Analysis and Design Synthesis (PADS) computer program. Volume 2: Program description, part 1

NASA Technical Reports Server (NTRS)

1972-01-01

The Performance Analysis and Design Synthesis (PADS) computer program has a two-fold purpose. It can size launch vehicles in conjunction with calculus-of-variations optimal trajectories and can also be used as a general-purpose branched trajectory optimization program. In the former use, it has the Space Shuttle Synthesis Program as well as a simplified stage weight module for optimally sizing manned recoverable launch vehicles. For trajectory optimization alone or with sizing, PADS has two trajectory modules. The first trajectory module uses the method of steepest descent; the second employs the method of quasilinearization, which requires a starting solution from the first trajectory module. For Volume 1 see N73-13199.

KSC-04pd1223

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operator Kenny Allen makes adjustments on one of the recently acquired Contraves-Goerz Kineto Tracking Mounts (KTM). There are 10 KTMs certified for use on the Eastern Range. The KTM, which is trailer-mounted with a center console/seat and electric drive tracking mount, includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff.

KSC-04pd1221

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operators Rick Worthington (left) and Kenny Allen work on one of the recently acquired Contraves-Goerz Kineto Tracking Mounts (KTM). There are 10 KTMs certified for use on the Eastern Range. The KTM, which is trailer-mounted with a center console/seat and electric drive tracking mount, includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff.

KSC-04pd1225

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operator Kenny Allen stands in the center console area of one of the recently acquired Contraves-Goerz Kineto Tracking Mounts (KTM). There are 10 KTMs certified for use on the Eastern Range. The KTM, which is trailer-mounted with an electric-drive tracking mount, includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff.

KSC-04pd1224

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operator Rick Wetherington sits in the center console seat of one of the recently acquired Contraves-Goerz Kineto Tracking Mounts (KTM). There are 10 KTMs certified for use on the Eastern Range. The KTM, which is trailer-mounted with an electric drive tracking mount, includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff.

KSC-04pd1222

NASA Image and Video Library

2004-05-19

KENNEDY SPACE CENTER, FLA. -- Johnson Controls operators Rick Wetherington (left) and Kenny Allen work on two of the recently acquired Contraves-Goerz Kineto Tracking Mounts (KTM). There are 10 KTMs certified for use on the Eastern Range. The KTM, which is trailer-mounted with a center console/seat and electric drive tracking mount, includes a two-camera, camera control unit that will be used during launches. The KTM is designed for remotely controlled operations and offers a combination of film, shuttered and high-speed digital video, and FLIR cameras configured with 20-inch to 150-inch focal length lenses. The KTMs are generally placed in the field and checked out the day before a launch and manned 3 hours prior to liftoff.

Spaceport Command and Control System Software Development

NASA Technical Reports Server (NTRS)

Glasser, Abraham

2017-01-01

The Spaceport Command and Control System (SCCS) is the National Aeronautics and Space Administration's (NASA) launch control system for the Orion capsule and Space Launch System, the next generation manned rocket currently in development. This large system requires a large amount of intensive testing that will properly measure the capabilities of the system. Automating the test procedures would save the project money from human labor costs, as well as making the testing process more efficient. Therefore, the Exploration Systems Division (formerly the Electrical Engineering Division) at Kennedy Space Center (KSC) has recruited interns for the past two years to work alongside full-time engineers to develop these automated tests, as well as innovate upon the current automation process.

Summary of lightning activities by NASA for the Apollo Soyuz test project: Supplement no. 1 to Apollo Soyuz mission evaluation report

NASA Technical Reports Server (NTRS)

1976-01-01

To avoid the possibility of an unnecessary launch delay, a special program was initiated to provide aircraft measurement of electric fields at various altitudes over the Apollo vehicle launch pad. Eight aircraft, each equipped with electric field meters, were used in the program. This program and some of the more important findings are discussed. Also included is a summary of the history of manned space vehicle involvement with lightning, a brief description of the lightning instrumentation in use at KSC (Kennedy Space Center) at the time of the Apollo Soyuz mission and a discussion of the airborne instrumentation and related data.

Pitch Guidance Optimization for the Orion Abort Flight Tests

NASA Technical Reports Server (NTRS)

Stillwater, Ryan Allanque

2010-01-01

The National Aeronautics and Space Administration created the Constellation program to develop the next generation of manned space vehicles and launch vehicles. The Orion abort system is initiated in the event of an unsafe condition during launch. The system has a controller gains schedule that can be tuned to reduce the attitude errors between the simulated Orion abort trajectories and the guidance trajectory. A program was created that uses the method of steepest descent to tune the pitch gains schedule by an automated procedure. The gains schedule optimization was applied to three potential abort scenarios; each scenario tested using the optimized gains schedule resulted in reduced attitude errors when compared to the Orion production gains schedule.

Saturn Apollo Program

NASA Image and Video Library

1967-01-01

Workers at McDornel-Douglas install the Saturn IB S-IVB (second) stage for the Apollo-Soyuz mission into the company's S-IVB assembly and checkout tower in Huntington Beach, California. The Saturn IB launch vehicle was developed by the Marshall Space Flight Center (MSFC) as an interim vehicle in its "building block" approach to Saturn rocket development. This vehicle utilized the Saturn I technology to further develop and refine the capabilities of a larger booster and the Apollo spacecraft required for the manned lunar missions. The S-IVB stage, later used as the third stage of the Saturn V launch vehicle, was powered by a single J-2 engine initially capable of 200,000 pounds of thrust.

One Man's Invasion Is Another Man's Advance: National History in Japan and Korea.

ERIC Educational Resources Information Center

Hurst, G. Cameron, III

The altering of the presentation of Japan's imperialist adventures in Japanese high school history textbooks reflects a continuing dispute between Japan and her Asian neighbors, as well as between a politically conservative bureaucracy in the Ministry of Education and a historical profession heavily influenced by "progressives" who write…

Saturn Apollo Program

NASA Image and Video Library

1969-07-24

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. The Saturn V vehicle was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun. Aboard were Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. Armstrong was the first human to ever stand on the lunar surface, Aldrin. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF). Donned in biological isolation garments, the Apollo 11 crew members wave to well wishers as they leave the pick up helicopter making their way to the MQF. This portable facility served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Saturn Apollo Program

NASA Image and Video Library

1969-07-24

The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center, Florida via the Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. The Saturn V vehicle was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Wernher von Braun. Aboard the craft were astronauts Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. Armstrong was the first human to ever stand on the lunar surface followed by Aldrin. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF). Donned in biological isolation garments, the Apollo 11 crew members (front to rear) Armstrong, Collins, and Aldrin leave the pick up helicopter making their way to the MQF. This portable facility served as their home until they reached the NASA Manned Spacecraft Center Lunar Receiving Laboratory in Houston, Texas. With the success of Apollo 11 mission the national objective to land men on the Moon and return them safely to Earth had been accomplished.

Saturn Apollo Program

NASA Image and Video Library

1969-07-24

Donned in biological isolation garments, the Apollo 11 crew members, (L-R) Edwin Aldrin, Neil Armstrong (waving), and Michael Collins exit the recovery pick up helicopter to board the U.S.S. Hornet aircraft carrier after splashdown. The recovery operation took place in the Pacific Ocean where Navy para-rescue men recovered the capsule housing the 3-man Apollo 11 crew. The crew was airlifted to safety aboard the U.S.S. Hornet, where they were quartered in a Mobile Quarantine Facility (MQF). This portable facility served as their home until they reached the NASA Manned Spacecraft Center (MSC) Lunar Receiving Laboratory in Houston, Texas. The Apollo 11 mission, the first manned lunar mission, launched from the Kennedy Space Center (KSC), Florida via the Saturn V launch vehicle on July 16, 1969 and safely returned to Earth on July 24, 1969. Aboard were Neil A. Armstrong, commander; Michael Collins, Command Module (CM) pilot; and Edwin E. Aldrin Jr., Lunar Module (LM) pilot. The CM, piloted by Michael Collins remained in a parking orbit around the Moon while the LM, named “Eagle’’, carrying astronauts Neil Armstrong and Edwin Aldrin, landed on the Moon. Armstrong was the first human to ever stand on the lunar surface, followed by Aldrin. During 2½ hours of surface exploration, the crew collected 47 pounds of lunar surface material for analysis back on Earth. With the success of Apollo 11, the national objective to land men on the Moon and return them safely to Earth had been accomplished. The Saturn V vehicle was developed by the Marshall Space Flight Center (MSFC) under the direction of Dr. Werher von Braun.

Space Station Human Factors Research Review. Volume 1: EVA Research and Development

NASA Technical Reports Server (NTRS)

Cohen, Marc M. (Editor); Vykukal, H. C. (Editor)

1988-01-01

An overview is presented of extravehicular activity (EVA) research and development activities at Ames. The majority of the program was devoted to presentations by the three contractors working in parallel on the EVA System Phase A Study, focusing on Implications for Man-Systems Design. Overhead visuals are included for a mission results summary, space station EVA requirements and interface accommodations summary, human productivity study cross-task coordination, and advanced EVAS Phase A study implications for man-systems design. Articles are also included on subsea approach to work systems development and advanced EVA system design requirements.

Advanced beamed-energy and field propulsion concepts

NASA Technical Reports Server (NTRS)

Myrabo, L. N.

1983-01-01

Specific phenomena which might lead to major advances in payload, range and terminal velocity of very advanced vehicle propulsion are studied. The effort focuses heavily on advanced propulsion spinoffs enabled by current government-funded investigations in directed-energy technology: i.e., laser, microwave, and relativistic charged particle beams. Futuristic (post-year 2000) beamed-energy propulsion concepts which indicate exceptional promise are identified and analytically investigated. The concepts must be sufficiently developed to permit technical understanding of the physical processes involved, assessment of the enabling technologies, and evaluation of their merits over conventional systems. Propulsion concepts that can be used for manned and/or unmanned missions for purposes of solar system exploration, planetary landing, suborbital flight, transport to orbit, and escape are presented. Speculations are made on the chronology of milestones in beamed-energy propulsion development, such as in systems applications of defense, satellite orbit-raising, global aerospace transportation, and manned interplanetary carriers.

Sensitivity Analysis of Launch Vehicle Debris Risk Model

NASA Technical Reports Server (NTRS)

Gee, Ken; Lawrence, Scott L.

2010-01-01

As part of an analysis of the loss of crew risk associated with an ascent abort system for a manned launch vehicle, a model was developed to predict the impact risk of the debris resulting from an explosion of the launch vehicle on the crew module. The model consisted of a debris catalog describing the number, size and imparted velocity of each piece of debris, a method to compute the trajectories of the debris and a method to calculate the impact risk given the abort trajectory of the crew module. The model provided a point estimate of the strike probability as a function of the debris catalog, the time of abort and the delay time between the abort and destruction of the launch vehicle. A study was conducted to determine the sensitivity of the strike probability to the various model input parameters and to develop a response surface model for use in the sensitivity analysis of the overall ascent abort risk model. The results of the sensitivity analysis and the response surface model are presented in this paper.

ASUR

NASA Technical Reports Server (NTRS)

1991-01-01

The Ecole Polytechnique Feminine (EPF) is a French engineering school for women. The students who presented the project at the Summer Conference are in the fourth year of a five year program. For the second time, the EPF worked on an aeronautical project with the Ohio State University. This year, the theme was to design a hypersonic carrier aimed to launch an orbiter at Mach 6, a range of 375 miles and an altitude of 95,000 ft. The plane was called ASUR which in French means the blue sky, the same sky that links our countries across the ocean. Moreover, ASUR is an anagram of USRA. This work benefits from work on reusable hypersonic aircraft in Europe, and especially on two of them: STAR-H and Sanger. STAR-H is a French project. This hypersonic aircraft would replace Ariane 5 in launching a shuttle smaller than Hermes. Sanger is a German project. Its objective is to launch a manned shuttle called HORUS, but Ariane 5 would be kept for heavy cargo launches. These two projects are in competition in Europe to be a launcher of the European Space Agency.

Going Boldly Beyond: Progress on NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Singer, Jody; Crumbly, Chris

2013-01-01

NASA's Space Launch System is implementing an evolvable configuration approach to system development in a resource-constrained era. Legacy systems enable non-traditional development funding and contribute to sustainability and affordability. Limited simultaneous developments reduce cost and schedule risk. Phased approach to advanced booster development enables innovation and competition, incrementally demonstrating affordability and performance enhancements. Advanced boosters will provide performance for the most capable heavy lift launcher in history, enabling unprecedented space exploration benefiting all of humanity.

A review of advances in the study of diseases of fish: 1954-1964

USGS Publications Warehouse

Post, G.

1965-01-01

STUDY OF DISEASE IN ANIMALS, INCLUDING MAN, has progressed rapidly in the past decade. Looking back, we find amazing success in the study of man's diseases and possibly only a little less success in studies of diseases of domesticated homeothermic animals. We who are interested in the poikilothermic animals may feel at times that we have not advanced so rapidly in our field. The reason for this may be closely associated with economics. The market for drugs and therapeutic agents is greater for domestic livestock than for cultured fishes. A larger income is derived from rearing domestic livestock. Therefore, more public funds are available for study of diseases of man and domestic livestock, while such funds are limited for the study of diseases of fish. The Federal and State fish-cultural systems, as well as colleges and universities, have been most active in research on fish disease and probably will continue to be so.

Atmospheric statistics for aerospace vehicle operations

NASA Technical Reports Server (NTRS)

Smith, O. E.; Batts, G. W.

1993-01-01

Statistical analysis of atmospheric variables was performed for the Shuttle Transportation System (STS) design trade studies and the establishment of launch commit criteria. Atmospheric constraint statistics have been developed for the NASP test flight, the Advanced Launch System, and the National Launch System. The concepts and analysis techniques discussed in the paper are applicable to the design and operations of any future aerospace vehicle.

Pathfinder

NASA Image and Video Library

1966-05-21

The Delta Clipper-Experimental Advanced (DC-XA) is a single-stage-to-orbit, vertical takeoff / vertical landing launch vehicle concept, whose development was geared to significantly reduce launch cost and provided a test bed for NASA Reusable Launch Vehicle (RLV) technology. This photograph shows the descending vehicle landing during the first successful test flight at White Sands Missile Range, New Mexico. The program was discontinued in 2003.

Structural Dynamics Testing of Advanced Stirling Convertor Components

NASA Technical Reports Server (NTRS)

Oriti, Salvatore M.; Williams, Zachary Douglas

2013-01-01

NASA Glenn Research Center has been supporting the development of Stirling energy conversion for use in space. Lockheed Martin has been contracted by the Department of Energy to design and fabricate flight-unit Advanced Stirling Radioisotope Generators, which utilize Sunpower, Inc., free-piston Advanced Stirling Convertors. The engineering unit generator has demonstrated conversion efficiency in excess of 20 percent, offering a significant improvement over existing radioisotope-fueled power systems. NASA Glenn has been supporting the development of this generator by developing the convertors through a technology development contract with Sunpower, and conducting research and experiments in a multitude of areas, such as high-temperature material properties, organics testing, and convertor-level extended operation. Since the generator must undergo launch, several launch simulation tests have also been performed at the convertor level. The standard test sequence for launch vibration exposure has consisted of workmanship and flight acceptance levels. Together, these exposures simulate what a flight convertor will experience. Recently, two supplementary tests were added to the launch vibration simulation activity. First was a vibration durability test of the convertor, intended to quantify the effect of vibration levels up to qualification level in both the lateral and axial directions. Second was qualification-level vibration of several heater heads with small oxide inclusions in the material. The goal of this test was to ascertain the effect of the inclusions on launch survivability to determine if the heater heads were suitable for flight.

STS-27 Atlantis, Orbiter Vehicle (OV) 104, liftoff

NASA Image and Video Library

1988-12-02

S88-55870 (2 Dec. 1988) --- The space shuttle Atlantis and its five-man crew of astronauts are launched from Kennedy Space Center?s Pad 39B at 9:30 a.m. (EST), Dec. 2, 1988. Onboard the Department of Defense?dedicated mission are astronauts Robert L. Gibson, Guy S. Gardner, Jerry L. Ross, Richard M. (Mike) Mullane and Williams M. Shepherd. Photo credit: NASA

Space station assembly/servicing capabilities

NASA Technical Reports Server (NTRS)

Joyce, Joseph

1986-01-01

The aim is to place a permanently manned space station on-orbit around the Earth, which is international in scope. The program is nearing the close of the system definition and preliminary design phase. The first shuttle launch for space station assembly on-orbit is estimated for January 1993. Topics perceived to be important to on-orbit assembly and servicing are discussed. This presentation is represented by charts.

Brevard Top Scholars

NASA Image and Video Library

2017-05-05

Kennedy Space Center Associate Director Kelvin Manning addresses about 40 Brevard County high school seniors regarding NASA's and Kennedy’s roles and missions during Brevard Top Scholars Day at Kennedy Space Center on May 5. Kennedy's Office of Education coordinated the event that featured a special behind-the-scenes tour of Kennedy, including prototype shops, cryogenic labs and facilities such as the Vehicle Assembly Building and the Launch Control Center firing rooms.

CRAWLER HIDDEN UNDER MOBILE LAUNCHER MOVES APOLLO 17 FROM VEHICLE ASSEMBLY BUILDING AS TRIP TO LAUNC

NASA Technical Reports Server (NTRS)

1972-01-01

The Apollo 17 space vehicle was moved today from the Vehicle Assembly Building to Complex 39's pad A in preparation for its launch with Astronauts Eugene A. Cernan, Commander; Ronald A. Evans, Command Module Pilot; and Dr. Harrison H. ''Jack'' Schmitt, Lunar Module Pilot, on the sixth U.S. manned lunar landing mission on December 6, 1972.

Inverse synthetic aperture radar imagery of a man with a rocket propelled grenade launcher

NASA Astrophysics Data System (ADS)

Tran, Chi N.; Innocenti, Roberto; Kirose, Getachew; Ranney, Kenneth I.; Smith, Gregory

2004-08-01

As the Army moves toward more lightly armored Future Combat System (FCS) vehicles, enemy personnel will present an increasing threat to U.S. soldiers. In particular, they face a very real threat from adversaries using shoulder-launched, rocket propelled grenade (RPG). The Army Research Laboratory has utilized its Aberdeen Proving Ground (APG) turntable facility to collect very high resolution, fully polarimetric Ka band radar data at low depression angles of a man holding an RPG. In this paper, we examine the resulting low resolution and high resolution range profiles; and based on the observed radar cross section (RCS) value, we attempt to determine the utility of Ka band radar for detecting enemy personnel carrying RPG launchers.

Non-ionising electromagnetic environments on manned spacecraft.

PubMed

Murphy, J R

1989-08-01

Future space travellers and settlers will be exposed to a variety of electromagnetic fields (EMFs). Extrinsic sources will include solar and stellar fluxes, planetary fluxes, and supernovae. Intrinsic sources may include fusion and ion engines, EMFs from electrical equipment, radar, lighting, superconduction energy storage systems, magnetic bearings on gyroscopic control and orientation systems, and magnetic rail microprobe launch systems. Communication sources may include radio and microwave frequencies, and laser generating systems. Magnetic fields may also be used for deflection of radiation. There is also a loss of the normal Geomagnetic field (GMF) which includes static, alternating, and time-varying components. This paper reviews exposure limits and the biological effects of EMFs, and evidence for an electromagnetic sense organ and a relationship between man and the Geomagnetic field.

3D Reacting Flow Analysis of LANTR Nozzles

NASA Astrophysics Data System (ADS)

Stewart, Mark E. M.; Krivanek, Thomas M.; Hemminger, Joseph A.; Bulman, M. J.

2006-01-01

This paper presents performance predictions for LANTR nozzles and the system implications for their use in a manned Mars mission. The LANTR concept is rocket thrust augmentation by injecting Oxygen into the nozzle to combust the Hydrogen exhaust of a Nuclear Thermal Rocket. The performance predictions are based on three-dimensional reacting flow simulations using VULCAN. These simulations explore a range of O2/H2 mixture ratios, injector configurations, and concepts. These performance predictions are used for a trade analysis within a system study for a manned Mars mission. Results indicate that the greatest benefit of LANTR will occur with In-Situ Resource Utilization (ISRU). However, Hydrogen propellant volume reductions may allow greater margins for fitting tanks within the launch vehicle where packaging issues occur.

A Method of Trajectory Design for Manned Asteroids Exploration

NASA Astrophysics Data System (ADS)

Gan, Q. B.; Zhang, Y.; Zhu, Z. F.; Han, W. H.; Dong, X.

2014-11-01

A trajectory optimization method of the nuclear propulsion manned asteroids exploration is presented. In the case of launching between 2035 and 2065, based on the Lambert transfer orbit, the phases of departure from and return to the Earth are searched at first. Then the optimal flight trajectory in the feasible regions is selected by pruning the flight sequences. Setting the nuclear propulsion flight plan as propel-coast-propel, and taking the minimal mass of aircraft departure as the index, the nuclear propulsion flight trajectory is separately optimized using a hybrid method. With the initial value of the optimized local parameters of each three phases, the global parameters are jointedly optimized. At last, the minimal departure mass trajectory design result is given.

Why send humans to Mars?

NASA Technical Reports Server (NTRS)

Sagan, Carl

1991-01-01

The proposed Space Exploration Initiative (SDI) to launch a manned flight to Mars is examined in the current light of growing constraints in costs and other human requirements. Sharing the huge costs of such a program among a group of nations might become low enough for the project to be feasible. Robotic missions, equipped with enhanced artificial intelligence, appear to be capable of satisfying mission requirements at 10 percent or less, of the cost of a manned flight. Various additional pros and cons are discussed regarding both SDI generally and a Mars mission. It is suggested that R&D projects be pursued that can be better justified and can also contribute to human mission to Mars if eventually a decision to go is made.

Multi-Terrain Earth Landing Systems Applicable for Manned Space Capsules

NASA Technical Reports Server (NTRS)

Fasanella, Edwin L.

2008-01-01

A key element of the President's Vision for Space Exploration is the development of a new space transportation system to replace Shuttle that will enable manned exploration of the moon, Mars, and beyond. NASA has tasked the Constellation Program with the development of this architecture, which includes the Ares launch vehicle and Orion manned spacecraft. The Orion spacecraft must carry six astronauts and its primary structure should be reusable, if practical. These requirements led the Constellation Program to consider a baseline land landing on return to earth. To assess the landing system options for Orion, a review of current operational parachute landing systems such as those used for the F-111 escape module and the Soyuz is performed. In particular, landing systems with airbags and retrorockets that would enable reusability of the Orion capsule are investigated. In addition, Apollo tests and analyses conducted in the 1960's for both water and land landings are reviewed. Finally, tests and dynamic finite element simulations to understand land landings for the Orion spacecraft are also presented.

Manned Mars Explorer project: Guidelines for a manned mission to the vicinity of Mars using Phobos as a staging outpost; schematic vehicle designs considering chemical and nuclear electric propulsion

NASA Technical Reports Server (NTRS)

Nolan, Sean; Neubek, Deb; Baxmann, C. J.

1988-01-01

The Manned Mars Explorer (MME) project responds to the fundamental problems of sending human beings to Mars in a mission scenario and schematic vehicle designs. The mission scenario targets an opposition class Venus inbound swingby for its trajectory with concentration on Phobos and/or Deimos as a staging base for initial and future Mars vicinity operations. Optional vehicles are presented as a comparison using nuclear electric power/propulsion technology. A Manned Planetary Vehicle and Crew Command Vehicle are used to accomplish the targeted mission. The Manned Planetary Vehicle utilizes the mature technology of chemical propulsion combined with an advanced aerobrake, tether and pressurized environment system. The Crew Command Vehicle is the workhorse of the mission performing many different functions including a manned Mars landing, and Phobos rendezvous.

NASA's Advanced Space Transportation Hypersonic Program

NASA Technical Reports Server (NTRS)

Hueter, Uwe; McClinton, Charles; Cook, Stephen (Technical Monitor)

2002-01-01

NASA's has established long term goals for access-to-space. NASA's third generation launch systems are to be fully reusable and operational in approximately 25 years. The goals for third generation launch systems are to reduce cost by a factor of 100 and improve safety by a factor of 10,000 over current conditions. The Advanced Space Transportation Program Office (ASTP) at NASA's Marshall Space Flight Center in Huntsville, AL has the agency lead to develop third generation space transportation technologies. The Hypersonics Investment Area, part of ASTP, is developing the third generation launch vehicle technologies in two main areas, propulsion and airframes. The program's major investment is in hypersonic airbreathing propulsion since it offers the greatest potential for meeting the third generation launch vehicles. The program will mature the technologies in three key propulsion areas, scramjets, rocket-based combined cycle and turbine-based combination cycle. Ground and flight propulsion tests are being planned for the propulsion technologies. Airframe technologies will be matured primarily through ground testing. This paper describes NASA's activities in hypersonics. Current programs, accomplishments, future plans and technologies that are being pursued by the Hypersonics Investment Area under the Advanced Space Transportation Program Office will be discussed.

An Alternative Approach to Human Servicing of Manned Earth Orbiting Spacecraft

NASA Technical Reports Server (NTRS)

Mularski, John; Alpert, Brian

2011-01-01

As manned spacecraft have grown larger and more complex, they have come to rely on spacewalks or Extravehicular Activities (EVA) for both mission success and crew safety. Typically these spacecraft maintain all of the hardware and trained personnel needed to perform an EVA on-board at all times. Maintaining this capability requires volume and up-mass for storage of EVA hardware, crew time for ground and on-orbit training, and on-orbit maintenance of EVA hardware . This paper proposes an alternative methodology to utilize launch-on-need hardware and crew to provide EVA capability for space stations in Earth orbit after assembly complete, in the same way that most people would call a repairman to fix something at their home. This approach would not only reduce ground training requirements and save Intravehicular Activity (IVA) crew time in the form of EVA hardware maintenance and on-orbit training, but would also lead to more efficient EVAs because they would be performed by specialists with detailed knowledge and training stemming from their direct involvement in the development of the EVA. The on-orbit crew would then be available to focus on the immediate response to the failure as well as the day-to-day operations of the spacecraft and payloads. This paper will look at how current ISS unplanned EVAs are conducted, including the time required for preparation, and offer alternatives for future spacecraft utilizing lessons learned from ISS. As this methodology relies entirely on the on-time and on-need launch of spacecraft, any space station that utilized this approach would need a robust transportation system including more than one launch vehicle capable of carrying crew. In addition the fault tolerance of the space station would be an important consideration in how much time was available for EVA preparation after the failure. Each future program would have to weigh the risk of on-time launch against the increase in available crew time for the main objective of the spacecraft.

Intelligent Systems Technologies for Ops

NASA Technical Reports Server (NTRS)

Smith, Ernest E.; Korsmeyer, David J.

2012-01-01

As NASA supports International Space Station assembly complete operations through 2020 (or later) and prepares for future human exploration programs, there is additional emphasis in the manned spaceflight program to find more efficient and effective ways of providing the ground-based mission support. Since 2006 this search for improvement has led to a significant cross-fertilization between the NASA advanced software development community and the manned spaceflight operations community. A variety of mission operations systems and tools have been developed over the past decades as NASA has operated the Mars robotic missions, the Space Shuttle, and the International Space Station. NASA Ames Research Center has been developing and applying its advanced intelligent systems research to mission operations tools for both unmanned Mars missions operations since 2001 and to manned operations with NASA Johnson Space Center since 2006. In particular, the fundamental advanced software development work under the Exploration Technology Program, and the experience and capabilities developed for mission operations systems for the Mars surface missions, (Spirit/Opportunity, Phoenix Lander, and MSL) have enhanced the development and application of advanced mission operation systems for the International Space Station and future spacecraft. This paper provides an update on the status of the development and deployment of a variety of intelligent systems technologies adopted for manned mission operations, and some discussion of the planned work for Autonomous Mission Operations in future human exploration. We discuss several specific projects between the Ames Research Center and the Johnson Space Centers Mission Operations Directorate, and how these technologies and projects are enhancing the mission operations support for the International Space Station, and supporting the current Autonomous Mission Operations Project for the mission operation support of the future human exploration programs.

Technology Innovations from NASA's Next Generation Launch Technology Program

NASA Technical Reports Server (NTRS)

Cook, Stephen A.; Morris, Charles E. K., Jr.; Tyson, Richard W.

2004-01-01

NASA's Next Generation Launch Technology Program has been on the cutting edge of technology, improving the safety, affordability, and reliability of future space-launch-transportation systems. The array of projects focused on propulsion, airframe, and other vehicle systems. Achievements range from building miniature fuel/oxygen sensors to hot-firings of major rocket-engine systems as well as extreme thermo-mechanical testing of large-scale structures. Results to date have significantly advanced technology readiness for future space-launch systems using either airbreathing or rocket propulsion.

Experimental study of ELF signatures developed by ballistic missile launch

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

Peglow, S.G.; Rynne, T.M.

1993-04-08

The Lawrence Livermore National Laboratory (Livermore, CA) and SARA, Inc. participated in the ATMD missile launch activities that occurred at WSMR during January 1993. These tests involved the launch of Lance missiles with a subsequent direction of F-15Es into the launch area for subsequent detection and simulated destruction of redeployed missile launchers, LLNL and SARA deployed SARN`s ELF sensors and various data acquisition systems for monitoring of basic phenomena. On 25 January 1993, a single missile launch allowed initial measurements of the phenomena and an assessment of appropriate sensor sensitivity settings as well as the appropriateness of the sensor deploymentmore » sites (e.g., with respect to man-made ELF sources such as power distributions and communication lines). On 27 January 1993, a measurement of a double launch of Lance missiles was performed. This technical report covers the results of the analysis of latter measurements. An attempt was made to measure low frequency electromagnetic signatures that may be produced during a missile launch. Hypothetical signature production mechanisms include: (1) Perturbations of the earth geo-potential during the launch of the missile. This signature may arise from the interaction of the ambient electric field with the conducting body of the missile as well as the partially ionized exhaust plume. (2) Production of spatial, charge sources from triboelectric-like mechanisms. Such effects may occur during the initial interaction of the missile plume with the ground material and lead to an initial {open_quotes}spike{close_quotes} output, Additionally, there may exist charge transfer mechanisms produced during the exhausting of the burnt fuel oxidizer.« less

PIV Measurements of the CEV Hot Abort Motor Plume for CFD Validation

NASA Technical Reports Server (NTRS)

Wernet, Mark; Wolter, John D.; Locke, Randy; Wroblewski, Adam; Childs, Robert; Nelson, Andrea

2010-01-01

NASA s next manned launch platform for missions to the moon and Mars are the Orion and Ares systems. Many critical aspects of the launch system performance are being verified using computational fluid dynamics (CFD) predictions. The Orion Launch Abort Vehicle (LAV) consists of a tower mounted tractor rocket tasked with carrying the Crew Module (CM) safely away from the launch vehicle in the event of a catastrophic failure during the vehicle s ascent. Some of the predictions involving the launch abort system flow fields produced conflicting results, which required further investigation through ground test experiments. Ground tests were performed to acquire data from a hot supersonic jet in cross-flow for the purpose of validating CFD turbulence modeling relevant to the Orion Launch Abort Vehicle (LAV). Both 2-component axial plane Particle Image Velocimetry (PIV) and 3-component cross-stream Stereo Particle Image Velocimetry (SPIV) measurements were obtained on a model of an Abort Motor (AM). Actual flight conditions could not be simulated on the ground, so the highest temperature and pressure conditions that could be safely used in the test facility (nozzle pressure ratio 28.5 and a nozzle temperature ratio of 3) were used for the validation tests. These conditions are significantly different from those of the flight vehicle, but were sufficiently high enough to begin addressing turbulence modeling issues that predicated the need for the validation tests.

Space Launch System Ascent Flight Control Design

NASA Technical Reports Server (NTRS)

Orr, Jeb S.; Wall, John H.; VanZwieten, Tannen S.; Hall, Charles E.

2014-01-01

A robust and flexible autopilot architecture for NASA's Space Launch System (SLS) family of launch vehicles is presented. The SLS configurations represent a potentially significant increase in complexity and performance capability when compared with other manned launch vehicles. It was recognized early in the program that a new, generalized autopilot design should be formulated to fulfill the needs of this new space launch architecture. The present design concept is intended to leverage existing NASA and industry launch vehicle design experience and maintain the extensibility and modularity necessary to accommodate multiple vehicle configurations while relying on proven and flight-tested control design principles for large boost vehicles. The SLS flight control architecture combines a digital three-axis autopilot with traditional bending filters to support robust active or passive stabilization of the vehicle's bending and sloshing dynamics using optimally blended measurements from multiple rate gyros on the vehicle structure. The algorithm also relies on a pseudo-optimal control allocation scheme to maximize the performance capability of multiple vectored engines while accommodating throttling and engine failure contingencies in real time with negligible impact to stability characteristics. The architecture supports active in-flight disturbance compensation through the use of nonlinear observers driven by acceleration measurements. Envelope expansion and robustness enhancement is obtained through the use of a multiplicative forward gain modulation law based upon a simple model reference adaptive control scheme.

Overview of Japanese Earth observation programs

NASA Astrophysics Data System (ADS)

Shimoda, Haruhisa; Honda, Yoshiaki

2017-09-01

Five programs, i.e. ASTER, GOSAT, GCOM-W1, GPM and ALOS-2 are going on in Japanese Earth Observation programs. ASTER has lost its short wave infrared channels. AMSR-E stopped its operation, but it started its operation from Sep. 2012 with slow rotation speed. It finally stopped on December 2015. GCOM-W1 was launched on 18, May, 2012 and is operating well as well as GOSAT. ALOS (Advanced Land Observing Satellite) was successfully launched on 24th Jan. 2006. ALOS carries three instruments, i.e., PRISM (Panchromatic Remote Sensing Instrument for Stereo Mapping), AVNIR-2 (Advanced Visible and Near Infrared Radiometer), and PALSAR (Phased Array L band Synthetic Aperture Radar). Unfortunately, ALOS has stopped its operation on 22nd, April, 2011 by power loss. GOSAT (Greenhouse Gas Observation Satellite) was successfully launched on 29, January, 2009. GOSAT carries 2 instruments, i.e. a green house gas sensor (TANSO-FTS) and a cloud/aerosol imager (TANSO-CAI). The main sensor is a Fourier transform spectrometer (FTS) and covers 0.76 to 15 μm region with 0.2 to 0.5 cm-1 resolution. SMILES (Superconducting Millimeter wave Emission Spectrometer) was launched on September 2009 to ISS and started the observation, but stopped its operation on April 2010. GPM (Global Precipitation Mission) core satellite was launched on Feb. 2014. GPM is a joint project with NASA and carries two instruments. JAXA has developed DPR (Dual frequency Precipitation Radar) which is a follow on of PR on TRMM. ALOS F/O satellites are divided into two satellites, i.e. SAR and optical satellites. The first one of ALOS F/O is called ALOS 2 and carries L-band SAR. It was launched on May 2014. JAXA is planning to launch follow on of optical sensors. It is now called Advanced Optical Satellite and the planned launch date is fiscal 2019. Other future satellites are GCOM-C1 (ADEOS-2 follow on), GOSAT-2 and EarthCare. GCOM-C1 will be launched on 2017 and GOSAT-2 will be launched on fiscal 2018. Another project is EarthCare. It is a joint project with ESA and JAXA is going to provide CPR (Cloud Profiling Radar). EarthCare will be launched on 2019.

Next generation earth-to-orbit space transportation systems: Unmanned vehicles and liquid/hybrid boosters

NASA Technical Reports Server (NTRS)

Hueter, Uwe

1991-01-01

The United States civil space effort when viewed from a launch vehicle perspective tends to categorize into pre-Shuttle and Shuttle eras. The pre-Shuttle era consisted of expendable launch vehicles where a broad set of capabilities were matured in a range of vehicles, followed by a clear reluctance to build on and utilize those systems. The Shuttle era marked the beginning of the U.S. venture into reusable space launch vehicles and the consolidation of launch systems used to this one vehicle. This led to a tremendous capability, but utilized men on a few missions where it was not essential and compromised launch capability resiliency in the long term. Launch vehicle failures, between the period of Aug. 1985 and May 1986, of the Titan 34D, Shuttle Challenger, and the Delta vehicles resulted in a reassessment of U.S. launch vehicle capability. The reassessment resulted in President Reagan issuing a new National Space Policy in 1988 calling for more coordination between Federal agencies, broadening the launch capabilities and preparing for manned flight beyond the Earth into the solar system. As a result, the Department of Defense (DoD) and NASA are jointly assessing the requirements and needs for this nations's future transportation system. Reliability/safety, balanced fleet, and resiliency are the cornerstone to the future. An insight is provided into the current thinking in establishing future unmanned earth-to-orbit (ETO) space transportation needs and capabilities. A background of previous launch capabilities, future needs, current and proposed near term systems, and system considerations to assure future mission need will be met, are presented. The focus is on propulsion options associated with unmanned cargo vehicles and liquid booster required to assure future mission needs will be met.

Automation Applications in an Advanced Air Traffic Management System : Volume 4A. Automation Requirements.

DOT National Transportation Integrated Search

1974-08-01

Volume 4 describes the automation requirements. A presentation of automation requirements is made for an advanced air traffic management system in terms of controller work force, computer resources, controller productivity, system manning, failure ef...

Draft environmental impact statement: Space Shuttle Advanced Solid Rocket Motor Program

NASA Technical Reports Server (NTRS)

1988-01-01

The proposed action is design, development, testing, and evaluation of Advanced Solid Rocket Motors (ASRM) to replace the motors currently used to launch the Space Shuttle. The proposed action includes design, construction, and operation of new government-owned, contractor-operated facilities for manufacturing and testing the ASRM's. The proposed action also includes transport of propellant-filled rocket motor segments from the manufacturing facility to the testing and launch sites and the return of used and/or refurbished segments to the manufacturing site.

A new look at oxygen production on Mars - In situ propellant production (ISPP)

NASA Technical Reports Server (NTRS)

Frisbee, Robert H.; French, James R., Jr.; Lawton, Emil A.

1987-01-01

Consideration is given to the technique of producing oxygen on Mars from CO2 in the Martian atmosphere via in situ propellent production (ISPP). Mission implications of ISPP for both manned and unmanned Mars missions are described as well as ways to improve system reliability. Technology options that improve reliability and reduce power requirements include the use of adsorption pumps and advanced zirconia membranes. It is concluded that both manned and unmanned missions will benefit greatly from ISPP, especially in the context of a permanent manned base on Mars.

Environmental control and life support technologies for advanced manned space missions

NASA Technical Reports Server (NTRS)

Powell, F. T.; Wynveen, R. A.; Lin, C.

1986-01-01

Regenerative environmental control and life support system (ECLSS) technologies are found by the present evaluation to have reached a degree of maturity that recommends their application to long duration manned missions. The missions for which regenerative ECLSSs are attractive in virtue of the need to avoid expendables and resupply requirements have been identified as that of the long duration LEO Space Station, long duration stays at GEO, a permanently manned lunar base (or colony), manned platforms located at the earth-moon libration points L4 or L5, a Mars mission, deep space exploration, and asteroid exploration. A comparison is made between nonregenerative and regenerative ECLSSs in the cases of 10 essential functions.

End of Life Disposal for Three Libration Point Missions through Manipulation of the Jacobi Constant and Zero Velocity Curves

NASA Technical Reports Server (NTRS)

Petersen, Jeremy; Brown, Jonathan

2015-01-01

Flight Dynamics Facility (FDF) located at NASA Goddard Space Flight Center (GSFC) provides the flight dynamics expertise for three Sun-Earth Moon L1 missions. Advanced Composition Explorer (ACE) launched August 1997 Solar and Heliospheric Observatory (SOHO) launched December 1995 Global Geospace Science WIND satellite launched November 1994 entered Lagrange point orbit in 2004.

KSC-97PC1238

NASA Image and Video Library

1997-08-13

The Advanced Composition Explorer (ACE) spacecraft is placed atop its launch vehicle at Launch Complex 17A. Scheduled for launch on a Delta II rocket from Cape Canaveral Air Station on Aug. 24, ACE will study low-energy particles of solar origin and high-energy galactic particles. The collecting power of instruments aboard ACE is 10 to 1,000 times greater than anything previously flown to collect similar data by NASA

KSC-97PC1240

NASA Image and Video Library

1997-08-13

The Advanced Composition Explorer (ACE) spacecraft is placed atop its launch vehicle at Launch Complex 17A. Scheduled for launch on a Delta II rocket from Cape Canaveral Air Station on Aug. 24, ACE will study low-energy particles of solar origin and high-energy galactic particles. The collecting power of instruments aboard ACE is 10 to 1,000 times greater than anything previously flown to collect similar data by NASA

Project Argo: The design and analysis of an all-propulsive and an aeroassisted version of a manned space transportation vehicle

NASA Technical Reports Server (NTRS)

1989-01-01

Project Argo is the design of a manned Space Transportation Vehicle (STV) that would transport payloads between LEO (altitude lying between 278 to 500 km above the Earth) and GEO (altitude is approximately 35,800 km above the Earth) and would be refueled and refurbished at the Space Station Freedom. Argo would be man's first space-based manned vehicle and would provide a crucial link to geosynchronous orbit where the vast majority of satellites are located. The vehicle could be built and launched shortly after the space station and give invaluable space experience while serving as a workhorse to deliver and repair satellites. Eventually, if a manned space station is established in GEO, then Argo could serve as the transport between the Space Station Freedom and a Geostation. If necessary, modifications could be made to allow the vehicle to reach the moon or possibly Mars. Project Argo is unique in that it consists of the design and comparison of two different concepts to accomplish the same mission. The first is an all-propulsive vehicle which uses chemical propulsion for all of its major maneuvers between LEO and GEO. The second is a vehicle that uses aeroassisted braking during its return from GEO to LEO by passing through the upper portions of the atmosphere.

Advanced Concept

NASA Image and Video Library

2008-02-15

Shown is a concept illustration of the Ares I crew launch vehicle, left, and Ares V cargo launch vehicle. Ares I will carry the Orion Crew Exploration Vehicle to space. Ares V will serve as NASA's primary vehicle for delivery of large-scale hardware to space.

A Shuttle Derived Vehicle launch system

NASA Technical Reports Server (NTRS)

Tewell, J. R.; Buell, D. N.; Ewing, E. S.

1982-01-01

This paper describes a Shuttle Derived Vehicle (SDV) launch system presently being studied for the NASA by Martin Marietta Aerospace which capitalizes on existing Shuttle hardware elements to provide increased accommodations for payload weight, payload volume, or both. The SDV configuration utilizes the existing solid rocket boosters, external tank and the Space Shuttle main engines but replaces the manned orbiter with an unmanned, remotely controlled cargo carrier. This cargo carrier substitution more than doubles the performance capability of the orbiter system and is realistically achievable for minimal cost. The advantages of the SDV are presented in terms of performance and economics. Based on these considerations, it is concluded that an unmanned SDV offers a most attractive complement to the present Space Transportation System.

Document handover of ISS Flight Control room to new Flight Control Room in old MCC

NASA Image and Video Library

2006-10-06

JSC2006-E-43860 (6 Oct. 2006)--- International Space Station flight controllers have this area as their new home with increased technical capabilities, more workspace and a long, distinguished history. The newly updated facility is just down the hall from its predecessor at NASA's Johnson Space Center, Houston. Known as Flight Control Room 1, it was first used to control a space flight 38 years ago, the mission of Apollo 7 launched Oct. 11, 1968. It was one of two control rooms for NASA's manned missions. The room it replaces in its new ISS role, designated the Blue Flight Control Room, had been in operation since the first station component was launched in 1998.

KSC-99pp0874

NASA Image and Video Library

1999-07-16

KENNEDY SPACE CENTER, FLA. -- NASA Administrator Daniel S. Goldin addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin "Buzz" Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7

A model for evaluation of satellite population management alternatives

NASA Astrophysics Data System (ADS)

Penny, R. E., Jr.; Jones, R. K.

1983-12-01

A Q-GERT model was developed to simulate the satellite environment, including the untracked man-made population, and to calculate a probability of collision for any satellite of interest. Provision for launches, explosions, collisions (including ASAT), retrieval, reposition, and decay was made. The model is structured to easily vary the rates at which these activities occur and to observe changes in the satellite population through which a satellite of interest must travel. Variance of the rates, and the resultant change in probability of collision allows evaluation of satellite population management alternatives such as reducing launch rates or increasing retrieval of spent, but still capable of exploding, satellites. The model is proposed for use by both the USAF SPACE COMMAND and NASA.

Evolution of Safety Analysis to Support New Exploration Missions

NASA Technical Reports Server (NTRS)

Thrasher, Chard W.

2008-01-01

NASA is currently developing the Ares I launch vehicle as a key component of the Constellation program which will provide safe and reliable transportation to the International Space Station, back to the moon, and later to Mars. The risks and costs of the Ares I must be significantly lowered, as compared to other manned launch vehicles, to enable the continuation of space exploration. It is essential that safety be significantly improved, and cost-effectively incorporated into the design process. This paper justifies early and effective safety analysis of complex space systems. Interactions and dependences between design, logistics, modeling, reliability, and safety engineers will be discussed to illustrate methods to lower cost, reduce design cycles and lessen the likelihood of catastrophic events.

NASA Administrator Dan Goldin speaks at Apollo 11 anniversary banquet.

NASA Technical Reports Server (NTRS)

1999-01-01

NASA Administrator Daniel S. Goldin addresses the audience at the Apollo 11 anniversary banquet honoring the Apollo team, the people who made the entire lunar landing program possible. The banquet was held in the Apollo/Saturn V Center, part of the KSC Visitor Complex. This is the 30th anniversary of the Apollo 11 launch and moon landing, July 16 and July 20, 1969. Among the guests at the banquet were former Apollo astronauts are Neil A. Armstrong and Edwin 'Buzz' Aldrin who flew on Apollo 11, the launch of the first moon landing; Gene Cernan, who flew on Apollo 10 and 17 and was the last man to walk on the moon; and Walt Cunningham, who flew on Apollo 7.

Advanced Launch System advanced development oxidizer turbopump program: Technical implementation plan

NASA Technical Reports Server (NTRS)

Ferlita, F.

1989-01-01

The Advanced Launch Systems (ALS) Advanced Development Oxidizer Turbopump Program has designed, fabricated and demonstrated a low cost, highly reliable oxidizer turbopump for the Space Transportation Engine that minimizes the recurring cost for the ALS engines. Pratt and Whitney's (P and W's) plan for integrating the analyses, testing, fabrication, and other program efforts is addressed. This plan offers a comprehensive description of the total effort required to design, fabricate, and test the ALS oxidizer turbopump. The proposed ALS oxidizer turbopump reduces turbopump costs over current designs by taking advantage of design simplicity and state-of-the-art materials and producibility features without compromising system reliability. This is accomplished by selecting turbopump operating conditions that are within known successful operating regions and by using proven manufacturing techniques.

Automation Applications in an Advanced Air Traffic Management System : Volume 4B. Automation Requirements (Concluded)

DOT National Transportation Integrated Search

1974-08-01

Volume 4 describes the automation requirements. A presentation of automation requirements is made for an advanced air traffic management system in terms of controller work for-e, computer resources, controller productivity, system manning, failure ef...

Work, Leisure Time and Adult Education in Technically Advanced Industrial Countries.

ERIC Educational Resources Information Center

European Centre for Leisure and Education, Prague (Czechoslovakia).

An outline of the increasing amount of change required of modern man, specifically in Czechoslovakia, to cope with the demands of a rapidly advancing technology is presented. Consideration is given to leisure time, work requirements, and educational needs. (CK)