IAL SPACE: A test laboratory for the ISO cryogenic payload

NASA Technical Reports Server (NTRS)

Cucchiaro, A.; Henrist, M.; Macau, J. P.; Ninane, N.; Blanpain, R.

1990-01-01

The ESA Infrared Space Observatory (ISO) satellite is a 3 axes pointed platform designed to make accurate pointed observations of astronomical objects and sources in the wavelength range between 2.5 and 200 microns. ISO is composed of a service module and a payload module which is a large cylindrical vacuum vessel. The vessel is in fact a cryostat (capacity of 2250 l of liquid He II) which contains the telescope and the four focal scientific instruments. The latter being cooled up to a temperature less than 4 K. The qualification of the payload requires the measurement respectively of: the image quality of the telescope through wave front error (WFE) measurements; and the optical alignment of the scientific instruments with respect to the telescope axis and the telescope focus, and this under cryogenic conditions. Consequently, since 1988, the FOCAL 5 IAL Space facility has been upgraded in order to perform the cryogenic optical tests of the ISO optical subsystems.

Geostationary payload concepts for personal satellite communications

NASA Technical Reports Server (NTRS)

Benedicto, J.; Rinous, P.; Roberts, I.; Roederer, A.; Stojkovic, I.

1993-01-01

This paper reviews candidate satellite payload architectures for systems providing world-wide communication services to mobile users equipped with hand-held terminals based on large geostationary satellites. There are a number of problems related to the payload architecture, on-board routing and beamforming, and the design of the S-band Tx and L-band Rx antenna and front ends. A number of solutions are outlined, based on trade-offs with respect to the most significant performance parameters such as capacity, G/T, flexibility of routing traffic to beams and re-configuration of the spot-beam coverage, and payload mass and power. Candidate antenna and front-end configurations were studied, in particular direct radiating arrays, arrays magnified by a reflector and active focused reflectors with overlapping feed clusters for both transmit (multimax) and receive (beam synthesis). Regarding the on-board routing and beamforming sub-systems, analog techniques based on banks of SAW filters, FET or CMOS switches and cross-bar fixed and variable beamforming are compared with a hybrid analog/digital approach based on Chirp Fourier Transform (CFT) demultiplexer combined with digital beamforming or a fully digital processor implementation, also based on CFT demultiplexing.

Design and analysis of truck body for increasing the payload capacity

NASA Astrophysics Data System (ADS)

Vamshi Krishna, K.; Yugandhar Reddy, K.; Venugopal, K.; Ravi, K.

2017-11-01

Truck industry is a major source of transportation in India. With an average truck travelling about 300 kilometers per day [1], every kilogram of truck weight is of concern to the industry in order to get the best out of the truck. The main objective of this project is to increase the payload capacity of automotive truck body. Every kilogram of increased vehicle weight will decrease the vehicle payload capacity in turn increasing the manufacturing cost and reducing the fuel economy by increase the fuel consumption. With the intension of weight reduction, standard truck body has been designed and analyzed in ANSYS software. C-cross section beams were used instead of conventional rectangular box sections to reduce the weight of the body. Light-weight Aluminum alloy Al 6061 T6 is used to increase the payload capacity. The strength of the Truck platform is monitored in terms of deformation and stress concentration. These parameters will be obtained in structural analysis test condition environment. For reducing the stress concentration the concept of beams of uniform strength is used. Accordingly necessary modifications are done so that the optimized model has a better stress distribution and much lesser weight compared to the conventional model. The results obtained by analyzing the modified model are compared with the standard model.

Next generation sensing platforms for extended deployments in large-scale, multidisciplinary, adaptive sampling and observational networks

NASA Astrophysics Data System (ADS)

Cross, J. N.; Meinig, C.; Mordy, C. W.; Lawrence-Slavas, N.; Cokelet, E. D.; Jenkins, R.; Tabisola, H. M.; Stabeno, P. J.

2016-12-01

New autonomous sensors have dramatically increased the resolution and accuracy of oceanographic data collection, enabling rapid sampling over extremely fine scales. Innovative new autonomous platofrms like floats, gliders, drones, and crawling moorings leverage the full potential of these new sensors by extending spatiotemporal reach across varied environments. During 2015 and 2016, The Innovative Technology for Arctic Exploration Program at the Pacific Marine Environmental Laboratory tested several new types of fully autonomous platforms with increased speed, durability, and power and payload capacity designed to deliver cutting-edge ecosystem assessment sensors to remote or inaccessible environments. The Expendable Ice-Tracking (EXIT) gloat developed by the NOAA Pacific Marine Environmental Laboratory (PMEL) is moored near bottom during the ice-free season and released on an autonomous timer beneath the ice during the following winter. The float collects a rapid profile during ascent, and continues to collect critical, poorly-accessible under-ice data until melt, when data is transmitted via satellite. The autonomous Oculus sub-surface glider developed by the University of Washington and PMEL has a large power and payload capacity and an enhanced buoyancy engine. This 'coastal truck' is designed for the rapid water column ascent required by optical imaging systems. The Saildrone is a solar and wind powered ocean unmanned surface vessel (USV) developed by Saildrone, Inc. in partnership with PMEL. This large-payload (200 lbs), fast (1-7 kts), durable (46 kts winds) platform was equipped with 15 sensors designed for ecosystem assessment during 2016, including passive and active acoustic systems specially redesigned for autonomous vehicle deployments. The senors deployed on these platforms achieved rigorous accuracy and precision standards. These innovative platforms provide new sampling capabilities and cost efficiencies in high-resolution sensor deployment, including reconnaissance for annual fisheries and marine mammal surveys; better linkages between sustained observing platforms; and adaptive deployments that can easily target anomalies as they arise.

Ultrasound-propelled nanoporous gold wire for efficient drug loading and release.

PubMed

Garcia-Gradilla, Victor; Sattayasamitsathit, Sirilak; Soto, Fernando; Kuralay, Filiz; Yardımcı, Ceren; Wiitala, Devan; Galarnyk, Michael; Wang, Joseph

2014-10-29

Ultrasound (US)-powered nanowire motors based on nanoporous gold segment are developed for increasing the drug loading capacity. The new highly porous nanomotors are characterized with a tunable pore size, high surface area, and high capacity for the drug payload. These nanowire motors are prepared by template membrane deposition of a silver-gold alloy segment followed by dealloying the silver component. The drug doxorubicin (DOX) is loaded within the nanopores via electrostatic interactions with an anionic polymeric coating. The nanoporous gold structure also facilitates the near-infrared (NIR) light controlled release of the drug through photothermal effects. Ultrasound-driven transport of the loaded drug toward cancer cells followed by NIR-light triggered release is illustrated. The incorporation of the nanoporous gold segment leads to a nearly 20-fold increase in the active surface area compared to common gold nanowire motors. It is envisioned that such US-powered nanomotors could provide a new approach to rapidly and efficiently deliver large therapeutic payloads in a target-specific manner. © 2014 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

Large capacity oblique all-wing transport aircraft

NASA Technical Reports Server (NTRS)

Galloway, Thomas L.; Phillips, James A.; Kennelly, Robert A., Jr.; Waters, Mark H.

1996-01-01

Dr. R. T. Jones first developed the theory for oblique wing aircraft in 1952, and in subsequent years numerous analytical and experimental projects conducted at NASA Ames and elsewhere have established that the Jones' oblique wing theory is correct. Until the late 1980's all proposed oblique wing configurations were wing/body aircraft with the wing mounted on a pivot. With the emerging requirement for commercial transports with very large payloads, 450-800 passengers, Jones proposed a supersonic oblique flying wing in 1988. For such an aircraft all payload, fuel, and systems are carried within the wing, and the wing is designed with a variable sweep to maintain a fixed subsonic normal Mach number. Engines and vertical tails are mounted on pivots supported from the primary structure of the wing. The oblique flying wing transport has come to be known as the Oblique All-Wing (OAW) transport. This presentation gives the highlights of the OAW project that was to study the total concept of the OAW as a commercial transport.

Geostationary platform systems concepts definition study. Volume 2A: Appendixes, book 1

NASA Technical Reports Server (NTRS)

1980-01-01

Appendixes addressing various aspects of a geostationary platform concepts definition study are given. Communication platform traffic requirements, video conferencing forecast, intersatellite link capacity requirements, link budgets, payload data, payload assignments, and platform synthesis are addressed.

Broad Area Wireless Networking Via High Altitude Platforms

DTIC Science & Technology

2013-06-01

35  Figure 12.  Sprint WiMAX handset. From [24...altitude of 21K meters , a payload capacity of 100 kg, and 1000 watts of onboard power for payload requirements. They also developed a series of...providing 24-hour coverage. The balloons are launched with a recoverable payload and operated at an altitude of 24K–30K meters to provide a coverage area

Advanced payload concepts and system architecture for emerging services in Indian National Satellite Systems

NASA Astrophysics Data System (ADS)

Balasubramanian, E. P.; Rao, N. Prahlad; Sarkar, S.; Singh, D. K.

2008-07-01

Over the past two decades Indian Space Research Organization (ISRO) has developed and operationalized satellites to generate a large capacity of transponders for telecommunication service use in INSAT system. More powerful on-board transmitters are built to usher-in direct-to-home broadcast services. These have transformed the Satcom application scenario in the country. With the proliferation of satellite technology, a shift in the Indian market is witnessed today in terms of demand for new services like Broadband Internet, Interactive Multimedia, etc. While it is imperative to pay attention to market trends, ISRO is also committed towards taking the benefits of technological advancement to all round growth of our population, 70% of which dwell in rural areas. The initiatives already taken in space application related to telemedicine, tele-education and Village Resource Centres are required to be taken to a greater height of efficiency. These targets pose technological challenges to build a large capacity and cost-effective satellite system. This paper addresses advanced payload concepts and system architecture along with the trade-off analysis on design parameters in proposing a new generation satellite system capable of extending the reach of the Indian broadband structure to individual users, educational and medical institutions and enterprises for interactive services. This will be a strategic step in the evolution of INSAT system to employ advanced technology to touch every human face of our population.

Targeted Drug-Carrying Bacteriophages as Antibacterial Nanomedicines▿

PubMed Central

Yacoby, Iftach; Bar, Hagit; Benhar, Itai

2007-01-01

While the resistance of bacteria to traditional antibiotics is a major public health concern, the use of extremely potent antibacterial agents is limited by their lack of selectivity. As in cancer therapy, antibacterial targeted therapy could provide an opportunity to reintroduce toxic substances to the antibacterial arsenal. A desirable targeted antibacterial agent should combine binding specificity, a large drug payload per binding event, and a programmed drug release mechanism. Recently, we presented a novel application of filamentous bacteriophages as targeted drug carriers that could partially inhibit the growth of Staphylococcus aureus bacteria. This partial success was due to limitations of drug-loading capacity that resulted from the hydrophobicity of the drug. Here we present a novel drug conjugation chemistry which is based on connecting hydrophobic drugs to the phage via aminoglycoside antibiotics that serve as solubility-enhancing branched linkers. This new formulation allowed a significantly larger drug-carrying capacity of the phages, resulting in a drastic improvement in their performance as targeted drug-carrying nanoparticles. As an example for a potential systemic use for potent agents that are limited for topical use, we present antibody-targeted phage nanoparticles that carry a large payload of the hemolytic antibiotic chloramphenicol connected through the aminoglycoside neomycin. We demonstrate complete growth inhibition toward the pathogens Staphylococcus aureus, Streptococcus pyogenes, and Escherichia coli with an improvement in potency by a factor of ∼20,000 compared to the free drug. PMID:17404004

JEFF: Air transport system design simulation

NASA Technical Reports Server (NTRS)

1992-01-01

Jeff is a remotely piloted vehicle designed by the Blue Team, a division of AE441, Inc., to fulfill the mission proposed by G-Dome Enterprises: to build a cost efficient aircraft to service Aeroworld with overnight cargo delivery. The design of Jeff was most significantly influenced by the need to minimize costs. This objective was pursued by building fewer large planes as opposed to many small planes. Thus, by building an aircraft with a large payload capacity, G-Dome Enterprises will be able to minimize the large costs and the large number of cycles that are associated with a large fleet. Another factor which had a significant influence on our design was the constraint that our design had to fit into a 2'x2'x5' storage container. This constraint meant that unless we wanted to build foldable wings that Jeff's span would be limited to 10 feet. Since this was not enough lifting surface to suit our needs a canard configuration was chosen to get the needed lifting surface and avoid the structural dilemma of foldable wings. The aircraft is constructed mainly of balsa, with spruce wing and canard spars and a monokote covering. It was designed to support a maximum payload weight of 35 oz. (total aircraft weight of 108 oz.) and withstand a maximum load factor of 2.5.

KSC-06pd2454

NASA Image and Video Library

2006-11-06

KENNEDY SPACE CENTER, FLA. -- Lamps spotlight the payload canister transporter as it slowly carries its cargo past the Vehicle Assembly Building on the road to Launch Pad 39B for mission STS-116. Inside the canister are the SPACEHAB module and the port 5 truss segment, which will be moved into the payload changeout room at the pad and transferred into Space Shuttle Discovery's payload bay once the vehicle has rolled out to the pad. The payload canister is 65 feet long, 18 feet wide and 18 feet, 7 inches high. It has the capability to carry vertically or horizontally processed payloads up to 15 feet in diameter and 60 feet long, matching the capacity of the orbiter payload bay. It can carry payloads weighing up to 65,000 pounds. Clamshell-shaped doors at the top of the canister operate like the orbiter payload bay doors, with the same allowable clearances. Photo credit: NASA/George Shelton

A-2000: Close air support aircraft design team

NASA Technical Reports Server (NTRS)

Carrannanto, Paul; Lim, Don; Lucas, Evangeline; Risse, Alan; Weaver, Dave; Wikse, Steve

1991-01-01

The US Air Force is currently faced with the problem of providing adequate close air support for ground forces. Air response to troops engaged in combat must be rapid and devastating due to the highly fluid battle lines of the future. The A-2000 is the result of a study to design an aircraft to deliver massive fire power accurately. The low cost A-2000 incorporates: large weapons payload; excellent maneuverability; all weather and terrain following capacity; redundant systems; and high survivability.

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

NASA Technical Reports Server (NTRS)

Napp, Robert

1994-01-01

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

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

NASA Technical Reports Server (NTRS)

May, Todd A.; Creech, Stephen D.

2012-01-01

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

Design, testing, and installation of a high-precision hexapod for the Hobby-Eberly Telescope dark energy experiment (HETDEX)

NASA Astrophysics Data System (ADS)

Zierer, Joseph J.; Beno, Joseph H.; Weeks, Damon A.; Soukup, Ian M.; Good, John M.; Booth, John A.; Hill, Gary J.; Rafal, Marc D.

2012-09-01

Engineers from The University of Texas at Austin Center for Electromechanics and McDonald Observatory have designed, built, and laboratory tested a high payload capacity, precision hexapod for use on the Hobby-Eberly telescope as part of the HETDEX Wide Field Upgrade (WFU). The hexapod supports the 4200 kg payload which includes the wide field corrector, support structure, and other optical/electronic components. This paper provides a recap of the hexapod actuator mechanical and electrical design including a discussion on the methods used to help determine the actuator travel to prevent the hexapod payload from hitting any adjacent, stationary hardware. The paper describes in detail the tooling and methods used to assemble the full hexapod, including many of the structures and components which are supported on the upper hexapod frame. Additionally, details are provided on the installation of the hexapod onto the new tracker bridge, including design decisions that were made to accommodate the lift capacity of the Hobby- Eberly Telescope dome crane. Laboratory testing results will be presented verifying that the performance goals for the hexapod, including positioning, actuator travel, and speeds have all been achieved. This paper may be of interest to mechanical and electrical engineers responsible for the design and operations of precision hardware on large, ground based telescopes. In summary, the hexapod development cycle from the initial hexapod actuator performance requirements and design, to the deployment and testing on the newly designed HET tracker system is all discussed, including lessons learned through the process.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

At the SPACEHAB Facility, STS-96 Mission Specialist Ellen Ochoa and Commander Kent Rominger pause during a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station. Other crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Tamara Jernigan, Dan Barry, Julie Payette and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m. EDT.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 Mission Specialist Julie Payette closes a container, part of the equipment to be carried on the SPACEHAB and mission STS-96. She and other crew members Commander Kent Rominger, Pilot Rick Husband, and Mission Speciaists Ellen Ochoa, Tamara Jernigan, Dan Barry and Valery Tokarev of Russia are at KSC for a payload Interface Verification Test for the upcoming mission to the International Space Station . Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

Posing on the platform next to the SPACEHAB Logistics Double Module in the SPACEHAB Facility are the STS-96 crew (from left) Mission Specialists Dan Barry, Tamara Jernigan, Valery Tokarev of Russia, and Julie Payette; Pilot Rick Husband; Mission Specialist Ellen Ochoa; and Commander Kent Rominger. The crew is at KSC for a payload Interface Verification Test for their upcoming mission to the International Space Station. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

At the SPACEHAB Facility, STS-96 Mission Specialist Ellen Ochoa and Commander Kent Rominger smile for the camera during a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station. Other crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Tamara Jernigan, Dan Barry, Julie Payette and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m. EDT.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) for the upcoming mission to the International Space Station , Chris Jaskolka of Boeing points out a piece of equipment in the SPACEHAB module to STS-96 Commander Kent Rominger, Mission Specialist Ellen Ochoa and Pilot Rick Husband. Other crew members visiting KSC for the IVT are Mission Specialists Tamara Jernigan, Dan Barry, Julie Payette and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m. EDT.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 Mission Specialists Dan Barry and Tamara Jernigan discuss procedures during a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station. Other STS-96 crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband and Mission Specialists Ellen Ochoa, Julie Payette and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, James Behling, with Boeing, talks about equipment for mission STS-96 during a payload Interface Verification Test (IVT). Watching are (from left) Mission Specialists Ellen Ochoa, Julie Payette and Dan Berry, and Pilot Rick Husband. Other STS-96 crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station, STS-96 Mission Specialists Julie Payette, Dan Barry, and Valery Tokarev of Russia, look at a Sequential Shunt Unit in the SPACEHAB Facility. Other crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband, and Mission Specialists Ellen Ochoa and Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m. EDT.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station are (left to right) Mission Specialists Valery Tokarev, Julie Payette (holding a lithium hydroxide canister) and Dan Barry. Other crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband and Mission Specialists Ellen Ochoa and Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, the STS-96 crew looks over equipment during a payload Interface Verification Test for the upcoming mission to the International Space Station. From left are Commander Kent Rominger, Mission Specialists Tamara Jernigan and Valery Tokarev of Russia, Pilot Rick Husband, and Mission Specialists Ellen Ochoa and Julie Payette (backs to the camera). They are listening to Chris Jaskolka of Boeing talk about the equipment. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m. EDT.

Large Payload Ground Transportation and Test Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.

2016-01-01

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

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of the orbiter Atlantis, STS-98 Commander Ken Cockrell (center) and Mission Specialist Marsha Ivins (right) look over the mission payload, the U.S. Lab Destiny (in the background). The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of Atlantis, two workers (background and right) watch STS-98 Robert Curbeam practice work he will do on the U.S. Lab Destiny in space. The mission payload, Destiny is a key element in the construction of the International Space Station. The lab is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. The STS-98 crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

Space Station accommodation of attached payloads

NASA Technical Reports Server (NTRS)

Browning, Ronald K.; Gervin, Janette C.

1987-01-01

The Attached Payload Accommodation Equipment (APAE), which provides the structure to attach payloads to the Space Station truss assembly, to access Space Station resources, and to orient payloads relative to specified targets, is described. The main subelements of the APAE include a station interface adapter, payload interface adapter, subsystem support module, contamination monitoring system, payload pointing system, and attitude determination system. These components can be combined to provide accommodations for small single payloads, small multiple payloads, large self-supported payloads, carrier-mounted payloads, and articulated payloads. The discussion also covers the power, thermal, and data/communications subsystems and operations.

Hydraulic manipulator research at ORNL

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

Kress, R.L.; Jansen, J.F.; Love, L.J.

1997-03-01

Recently, task requirements have dictated that manipulator payload capacity increase to accommodate greater payloads, greater manipulator length, and larger environmental interaction forces. General tasks such as waste storage tank cleanup and facility dismantlement and decommissioning require manipulator life capacities in the range of hundreds of pounds rather than tens of pounds. To meet the increased payload capacities demanded by present-day tasks, manipulator designers have turned once again to hydraulics as a means of actuation. In order to successfully design, build, and deploy a new hydraulic manipulator (or subsystem), sophisticated modeling, analysis, and control experiments are usually needed. Oak Ridge Nationalmore » Laboratory (ORNL) has a history of projects that incorporate hydraulics technology, including mobile robots, teleoperated manipulators, and full-scale construction equipment. In addition, to support the development and deployment of new hydraulic manipulators, ORNL has outfitted a significant experimental laboratory and has developed the software capability for research into hydraulic manipulators, hydraulic actuators, hydraulic systems, modeling of hydraulic systems, and hydraulic controls. The purpose of this article is to describe the past hydraulic manipulator developments and current hydraulic manipulator research capabilities at ORNL. Included are example experimental results from ORNL`s flexible/prismatic test stand.« less

Potential Large Decadal Missions Enabled by Nasas Space Launch System

NASA Technical Reports Server (NTRS)

Stahl, H. Philip; Hopkins, Randall C.; Schnell, Andrew; Smith, David Alan; Jackman, Angela; Warfield, Keith R.

2016-01-01

Large space telescope missions have always been limited by their launch vehicle's mass and volume capacities. The Hubble Space Telescope (HST) was specifically designed to fit inside the Space Shuttle and the James Webb Space Telescope (JWST) is specifically designed to fit inside an Ariane 5. Astrophysicists desire even larger space telescopes. NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. NASA's "Planning for the 2020 Decadal Survey" calls for a Habitable Exoplanet Imaging (HabEx) and a LUVOIR as well as Far-IR and an X-Ray Surveyor missions. Packaging larger space telescopes into existing launch vehicles is a significant engineering complexity challenge that drives cost and risk. NASA's planned Space Launch System (SLS), with its 8 or 10-m diameter fairings and ability to deliver 35 to 45-mt of payload to Sun-Earth-Lagrange-2, mitigates this challenge by fundamentally changing the design paradigm for large space telescopes. This paper reviews the mass and volume capacities of the planned SLS, discusses potential implications of these capacities for designing large space telescope missions, and gives three specific mission concept implementation examples: a 4-m monolithic off-axis telescope, an 8-m monolithic on-axis telescope and a 12-m segmented on-axis telescope.

Potential large missions enabled by NASA's space launch system

NASA Astrophysics Data System (ADS)

Stahl, H. Philip; Hopkins, Randall C.; Schnell, Andrew; Smith, David A.; Jackman, Angela; Warfield, Keith R.

2016-07-01

Large space telescope missions have always been limited by their launch vehicle's mass and volume capacities. The Hubble Space Telescope (HST) was specifically designed to fit inside the Space Shuttle and the James Webb Space Telescope (JWST) is specifically designed to fit inside an Ariane 5. Astrophysicists desire even larger space telescopes. NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. NASA's "Planning for the 2020 Decadal Survey" calls for a Habitable Exoplanet Imaging (HabEx) and a LUVOIR as well as Far-IR and an X-Ray Surveyor missions. Packaging larger space telescopes into existing launch vehicles is a significant engineering complexity challenge that drives cost and risk. NASA's planned Space Launch System (SLS), with its 8 or 10-m diameter fairings and ability to deliver 35 to 45-mt of payload to Sun-Earth-Lagrange-2, mitigates this challenge by fundamentally changing the design paradigm for large space telescopes. This paper reviews the mass and volume capacities of the planned SLS, discusses potential implications of these capacities for designing large space telescope missions, and gives three specific mission concept implementation examples: a 4-m monolithic off-axis telescope, an 8-m monolithic on-axis telescope and a 12-m segmented on-axis telescope.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Along with Scott Thurston (left), of the VITT office, members of the STS-98 crew Mission Specialist Robert Curbeam, Commander Ken Cockrell and Mission Specialist Marsha Ivins are in Atlantis''' payload bay to check out their mission payload, the U.S. Lab Destiny. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

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

NASA Technical Reports Server (NTRS)

Thompson, Sean W.; Lake, Robert E.

2014-01-01

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

Parameter design and experimental study of a bifunctional isolator for optical payload protection and stabilization

NASA Astrophysics Data System (ADS)

Wang, Guang-yuan; Guan, Xin; Cao, Dong-jing; Tang, Shao-fan; Chen, Xiang; Liang, Lu; Zheng, Gang-tie

2017-11-01

With the raise of resolution, optical payloads are becoming increasingly sensitive to satellite jitter. An approach where the entire spacecraft is pointed with great accuracy requires sophisticated and expensive bus design. In an effort to lower the overall cost of space missions that require highly stable line-of-sight pointing, a method of separating the bus and the payload with low frequency isolators is proposed. This isolation system can block the transmission of disturbance and allow relatively large bus motion. However, if the isolator is linear then there is a trade-off between isolation and static deflection as the launch and the on-orbit stage have difference requirements on the isolation frequency. Otherwise, an extra locking system should be appended to protect the payload before getting into orbit, as the STABLE isolation system[1] and the MIM isolation system[2] did. To overcome this limitation, an alternative approach is to design a nonlinear isolator with high-static stiffness during launch and low dynamic stiffness on orbit. Several specially designed nonlinear isolators have achieved low dynamic stiffness with large static load capacity. Virgin[3] considered a structure made from a highly deformed elastic element to achieve a softening spring. Platus[4] exploited the buckling of beams under axial load in a specific configuration to achieve a negative stiffness in combination with a positive stiffness, and hence low-dynamic stiffness. Others have achieved the same by connecting linear springs with positive stiffness in parallel with elements of negative stiffness[5] [7]. In the present study, a bifunctional isolator has been developed for optical payloads. The isolator have good performance both during launch and on orbit because of its specially designed nonlinear stiffness and damping. The isolator works in a linear part with low stiffness and small damping ratio under the micro-vibration and microgravity on orbit. The transmissibility requirement and the displacement restriction during launch are satisfied by tuning the nonlinear stiffness and damping parameters. A group of sample isolators are designed tested both statically and dynamically.

Way Forward for High Performance Payload Processing Development

NASA Astrophysics Data System (ADS)

Notebaert, Olivier; Franklin, John; Lefftz, Vincent; Moreno, Jose; Patte, Mathieu; Syed, Mohsin; Wagner, Arnaud

2012-08-01

Payload processing is facing technological challenges due to the large increase of performance requirements of future scientific, observation and telecom missions as well as the future instruments technologies capturing much larger amount of data. For several years, with the perspective of higher performance together with the planned obsolescence of solutions covering the current needs, ESA and the European space industry has been developing several technology solutions. Silicon technologies, radiation mitigation techniques and innovative functional architectures are developed with the goal of designing future space qualified processing devices with a much higher level of performance than today. The fast growing commercial market application have developed very attractive technologies but which are not fully suitable with respect to their tolerance to space environment. Without the financial capacity to explore and develop all possible technology paths, a specific and global approach is required to cover the future mission needs and their necessary performance targets with effectiveness.The next sections describe main issues and priorities and provides further detailed relevant for this approach covering the high performance processing technology.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- STS-98 Mission Specialist Marsha Ivins (center, pointing) checks out the U.S. Lab Destiny in the payload bay of the orbiter Atlantis. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. Destiny, a key element in the construction of the International Space Station, is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, the STS-96 crew looks at equipment as part of a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station . From left are Mission Specialist Ellen Ochoa (behind the opened storage cover ), Commander Kent Rominger, Pilot Rick Husband (holding a lithium hydroxide canister) and Mission Specialists Dan Barry, Valery Tokarev of Russia and Julie Payette. In the background is TTI interpreter Valentina Maydell. The other crew member at KSC for the IVT is Mission Specialist Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 crew members look over equipment during a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station. From left are Khristal Parker, with Boeing; Mission Specialist Dan Barry, Pilot Rick Husband, Mission Specialist Tamara Jernigan, and at the far right, Mission Specialist Julie Payette. An unidentified worker is in the background. Also at KSC for the IVT are Commander Kent Rominger and Mission Specialists Ellen Ochoa and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, (left to right) STS-96 Pilot Rick Husband and Mission Specialists Julie Payette and Ellen Ochoa work the straps on the Sequential Shunt Unit (SSU) in front of them. The STS-96 crew is at KSC for a payload Interface Verification Test (IVT) for its upcoming mission to the International Space Station . Other crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan, Dan Barry and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (left) and Commander Kent Rominger (second from right) listen to Lynn Ashby (far right), with JSC, talking about the SPACEHAB equipment in front of them during a payload Interface Verification Test (IVT). In the background behind Tokarev is TTI interpreter Valentina Maydell. Other STS-96 crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Dan Barry, Ellen Ochoa, Tamara Jernigan and Julie Payette. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (second from left) and Commander Kent Rominger learn about the Sequential Shunt Unit (SSU) in front of them from Lynn Ashby (far right), with Johnson Space Center. At the far left looking on is TTI interpreter Valentina Maydell. Other crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Ellen Ochoa, Tamara Jernigan, Dan Barry and Julie Payette. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev (in foreground) of the Russian Space Agency closes a container, part of the equipment that will be in the SPACEHAB module on mission STS-96. Behind Tokarev are Pilot Rick Husband (left) and Mission Specialist Dan Barry (right). Other crew members at KSC for a payload Interface Verification Test for the upcoming mission to the International Space Station are Commander Kent Rominger and Mission Specialists Ellen Ochoa, Tamara Jernigan and Julie Payette. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Mission Specialist Tamara Jernigan checks over instructions while Mission Specialist Dan Barry looks up from the Sequential Shunt Unit (SSU) in front of him to other equipment Lynn Ashby (right), with Johnson Space Center, is pointing at. Other crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband, and Mission Specialists Ellen Ochoa, Julie Payette and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Pilot Rick Husband and Mission Specialist Ellen Ochoa (on the left) and Mission Specialist Julie Payette (on the far right) listen to Khristal Parker (second from right), with Boeing, explain about the equipment in front of them. Other crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan, Dan Barry and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station are (kneeling) STS-96 Mission Specialists Julie Payette and Ellen Ochoa, Pilot Rick Husband, and (standing at right) Mission Specialist Dan Barry. At the left is James Behling, with Boeing, explaining some of the equipment that will be on board STS-96. Other STS-96 crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan and Valery Tokarev of Russia. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

The first dedicated life sciences mission - Spacelab 4

NASA Astrophysics Data System (ADS)

Cramer, D. R.; Reid, D. H.; Klein, H. P.

Spacelab is a large versatile laboratory carried in the bay of the Shuttle Orbiter. The first Spacelab mission dedicated entirely to Life Sciences is known as Spacelab 4. It is scheduled for launch in late 1985 and will remain aloft for seven days. This payload consists of 25 tentatively selected investigations combined into a comprehensive integrated exploration of the effects of acute weightlessness on living systems. An emphasis is placed on studying physiological changes that have been previously observed in manned space flight. This payload has complementary designs in the human and animal investigations in order to validate animal models of human physiology in weightlessness. The experimental subjects include humans, squirrel monkeys, laboratory rats, several species of plants, and frog eggs. The primary scientific objectives include study of the acute cephalic fluid shift, cardiovascular adaptation to weightlessness, including postflight reductions in orthostatic tolerance and exercise capacity, and changes in vestibular function, including space motion sickness, associated with weightlessness. Secondary scientific objectives include the study of red cell mass reduction, negative nitrogen balance, altered calcium metabolism, suppressed in vitro lymphocyte reactivity, gravitropism and photropism in plants, and fertilization and early development in frog eggs. The rationale behind this payload, the selection process, and details of the individual investigations are presented in this paper.

Large-payload earth-orbit transportation with electric propulsion

NASA Technical Reports Server (NTRS)

Stearns, J. W.

1976-01-01

Economical unmanned earth orbit transportation for large payloads is evaluated. The high exhaust velocity achievable with electric propulsion is attractive because it minimizes the propellant that must be carried to low earth orbit. Propellant transport is a principal cost item. Electric propulsion subsystems utilizing advanced ion thrusters are compared to magnetoplasmadynamic (MPD) thrust subsystems. For very large payloads, a large lift vehicle is needed to low earth orbit, and argon propellant is required for electric propulsion. Under these circumstances, the MPD thruster is shown to be desirable over the ion thruster for earth orbit transportation.

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

DTIC Science & Technology

1979-08-01

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

Mobile User Objective System (MUOS)

DTIC Science & Technology

2013-12-01

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

Mars Mobile Lander Systems for 2005 and 2007 Launch Opportunities

NASA Technical Reports Server (NTRS)

Sabahi, D.; Graf, J. E.

2000-01-01

A series of Mars missions are proposed for the August 2005 launch opportunity on a medium class Evolved Expendable Launch Vehicle (EELV) with a injected mass capability of 2600 to 2750 kg. Known as the Ranger class, the primary objective of these Mars mission concepts are: (1) Deliver a mobile platform to Mars surface with large payload capability of 150 to 450 kg (depending on launch opportunity of 2005 or 2007); (2) Develop a robust, safe, and reliable workhorse entry, descent, and landing (EDL) capability for landed mass exceeding 750 kg; (3) Provide feed forward capability for the 2007 opportunity and beyond; and (4) Provide an option for a long life telecom relay orbiter. A number of future Mars mission concepts desire landers with large payload capability. Among these concepts are Mars sample return (MSR) which requires 300 to 450 kg landed payload capability to accommodate sampling, sample transfer equipment and a Mars ascent vehicle (MAV). In addition to MSR, large in situ payloads of 150 kg provide a significant step up from the Mars Pathfinder (MPF) and Mars Polar Lander (MPL) class payloads of 20 to 30 kg. This capability enables numerous and physically large science instruments as well as human exploration development payloads. The payload may consist of drills, scoops, rock corers, imagers, spectrometers, and in situ propellant production experiment, and dust and environmental monitoring.

Broadband and scalable mobile satellite communication system for future access networks

NASA Astrophysics Data System (ADS)

Ohata, Kohei; Kobayashi, Kiyoshi; Nakahira, Katsuya; Ueba, Masazumi

2005-07-01

Due to the recent market trends, NTT has begun research into next generation satellite communication systems, such as broadband and scalable mobile communication systems. One service application objective is to provide broadband Internet access for transportation systems, temporal broadband access networks and telemetries to remote areas. While these are niche markets the total amount of capacity should be significant. We set a 1-Gb/s total transmission capacity as our goal. Our key concern is the system cost, which means that the system should be unified system with diversified services and not tailored for each application. As satellites account for a large portion of the total system cost, we set the target satellite size as a small, one-ton class dry mass with a 2-kW class payload power. In addition to the payload power and weight, the mobile satellite's frequency band is extremely limited. Therefore, we need to develop innovative technologies that will reduce the weight and maximize spectrum and power efficiency. Another challenge is the need for the system to handle up to 50 dB and a wide data rate range of other applications. This paper describes the key communication system technologies; the frequency reuse strategy, multiplexing scheme, resource allocation scheme, and QoS management algorithm to ensure excellent spectrum efficiency and support a variety of services and quality requirements in the mobile environment.

Demonstrating Acquisition of Real-Time Thermal Data Over Fires Utilizing UAVs

NASA Technical Reports Server (NTRS)

Ambrosia, Vincent G.; Wegener, Steven S.; Brass, James A.; Buechel, Sally W.; Peterson, David L. (Technical Monitor)

2002-01-01

A disaster mitigation demonstration, designed to integrate remote-piloted aerial platforms, a thermal infrared imaging payload, over-the-horizon (OTH) data telemetry and advanced image geo-rectification technologies was initiated in 2001. Project FiRE incorporates the use of a remotely piloted Uninhabited Aerial Vehicle (UAV), thermal imagery, and over-the-horizon satellite data telemetry to provide geo-corrected data over a controlled burn, to a fire management community in near real-time. The experiment demonstrated the use of a thermal multi-spectral scanner, integrated on a large payload capacity UAV, distributing data over-the-horizon via satellite communication telemetry equipment, and precision geo-rectification of the resultant data on the ground for data distribution to the Internet. The use of the UAV allowed remote-piloted flight (thereby reducing the potential for loss of human life during hazardous missions), and the ability to "finger and stare" over the fire for extended periods of time (beyond the capabilities of human-pilot endurance). Improved bit-rate capacity telemetry capabilities increased the amount, structure, and information content of the image data relayed to the ground. The integration of precision navigation instrumentation allowed improved accuracies in geo-rectification of the resultant imagery, easing data ingestion and overlay in a GIS framework. We focus on these technological advances and demonstrate how these emerging technologies can be readily integrated to support disaster mitigation and monitoring strategies regionally and nationally.

Designing astrophysics missions for NASA's Space Launch System

NASA Astrophysics Data System (ADS)

Stahl, H. Philip; Hopkins, Randall C.; Schnell, Andrew; Smith, David Alan; Jackman, Angela; Warfield, Keith R.

2016-10-01

Large space telescope missions have always been limited by their launch vehicle's mass and volume capacities. The Hubble Space Telescope was specifically designed to fit inside the Space Shuttle and the James Webb Space Telescope was specifically designed to fit inside an Ariane 5. Astrophysicists desire even larger space telescopes. NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultrahigh-contrast spectroscopy and coronagraphy. Association of Universities for Research in Astronomy's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. NASA's "Planning for the 2020 Decadal Survey" calls for a Habitable Exoplanet Imaging (HabEx) and an LUVOIR as well as Far-IR and an X-ray Surveyor missions. Packaging larger space telescopes into existing launch vehicles is a significant engineering complexity challenge that drives cost and risk. NASA's planned Space Launch System (SLS), with its 8- or 10-m diameter fairings and ability to deliver 35 to 45 mt of payload to Sun-Earth-Lagrange-2, mitigates this challenge by fundamentally changing the design paradigm for large space telescopes. This paper introduces the mass and volume capacities of the planned SLS, provides a simple mass allocation recipe for designing large space telescope missions to this capacity, and gives three specific mission concept implementation examples: a 4-m monolithic off-axis telescope, an 8-m monolithic on-axis telescope, and a 12-m segmented on-axis telescope.

SMART-1/CLEMENTINE Study of Humorum and Procellarum Basins

NASA Astrophysics Data System (ADS)

Carey, William; Foing, Bernard H.; Koschny, Detlef; Pio Rossi, Angelo; Josset, Jean-Luc

A study undertaken by ESA to define a European Reference Architecture for Space Exploration is due to be completed in September 2008. The development of this architecture over the past twelve months has identified a number of key capabilities, among them a lunar lander system, which could form the basis for Europe's contribution to the future exploration of space in collaboration with International Partners. The focus of this paper will be on the lunar lander system, and will present the results of an analysis of possible payloads that could be accommodated by the lander. As the industrial study is at the Phase 0 or Pre-Phase A level, the design of such a lander system is at a very early stage in its development, but an estimation of the payload capacity allows a general assessment of the types of possible payloads that could be carried, currently this capacity is estimated at 1.1 tonnes of gross payload mass to the lunar surface (assuming an Ariane 5 ECA launch). An important characteristic of the lunar lander is that it provides a versatile and flexible system for utilisation in a broad range of lunar missions which include: - Independent lunar exploration missions for science, technology demonstration and research. - Delivery of logistics and cargo to support human surface sortie missions. - Delivery of logistics to a lunar base/outpost. - Deployment of individual infrastructure elements in support of a lunar base/outpost. Based on the above different types of missions, a number of configurations of "reference payload" sets are in the process of being defined that cover specific exploration objectives related primarily to capability demonstration, exploration enabling research and enabled science. Aspects covered include: ISRU, robotics, mobility, human preparation, life science and geology. This paper will present the current status of definition of the Reference Payload sets.

KSC-2012-1863

NASA Image and Video Library

2012-02-17

Space Shuttle Payloads: Kennedy Space Center was the hub for the final preparation and launch of the space shuttle and its payloads. The shuttle carried a wide variety of payloads into Earth orbit. Not all payloads were installed in the shuttle's cargo bay. In-cabin payloads were carried in the shuttle's middeck. Cargo bay payloads were typically large payloads which did not require a pressurized environment, such as interplanetary space probes, earth-orbiting satellites, scientific laboratories and International Space Station trusses and components. Poster designed by Kennedy Space Center Graphics Department/Greg Lee. Credit: NASA

14 CFR 125.73 - Contents.

Code of Federal Regulations, 2010 CFR

2006-01-01

... HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE... include— (a) The name of each management person who is authorized to act for the certificate holder, the...) Procedures for ensuring compliance with airplane weight and balance limitations; (c) Copies of the...

14 CFR 125.407 - Maintenance log: Airplanes.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Maintenance log: Airplanes. 125.407 Section... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported...

14 CFR 125.407 - Maintenance log: Airplanes.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Maintenance log: Airplanes. 125.407 Section... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported...

14 CFR 125.91 - Airplane requirements: General.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplane requirements: General. 125.91... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements...

14 CFR 125.91 - Airplane requirements: General.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplane requirements: General. 125.91... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements...

14 CFR 125.407 - Maintenance log: Airplanes.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Maintenance log: Airplanes. 125.407 Section... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported...

14 CFR 125.91 - Airplane requirements: General.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplane requirements: General. 125.91... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements...

14 CFR 125.407 - Maintenance log: Airplanes.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Maintenance log: Airplanes. 125.407 Section... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported...

14 CFR 125.91 - Airplane requirements: General.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplane requirements: General. 125.91... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements...

14 CFR 125.91 - Airplane requirements: General.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane requirements: General. 125.91... AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements...

14 CFR 125.407 - Maintenance log: Airplanes.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Maintenance log: Airplanes. 125.407 Section... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Maintenance log: Airplanes. (a) Each person who takes corrective action or defers action concerning a reported...

Large Payload Transportation and Test Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.; Pope, James C.

2011-01-01

Ironically, the limiting factor to a national heavy lift strategy may not be the rocket technology needed to throw a heavy payload, but rather the terrestrial infrastructure - roads, bridges, airframes, and buildings - necessary to transport, acceptance test, and process large spacecraft. Failure to carefully consider how large spacecraft are designed, and where they are manufactured, tested, or launched, could result in unforeseen cost to modify/develop infrastructure, or incur additional risk due to increased handling or elimination of key verifications. During test and verification planning for the Altair project, a number of transportation and test issues related to the large payload diameter were identified. Although the entire Constellation Program - including Altair - was canceled in the 2011 NASA budget, issues identified by the Altair project serve as important lessons learned for future payloads that may be developed to support national "heavy lift" strategies. A feasibility study performed by the Constellation Ground Operations (CxGO) project found that neither the Altair Ascent nor Descent Stage would fit inside available transportation aircraft. Ground transportation of a payload this large over extended distances is generally not permitted by most states, so overland transportation alone would not have been an option. Limited ground transportation to the nearest waterway may be permitted, but water transportation could take as long as 66 days per production unit, depending on point of origin and acceptance test facility; transportation from the western United States would require transit through the Panama Canal to access the Kennedy Space Center launch site. Large payloads also pose acceptance test and ground processing challenges. Although propulsion, mechanical vibration, and reverberant acoustic test facilities at NASA s Plum Brook Station have been designed to accommodate large spacecraft, special handling and test work-arounds may be necessary, which could increase cost, schedule, and technical risk. Once at the launch site, there are no facilities currently capable of accommodating the combination of large payload size and hazardous processing (which includes hypergolic fuels, pyrotechnic devices, and high pressure gasses).

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of the orbiter Atlantis, STS-98 Mission Specialist Robert Curbeam works with equipment he will use in space to attach the U.S. Lab Destiny to the International Space Station. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the payload bay of the orbiter Atlantis, STS-98 Mission Specialists Thomas Jones (left) and Robert Curbeam (right) talk about their mission, attaching the U.S. Lab Destiny (in the background) to the International Space Station. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

Vibration isolation using six degree-of-freedom quasi-zero stiffness magnetic levitation

NASA Astrophysics Data System (ADS)

Zhu, Tao; Cazzolato, Benjamin; Robertson, William S. P.; Zander, Anthony

2015-12-01

In laboratories and high-tech manufacturing applications, passive vibration isolators are often used to isolate vibration sensitive equipment from ground-borne vibrations. However, in traditional passive isolation devices, where the payload weight is supported by elastic structures with finite stiffness, a design trade-off between the load capacity and the vibration isolation performance is unavoidable. Low stiffness springs are often required to achieve vibration isolation, whilst high stiffness is desired for supporting payload weight. In this paper, a novel design of a six degree of freedom (six-dof) vibration isolator is presented, as well as the control algorithms necessary for stabilising the passively unstable maglev system. The system applies magnetic levitation as the payload support mechanism, which realises inherent quasi-zero stiffness levitation in the vertical direction, and zero stiffness in the other five dofs. While providing near zero stiffness in multiple dofs, the design is also able to generate static magnetic forces to support the payload weight. This negates the trade-off between load capacity and vibration isolation that often exists in traditional isolator designs. The paper firstly presents the novel design concept of the isolator and associated theories, followed by the mechanical and control system designs. Experimental results are then presented to demonstrate the vibration isolation performance of the proposed system in all six directions.

Payload crew training scheduler (PACTS) user's manual

NASA Technical Reports Server (NTRS)

Shipman, D. L.

1980-01-01

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

Some aspects of hybrid-zeppelins. [optimization of delta wings for airships

NASA Technical Reports Server (NTRS)

Mackrodt, P. A.

1975-01-01

To increase an airship's maneuverability and payload capacity as well as to save bouyant gas it is proposed to outfit it with a slender delta-wing, which carries about one half of the total take-off weight of the vehicle. An optimization calculation based on the data of LZ 129 (the last airship, which saw passenger-service) leads to a Hybrid-Zeppelin with a wing of aspect-ratio 1.5 and 105 m span. The vehicle carries a payload of 40% of it's total take-off weight and consumes 0.8 t fuel per ton payload over a distance of 10000 km.

Position reporting system using small satellites

NASA Technical Reports Server (NTRS)

Pavesi, B.; Rondinelli, G.; Graziani, F.

1990-01-01

A system able to provide position reporting and monitoring services for mobile applications represents a natural complement to the Global Positioning System (GPS) navigation system. The system architecture is defined on the basis of the communications requirements derived by user needs, allowing maximum flexibility in the use of channel capacity, and a very simple and low cost terminal. The payload is sketched, outlining the block modularity and the use of qualified hardware. The global system capacity is also derived. The spacecraft characteristics are defined on the basis of the payload requirements. A small bus optimized for Ariane IV, Delta II vehicles and based on the modularity concept is presented. The design takes full advantage of each launcher with a common basic bus or bus elements for a mass production.

47 CFR 101.141 - Microwave modulation.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 2 DS-1 1.60 6.17 N/A 4 DS-1 2.50 6.17 N/A 4 DS-1 3.75 12.3 N/A 8 DS-1 5.0 18.5 N/A 12 DS-1 10.0 44.7..., the minimum payload capacity must be 12.3 Mbits/s. (5) Transmitters carrying digital motion video... section, provided that at least 50 percent of the payload is digital video motion material and the minimum...

Simulation of the Deployment and Orbit Operations of the NPS-SCAT CubeSat

DTIC Science & Technology

2008-04-01

Vehicle EPF Extended Payload Fairings ESPA EELV Secondary Payload Adapter g Gravitational acceleration constant at sea level on the Earth GSO...Cell Measurement System SOC State Of Charge SPL Secondary Payload SRB Solid Rocket Booster XEPF Extended EPF xvii ACKNOWLEDGMENTS...incorporates the flight proven 4 m diameter Atlas V 12.0 m Large Payload Fairing (LPF), the 12.9 m Extended Payload Fairing ( EPF ), or the 13.8 m

14 CFR § 125.73 - Contents.

Code of Federal Regulations, 2010 CFR

2017-01-01

...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS... manual must include— (a) The name of each management person who is authorized to act for the certificate... the attention of the pilot in command before, during, and after completion of a flight; (g) Procedures...

14 CFR 125.93 - Airplane limitations.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplane limitations. 125.93 Section 125.93...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements § 125.93 Airplane...

14 CFR 125.355 - Airplane equipment.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplane equipment. 125.355 Section 125.355...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Release Rules § 125.355 Airplane...

14 CFR 125.355 - Airplane equipment.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplane equipment. 125.355 Section 125.355...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Release Rules § 125.355 Airplane...

14 CFR 125.355 - Airplane equipment.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Airplane equipment. 125.355 Section 125.355...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Release Rules § 125.355 Airplane...

14 CFR 125.93 - Airplane limitations.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplane limitations. 125.93 Section 125.93...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements § 125.93 Airplane...

14 CFR 125.355 - Airplane equipment.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplane equipment. 125.355 Section 125.355...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Release Rules § 125.355 Airplane...

14 CFR 125.93 - Airplane limitations.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Airplane limitations. 125.93 Section 125.93...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements § 125.93 Airplane...

14 CFR 125.75 - Airplane flight manual.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Airplane flight manual. 125.75 Section 125... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Airplane flight manual. (a) Each certificate holder shall keep a current approved Airplane Flight Manual or...

14 CFR 125.93 - Airplane limitations.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Airplane limitations. 125.93 Section 125.93...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements § 125.93 Airplane...

14 CFR 125.73 - Contents.

Code of Federal Regulations, 2010 CFR

1999-01-01

... 14 Aeronautics and Space 2 1999-01-01 1999-01-01 false Contents. 125.73 Section 125.73 AIR CARRIERS AND OPERATORS FOR COMPENSATION OR HIRE: CERTIFICATION AND OPERATIONS CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE Special Federal Aviation...

14 CFR 125.93 - Airplane limitations.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane limitations. 125.93 Section 125.93...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Airplane Requirements § 125.93 Airplane...

14 CFR 125.355 - Airplane equipment.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane equipment. 125.355 Section 125.355...: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6,000 POUNDS OR MORE; AND RULES GOVERNING PERSONS ON BOARD SUCH AIRCRAFT Flight Release Rules § 125.355 Airplane...

14 CFR 125.75 - Airplane flight manual.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Airplane flight manual. 125.75 Section 125... OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD CAPACITY OF 6... Airplane flight manual. (a) Each certificate holder shall keep a current approved Airplane Flight Manual or...

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Members of the STS-98 crew, along with Scott Thurston (left), with the VITT office, check out the U.S. Lab Destiny in the payload bay of the orbiter Atlantis. Wearing white caps are Commander Ken Cockrell (center) and Mission Specialist Marsha Ivins (right). The crew is at KSC for Terminal Countdown Demonstration Test activities, which include a simulated launch countdown. Destiny, a key element in the construction of the International Space Station, is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

STS-98 crew checks out the U.S. Lab Destiny in Atlantis' payload bay

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- STS-98 Mission Specialist Robert Curbeam (left), Commander Ken Cockrell (center) and Mission Specialist Marsha Ivins (right) look over the U.S. Lab Destiny in the payload bay of the orbiter Atlantis. Behind Ivins is Scott Thurston, of the VITT office. The crew is at KSC for Terminal Countdown Demonstration Test activities, which also include a simulated launch countdown. A key element in the construction of the International Space Station, Destiny is a pressurized module designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 13 locations especially designed to support experiments. The module already has five system racks installed inside. Launch of STS-98 on its 11-day mission is scheduled for Jan. 19 at 2:11 a.m. EST.

Optical data transmission technology for fixed and drag-on STS payloads umbilicals. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

St.denis, R. W.

1981-01-01

The feasibility of using optical data handling methods to transmit payload checkout and telemetry is discussed. Optical communications are superior to conventional communication systems for the following reasons: high data capacity optical channels; small and light weight optical cables; and optical signal immunity to electromagnetic interference. Task number one analyzed the ground checkout data requirements that may be expected from the payload community. Task number two selected the optical approach based on the interface requirements, the location of the interface, the amount of time required to reconfigure hardware, and the method of transporting the optical signal. Task number three surveyed and selected optical components for the two payload data link. Task number four makes a qualitative comparison of the conventional electrical communication system and the proposed optical communication system.

STS-96 crew takes part in payload Interface Verification Test

NASA Technical Reports Server (NTRS)

1999-01-01

In the SPACEHAB Facility, (from left) STS-96 Mission Specialist Julie Payette, Pilot Rick Husband and Mission Specialist Ellen Ochoa learn about the Sequential Shunt Unit (SSU) in front of them from Lynn Ashby (far right), with Johnson Space Center. The STS-96 crew is at KSC for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station . Other crew members at KSC for the IVT are Commander Kent Rominger and Mission Specialists Tamara Jernigan, Dan Barry and Valery Tokarev of Russia. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m.

NASA 60 GHz intersatellite communication link definition study. Baseline document

NASA Technical Reports Server (NTRS)

1986-01-01

The overall system and component concepts for a 60 GHz intersatellite communications link system (ICLS) are described. The ICLS was designed to augment the capabilities of the current Tracking and Data Relay Satellite System (TDRSS), providing a data rate capacity large enough to accommodate the expected rates for user satellites (USAT's) in the post-1995 timeframe. The use of 60 GHz for the anticipated successor to TDRSS, the Tracking and Data Acquisition System (TDAS), was selected because of current technology development that will enable multigigibit data rates. Additionally, the attenuation of the earth's atmosphere at 60 GHz means that there is virtually no possibility of terrestrially generated interference (intentional or accidental) or terrestrially based intercept. The ICLS includes the following functional areas: (1) the ICLS payload package on the GEO TDAS satellite that communicates simultaneously with up to five LEO USAT's; (2) the payload package on the USAT that communicates with the TDAS satellite; and (3) the crosslink payload package on the TDAS satellite that communicates with another TDAS satellite. Two methods of data relay on-board the TDAS spacecraft were addressed. One is a complete baseband system (demod and remod) with a bi-directional 2 Gbps data stream; the other is a channelized system wherein some of the channels are baseband and others are merely frequency translated before re-transmission. Descriptions of the TDAS antenna, transmitter, receiver, and mechanical designs are presented.

Rideshare programs: a historical perspective

NASA Astrophysics Data System (ADS)

Horais, Brian J.

2000-11-01

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

Payload isolation and stabilization by a Suspended Experiment Mount (SEM)

NASA Technical Reports Server (NTRS)

Bailey, Wayne L.; Desanctis, Carmine E.; Nicaise, Placide D.; Schultz, David N.

1992-01-01

Many Space Shuttle and Space Station payloads can benefit from isolation from crew or attitude control system disturbances. Preliminary studies have been performed for a Suspended Experiment Mount (SEM) system that will provide isolation from accelerations and stabilize the viewing direction of a payload. The concept consists of a flexible suspension system and payload-mounted control moment gyros. The suspension system, which is rigidly locked for ascent and descent, isolates the payload from high frequency disturbances. The control moment gyros stabilize the payload orientation. The SEM will be useful for payloads that require a lower-g environment than a manned vehicle can provide, such as materials processing, and for payloads that require stabilization of pointing direction, but not large angle slewing, such as nadir-viewing earth observation or solar viewing payloads.

Modular cell-internalizing aptamer nanostructure enables targeted delivery of large functional RNAs in cancer cell lines.

PubMed

Porciani, David; Cardwell, Leah N; Tawiah, Kwaku D; Alam, Khalid K; Lange, Margaret J; Daniels, Mark A; Burke, Donald H

2018-06-11

Large RNAs and ribonucleoprotein complexes have powerful therapeutic potential, but effective cell-targeted delivery tools are limited. Aptamers that internalize into target cells can deliver siRNAs (<15 kDa, 19-21 nt/strand). We demonstrate a modular nanostructure for cellular delivery of large, functional RNA payloads (50-80 kDa, 175-250 nt) by aptamers that recognize multiple human B cell cancer lines and transferrin receptor-expressing cells. Fluorogenic RNA reporter payloads enable accelerated testing of platform designs and rapid evaluation of assembly and internalization. Modularity is demonstrated by swapping in different targeting and payload aptamers. Both modules internalize into leukemic B cell lines and remained colocalized within endosomes. Fluorescence from internalized RNA persists for ≥2 h, suggesting a sizable window for aptamer payloads to exert influence upon targeted cells. This demonstration of aptamer-mediated, cell-internalizing delivery of large RNAs with retention of functional structure raises the possibility of manipulating endosomes and cells by delivering large aptamers and regulatory RNAs.

KENNEDY SPACE CENTER, FLA. - The orbiter Ku-band antenna looms large in this view of the Space Shuttle Atlantis' payload bay. Visible just past the antenna system - stowed on the starboard side of the payload bay wall - is the Orbiter Docking System (ODS), and connected to the ODS via a tunnel is the Spacehab Double Module in the aft area of the payload bay. This photograph was taken from the starboard wing platform on the fifth level of the Payload Changeout Room (PCR) at Launch Pad 39A. Work is under way in the PCR to close Atlantis' payload bay doors for flight. Atlantis currently is being targeted for liftoff on Mission STS-79, the fourth docking of the U.S. Shuttle to the Russian Space Station Mir, around Sept. 12.

NASA Image and Video Library

1996-08-22

KENNEDY SPACE CENTER, FLA. - The orbiter Ku-band antenna looms large in this view of the Space Shuttle Atlantis' payload bay. Visible just past the antenna system - stowed on the starboard side of the payload bay wall - is the Orbiter Docking System (ODS), and connected to the ODS via a tunnel is the Spacehab Double Module in the aft area of the payload bay. This photograph was taken from the starboard wing platform on the fifth level of the Payload Changeout Room (PCR) at Launch Pad 39A. Work is under way in the PCR to close Atlantis' payload bay doors for flight. Atlantis currently is being targeted for liftoff on Mission STS-79, the fourth docking of the U.S. Shuttle to the Russian Space Station Mir, around Sept. 12.

Attached shuttle payload carriers: Versatile and affordable access to space

NASA Technical Reports Server (NTRS)

1990-01-01

The shuttle has been primarily designed to be a versatile vehicle for placing a variety of scientific and technological equipment in space including very large payloads; however, since many large payloads do not fill the shuttle bay, the space and weight margins remaining after the major payloads are accommodated often can be made available to small payloads. The Goddard Space Flight Center (GSFC) has designed standardized mounting structures and other support systems, collectively called attached shuttle payload (ASP) carriers, to make this additional space available to researchers at a relatively modest cost. Other carrier systems for ASP's are operated by other NASA centers. A major feature of the ASP carriers is their ease of use in the world of the Space Shuttle. ASP carriers attempt to minimized the payload interaction with Space Transportation System (STS) operations whenever possible. Where this is not possible, the STS services used are not extensive. As a result, the interfaces between the carriers and the STS are simplified. With this near autonomy, the requirements for supporting documentation are considerably lessened and payload costs correspondingly reduced. The ASP carrier systems and their capabilities are discussed in detail. The range of available capabilities assures that an experimenter can select the simplest, most cost-effective carrier that is compatible with his or her experimental objectives. Examples of payloads which use ASP basic hardware in nonstandard ways are also described.

Determination of ASPS performance for large payloads in the shuttle orbiter disturbance environment. [digital simulation

NASA Technical Reports Server (NTRS)

Keckler, C. R.; Kibler, K. S.; Powell, L. F.

1979-01-01

A high fidelity simulation of the annular suspension and pointing system (ASPS), its payload, and the shuttle orbiter was used to define the worst case orientations of the ASPS and its payload for the various vehicle disturbances, and to determine the performance capability of the ASPS under these conditions. The most demanding and largest proposed payload, the Solar Optical Telescope was selected for study. It was found that, in all cases, the ASPS more than satisfied the payload's requirements. It is concluded that, to satisfy facility class payload requirements, the ASPS or a shuttle orbiter free-drift mode (control system off) should be utilized.

New developments for SAW channelization for mobile satellite payloads

NASA Technical Reports Server (NTRS)

Peach, R. C.; Mabson, P.

1995-01-01

The use of SAW technology in mobile communication payloads is becoming widely accepted by the industry since being pioneered by Inmarsat for its third generation of satellites. This paper presents new developments in this area, including broadband processors of the Inmarsat 3 type, and the use of SAW filters at L-band. It is demonstrated that SAW processors have considerable potential for increasing the capacity of future communications payloads, while allowing fully transparent operation without any restriction on traffic type or modulation format. In addition to the evolutionary development of Inmarsat type processors, new SAW applications have also emerged recently. Therefore, despite the rapid changes in the industry, it is predicted that SAW processing has a strong future in satellite communications.

Two lighter than air systems in opposing flight regimes: An unmanned short haul, heavy load transport balloon and a manned, light payload airship

NASA Technical Reports Server (NTRS)

Pohl, R. A.

1975-01-01

Lighter Than Air vehicles are generally defined or categorized by the shape of the balloon, payload capacity and operational flight regime. Two balloon systems that are classed as being in opposite categories are described. One is a cable guided, helium filled, short haul, heavy load transport Lighter Than Air system with a natural shaped envelope. The other is a manned, aerodynamic shaped airship which utilizes hot air as the buoyancy medium and is in the light payload class. While the airship is in the design/fabrication phase with flight tests scheduled for the latter part of 1974, the transport balloon system has been operational for some eight years.

Large Payload Ground Transportation and Test Considerations

NASA Technical Reports Server (NTRS)

Rucker, Michelle A.

2016-01-01

During test and verification planning for the Altair lunar lander project, a National Aeronautics and Space Administration (NASA) study team identified several ground transportation and test issues related to the large payload diameter. Although the entire Constellation Program-including Altair-has since been canceled, issues identified by the Altair project serve as important lessons learned for payloads greater than 7 m diameter being considered for NASA's new Space Launch System (SLS). A transportation feasibility study found that Altair's 8.97 m diameter Descent Module would not fit inside available aircraft. Although the Ascent Module cabin was only 2.35 m diameter, the long reaction control system booms extended nearly to the Descent Module diameter, making it equally unsuitable for air transportation without removing the booms and invalidating assembly workmanship screens or acceptance testing that had already been performed. Ground transportation of very large payloads over extended distances is not generally permitted by most states, so overland transportation alone would not be an option. Limited ground transportation to the nearest waterway may be possible, but water transportation could take as long as 66 days per production unit, depending on point of origin and acceptance test facility; transportation from the western United States would require transit through the Panama Canal to access the Kennedy Space Center launch site. Large payloads also pose acceptance test and ground processing challenges. Although propulsion, mechanical vibration, and reverberant acoustic test facilities at NASA's Plum Brook Station have been designed to accommodate large spacecraft, special handling and test work-arounds may be necessary, which could increase cost, schedule, and technical risk. Once at the launch site, there are no facilities currently capable of accommodating the combination of large payload size and hazardous processing such as hypergolic fuels, pyrotechnic devices, and high pressure gasses. Ironically, the limiting factor to a national heavy lift strategy may not be the rocket technology needed to throw a heavy payload, but rather the terrestrial infrastructure-roads, bridges, airframes, and buildings-necessary to transport, acceptance test, and process large spacecraft. Failure to carefully consider where and how large spacecraft are manufactured, tested, and launched could result in unforeseen cost to modify existing (or develop new) infrastructure, or incur additional risk due to increased handling operations or eliminating key verifications.

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

NASA Technical Reports Server (NTRS)

1972-01-01

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

An overview of the 1984 Battelle outside users payload model

NASA Astrophysics Data System (ADS)

Day, J. B.; Conlon, R. J.; Neale, D. B.; Fischer, N. H.

1984-10-01

The methodology and projections from a model for the market for non-NASA, non-DOD, reimbursable payloads from the non-Soviet bloc countries over the 1984-2000 AD time period are summarized. High and low forecast ranges were made based on demand forecasts by industrial users, NASA estimates, and other publications. The launches were assumed to be alloted to either the Shuttle or the Ariane. The greatest demand for launch services is expected to come form communications and materials processing payloads, the latter either becoming a large user or remaining a research item. The number of Shuttle payload equivalents over the reference time spanis projected as 84-194, showing the large variance that is dependent on the progress in materials processing operations.

Enabling Science and Deep Space Exploration through Space Launch System (LSL) Secondary Payload Opportunities

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). By reaching this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. NASA is making investments to expand science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1), currently planned for launch no earlier than July 2018, will be the first mission to carry such payloads on the SLS. The EM-1 launch will include thirteen 6U Cubesat small satellites that will be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and deployment will be described to provide potential payload users an understanding of this unique exploration capability.

KSC-06pd1673

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is moved into position beneath the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1670

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - Shortly after midnight, the payload canister makes a slow journey to Launch Pad 39B. Inside the canister is the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1674

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - Nearing dawn on Launch Pad 39B, the payload canister is in position to be lifted into the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1676

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is lifted toward the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The red umbilical lines are still attached to the transporter, lower right. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1672

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - After a several-hour trip from the Canister Rotation Facility, the payload canister arrives on Launch Pad 39B. Inside the canister is the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The canister will be positioned alongside the rotating service structure and beneath the payload changeout room (PCR) for transfer of the truss into the PCR. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

KSC-06pd1675

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is lifted toward the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The red umbilical lines are still attached, lower right. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

A new collage steganographic algorithm using cartoon design

NASA Astrophysics Data System (ADS)

Yi, Shuang; Zhou, Yicong; Pun, Chi-Man; Chen, C. L. Philip

2014-02-01

Existing collage steganographic methods suffer from low payload of embedding messages. To improve the payload while providing a high level of security protection to messages, this paper introduces a new collage steganographic algorithm using cartoon design. It embeds messages into the least significant bits (LSBs) of color cartoon objects, applies different permutations to each object, and adds objects to a cartoon cover image to obtain the stego image. Computer simulations and comparisons demonstrate that the proposed algorithm shows significantly higher capacity of embedding messages compared with existing collage steganographic methods.

Steganography based on pixel intensity value decomposition

NASA Astrophysics Data System (ADS)

Abdulla, Alan Anwar; Sellahewa, Harin; Jassim, Sabah A.

2014-05-01

This paper focuses on steganography based on pixel intensity value decomposition. A number of existing schemes such as binary, Fibonacci, Prime, Natural, Lucas, and Catalan-Fibonacci (CF) are evaluated in terms of payload capacity and stego quality. A new technique based on a specific representation is proposed to decompose pixel intensity values into 16 (virtual) bit-planes suitable for embedding purposes. The proposed decomposition has a desirable property whereby the sum of all bit-planes does not exceed the maximum pixel intensity value, i.e. 255. Experimental results demonstrate that the proposed technique offers an effective compromise between payload capacity and stego quality of existing embedding techniques based on pixel intensity value decomposition. Its capacity is equal to that of binary and Lucas, while it offers a higher capacity than Fibonacci, Prime, Natural, and CF when the secret bits are embedded in 1st Least Significant Bit (LSB). When the secret bits are embedded in higher bit-planes, i.e., 2nd LSB to 8th Most Significant Bit (MSB), the proposed scheme has more capacity than Natural numbers based embedding. However, from the 6th bit-plane onwards, the proposed scheme offers better stego quality. In general, the proposed decomposition scheme has less effect in terms of quality on pixel value when compared to most existing pixel intensity value decomposition techniques when embedding messages in higher bit-planes.

STS-83 Crew Arrival for TCDT

NASA Technical Reports Server (NTRS)

1997-01-01

Members of the STS-83 flight crew pose alongside a T-33 jet trainer aircraft after arriving at the KSC Shuttle Landing Facility for Terminal Countdown Demonstration (TCDT) exercises for that space flight. They are (left to right) Payload Specialist Roger K. Crouch; Pilot Susan L. Still; Mission Commander James D. Halsell, Jr.; Mission Specialist Michael L. Gernhardt; Payload Specialist She is the second woman to fly in this capacity on the Space Shuttle. The Microgravity Science Laboratory-1 (MSL-1) Spacelab module is the primary payload on this 16-day mission. The MSL-1 will used to test some of the hardware, facilities and procedures that are planned for use on the International Space Station, while the seven-member crew conducts combustion, protein crystal growth and materials processing experiments.

LSST system analysis and integration task for an advanced science and application space platform

NASA Technical Reports Server (NTRS)

1980-01-01

To support the development of an advanced science and application space platform (ASASP) requirements of a representative set of payloads requiring large separation distances selected from the Science and Applications Space Platform data base. These payloads were a 100 meter diameter atmospheric gravity wave antenna, a 100 meter by 100 meter particle beam injection experiment, a 2 meter diameter, 18 meter long astrometric telescope, and a 15 meter diameter, 35 meter long large ambient deployable IR telescope. A low earth orbit at 500 km altitude and 56 deg inclination was selected as being the best compromise for meeting payload requirements. Platform subsystems were defined which would support the payload requirements and a physical platform concept was developed. Structural system requirements which included utilities accommodation, interface requirements, and platform strength and stiffness requirements were developed. An attitude control system concept was also described. The resultant ASASP concept was analyzed and technological developments deemed necessary in the area of large space systems were recommended.

Performance Characteristics For The Orbiter Camera Payload System's Large Format Camera (LFC)

NASA Astrophysics Data System (ADS)

MoIIberg, Bernard H.

1981-11-01

The Orbiter Camera Payload System, the OCPS, is an integrated photographic system which is carried into Earth orbit as a payload in the Shuttle Orbiter vehicle's cargo bay. The major component of the OCPS is a Large Format Camera (LFC) which is a precision wide-angle cartographic instrument that is capable of produc-ing high resolution stereophotography of great geometric fidelity in multiple base to height ratios. The primary design objective for the LFC was to maximize all system performance characteristics while maintaining a high level of reliability compatible with rocket launch conditions and the on-orbit environment.

KSC-99pp0208

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- In the SPACEHAB Facility for a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station are (left to right) Mission Specialists Valery Tokarev, Julie Payette (holding a lithium hydroxide canister) and Dan Barry. Other crew members at KSC for the IVT are Commander Kent Rominger, Pilot Rick Husband and Mission Specialists Ellen Ochoa and Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

Technical Report: Unmanned Helicopter Solution for Survey-Grade Lidar and Hyperspectral Mapping

NASA Astrophysics Data System (ADS)

Kaňuk, Ján; Gallay, Michal; Eck, Christoph; Zgraggen, Carlo; Dvorný, Eduard

2018-05-01

Recent development of light-weight unmanned airborne vehicles (UAV) and miniaturization of sensors provide new possibilities for remote sensing and high-resolution mapping. Mini-UAV platforms are emerging, but powerful UAV platforms of higher payload capacity are required to carry the sensors for survey-grade mapping. In this paper, we demonstrate a technological solution and application of two different payloads for highly accurate and detailed mapping. The unmanned airborne system (UAS) comprises a Scout B1-100 autonomously operating UAV helicopter powered by a gasoline two-stroke engine with maximum take-off weight of 75 kg. The UAV allows for integrating of up to 18 kg of a customized payload. Our technological solution comprises two types of payload completely independent of the platform. The first payload contains a VUX-1 laser scanner (Riegl, Austria) and a Sony A6000 E-Mount photo camera. The second payload integrates a hyperspectral push-broom scanner AISA Kestrel 10 (Specim, Finland). The two payloads need to be alternated if mapping with both is required. Both payloads include an inertial navigation system xNAV550 (Oxford Technical Solutions Ltd., United Kingdom), a separate data link, and a power supply unit. Such a constellation allowed for achieving high accuracy of the flight line post-processing in two test missions. The standard deviation was 0.02 m (XY) and 0.025 m (Z), respectively. The intended application of the UAS was for high-resolution mapping and monitoring of landscape dynamics (landslides, erosion, flooding, or crops growth). The legal regulations for such UAV applications in Switzerland and Slovakia are also discussed.

Payload canister transporter in VPF clean room

NASA Technical Reports Server (NTRS)

1984-01-01

Payload canister transporter in Vertical Processing Facility (VPF) Clean Room loaded with Earth Radiation Budget Satellite (ERBS), Large Format Camera (LFC) and Orbital Refueling System (ORS) for STS-41G mission.

KSC-06pd1671

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - Shortly after midnight, the payload canister and convoy negotiate the turn on the Saturn Causeway, heading for Launch Pad 39B. Inside the canister is the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

Design and performance analysis of an aero-maneuvering orbital-transfer vehicle concept

NASA Technical Reports Server (NTRS)

Menees, G. P.

1985-01-01

Systems requirements for design-optimized, lateral-turn performance were determined for reusable, space-based applications and low-Earth orbits involving large multiple plane-inclination changes. The aerothermodynamic analysis is the most advanced available for rarefield-hypersonic flow over lifting surfaces at incidence. The effects of leading-edge bluntness, low-density viscous phenomena, and finite-rate flow-field chemistry and surface catalysis are accounted for. The predicted aerothermal heating characteristics are correlated with thermal-control and flight-performance capabilities. The mission payload capacity for delivery, retrieval, and combined operations was determined for round-trip sorties extending to polar orbits. Recommendations are given for future design refinements. The results help to identify technology issues required to develop prototype operational vehicles.

Space science/space station attached payload pointing accommodation study: Technology assessment white paper

NASA Technical Reports Server (NTRS)

Lin, Richard Y.; Mann, Kenneth E.; Laskin, Robert A.; Sirlin, Samuel W.

1987-01-01

Technology assessment is performed for pointing systems that accommodate payloads of large mass and large dimensions. Related technology areas are also examined. These related areas include active thermal lines or power cables across gimbals, new materials for increased passive damping, tethered pointing, and inertially reacting pointing systems. Conclusions, issues and concerns, and recommendations regarding the status and development of large pointing systems for space applications are made based on the performed assessments.

An integrated Ka/Ku-band payload for personal, mobile and private business communications

NASA Technical Reports Server (NTRS)

Hayes, Edward J.; Keelty, J. Malcolm

1991-01-01

The Canadian Department of Communications has been studying options for a government-sponsored demonstration payload to be launched before the end of the century. A summary of the proposed system concepts and network architectures for providing an advanced private business network service at Ku-band and personal and mobile communications at Ka-band is presented. The system aspects addressed include coverage patterns, traffic capacity, and grade of service, multiple access options as well as special problems, such as Doppler in mobile applications. Earth terminal types and the advanced payload concept proposed in a feasibility study for the demonstration mission are described. This concept is a combined Ka-band/Ku-band payload which incorporates a number of advanced satellite technologies including a group demodulator to convert single-channel-per-carrier frequency division multiple access uplink signals to a time division multiplex downlink, on-board signal regeneration, and baseband switching to support packet switched data operation. The on-board processing capability of the payload provides a hubless VSAT architecture which permits single-hop full mesh interconnectivity. The Ka-band and Ku-band portions of the payload are fully integrated through an on-board switch, thereby providing the capability for fully integrated services, such as using the Ku-band VSAT terminals as gateway stations for the Ka-band personal and mobile communications services.

Entry Descent and Landing Workshop Proceedings. Volume 1; Inflatable Reentry Vehicle Experiment-3 (IRVE-3) Project Overview & Instrumentation

NASA Technical Reports Server (NTRS)

Dillman, Robert

2015-01-01

Entry mass at Mars is limited by the payload size that can be carried by a rigid capsule that can fit inside the launch vehicle fairing. Landing altitude at Mars is limited by ballistic coefficient (mass per area) of entry body. Inflatable technologies allow payload to use full diameter of launch fairing, and deploy larger aeroshell before atmospheric interface, landing more payload at a higher altitude. Also useful for return of large payloads from Low Earth Orbit (LEO).

KSC-06pd1677

NASA Image and Video Library

2006-07-26

KENNEDY SPACE CENTER, FLA. - On Launch Pad 39B, the payload canister is lifted toward the payload changeout room (PCR) for transfer of its cargo into the PCR. The canister holds the payload for Atlantis and mission STS-115, the Port 3/4 truss segment with two large solar arrays. The red umbilical lines are still attached to the transporter, below it. To the right of the rotating structure is the fixed service structure with the 80-foot lightning mast on top. The payload changeout room provides an environmentally clean or "white room" condition in which to receive a payload transferred from a protective payload canister. After the shuttle arrives at the pad, the rotating service structure will close around it and the payload will then be transferred into Atlantis' payload bay. Atlantis' launch window begins Aug. 28. During its 11-day mission to the International Space Station, the STS-115 crew of six astronauts will install the truss, a 17-ton segment of the space station's truss backbone. Photo credit: NASA/George Shelton

Maximizing Launch Vehicle and Payload Design Via Early Communications

NASA Technical Reports Server (NTRS)

Morris, Bruce

2010-01-01

The United States? current fleet of launch vehicles is largely derived from decades-old designs originally made for payloads that no longer exist. They were built primarily for national security or human exploration missions. Today that fleet can be divided roughly into small-, medium-, and large-payload classes based on mass and volume capability. But no vehicle in the U.S. fleet is designed to accommodate modern payloads. It is usually the payloads that must accommodate the capabilities of the launch vehicles. This is perhaps most true of science payloads. It was this paradigm that the organizers of two weekend workshops in 2008 at NASA's Ames Research Center sought to alter. The workshops brought together designers of NASA's Ares V cargo launch vehicle (CLV) with scientists and payload designers in the astronomy and planetary sciences communities. Ares V was still in a pre-concept development phase as part of NASA?s Constellation Program for exploration beyond low Earth orbit (LEO). The space science community was early in a Decadal Survey that would determine future priorities for research areas, observations, and notional missions to make those observations. The primary purpose of the meetings in April and August of 2008, including the novel format, was to bring vehicle designers together with space scientists to discuss the feasibility of using a heavy lift capability to launch large observatories and explore the Solar System. A key question put to the science community was whether this heavy lift capability enabled or enhanced breakthrough science. The meetings also raised the question of whether some trade-off between mass/volume and technical complexity existed that could reduce technical and programmatic risk. By engaging the scientific community early in the vehicle design process, vehicle engineers sought to better understand potential limitations and requirements that could be added to the Ares V from the mission planning community. From the vehicle standpoint, while the human exploration mission could not be compromised to accommodate other payloads, the design might otherwise be tailored to not exclude other payload requirements. This paper summarizes the findings of the workshops and discusses the benefits of bringing together the vehicle design and science communities early in their concept phases

Increasing the usefulness of Shuttle with SPACEHAB

NASA Astrophysics Data System (ADS)

Stone, Barbara A.; Rossi, David A.

1992-08-01

SPACEHAB is a pressurized laboratory, approximately 10 feet long and 13 feet in diameter, which fits in the forward position of the Shuttle payload bay and connects to the crew compartment through the Orbiter airlock. SPACEHAB modules may contain up to 61 standard middeck lockers, providing 1100 cubic feet of pressurized work space. SPACEHAB'S capacity offers crew-tended access to the microgravity environment for experimentation, technology development, and small-scale production. The modules are designed to facilitate the user's ability to quickly and inexpensively develop and integrate a microgravity payload. Payloads are typically integrated into the SPACEHAB module in standard SPACEHAB lockers or SPACEHAB racks. Lockers are designed to offer identical user interfaces as standard Space Shuttle middeck lockers. SPACEHAB racks are interchangeable with Space Station Freedom racks, allowing hardware to be qualified for early station use.

Smart doxorubicin nanoparticles with high drug payload for enhanced chemotherapy against drug resistance and cancer diagnosis

NASA Astrophysics Data System (ADS)

Yu, Caitong; Zhou, Mengjiao; Zhang, Xiujuan; Wei, Weijia; Chen, Xianfeng; Zhang, Xiaohong

2015-03-01

Considering the obvious advantages in efficacy and price, doxorubicin (DOX) has been widely used for a range of cancers, which is usually encapsulated in various nanocarriers for drug delivery. Although effective, in most nanocarrier-based delivery systems, the drug loading capacity of DOX is rather low; this can lead to undesired systemic toxicity and excretion concern. Herein, we report for the first time the usage of pure doxorubicin nanoparticles (DOX NPs) without addition of any carriers for enhanced chemotherapy against drug-resistance. The drug payload reaches as high as 90.47%, which largely surpassed those in previous reports. These PEG stabilized DOX NPs exhibit good biocompatibility and stability, long blood circulation time, fast release in an acidic environment and high accumulation in tumors. Compared with free DOX, DOX NPs display a dramatically enhanced anticancer therapeutic efficacy in the inhibition of cell and tumor growth. Moreover, they can also be readily incorporated with other anticancer drugs for synergistic chemotherapy to overcome the drug resistance of cancers. The fluorescence properties of DOX also endow these NPs with imaging capabilities, thus making it a multifunctional system for diagnosis and treatment. This work demonstrates great potential of DOX NPs for cancer diagnosis, therapy and overcoming drug tolerance.Considering the obvious advantages in efficacy and price, doxorubicin (DOX) has been widely used for a range of cancers, which is usually encapsulated in various nanocarriers for drug delivery. Although effective, in most nanocarrier-based delivery systems, the drug loading capacity of DOX is rather low; this can lead to undesired systemic toxicity and excretion concern. Herein, we report for the first time the usage of pure doxorubicin nanoparticles (DOX NPs) without addition of any carriers for enhanced chemotherapy against drug-resistance. The drug payload reaches as high as 90.47%, which largely surpassed those in previous reports. These PEG stabilized DOX NPs exhibit good biocompatibility and stability, long blood circulation time, fast release in an acidic environment and high accumulation in tumors. Compared with free DOX, DOX NPs display a dramatically enhanced anticancer therapeutic efficacy in the inhibition of cell and tumor growth. Moreover, they can also be readily incorporated with other anticancer drugs for synergistic chemotherapy to overcome the drug resistance of cancers. The fluorescence properties of DOX also endow these NPs with imaging capabilities, thus making it a multifunctional system for diagnosis and treatment. This work demonstrates great potential of DOX NPs for cancer diagnosis, therapy and overcoming drug tolerance. Electronic supplementary information (ESI) available. See DOI: 10.1039/c5nr00290g

The development of a high-capacity instrument module heat transport system, appendixes

NASA Technical Reports Server (NTRS)

1981-01-01

Data sheets provide temperature requirements for 82 individual instruments that are under development or planned for grouping on a space platform or pallet. The scientific objectives of these instrument packages are related to solar physics, space plasma physics, astronomy, high energy astrophysics, resources observations, environmental observations, materials processing, and life sciences. System specifications are given for a high capacity instrument module heat transport system to be used with future payloads.

About White Sands Missile Range

NASA Technical Reports Server (NTRS)

1991-01-01

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

On locating steganographic payload using residuals

NASA Astrophysics Data System (ADS)

Quach, Tu-Thach

2011-02-01

Locating steganographic payload usingWeighted Stego-image (WS) residuals has been proven successful provided a large number of stego images are available. In this paper, we revisit this topic with two goals. First, we argue that it is a promising approach to locate payload by showing that in the ideal scenario where the cover images are available, the expected number of stego images needed to perfectly locate all load-carrying pixels is the logarithm of the payload size. Second, we generalize cover estimation to a maximum likelihood decoding problem and demonstrate that a second-order statistical cover model can be used to compute residuals to locate payload embedded by both LSB replacement and LSB matching steganography.

Determining potential 30/20 GHZ domestic satellite system concepts and establishment of a suitable experimental configuration

NASA Technical Reports Server (NTRS)

Stevens, G. H.; Anzic, G.

1979-01-01

NASA is conducting a series of millimeter wave satellite communication systems and market studies to: (1) determine potential domestic 30/20 GHz satellite concepts and market potential, and (2) establish the requirements for a suitable technology verification payload which, although intended to be modest in capacity, would sufficiently demonstrate key technologies and experimentally address key operational issues. Preliminary results and critical issues of the current contracted effort are described. Also included is a description of a NASA-developed multibeam satellite payload configuration which may be representative of concepts utilized in a technology flight verification program.

Feasibility evaluation and study of adapting the attitude reference system to the Orbiter camera payload system's large format camera

NASA Technical Reports Server (NTRS)

1982-01-01

A design concept that will implement a mapping capability for the Orbital Camera Payload System (OCPS) when ground control points are not available is discussed. Through the use of stellar imagery collected by a pair of cameras whose optical axis are structurally related to the large format camera optical axis, such pointing information is made available.

Sensing and communication trade-offs in picosatellite formation flying missions.

PubMed

Arnon, Shlomi; Kedar, Debbie

2009-10-01

One of the primary challenges in all small satellite design is the attainment of adequate sensing and communication capabilities within the stringent spatial limitations. These can be defined in terms of surface area expenditure for the different payloads. There is an inevitable trade-off between enhancing the sensing capacity at the expense of reducing communication capabilities on the one hand and, on the other hand, increasing the communication capacity to the detriment of the sensing ability. Careful balancing of the conflicting demands is necessary to achieve acceptable performance levels. In this paper we study two intersatellite optical wireless communication scenarios: (i) a direct link between two satellites and (ii) a folded path link between a master satellite and a picosatellite equipped with a modulatable retroreflector. In the latter case the picosatellite does not have a laser transmitter and the data carrier is the retroreflected beam from the master satellite. The data rate, which is bounded by the sensing payload resolution, is derived using diffraction theory and Shannon capacity considerations. We develop a mathematical model to describe the interrelations between sensing and communication facilities in a picosatellite flight formation using optical technologies and demonstrate system performance trade-offs with a numerical example.

Evaluation of on-board hydrogen storage methods f or high-speed aircraft

NASA Technical Reports Server (NTRS)

Akyurtlu, Ates; Akyurtlu, Jale F.

1991-01-01

Hydrogen is the fuel of choice for hypersonic vehicles. Its main disadvantage is its low liquid and solid density. This increases the vehicle volume and hence the drag losses during atmospheric flight. In addition, the dry mass of the vehicle is larger due to larger vehicle structure and fuel tankage. Therefore it is very desirable to find a fuel system with smaller fuel storage requirements without deteriorating the vehicle performance substantially. To evaluate various candidate fuel systems, they were first screened thermodynamically with respect to their energy content and cooling capacities. To evaluate the vehicle performance with different fuel systems, a simple computer model is developed to compute the vehicle parameters such as the vehicle volume, dry mass, effective specific impulse, and payload capacity. The results indicate that if the payload capacity (or the gross lift-off mass) is the most important criterion, only slush hydrogen and liquid hydrogen - liquid methane gel shows better performance than the liquid hydrogen vehicle. If all the advantages of a smaller vehicle are considered and a more accurate mass analysis can be performed, other systems using endothermic fuels such as cyclohexane, and some boranes may prove to be worthy of further consideration.

Secondary Payload Opportunities on NASA's Space Launch System (SLS) Enable Science and Deep Space Exploration

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). With this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. This first launch of SLS and the Orion Spacecraft is planned no later than November 2018 and will fly along a trans-lunar trajectory, testing the performance of the SLS and Orion systems for future missions. NASA is making investments to expand the science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1) will include thirteen 6U Cubesat small satellites to be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for the advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and deployment will be described to provide potential payload users an understanding of this unique exploration capability.

Low energy stage study. Volume 1: Executive summary. [propulsion system configurations for orbital launching of space shuttle payloads

NASA Technical Reports Server (NTRS)

1978-01-01

Cost effective approaches for placing automated payloads into circular and elliptical orbits using energy requirements significantly lower than that provided by the smallest, currently planned shuttle upper stage, SSUS-D, were investigated. Launch costs were derived using both NASA existing/planned launch approaches as well as new propulsion concepts meeting low-energy regime requirements. Candidate new propulsion approaches considered were solid (tandem, cluster, and controlled), solid/liquid combinations and all-liquid stages. Results show that the most economical way to deliver the 129 low energy payloads is basically with a new modular, short liquid bipropellant stage system for the large majority of the payloads. For the remainder of the payloads, use the shuttle with integral OMS and the Scout form for a few specialized payloads until the Shuttle becomes operational.

Orbital transfer and release of tethered payloads. Continuation of investigation of electrodynamic stabilization and control of long orbiting tethers Martinez-Sanchez, Manuel

NASA Technical Reports Server (NTRS)

Colombo, G.; Grossi, M. D.; Arnold, D.

1983-01-01

The effect of reeling operations on the orbital altitude of the tether system and the development of control laws to minimize tether rebound upon payload release were studied. The use of the tether for LEO/GEO payload orbital transfer was also investigated. It was concluded that (1) reeling operations can contribute a significant amount of energy to the orbit of the system and should be considered in orbit calculations and predictions, (2) deployment of payloads, even very large payloads, using tethers is a practical and fully stable operation, (3) tether augmented LEO/GEO transfer operations yield useful payload gains under the practical constraint of fixed size OTV's, and (4) orbit to orbit satellite retrieval is limited by useful revisit times to orbital inclinations of less than forty-five degrees.

Project UM-HAUL (UnManned Heavy pAyload Unloader and Lander): The design of a reusable lunar lander with an independent cargo unloader

NASA Technical Reports Server (NTRS)

1991-01-01

Project UM-Haul is the preliminary design of a reusable lunar transportation vehicle that travels between a lunar parking orbit and the lunar surface. This vehicle is an indispensible link in the overall task of establishing a lunar base as defined by the NASA Space Exploration Initiative. The response to this need consists of two independent vehicles: a lander and an unloader. The system can navigate and unload itself with a minimum amount of human intervention. The design addresses structural analysis, propulsion, power, controls, communications, payload handling and orbital operations. The Lander has the capacity to decend from low lunar orbit (LLO) to the lunar surface carrying a 7000 kg payload, plus the unloader, plus propellant for ascent to LLO. The Lander employs the Unloader by way of a motorized ramp. The Unloader is a terrain vehicle capable of carrying cargoes of 8,500 kg mass and employs a lift system to lower payloads to the ground. The system can perform ten missions before requiring major servicing.

Characterization of lunar surface materials for use in construction

NASA Technical Reports Server (NTRS)

Johnson, Stewart W.; Burns, Jack O.

1992-01-01

The Workshop on the Concept of a Common Lunar Lander, which was held at the NASA Johnson Space Center on July 1 and 2, 1991, discussed potential payloads to be placed on the Moon by a common, generic, unmanned, vehicle beginning late in this decade. At this workshop, a variety of payloads were identified including a class of one-meter (and larger) optical telescopes to operate on the lunar surface. These telescopes for lunar-based astronomy are presented in an earlier section of this report. The purpose of this section is to suggest that these and other payloads for the Common Lunar Lander be used to facilitate technology development for the proposed 16-meter Aperture UV/Visible/IR Large Lunar Telescope (LLT) and a large optical aperture-synthesis instrument analogous to the Very Large Array of the National Radio Astronomy Observatory.

ASPS performance with large payloads onboard the Shuttle Orbiter. [Annular Suspension and Pointing System

NASA Technical Reports Server (NTRS)

Keckler, C. R.

1980-01-01

A high fidelity digital computer simulation was used to establish the viability of the Annular Suspension and Pointing System (ASPS) for satisfying the pointing and stability requirements of facility class payloads, such as the Solar Optical Telescope, when subjected to the Orbiter disturbance environment. The ASPS and its payload were subjected to disturbances resulting from crew motions in the Orbiter aft flight deck and VRCS thruster firings. Worst case pointing errors of 0.005 arc seconds were experienced under the disturbance environment simulated; this is well within the 0.08 arc seconds requirement specified by the payload.

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

NASA Technical Reports Server (NTRS)

Meyer, K. A.

1980-01-01

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

Adaptive digital beamforming for a CDMA mobile communications payload

NASA Technical Reports Server (NTRS)

Munoz-Garcia, Samuel G.; Ruiz, Javier Benedicto

1993-01-01

In recent years, Spread-Spectrum Code Division Multiple Access (CDMA) has become a very popular access scheme for mobile communications due to a variety of reasons: excellent performance in multipath environments, high scope for frequency reuse, graceful degradation near saturation, etc. In this way, a CDMA system can support simultaneous digital communication among a large community of relatively uncoordinated users sharing a given frequency band. Nevertheless, there are also important problems associated with the use of CDMA. First, in a conventional CDMA scheme, the signature sequences of asynchronous users are not orthogonal and, as the number of active users increases, the self-noise generated by the mutual interference between users considerably degrades the performance, particularly in the return link. Furthermore, when there is a large disparity in received powers - due to differences in slant range or atmospheric attenuation - the non-zero cross-correlation between the signals gives rise to the so-called near-far problem. This leads to an inefficient utilization of the satellite resources and, consequently, to a drastic reduction in capacity. Several techniques were proposed to overcome this problem, such as Synchronized CDMA - in which the signature sequences of the different users are quasi-orthogonal - and power control. At the expense of increased network complexity and user coordination, these techniques enable the system capacity to be restored by equitably sharing the satellite resources among the users. An alternative solution is presented based upon the use of time-reference adaptive digital beamforming on board the satellite. This technique enables a high number of independently steered beams to be generated from a single phased array antenna, which automatically track the desired user signal and null the unwanted interference source. In order to use a time-reference adaptive antenna in a communications system, the main challenge is to obtain a reference signal highly correlated with the desired user signal and uncorrelated with the interferences. CDMA lends itself very easily to the generation of such a reference signal, thanks to the a priori knowledge of the user's signature sequence. First, the integration of an adaptive antenna in an asynchronous CDMA system is analyzed. The adaptive antenna system can provide increased interference rejection - much higher than that afforded by the code alone - and, since CDMA is mainly interference limited, any reduction in interference converts directly and linearly into an increase in capacity. Analyses and computer simulations are presented that show how an asynchronous CDMA system incorporating adaptive beamforming can provide at least as much capacity as a synchronous system. More importantly, the proposed concept allows the near-far effect to be mitigated without requiring a tight coordination of the users in terms of transmitted power control or network synchronization. The system is extremely robust to the near-far effect because the signals reaching the satellite from directions other than that of the desired user - which are likely to have different power levels - are adaptively canceled by the antenna. Finally, a payload architecture is presented that illustrates the practical implementation of this concept. This digital payload architecture demonstrates that with the advent of high performance CMOS digital processing, the on-board implementation of complex DSP techniques - in particular Digital Beamforming - has become possible, being most attractive for Mobile Satellite Communications.

Adaptive digital beamforming for a CDMA mobile communications payload

NASA Astrophysics Data System (ADS)

Munoz-Garcia, Samuel G.; Ruiz, Javier Benedicto

In recent years, Spread-Spectrum Code Division Multiple Access (CDMA) has become a very popular access scheme for mobile communications due to a variety of reasons: excellent performance in multipath environments, high scope for frequency reuse, graceful degradation near saturation, etc. In this way, a CDMA system can support simultaneous digital communication among a large community of relatively uncoordinated users sharing a given frequency band. Nevertheless, there are also important problems associated with the use of CDMA. First, in a conventional CDMA scheme, the signature sequences of asynchronous users are not orthogonal and, as the number of active users increases, the self-noise generated by the mutual interference between users considerably degrades the performance, particularly in the return link. Furthermore, when there is a large disparity in received powers - due to differences in slant range or atmospheric attenuation - the non-zero cross-correlation between the signals gives rise to the so-called near-far problem. This leads to an inefficient utilization of the satellite resources and, consequently, to a drastic reduction in capacity. Several techniques were proposed to overcome this problem, such as Synchronized CDMA - in which the signature sequences of the different users are quasi-orthogonal - and power control. At the expense of increased network complexity and user coordination, these techniques enable the system capacity to be restored by equitably sharing the satellite resources among the users. An alternative solution is presented based upon the use of time-reference adaptive digital beamforming on board the satellite. This technique enables a high number of independently steered beams to be generated from a single phased array antenna, which automatically track the desired user signal and null the unwanted interference source. In order to use a time-reference adaptive antenna in a communications system, the main challenge is to obtain a reference signal highly correlated with the desired user signal and uncorrelated with the interferences. CDMA lends itself very easily to the generation of such a reference signal, thanks to the a priori knowledge of the user's signature sequence. First, the integration of an adaptive antenna in an asynchronous CDMA system is analyzed. The adaptive antenna system can provide increased interference rejection - much higher than that afforded by the code alone - and, since CDMA is mainly interference limited, any reduction in interference converts directly and linearly into an increase in capacity. Analyses and computer simulations are presented that show how an asynchronous CDMA system incorporating adaptive beamforming can provide at least as much capacity as a synchronous system. More importantly, the proposed concept allows the near-far effect to be mitigated without requiring a tight coordination of the users in terms of transmitted power control or network synchronization. The system is extremely robust to the near-far effect because the signals reaching the satellite from directions other than that of the desired user - which are likely to have different power levels - are adaptively canceled by the antenna. Finally, a payload architecture is presented that illustrates the practical implementation of this concept.

The 15th Aerospace Mechanisms Symposium

NASA Technical Reports Server (NTRS)

1981-01-01

Technological areas covered include: aerospace propulsion; aerodynamic devices; crew safety; space vehicle control; spacecraft deployment, positioning, and pointing; deployable antennas/reflectors; and large space structures. Devices for payload deployment, payload retention, and crew extravehicular activities on the space shuttle orbiter are also described.

Vibration isolation versus vibration compensation on multiple payload platforms

NASA Technical Reports Server (NTRS)

Sirlin, S. W.

1989-01-01

There are many future science instruments with high performance pointing (sub microradian) requirements. To build a separate spacecraft for each payload is prohibitively expensive, especially as not all instruments need to be in space for a long duration. Putting multiple payloads on a single basebody that supplies power, communications, and orbit maintenance is cheaper, easier to service, and allows for the spacecraft bus to be reused as new instruments become available to replace old instruments. Once several payloads are mounted together, the articulation of one may disturb another. The situation is even more extreme when the basebody serves multiple purposes, such as space station which has construction, satellite servicing, and man motion adding to the disturbance environment. The challenge then is to maintain high performance at low cost in a multiple payload environment. The goal is to supply many future science instruments with high performance pointing (sub microradian). The options are independent spacecraft for each payload (expensive); or multiple payloads on a single basebody (cheaper, easier to service, basebody reusable for several short duration payloads). The problems are one payload can disturb another, and other activities create large disturbances (construction, satellite servicing, and man motion).

Antibody Drug Conjugates: Application of Quantitative Pharmacology in Modality Design and Target Selection.

PubMed

Sadekar, S; Figueroa, I; Tabrizi, M

2015-07-01

Antibody drug conjugates (ADCs) are a multi-component modality comprising of an antibody targeting a cell-specific antigen, a potent drug/payload, and a linker that can be processed within cellular compartments to release payload upon internalization. Numerous ADCs are being evaluated in both research and clinical settings within the academic and pharmaceutical industry due to their ability to selectively deliver potent payloads. Hence, there is a clear need to incorporate quantitative approaches during early stages of drug development for effective modality design and target selection. In this review, we describe a quantitative approach and framework for evaluation of the interplay between drug- and systems-dependent properties (i.e., target expression, density, localization, turnover, and affinity) in order to deliver a sufficient amount of a potent payload into the relevant target cells. As discussed, theoretical approaches with particular considerations given to various key properties for the target and modality suggest that delivery of the payload into particular effect cells to be more sensitive to antigen concentrations for targets with slow turnover rates as compared to those with faster internalization rates. Further assessments also suggest that increasing doses beyond the threshold of the target capacity (a function of target internalization and expression) may not impact the maximum amount of payload delivered to the intended effect cells. This article will explore the important application of quantitative sciences in selection of the target and design of ADC modalities.

The winged horse

NASA Astrophysics Data System (ADS)

Nichols, Robert G.

1989-02-01

The development and commercialization of the Pegasus unmanned launch vehicle are discussed. The materials used in Pegasus construction, the payload capacity, and possible commercial users and missions for the Pegasus are examined. The Pegasus configuration and mission profile are illustrated and the Pegasus is compared with other unmanned launch vehicles.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

The International Space Station (ISS), with the newly installed U.S. Laboratory, Destiny, is backdropped over clouds, water and land in South America. South Central Chile shows up at the bottom of the photograph. Just below the Destiny, the Chacao Charnel separates the large island of Chile from the mainland and connects the Gulf of Coronado on the Pacific side with the Gulf of Ancud, southwest of the city of Puerto Montt. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

International Space Station (ISS)

NASA Image and Video Library

2001-02-16

The International Space Station (ISS), with the newly installed U.S. Laboratory, Destiny, is backdropped over clouds, water and land in South America. South Central Chile shows up at the bottom of the photograph. Just below the Destiny, the Chacao Charnel separates the large island of Chile from the mainland and connects the Gulf of Coronado on the Pacific side with the Gulf of Ancud, southwest of the city of Puerto Montt. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

KSC-99pd0209

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- In the SPACEHAB Facility, the STS-96 crew looks at equipment as part of a payload Interface Verification Test (IVT) for their upcoming mission to the International Space Station . From left are Mission Specialist Ellen Ochoa (behind the opened storage cover ), Commander Kent Rominger, Pilot Rick Husband (holding a lithium hydroxide canister) and Mission Specialists Dan Barry, Valery Tokarev of Russia and Julie Payette. In the background is TTI interpreter Valentina Maydell. The other crew member at KSC for the IVT is Mission Specialist Tamara Jernigan. Mission STS-96 carries the SPACEHAB Logistics Double Module, which has equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

KSC-99pp0201

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- In the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (left) and Commander Kent Rominger (second from right) listen to Lynn Ashby (far right), with JSC, talking about the SPACEHAB equipment in front of them during a payload Interface Verification Test (IVT). In the background behind Tokarev is TTI interpreter Valentina Maydell. Other STS-96 crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Dan Barry, Ellen Ochoa, Tamara Jernigan and Julie Payette. Mission STS-96 carries the SPACEHAB Logistics Double Module, which will have equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. It carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

KSC-99pd0214

NASA Image and Video Library

1999-02-11

KENNEDY SPACE CENTER, FLA. -- During a payload Interface Verification Test (IVT) in the SPACEHAB Facility, STS-96 Mission Specialist Valery Tokarev of Russia (second from left) and Commander Kent Rominger learn about the Sequential Shunt Unit (SSU) in front of them from Lynn Ashby (far right), with Johnson Space Center. At the far left looking on is TTI interpreter Valentina Maydell. Other crew members at KSC for the IVT are Pilot Rick Husband and Mission Specialists Ellen Ochoa, Tamara Jernigan, Dan Barry and Julie Payette. The SSU is part of the cargo on Mission STS-96, which carries the SPACEHAB Logistics Double Module, with equipment to further outfit the International Space Station service module and equipment that can be off-loaded from the early U.S. assembly flights. The SPACEHAB carries internal logistics and resupply cargo for station outfitting, plus an external Russian cargo crane to be mounted to the exterior of the Russian station segment and used to perform space walking maintenance activities. The double module stowage provides capacity of up to 10,000 lbs. with the ability to accommodate powered payloads, four external rooftop stowage locations, four double-rack locations (two powered), up to 61 bulkhead-mounted middeck locker locations, and floor storage for large unique items and Soft Stowage. STS-96 is targeted to launch May 20 about 9:32 a.m

Research Opportunities on board Virgin Galactic's SpaceShipTwo

NASA Astrophysics Data System (ADS)

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

2013-09-01

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

Early Program Development

NASA Image and Video Library

1989-01-01

This 1989 artist's rendering shows how a Shuttle-C would look during launch. As envisioned by Marshall Space Flight Center plarners, the Shuttle-C would be an unmanned heavy-lift cargo vehicle derived from Space Shuttle elements. The vehicle would utilize the basic Shuttle propulsion units (Solid Rocket Boosters, Space Shuttle Main Engine, External Tank), but would replace the Orbiter with an unmanned Shuttle-C Cargo Element (SCE). The SCE would have a payload bay lenght of eighty-two feet, compared to sixty feet for the Orbiter cargo bay, and would be able to deliver 170,000 pound payloads to low Earth orbit, more than three times the Orbiter's capacity.

Early Program Development

NASA Image and Video Library

1989-01-01

In this 1989 artist's concept, the Shuttle-C floats in space with its cargo bay doors open. As envisioned by Marshall Space Flight Center plarners, the Shuttle-C would be an unmanned heavy lift cargo vehicle derived from Space Shuttle elements. The vehicle would utilize the basic Shuttle propulsion units (Solid Rocket Boosters, Space Shuttle Main Engine, External Tank), but would replace the Oribiter with an unmanned Shuttle-C Cargo Element (SCE). The SCE would have a payload bay length of eighty-two feet, compared to sixty feet for the Orbiter cargo bay, and would be able to deliver 170,000 pound payloads to low Earth orbit, more than three times the Orbiter's capacity.

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

DTIC Science & Technology

1984-12-15

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

Rapid prototyping and AI programming environments applied to payload modeling

NASA Technical Reports Server (NTRS)

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

1987-01-01

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

A Definition of STS Accommodations for Attached Payloads

NASA Technical Reports Server (NTRS)

Echols, F. L.; Broome, P. A.

1983-01-01

An input to a study conducted to define a set of carrier avionics for supporting large structures experiments attached to the Space Shuttle Orbiter is reported. The "baseline" Orbier interface used in developing the avionics concept for the Space Technology Experiments Platform, STEP, which Langley Research Center has proposed for supporting experiments of this sort is defined. Primarily, flight operations capabilities and considerations and the avionics systems capabilities that are available to a payload as a "mixed cargo" user of the Space Transportation System are addressed. Ground operations for payload integration at Kennedy Space Center, and ground operations for payload support during the mission are also discussed.

STS-79 Ku-band antenna, ODS and Spacehab module at PCR

NASA Technical Reports Server (NTRS)

1996-01-01

The orbiter Ku-band antenna looms large in this view of the Space Shuttle Atlantis' payload bay. Visible just past the antenna system -- stowed on the starboard side of the payload bay wall -- is the Orbiter Docking System (ODS), and connected to the ODS via a tunnel is the Spacehab Double Module in the aft area of the payload bay. This photograph was taken from the starboard wing platform on the fifth level of the Payload Changeout Room (PCR) at Launch Pad 39A. Work is under way in the PCR to close Atlantis' payload bay doors for flight. Atlantis currently is being targeted for liftoff on Mission STS-79, the fourth docking of the U.S. Shuttle to the Russian Space Station Mir, around September 12.

Technical Evaluation Report

DTIC Science & Technology

2006-10-01

measuring unit and the control computer have been flight tested using both a small UAV and the PRP-560 “ Ranger ” patrol and rescue hovercraft, which...version based on the G9- Galaxy ram air parachute. Recently, in an effort to further extend the system’s payload capacity, developmental flight tests

SHUTTLE - PAYLOADS (STS-41G) - KSC

NASA Image and Video Library

1984-10-05

Payload canister transporter in Vertical Processing Facility Clean Room loaded with Earth Radiation Budget Experiment (ERBS), Large Format Camera (LFC), and Orbital Reservicing System (ORS) for STS-41G Mission. 1. STS-41G - EXPERIMENTS 2. CAMERAS - LFC KSC, FL Also available in 4x5 CN

Commercially Hosted Government Payloads: Lessons from Recent Programs

NASA Technical Reports Server (NTRS)

Andraschko, Mark A.; Antol, Jeffrey; Horan, Stephen; Neil, Doreen

2011-01-01

In a commercially hosted operational mode, a scientific instrument or operational device is attached to a spacecraft but operates independently from the spacecraft s primary mission. Despite the expected benefits of this arrangement, there are few examples of hosted payload programs actually being executed by government organizations. The lack of hosted payload programs is largely driven by programmatic challenges, both real and perceived, rather than by technical challenges. Partly for these reasons, NASA has not sponsored a hosted payload program, in spite of the benefits and visible community interest in doing so. In the interest of increasing the use of hosted payloads across the space community, this paper seeks to alleviate concerns about hosted payloads by identifying these programmatic challenges and presenting ways in which they can be avoided or mitigated. Despite the challenges, several recent hosted payload programs have been successfully completed or are currently in progress. This paper presents an assessment of these programs, with a focus on acquisition, costs, schedules, risks, and other programmatic aspects. The hosted payloads included in this study are the Federal Aviation Administration's Wide Area Augmentation System (WAAS) payloads, United States Coast Guard's Automatic Identification System (AIS) demonstration payload, Department of Defense's IP Router In Space (IRIS) demonstration payload, the United States Air Force's Commercially Hosted Infrared Payload (CHIRP), and the Australian Defence Force's Ultra High Frequency (UHF) payload. General descriptions of each of these programs are presented along with issues that have been encountered and lessons learned from those experiences. A set of recommended approaches for future hosted payload programs is presented, with a focus on addressing risks or potential problem areas through smart and flexible contracting up front. This set of lessons and recommendations is broadly applicable to future hosted payload programs, whether they are technology demonstrations, communications systems, or operational sensors. Additionally, we present a basic cost model for commercial access to space for hosted payloads as a function of payload mass

Internet Based Remote Operations

NASA Technical Reports Server (NTRS)

Chamberlain, James

1999-01-01

This is the Final Report for the Internet Based Remote Operations Contract, has performed payload operations research support tasks March 1999 through September 1999. These tasks support the GSD goal of developing a secure, inexpensive data, voice, and video mission communications capability between remote payload investigators and the NASA payload operations team in the International Space Station (ISS) era. AZTek has provided feedback from the NASA payload community by utilizing its extensive payload development and operations experience to test and evaluate remote payload operations systems. AZTek has focused on use of the "public Internet" and inexpensive, Commercial-off-the-shelf (COTS) Internet-based tools that would most benefit "small" (e.g., $2 Million or less) payloads and small developers without permanent remote operations facilities. Such projects have limited budgets to support installation and development of high-speed dedicated communications links and high-end, custom ground support equipment and software. The primary conclusions of the study are as follows: (1) The trend of using Internet technology for "live" collaborative applications such as telescience will continue. The GSD-developed data and voice capabilities continued to work well over the "public" Internet during this period. 2. Transmitting multiple voice streams from a voice-conferencing server to a client PC to be mixed and played on the PC is feasible. 3. There are two classes of voice vendors in the market: - Large traditional phone equipment vendors pursuing integration of PSTN with Internet, and Small Internet startups.The key to selecting a vendor will be to find a company sufficiently large and established to provide a base voice-conferencing software product line for the next several years.

Space Launch System for Exploration and Science

NASA Astrophysics Data System (ADS)

Klaus, K.

2013-12-01

Introduction: The Space Launch System (SLS) is the most powerful rocket ever built and provides a critical heavy-lift launch capability enabling diverse deep space missions. The exploration class vehicle launches larger payloads farther in our solar system and faster than ever before. The vehicle's 5 m to 10 m fairing allows utilization of existing systems which reduces development risks, size limitations and cost. SLS lift capacity and superior performance shortens mission travel time. Enhanced capabilities enable a myriad of missions including human exploration, planetary science, astrophysics, heliophysics, planetary defense and commercial space exploration endeavors. Human Exploration: SLS is the first heavy-lift launch vehicle capable of transporting crews beyond low Earth orbit in over four decades. Its design maximizes use of common elements and heritage hardware to provide a low-risk, affordable system that meets Orion mission requirements. SLS provides a safe and sustainable deep space pathway to Mars in support of NASA's human spaceflight mission objectives. The SLS enables the launch of large gateway elements beyond the moon. Leveraging a low-energy transfer that reduces required propellant mass, components are then brought back to a desired cislunar destination. SLS provides a significant mass margin that can be used for additional consumables or a secondary payloads. SLS lowers risks for the Asteroid Retrieval Mission by reducing mission time and improving mass margin. SLS lift capacity allows for additional propellant enabling a shorter return or the delivery of a secondary payload, such as gateway component to cislunar space. SLS enables human return to the moon. The intermediate SLS capability allows both crew and cargo to fly to translunar orbit at the same time which will simplify mission design and reduce launch costs. Science Missions: A single SLS launch to Mars will enable sample collection at multiple, geographically dispersed locations and a low-risk, direct return of Martian material. For the Europa Clipper mission the SLS eliminates Venus and Earth flybys, providing a direct launch to the Jovian system, arriving four years earlier than missions utilizing existing launch vehicles. This architecture allows increased mass for radiation shielding, expansion of the science payload and provides a model for other outer planet missions. SLS provides a direct launch to the Uranus system, reducing travel time by two years when compared to existing launch capabilities. SLS can launch the Advanced Technology Large-Aperture Space Telescope (ATLAST 16 m) to SEL2, providing researchers 10 times the resolution of the James Webb Space Telescope and up to 300 times the sensitivity of the Hubble Space Telescope. SLS is the only vehicle capable of deploying telescopes of this mass and size in a single launch. It simplifies mission design and reduces risks by eliminating the need for multiple launches and in-space assembly. SLS greatly shortens interstellar travel time, delivering the Interstellar Explorer to 200 AU in about 15 years with a maximum speed of 63 km/sec--13.3 AU per year (Neptune orbits the sun at an approximate distance of 30 AU ).

Navy Virginia (SSN-774) Class Attack Submarine Procurement: Background and Issues for Congress

DTIC Science & Technology

2016-02-12

Tomahawk cruise missiles or other payloads, such as large-diameter unmanned underwater vehicles (UUVs). The Navy’s FY2016 30-year SSN procurement plan, if...again on a smaller scale than possible with the SSGNs);  covert offensive and defensive mine warfare;  anti-submarine warfare (ASW); and  anti...Tomahawk cruise missiles or other payloads, such as large-diameter unmanned underwater vehicles (UUVs). 17 The four additional launch tubes in the

The remote characterization of vegetation using Unmanned Aerial Vehicle photography

USDA-ARS?s Scientific Manuscript database

Unmanned Aerial Vehicles (UAVs) can fly in place of piloted aircraft to gather remote sensing information on vegetation characteristics. The type of sensors flown depends on the instrument payload capacity available, so that, depending on the specific UAV, it is possible to obtain video, aerial phot...

14 CFR 125.271 - Emergency and emergency evacuation duties.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Emergency and emergency evacuation duties. 125.271 Section 125.271 Aeronautics and Space FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD...

14 CFR 26.43 - Holders of and applicants for type certificates-Repairs.

Code of Federal Regulations, 2014 CFR

2014-01-01

... payload capacity of 7,500 pounds or more. (b) List of fatigue critical baseline structure. For airplanes...) Identify fatigue critical baseline structure for all airplane model variations and derivatives approved... affects fatigue critical baseline structure identified under paragraph (b)(1) of this section; (2) Perform...

14 CFR 26.43 - Holders of and applicants for type certificates-Repairs.

Code of Federal Regulations, 2011 CFR

2011-01-01

... payload capacity of 7,500 pounds or more. (b) List of fatigue critical baseline structure. For airplanes...) Identify fatigue critical baseline structure for all airplane model variations and derivatives approved... affects fatigue critical baseline structure identified under paragraph (b)(1) of this section; (2) Perform...

14 CFR 26.43 - Holders of and applicants for type certificates-Repairs.

Code of Federal Regulations, 2012 CFR

2012-01-01

... payload capacity of 7,500 pounds or more. (b) List of fatigue critical baseline structure. For airplanes...) Identify fatigue critical baseline structure for all airplane model variations and derivatives approved... affects fatigue critical baseline structure identified under paragraph (b)(1) of this section; (2) Perform...

14 CFR 26.43 - Holders of and applicants for type certificates-Repairs.

Code of Federal Regulations, 2013 CFR

2013-01-01

... payload capacity of 7,500 pounds or more. (b) List of fatigue critical baseline structure. For airplanes...) Identify fatigue critical baseline structure for all airplane model variations and derivatives approved... affects fatigue critical baseline structure identified under paragraph (b)(1) of this section; (2) Perform...

14 CFR 26.43 - Holders of and applicants for type certificates-Repairs.

Code of Federal Regulations, 2010 CFR

2010-01-01

... payload capacity of 7,500 pounds or more. (b) List of fatigue critical baseline structure. For airplanes...) Identify fatigue critical baseline structure for all airplane model variations and derivatives approved... affects fatigue critical baseline structure identified under paragraph (b)(1) of this section; (2) Perform...

Shuttle payload bay dynamic environments: Summary and conclusion report for STS flights 1-5 and 9

NASA Technical Reports Server (NTRS)

Oconnell, M.; Garba, J.; Kern, D.

1984-01-01

The vibration, acoustic and low frequency loads data from the first 5 shuttle flights are presented. The engineering analysis of that data is also presented. Vibroacoustic data from STS-9 are also presented because they represent the only data taken on a large payload. Payload dynamic environment predictions developed by the participation of various NASA and industrial centers are presented along with a comparison of analytical loads methodology predictions with flight data, including a brief description of the methodologies employed in developing those predictions for payloads. The review of prediction methodologies illustrates how different centers have approached the problems of developing shuttle dynamic environmental predictions and criteria. Ongoing research activities related to the shuttle dynamic environments are also described. Analytical software recently developed for the prediction of payload acoustic and vibration environments are also described.

CHARGE-2 rocket observations of vehicle charging and charge neutralization

NASA Astrophysics Data System (ADS)

Banks, P. M.; Gilchrist, B. E.; Neubert, T.; Myers, N.; Raitt, W. J.; Williamson, P. R.; Fraser-Smith, A. C.; Sasaki, S.

Observations of electrical charging and other phenomena have been made in the ionosphere with the CHARGE-2 tethered rocket system. In this experiment, two electrically connected payloads with a variety of plasma instruments measured effects associated with operation of a 1 keV, 40 mA electron gun and a 450-volt dc power supply. During electron beam operations, it was found that both mother and daughter payloads reached high positive potentials as a consequence of the restricted electron current collecting area of the payloads. During neutral gas thruster firings, the payload potentials were dramatically reduced, indicating that electrical discharges could effectively ground each payload to plasma potential. Other thruster-related effects were also seen, including substantial reductions of return current-associated electrical noise at HF and VLF and large increases in 3914 A light in the plasma sheath.

Proceedings of the 14th Aerospace Mechanisms Symposium

NASA Technical Reports Server (NTRS)

1980-01-01

Technological areas covered include aviation propulsion, aerodynamic devices, and crew safety; space vehicle propulsion, guidance and control; spacecraft deployment, positioning, and pointing; spacecraft bearings, gimbals, and lubricants; and large space structures. Devices for payload deployment, payload retention, and crew extravehicular activity on the space shuttle orbiter are also described.

Canadian robotic arm is moved to the payload canister for STS-100

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - Centered over the payload canister in the Space Station Processing Facility, the overhead crane begins lowering the Canadian robotic arm, SSRMS, on its pallet inside. The arm is 57.7 feet (17.6 meters) long when fully extended and has seven motorized joints. It is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self-relocatable with a Latching End Effector, so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. The SSRMS is part of the payload on mission STS-100, scheduled to launch April 19 at 2:41 p.m. EDT from Launch Pad 39A, KSC.

Canadian robotic arm is moved to the payload canister for STS-100

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - An overhead crane moves along the top of the Space Station Processing Facility, carrying the Canadian robotic arm, SSRMS, on its pallet to the payload canister. The arm is 57.7 feet (17.6 meters) long when fully extended and has seven motorized joints. It is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self-relocatable with a Latching End Effector, so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. The SSRMS is part of the payload on mission STS-100, scheduled to launch April 19 at 2:41 p.m. EDT from Launch Pad 39A, KSC.

Canadian robotic arm is moved to the payload canister for STS-100

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - In the Space Station Processing Facility, an overhead crane lifts the pallet holding the Canadian robotic arm, SSRMS, to move it to the payload canister. The arm is 57.7 feet (17.6 meters) long when fully extended and has seven motorized joints. It is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self- relocatable with a Latching End Effector, so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. The SSRMS is part of the payload on mission STS-100, scheduled to launch April 19 at 2:41 p.m. EDT from Launch Pad 39A, KSC.

Neural controller for adaptive movements with unforeseen payloads.

PubMed

Kuperstein, M; Wang, J

1990-01-01

A theory and computer simulation of a neural controller that learns to move and position a link carrying an unforeseen payload accurately are presented. The neural controller learns adaptive dynamic control from its own experience. It does not use information about link mass, link length, or direction of gravity, and it uses only indirect uncalibrated information about payload and actuator limits. Its average positioning accuracy across a large range of payloads after learning is 3% of the positioning range. This neural controller can be used as a basis for coordinating any number of sensory inputs with limbs of any number of joints. The feedforward nature of control allows parallel implementation in real time across multiple joints.

Workshop Report on Ares V Solar System Science

NASA Technical Reports Server (NTRS)

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

2008-01-01

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

An overview on the TACTS mission using the new German research aircraft HALO in summer 2012

NASA Astrophysics Data System (ADS)

Engel, Andreas; Boenisch, Harald

2013-04-01

The TACTS (Transport and Composition in the UTLS) mission is the first large atmospheric mission of the new German research aircraft HALO. TACTS aims at improving our understanding of the transport processes which determine the chemical composition in the UTLS with a special emphasis on the transition from summer to fall. The mission was flown in August and September 2012 with a fully equipped aircraft carrying 13 different instruments measuring a wide range of chemical tracers with different lifetimes and different source-sink characteristics. The payload consists of both in-situ and remote sensing instruments. In addition to TACTS the same payload was employed to measure the chemical composition during a large north-south transect as part of the ESMVal project. Data are available up to to altitudes above 15 km, potential temperatures above 400 K and covering the latitude range from 65°S to 80°N. Due to the large payload a very wide range of measurements allows for a very good characterisation of the chemical composition. All instruments performed well and close to complete data sets are available for all flights performed during both missions. We present an overview of the scientific aims of TACTS, the payload, the measurements performed and some selected first results.

A rocket-borne microprocessor-based experiment for investigation of energetic particles in the D and E regions

NASA Technical Reports Server (NTRS)

Braswell, F. M.

1981-01-01

An energetic experiment using the Z80 family of microcomputer components is described. Data collected from the experiment allowed fast and efficient postprocessing, yielding both energy-spectrum and pitch-angle distribution of energetic particles in the D and E regions. Advanced microprocessor system architecture and software concepts were used in the design to cope with the large amount of data being processed. This required the Z80 system to operate at over 80% of its total capacity. The microprocessor system was included in the payloads of three rockets launched during the Energy Budget Campaign at ESRANGE, Kiruna, Sweden in November 1980. Based on preliminary examination of the data, the performance of the experiment was satisfactory and good data were obtained on the energy spectrum and pitch-angle distribution of the particles.

LMSS - From low data rate to voice services

NASA Astrophysics Data System (ADS)

Rogard, R.

1992-03-01

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

Ultra-heavy vertical lift system: The Heli-Stat. [helicopter - airship combination for materials handling

NASA Technical Reports Server (NTRS)

Piasecki, F. N.

1975-01-01

A hybrid VTOL airship which is combined with helicopters is evaluated. The static lift of the airship supports approximately the full empty weight of the entire assembly. The helicopter rotors furnish the lift to support the payload as well as the propulsion and control about all axes. Thus existing helicopters, with no new technology required, can be made to lift payloads of ten times the capacity of each one alone, and considerably more than that of any airship built so far. A vehicle is described which has a 75-ton payload, based on four existing CH-53D helicopters and an airship of 3,600,000 cu. ft. The method of interconnection is described along with discussion of control, instrumentation, drive system and critical design conditions. The vertical lift and positioning capabilities of this vehicle far exceed any other means available today, yet can be built with a minimum of risk, development cost and time.

The first dedicated life sciences mission - Spacelab 4

NASA Technical Reports Server (NTRS)

Cramer, D. R.; Reid, D. H.; Klein, H. P.

1983-01-01

The details of the payload and the experiments in Spacelab 4, the first Spacelab mission dedicated entirely to the life sciences, are discussed. The payload of Spacelab 4, carried in the bay of the Shuttle Orbiter, consists of 25 tentatively selected investigations combined into a comprehensive integrated exploration of the effects of acute weightlessness on living systems. The payload contains complementary designs in the human and animal investigations in order to validate animal models of human physiology in weightlessness. Animals used as experimental subjects will include squirrel monkeys, laboratory rats, several species of plants, and frog eggs. The main scientific objectives of the investigations include the study of the acute cephalic fluid shift, cardiovascular adaptation to weightlessness, including postflight reductions in orthostatic tolerance and exercise capacity, and changes in vestibular function, including space motion sickness, associated with weightlessness. Other scientific objective include the study of red cell mass reduction, negative nitrogen balance, altered calcium metabolism, suppressed in vitro lymphocyte reactivity, gravitropism and photropism in plants, and fertilization and early development in frog eggs.

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

NASA Astrophysics Data System (ADS)

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

2017-09-01

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

Space Launch System Co-Manifested Payload Options for Habitation

NASA Technical Reports Server (NTRS)

Smitherman, David

2015-01-01

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

Performance Characteristics of Lithium-Ion Prototype Batteries for Mars Surveyor Program 2001 Lander

NASA Technical Reports Server (NTRS)

Smart, M. C.; Ratnakumar, B. V.; Whitcanack, L.; Surampudi, S.; Byers, J.; Marsh, R. A.

2000-01-01

A viewgraph presentation outlines the scientific payload, expected launch date and tasks, and an image of the Mars Surveyor 2001 Lander components. The Lander's battery specifications are given. The program objectives for the Li-ion cells for the Lander are listed, and results performance evaluation and cycle life performance tests are outlined for different temperatures. Cell charge characteristics are described, and test data is presented for charge capacity at varying temperatures. Capacity retention and storage characteristics tests are described and results are shown.

14 CFR 125.175 - Protection of other airplane components against fire.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 3 2013-01-01 2013-01-01 false Protection of other airplane components... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Requirements § 125.175 Protection of other airplane components against fire. (a) Except as provided in...

14 CFR 125.175 - Protection of other airplane components against fire.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 3 2014-01-01 2014-01-01 false Protection of other airplane components... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Requirements § 125.175 Protection of other airplane components against fire. (a) Except as provided in...

14 CFR 125.175 - Protection of other airplane components against fire.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 3 2012-01-01 2012-01-01 false Protection of other airplane components... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Requirements § 125.175 Protection of other airplane components against fire. (a) Except as provided in...

14 CFR 125.175 - Protection of other airplane components against fire.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 3 2011-01-01 2011-01-01 false Protection of other airplane components... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Requirements § 125.175 Protection of other airplane components against fire. (a) Except as provided in...

14 CFR 125.175 - Protection of other airplane components against fire.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 3 2010-01-01 2010-01-01 false Protection of other airplane components... CERTIFICATION AND OPERATIONS: AIRPLANES HAVING A SEATING CAPACITY OF 20 OR MORE PASSENGERS OR A MAXIMUM PAYLOAD... Requirements § 125.175 Protection of other airplane components against fire. (a) Except as provided in...

Increasing the Endurance and Payload Capacity of Unmanned Vehicles with Thin-Film Photovoltaics

DTIC Science & Technology

2014-06-01

25  1.  Maximum Power Point Tracker .......................................................25  2.  DC-DC Power Conversion...An example of the amorphous silicon cell (from [28]). ...................................20  Figure 15.  The structure of a copper indium gallium ...for the final solar array with the maximum power point indicated

Canadian robotic arm is moved to the payload canister for STS-100

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - Workers on the floor of the Space Station Processing Facility follow along as the overhead crane carries the Canadian robotic arm, SSRMS, on its pallet to the payload canister. The arm is 57.7 feet (17.6 meters) long when fully extended and has seven motorized joints. It is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self-relocatable with a Latching End Effector, so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. The SSRMS is part of the payload on mission STS-100, scheduled to launch April 19 at 2:41 p.m. EDT from Launch Pad 39A, KSC.

STS-100 MPLM Raffaello is moved to the payload canister

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - The Multi-Purpose Logistics Module Raffaello is lowered into the payload canister alongside the Canadian robotic arm, SSRMS, already in place. Both elements are part of the payload on mission STS-100 to the International Space Station. Raffaello carries six system racks and two storage racks for the U.S. Lab. The arm has seven motorized joints and is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self-relocatable with a Latching End Effector so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. Launch of STS-100 is scheduled for April 19, 2001 at 2:41 p.m. EDT from Launch Pad 39A.

STS-100 MPLM Raffaello is moved to the payload canister

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - Viewed from the end, the Multi- Purpose Logistics Module Raffaello is lowered into the payload canister behind the Canadian robotic arm, SSRMS, already in place. Both elements are part of the payload on mission STS-100 to the International Space Station. Raffaello carries six system racks and two storage racks for the U.S. Lab. The arm has seven motorized joints and is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self- relocatable with a Latching End Effector so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. Launch of STS-100 is scheduled for April 19, 2001 at 2:41 p.m. EDT from Launch Pad 39A.

Canadian robotic arm is moved to the payload canister for STS-100

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - In the Space Station Processing Facility, the overhead crane rolls along the ceiling with the pallet and Canadian robotic arm, SSRMS, toward the payload canister, at right. The arm is 57.7 feet (17.6 meters) long when fully extended and has seven motorized joints. It is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self-relocatable with a Latching End Effector, so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. The SSRMS is part of the payload on mission STS-100, scheduled to launch April 19 at 2:41 p.m. EDT from Launch Pad 39A, KSC.

Canadian robotic arm is moved to the payload canister for STS-100

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - In the Space Station Processing Facility, the overhead crane carrying the pallet and Canadian robotic arm, SSRMS, nears the payload canister at right where the equipment will be placed. The arm is 57.7 feet (17.6 meters) long when fully extended and has seven motorized joints. It is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self-relocatable with a Latching End Effector, so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. The SSRMS is part of the payload on mission STS-100, scheduled to launch April 19 at 2:41 p.m. EDT from Launch Pad 39A, KSC.

Low-Cost Propellant Launch to LEO from a Tethered Balloon - 'Propulsion Depots' Not 'Propellant Depots'

NASA Technical Reports Server (NTRS)

Wilcox, Brian H.; Schneider, Evan G.; Vaughan, David A.; Hall, Jeffrey L.; Yu, Chi Yau

2011-01-01

As we have previously reported, it may be possible to launch payloads into low-Earth orbit (LEO) at a per-kilogram cost that is one to two orders of magnitude lower than current launch systems, using only a relatively small capital investment (comparable to a single large present-day launch). An attractive payload would be large quantities of high-performance chemical rocket propellant (e.g. Liquid Oxygen/Liquid Hydrogen (LO2/LH2)) that would greatly facilitate, if not enable, extensive exploration of the moon, Mars, and beyond.

ARM Aerial Facility ArcticShark Unmanned Aerial System

NASA Astrophysics Data System (ADS)

Schmid, B.; Hubbell, M.; Mei, F.; Carroll, P.; Mendoza, A.; Ireland, C.; Lewko, K.

2017-12-01

The TigerShark Block 3 XP-AR "ArcticShark" Unmanned Aerial System (UAS), developed and manufactured by Navmar Applied Sciences Corporation (NASC), is a single-prop, 60 hp rotary-engine platform with a wingspan of 6.5 m and Maximum Gross Takeoff Weight of 295 Kg. The ArcticShark is owned by the U.S. Department of Energy (DOE) and has been operated by Pacific Northwest National Laboratory (PNNL) since March 2017. The UAS will serve as an airborne atmospheric research observatory for DOE ARM, and, once fully operational, can be requested through ARM's annual call for proposals. The Arctic Shark is anticipated to measure a wide range of radiative, aerosol, and cloud properties using a variable instrument payload weighing up to 46 Kg. SATCOM-equipped, it is capable of taking measurements up to altitudes of 5.5 Km over ranges of up to 500 Km. The ArcticShark operates at airspeeds of 30 to 40 m/s, making it capable of slow sampling. With a full fuel load, its endurance exceeds 8 hours. The aircraft and its Mobile Operations Center (MOC) have been hardened specifically for operations in colder temperatures.ArcticShark's design facilitates rapid integration of various types of payloads. 2500 W of its 4000 W electrical systems is dedicated to payload servicing. It has an interior payload volume of almost 85 L and four wing-mounted pylons capable of carrying external probes. Its payload bay volume, electrical power, payload capacity, and flight characteristics enable the ArcticShark to accommodate multiple combinations of payloads in numerous configurations. Many instruments will be provided by the ARM Aerial Facility (AAF), but other organizations may eventually propose instrumentation for specific campaigns. AAF-provided measurement capabilities will include the following atmospheric state and thermodynamics: temperature, pressure, winds; gases: H2O and CO2; up- and down-welling broadband infrared and visible radiation; surface temperature; aerosol number concentration, size distribution, absorption composition (filter samples), and cloud-droplet size distribution.

Manned space flight nuclear system safety. Volume 4: Space shuttle nuclear system transportation. Part 1: Space shuttle nuclear safety

NASA Technical Reports Server (NTRS)

1972-01-01

An analysis of the nuclear safety aspects (design and operational considerations) in the transport of nuclear payloads to and from earth orbit by the space shuttle is presented. Three representative nuclear payloads used in the study were: (1) the zirconium hydride reactor Brayton power module, (2) the large isotope Brayton power system and (3) small isotopic heat sources which can be a part of an upper stage or part of a logistics module. Reference data on the space shuttle and nuclear payloads are presented in an appendix. Safety oriented design and operational requirements were identified to integrate the nuclear payloads in the shuttle mission. Contingency situations were discussed and operations and design features were recommended to minimize the nuclear hazards. The study indicates the safety, design and operational advantages in the use of a nuclear payload transfer module. The transfer module can provide many of the safety related support functions (blast and fragmentation protection, environmental control, payload ejection) minimizing the direct impact on the shuttle.

Structural Qualification Testing of the WindSat Payload Using Sine Bursts Near Structural Resonance

NASA Technical Reports Server (NTRS)

Pontius, Jim; Barnes, Donald; Broduer, Steve (Technical Monitor)

2001-01-01

Sine burst tests are often used for structural qualification of space flight hardware. In most instances, the driving frequency of the shaker is specified far below the structure's first resonant mode, such that the entire test article sees uniform acceleration. For large structures, this limits qualification testing to lower parts of the structure, or else it over-tests the lower structure to achieve qualification of the upper structure. The WindSat payload, a 10.5 foot tall graphite/epoxy, titanium, and aluminum radiometer, experiences accelerations at the six foot diameter reflector nearly four times that at the spacecraft interface. Due to size of the payload, the number of bonded joints, and the lightweight reflector support structure design and construction, using static pull testing to qualify all of the bonded joints in the upper structure would result in large, expensive, and extensive test fixturing. Sine burst testing near the first two structural resonant modes was performed on the WindSat payload to achieve the correct load factor distribution up the stack for structural qualification. In this presentation, how finite element method (FEM) sine burst predictions were used in conjunction with low level random and sine burst tests to achieve correct qualification test load factor distribution on the WindSat payload is discussed. Also presented is the risk mitigation approach for using the uncorrelated FEM in this procedure.

A magnetic shield/dual purpose mission

NASA Technical Reports Server (NTRS)

Watkins, Seth; Albertelli, Jamil; Copeland, R. Braden; Correll, Eric; Dales, Chris; Davis, Dana; Davis, Nechole; Duck, Rob; Feaster, Sandi; Grant, Patrick

1994-01-01

The objective of this work is to design, build, and fly a dual-purpose payload whose function is to produce a large volume, low intensity magnetic field and to test the concept of using such a magnetic field to protect manned spacecraft against particle radiation. An additional mission objective is to study the effect of this moving field on upper atmosphere plasmas. Both mission objectives appear to be capable of being tested using the same superconducting coil. The potential benefits of this magnetic shield concept apply directly to both earth-orbital and interplanetary missions. This payload would be a first step in assessing the true potential of large volume magnetic fields in the U.S. space program. Either converted launch systems or piggyback payload opportunities may be appropriate for this mission. The use of superconducting coils for magnetic shielding against solar flare radiation during manned interplanetary missions has long been contemplated and was considered in detail in the years preceding the Apollo mission. With the advent of new superconductors, it has now become realistic to reconsider this concept for a Mars mission. Even in near-earth orbits, large volume magnetic fields produced using conventional metallic superconductors allow novel plasma physics experiments to be contemplated. Both deployed field-coil and non-deployed field-coil shielding arrangements have been investigated, with the latter being most suitable for an initial test payload in a polar orbit.

Opportunities for Geoscience Research Onboard Virgin Galactic's SpaceShipTwo

NASA Astrophysics Data System (ADS)

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

2012-12-01

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

40 CFR 1051.801 - What definitions apply to this part?

Code of Federal Regulations, 2010 CFR

2010-07-01

... CFR part 90, 91, 1048, or 1054, where that engine is installed in a piece of equipment that is covered... CFR part 90, 91, 1048, or 1054, when that engine is installed in a piece of equipment that is covered... rear payload capacity of 350 pounds or more or seating for six or more passengers. Vehicles intended...

STS-100 MPLM Raffaello is moved to the payload canister

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. - Workers inside the payload canister wait for the Multi-Purpose Logistics Module Raffaello to be lowered inside. It joins the Canadian robotic arm, SSRMS, already in place. Both elements are part of the payload on mission STS- 100 to the International Space Station. Raffaello carries six system racks and two storage racks for the U.S. Lab. The arm has seven motorized joints and is capable of handling large payloads and assisting with docking the Space Shuttle. The SSRMS is self- relocatable with a Latching End Effector so it can be attached to complementary ports spread throughout the Station'''s exterior surfaces. Launch of STS-100 is scheduled for April 19, 2001 at 2:41 p.m. EDT from Launch Pad 39A.

Direct launch using the electric rail gun

NASA Technical Reports Server (NTRS)

Barber, J. P.

1983-01-01

The concept explored involves using a large single stage electric rail gun to achieve orbital velocities. Exit aerodynamics, launch package design and size, interior ballistics, system and component sizing and design concepts are treated. Technology development status and development requirements are identified and described. The expense of placing payloads in Earth orbit using conventional chemical rockets is considerable. Chemical rockets are very inefficient in converting chemical energy into payload kinetic energy. A rocket motor is relatively expensive and is usually expended on each launch. In addition specialized and expensive forms of fuel are required. Gun launching payloads directly to orbit from the Earth's surface is a possible alternative. Guns are much more energy efficient than rockets. The high capital cost of the gun installation can be recovered by reusing it over and over again. Finally, relatively inexpensive fuel and large quantities of energy are readily available to a fixed installation on the Earth's surface.

Parametric study of variation in cargo-airplane performance related to progression from current to spanloader designs

NASA Technical Reports Server (NTRS)

Toll, T. A.

1980-01-01

A parametric analysis was made to investigate the relationship between current cargo airplanes and possible future designs that may differ greatly in both size and configuration. The method makes use of empirical scaling laws developed from statistical studies of data from current and advanced airplanes and, in addition, accounts for payload density, effects of span distributed load, and variations in tail area ratio. The method is believed to be particularly useful for exploratory studies of design and technology options for large airplanes. The analysis predicts somewhat more favorable variations of the ratios of payload to gross weight and block fuel to payload as the airplane size is increased than has been generally understood from interpretations of the cube-square law. In terms of these same ratios, large all wing (spanloader) designs show an advantage over wing-fuselage designs.

Performance analysis of a laser propelled interorbital tansfer vehicle

NASA Technical Reports Server (NTRS)

Minovitch, M. A.

1976-01-01

Performance capabilities of a laser-propelled interorbital transfer vehicle receiving propulsive power from one ground-based transmitter was investigated. The laser transmits propulsive energy to the vehicle during successive station fly-overs. By applying a series of these propulsive maneuvers, large payloads can be economically transferred between low earth orbits and synchronous orbits. Operations involving the injection of large payloads onto escape trajectories are also studied. The duration of each successive engine burn must be carefully timed so that the vehicle reappears over the laser station to receive additional propulsive power within the shortest possible time. The analytical solution for determining these time intervals is presented, as is a solution to the problem of determining maximum injection payloads. Parameteric computer analysis based on these optimization studies is presented. The results show that relatively low beam powers, on the order of 50 MW to 60 MW, produce significant performance capabilities.

Project SPARC: Space-Based Aeroassisted Reusable Craft

NASA Technical Reports Server (NTRS)

1990-01-01

Future United States' space facilities include a Space Station in low Earth orbit (LEO) and a Geosynchronous Operations Support Center, or GeoShack, in geosynchronous orbit (GEO). One possible mode of transfer between the two orbits is an aerobraking vehicle. When traveling from GEO to LEO, the Earth's atmosphere can be used to aerodynamically reduce the velocity of the vehicle, which reduces the amount of propulsive change in velocity required for the mission. An aerobrake is added to the vehicle for this purpose, but the additional mass increases propellant requirements. This increase must not exceed the amount of propellant saved during the aeropass. The design and development of an aerobraking vehicle that will transfer crew and cargo between the Space Station and GeoShack is examined. The vehicle is referred to as Project SPARC, a SPace-based Aeroassisted Reusable Craft. SPARC consists of a removable 45 ft diameter aerobrake, two modified Pratt and Whitney Advanced Expander Engines with a liquid oxygen/liquid hydrogen propellant, a removable crew module with a maximum capacity of five, and standard sized payload bays providing a maximum payload capacity of 28,000 lbm. The aerobrake, a rigid, ellipsoidally blunted elliptical cone, provides lift at zero angle-of-attack due to a 73 deg rake angle, and is covered with a flexible multi-layer thermal protection system. Maximum dry mass of the vehicle without payload is 20,535 lbm, and the maximum propellant requirement is 79,753 lbm at an oxidizer to fuel ratio of 6/1. Key advantages of SPARC include its capability to meet mission changes, and its removable aerobrake and crew module.

Guntersville Workshop on Solar-Terrestrial Studies

NASA Technical Reports Server (NTRS)

1977-01-01

The separation of purely solar physics from magnetospheric physics, and the effects of solar activity on geomagnetic activity are investigations which can be accomplished using the shuttle orbiter in an extended sortie mode, or an unmanned solar terrestrial observatory powered by the power module in an extended duration mode. When the power module is used with the shuttle in a sortie support mode, both the instrument capacity and the time in orbit of the orbiter can be increased several fold. In the free-flyer mode, the power module would be capable of providing power, basic attitude control, basic thermal control and housekeeping communications for unmanned, large, independent mission payloads in low earth orbit for periods of 6 months or longer. Instrument requirements for interdisciplinary joint observational programs are discussed for studies of the magnetosphere, the atmosphere, sun-weather relationships. Description summary charts of the power module are included.

A new phase for NASA's communications satellite program

NASA Technical Reports Server (NTRS)

Dement, D. K.

1980-01-01

NASA's research in communications satellite technology is discussed, including orbit-efficient techniques and applications by the commercial sector. Attention is given to expanding the capacities of the C-band (6-4 GHz) and the Ku-band (14-11 GHz), opening the Ka-band (30/20 GHz), broadly applied 're-use' of the spectrum, and developing multibeam spacecraft antennas with on-board switching. Increasing wideband services in video, high-speed data, and voice trunking is considered, as are narrow-band systems that may be used for data collection or public safety, with possible expansion to a thin-route satellite system. In particular, communication for medical, disaster, or search-and-rescue emergencies may be met by the integration of a satellite service with land mobile communications via terrestrial radio links. Also considered is a large geostationary platform providing electrical power, thermal rejection, and orbital station-keeping for many communications payloads.

Scalable, high-capacity optical switches for Internet routers and moving platforms

NASA Astrophysics Data System (ADS)

Joe, In-Sung

Internet traffic nearly doubles every year, and we need faster routers with higher ports count, yet lower electrical power consumption. Current internet routers use electrical switches that consume large amounts of electrical power to operate at high data rates. These internet routers dissipate ˜ 10kW per rack, and their capacity is limited by cooling constraints. The power consumption is also critical for moving platforms. As avionics advance, the demand for larger capacity networks increases. Optical fibers are already chosen for high speed data transmission in advanced aircraft. In optical communication systems, integrated passive optical components, such as Array Waveguide Gratings (AWGs), have provided larger capacity with lower power consumption, because minimal electrical power is required for their operation. In addition, compact, wavelength-tunable semiconductor lasers with wide tuning ranges that can switch their wavelengths in tens of nanoseconds have been demonstrated. Here we present a wavelength-selective optical packet switch based on Waveguide Grating Routers (WGRs), passive splitters, and combiners. Tunable lasers on the transmitter side are the only active switching elements. The WGR is operated on multiple Free Spectral Ranges (FSRs) to achieve increased port count and switching capacity while maintaining strict-sense, non-blocking operation. Switching times of less than 24ns between two wavelengths covering three FSRs is demonstrated experimentally. The electrical power consumption, size, weight, and cost of our optical switch is compared with those of conventional electrical switches, showing substantial improvements at large throughputs (˜2 Tb/s full duplex). A revised switch design that does not suffer optical loss from star couplers is proposed. This switch design uses only WGRs, and it is suitable for networks with stringent power budgets. The burst nature of the optical packet transmission requires clock recovery for every incoming packet, and conventional continuous-mode receivers are not suitable for this application. An Embedded Clock Transport (ECT) technique is adopted here. The ECT combines a clock tone with the data payload before the transmission. Simple band pass filtering can extract the transmitted clock tone, and low pass filtering can recover the data. Error-free transmissions at 2.488 Gb/s with ˜16 ns clock recovery time were demonstrated.

Universal Batch Steganalysis

DTIC Science & Technology

2014-06-01

in large-scale datasets such as might be obtained by monitoring a corporate network or social network. Identifying guilty actors, rather than payload...by monitoring a corporate network or social network. Identifying guilty actors, rather than payload-carrying objects, is entirely novel in steganalysis...implementation using Compute Unified Device Architecture (CUDA) on NVIDIA graphics cards. The key to good performance is to combine computations so that

High performance photonic ADC for space applications

NASA Astrophysics Data System (ADS)

Pantoja, S.; Piqueras, M. A.; Villalba, P.; Martínez, B.; Rico, E.

2017-11-01

The flexibility required for future telecom payloads will require of more digital processing capabilities, moving from conventional analogue repeaters to more advanced and efficient analog subsystems or DSPbased solutions. Aggregate data throughputs will have to be handled onboard, creating the need for effective, ADC/DSP and DSP/DAC high speed links. Broadband payloads will have to receive, route and retransmit hundreds of channels and need to be designed so as to meet such requirements of larger bandwidth, system transparency and flexibility.[1][2] One important device in these new architectures is analog to digital converter (ADC) and its equivalent digital to analog converter (DAC). These will be the in/out interface for the use of digital processing in order to provide flexible beam to beam connectivity and variable bandwidth allocation. For telecom payloads having a large number of feeds and thus a large number of converters the mass and consumption of the mixer stage has become significant. Moreover, the inclusion of ADCs in the payload presents new trade-offs in design (jitter, quantization noise, ambiguity). This paper deals with an alternative solution of these two main problems with the exploitation of photonic techniques.

Graduate Student Researchers Program (GSRP)

NASA Technical Reports Server (NTRS)

Westerhoff, John

2004-01-01

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

Ares V: Shifting the Payload Design Paradigm

NASA Technical Reports Server (NTRS)

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

2009-01-01

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

Shuttle-Derived Launch Vehicles' Capablities: An Overview

NASA Technical Reports Server (NTRS)

Rothschild, William J.; Bailey, Debra A.; Henderson, Edward M.; Crumbly, Chris

2005-01-01

Shuttle-Derived Launch Vehicle (SDLV) concepts have been developed by a collaborative team comprising the Johnson Space Center, Marshall Space Flight Center, Kennedy Space Center, ATK-Thiokol, Lockheed Martin Space Systems Company, The Boeing Company, and United Space Alliance. The purpose of this study was to provide timely information on a full spectrum of low-risk, cost-effective options for STS-Derived Launch Vehicle concepts to support the definition of crew and cargo launch requirements for the Space Exploration Vision. Since the SDLV options use high-reliability hardware, existing facilities, and proven processes, they can provide relatively low-risk capabilities to launch extremely large payloads to low Earth orbit. This capability to reliably lift very large, high-dollar-value payloads could reduce mission operational risks by minimizing the number of complex on-orbit operations compared to architectures based on multiple smaller launchers. The SDLV options also offer several logical spiral development paths for larger exploration payloads. All of these development paths make practical and cost-effective use of existing Space Shuttle Program (SSP) hardware, infrastructure, and launch and flight operations systems. By utilizing these existing assets, the SDLV project could support the safe and orderly transition of the current SSP through the planned end of life in 2010. The SDLV concept definition work during 2004 focused on three main configuration alternatives: a side-mount heavy lifter (approximately 77 MT payload), an in-line medium lifter (approximately 22 MT Crew Exploration Vehicle payload), and an in-line heavy lifter (greater than 100 MT payload). This paper provides an overview of the configuration, performance capabilities, reliability estimates, concept of operations, and development plans for each of the various SDLV alternatives. While development, production, and operations costs have been estimated for each of the SDLV configuration alternatives, these proprietary data have not been included in this paper.

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.

A Versatile Lifting Device for Lunar Surface Payload Handling, Inspection and Regolith Transport Operations

NASA Technical Reports Server (NTRS)

Doggett, William R.; Dorsey, John T.; Collins, Timothy J.; King, Bruce D.; Mikulas, Martin M., Jr.

2008-01-01

Devices for lifting and transporting payloads and material are critical for efficient Earth-based construction operations. Devices with similar functionality will be needed to support lunar-outpost construction, servicing, inspection, regolith excavation, grading and payload placement. Past studies have proposed that only a few carefully selected devices are required for a lunar outpost. One particular set of operations involves lifting and manipulating payloads in the 100 kg to 3,000 kg range, which are too large or massive to be handled by unassisted astronauts. This paper will review historical devices used for payload handling in space and on earth to derive a set of desirable features for a device that can be used on planetary surfaces. Next, an innovative concept for a lifting device is introduced, which includes many of the desirable features. The versatility of the device is discussed, including its application to lander unloading, servicing, inspection, regolith excavation and site preparation. Approximate rules, which can be used to size the device for specific payload mass and reach requirements, are provided. Finally, details of a test-bed implementation of the innovative concept, which will be used to validate the structural design and develop operational procedures, is provided.

Destruction of Opportunistic Pathogens via Polymer Nanoparticle-Mediated Release of Plant-Based Antimicrobial Payloads

PubMed Central

Amato, Dahlia N.; Amato, Douglas V.; Mavrodi, Olga V.; Braasch, Dwaine A.; Walley, Susan E.; Douglas, Jessica R.

2017-01-01

The synthesis of antimicrobial thymol/carvacrol-loaded polythioether nanoparticles (NPs) via a one-pot, solvent-free miniemulsion thiol-ene photopolymerization process is reported. The active antimicrobial agents, thymol and carvacrol, are employed as “solvents” for the thiol-ene monomer phase in the miniemulsion to enable facile high capacity loading (≈50% w/w), excellent encapsulation efficiencies (>95%), and elimination of all postpolymerization purification processes. The NPs serve as high capacity reservoirs for slow-release and delivery of thymol/carvacrol-combination payloads that exhibit inhibitory and bactericidal activity (>99.9% kill efficiency at 24 h) against gram-positive and gram-negative bacteria, including both saprophytic (Bacillus subtilis ATCC 6633 and Escherichia coli ATCC 25922) and pathogenic species (E. coli ATCC 43895, Staphylococcus aureus RN6390, and Burkholderia cenocepacia K56-2). This report is among the first to demonstrate antimicrobial efficacy of essential oil-loaded nanoparticles against B. cenocepacia – an innately resistant opportunistic pathogen commonly associated with debilitating respiratory infections in cystic fibrosis. Although a model platform, these results point to promising pathways to particle-based delivery of plant-derived extracts for a range of antimicrobial applications, including active packaging materials, topical antiseptics, and innovative therapeutics. PMID:26946055

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.

Shuttle communication and tracking systems signal design and interface compatibility analysis

NASA Technical Reports Server (NTRS)

1986-01-01

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

Communication architecture for large geostationary platforms

NASA Technical Reports Server (NTRS)

Bond, F. E.

1979-01-01

Large platforms have been proposed for supporting multipurpose communication payloads to exploit economy of scale, reduce congestion in the geostationary orbit, provide interconnectivity between diverse earth stations, and obtain significant frequency reuse with large multibeam antennas. This paper addresses a specific system design, starting with traffic projections in the next two decades and discussing tradeoffs and design approaches for major components including: antennas, transponders, and switches. Other issues explored are selection of frequency bands, modulation, multiple access, switching methods, and techniques for servicing areas with nonuniform traffic demands. Three-major services are considered: a high-volume trunking system, a direct-to-user system, and a broadcast system for video distribution and similar functions. Estimates of payload weight and d.c. power requirements are presented. Other subjects treated are: considerations of equipment layout for servicing by an orbit transfer vehicle, mechanical stability requirements for the large antennas, and reliability aspects of the large number of transponders employed.

Deuterium microbomb rocket propulsion

NASA Astrophysics Data System (ADS)

Winterberg, F.

2010-01-01

Large scale manned space flight within the solar system is still confronted with the solution of two problems: (1) A propulsion system to transport large payloads with short transit times between different planetary orbits. (2) A cost effective lifting of large payloads into earth orbit. For the solution of the first problem a deuterium fusion bomb propulsion system is proposed where a thermonuclear detonation wave is ignited in a small cylindrical assembly of deuterium with a gigavolt-multimegaampere proton beam, drawn from the magnetically insulated spacecraft acting in the ultrahigh vacuum of space as a gigavolt capacitor. For the solution of the second problem, the ignition is done by argon ion lasers driven by high explosives, with the lasers destroyed in the fusion explosion and becoming part of the exhaust.

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

NASA Technical Reports Server (NTRS)

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

1993-01-01

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

Enhanced micro-vibration sensitive high-damping capacity and mechanical strength achieved in Al matrix composites reinforced with garnet-like lithium electrolyte

NASA Astrophysics Data System (ADS)

Wang, Xian-Ping; Zhang, Yi; Xia, Yu; Jiang, Wei-Bing; Liu, Hui; Liu, Wang; Gao, Yun-Xia; Zhang, Tao; Fang, Qian-Feng

2017-03-01

A novel micro-vibration sensitive-type high-damping Al matrix composites reinforced with Li7- x La3Zr2- x Nb x O12 (LLZNO, x = 0.25) was designed and prepared using an advanced spark plasma sintering (SPS) technique. The damping capacity and mechanical properties of LLZNO/Al composites (LLZNO content: 0-40 wt.%) were found to be greatly improved by the LLZNO addition. The maximum damping capacity and the ultimate tensile strength (UTS) of LLZNO/Al composite can be respectively up to 0.033 and 101.2 MPa in the case of 20 wt.% LLZNO addition. The enhancement of damping and mechanical properties of the composites was ascribed to the intrinsic high-damping capacity and strengthening effects of hard LLZNO particulate. This investigation provides a new insight to sensitively suppress micro-vibration of payloads in the aerospace environment.

Structural Dynamics and Control of Large Space Structures, 1982

NASA Technical Reports Server (NTRS)

Brumfield, M. L. (Compiler)

1983-01-01

Basic research in the control of large space structures is discussed. Active damping and control of flexible beams, active stabilization of flexible antenna feed towers, spacecraft docking, and robust pointing control of large space platform payloads are among the topics discussed.

Standard payload computer for the international space station

NASA Astrophysics Data System (ADS)

Knott, Karl; Taylor, Chris; Koenig, Horst; Schlosstein, Uwe

1999-01-01

This paper describes the development and application of a Standard PayLoad Computer (SPLC) which is being applied by the majority of ESA payloads accommodated on the International Space Station (ISS). The strategy of adopting of a standard computer leads to a radical rethink in the payload data handling procurement process. Traditionally, this has been based on a proprietary development with repeating costs for qualification, spares, expertise and maintenance for each new payload. Implementations have also tended to be unique with very little opportunity for reuse or utilisation of previous developments. While this may to some extent have been justified for short duration one-off missions, the availability of a standard, long term space infrastructure calls for a quite different approach. To support a large number of concurrent payloads, the ISS implementation relies heavily on standardisation, and this is particularly true in the area of payloads. Physical accommodation, data interfaces, protocols, component quality, operational requirements and maintenance including spares provisioning must all conform to a common set of standards. The data handling system and associated computer used by each payload must also comply with these common requirements, and thus it makes little sense to instigate multiple developments for the same task. The opportunity exists to provide a single computer suitable for all payloads, but with only a one-off development and qualification cost. If this is combined with the benefits of multiple procurement, centralised spares and maintenance, there is potential for great savings to be made by all those concerned in the payload development process. In response to the above drivers, the SPLC is based on the following concepts: • A one-off development and qualification process • A modular computer, configurable according to the payload developer's needs from a list of space-qualified items • An `open system' which may be added to by payload developers • Core software providing a suite of common communications services including a verified protocol implementation required to communicate with the ISS • A standardized ground support equipment and accompanying software development environment • The use of commercial hardware and software standards and products.

Communications platform payload definition study, executive summary

NASA Technical Reports Server (NTRS)

Clopp, H. W.; Hawkes, T. A.; Bertles, C. R.; Pontano, B. A.; Kao, T.

1986-01-01

Large geostationary communications platforms have been investigated in a number of studies since 1974 as a possible means to more effectively utilize the geostationary orbital arc and electromagnetic spectrum and to reduce overall satellite communications system costs. This NASA Lewis sponsored study addresses the commercial feasibility of various communications platform payload concepts circa 1998. It defines promising payload concepts, estimates recurring costs and identifies critical technologies needed to permit eventual commercialization. Ten communications service aggregation scenarios describing potential groupings of services were developed for a range of conditions. Payload concepts were defined for four of these scenarios: (1) Land Mobile Satellite Service (LMSS), meet 100% of CONUS plus Canada demand with a single platform; (2) Fixed Satellite Service (FSS) (Trunking + Customer Premises Service (CPS), meet 20% of CONUS demands; (3) FSS (Trunking + video distribution), 10 to 13% of CONUS demand; and (4) FSS (20% of demand) + Inter Satellite Links (ISL) + TDRSS/TDAS Data Distribution.

Launching rockets and small satellites from the lunar surface

NASA Technical Reports Server (NTRS)

Anderson, K. A.; Dougherty, W. M.; Pankow, D. H.

1985-01-01

Scientific payloads and their propulsion systems optimized for launch from the lunar surface differ considerably from their counterparts for use on earth. For spin-stabilized payloads, the preferred shape is a large diameter-to-length ratio to provide stability during the thrust phase. The rocket motor required for a 50-kg payload to reach an altitude of one lunar radius would have a mass of about 41 kg. To place spin-stabilized vehicles into low altitude circular orbits, they are first launched into an elliptical orbit with altitude about 840 km at aposelene. When the spacecraft crosses the desired circular orbit, small retro-rockets are fired to attain the appropriate direction and speed. Values of the launch angle, velocity increments, and other parameters for circular orbits of several altitudes are tabulated. To boost a 50-kg payload into a 100-km altitude circular orbit requires a total rocket motor mass of about 90 kg.

Launching rockets and small satellites from the lunar surface

NASA Astrophysics Data System (ADS)

Anderson, K. A.; Dougherty, W. M.; Pankow, D. H.

Scientific payloads and their propulsion systems optimized for launch from the lunar surface differ considerably from their counterparts for use on earth. For spin-stabilized payloads, the preferred shape is a large diameter-to-length ratio to provide stability during the thrust phase. The rocket motor required for a 50-kg payload to reach an altitude of one lunar radius would have a mass of about 41 kg. To place spin-stabilized vehicles into low altitude circular orbits, they are first launched into an elliptical orbit with altitude about 840 km at aposelene. When the spacecraft crosses the desired circular orbit, small retro-rockets are fired to attain the appropriate direction and speed. Values of the launch angle, velocity increments, and other parameters for circular orbits of several altitudes are tabulated. To boost a 50-kg payload into a 100-km altitude circular orbit requires a total rocket motor mass of about 90 kg.

Gradient Heating Facility in the Materials Science Double Rack (MSDR) on Spacelab-1 Module

NASA Technical Reports Server (NTRS)

1983-01-01

The Space Shuttle was designed to carry large payloads into Earth orbit. One of the most important payloads is Spacelab. The Spacelab serves as a small but well-equipped laboratory in space to perform experiments in zero-gravity and make astronomical observations above the Earth's obscuring atmosphere. In this photograph, Payload Specialist, Ulf Merbold, is working at Gradient Heating Facility on the Materials Science Double Rack (MSDR) inside the science module in the Orbiter Columbia's payload bay during STS-9, Spacelab-1 mission. Spacelab-1, the joint ESA (European Space Agency)/NASA mission, was the first operational flight for the Spacelab, and demonstrated new instruments and methods for conducting experiments that are difficult or impossible in ground-based laboratories. This facility performed, in extremely low gravity, a wide variety of materials processing experiments in crystal growth, fluid physics, and metallurgy. The Marshall Space Flight Center had overall management responsibilities.

The Orbiter camera payload system's large-format camera and attitude reference system

NASA Technical Reports Server (NTRS)

Schardt, B. B.; Mollberg, B. H.

1985-01-01

The Orbiter camera payload system (OCPS) is an integrated photographic system carried into earth orbit as a payload in the Space Transportation System (STS) Orbiter vehicle's cargo bay. The major component of the OCPS is a large-format camera (LFC), a precision wide-angle cartographic instrument capable of producing high-resolution stereophotography of great geometric fidelity in multiple base-to-height ratios. A secondary and supporting system to the LFC is the attitude reference system (ARS), a dual-lens stellar camera array (SCA) and camera support structure. The SCA is a 70 mm film system that is rigidly mounted to the LFC lens support structure and, through the simultaneous acquisition of two star fields with each earth viewing LFC frame, makes it possible to precisely determine the pointing of the LFC optical axis with reference to the earth nadir point. Other components complete the current OCPS configuration as a high-precision cartographic data acquisition system. The primary design objective for the OCPS was to maximize system performance characteristics while maintaining a high level of reliability compatible with rocket launch conditions and the on-orbit environment. The full OCPS configuration was launched on a highly successful maiden voyage aboard the STS Orbiter vehicle Challenger on Oct. 5, 1984, as a major payload aboard the STS-41G mission.

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

NASA Technical Reports Server (NTRS)

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

2016-01-01

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

FrankenRaven: A New Platform for Remote Sensing

NASA Astrophysics Data System (ADS)

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

2016-12-01

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

Plasma effects of active ion beam injections in the ionosphere at rocket altitudes

NASA Technical Reports Server (NTRS)

Arnoldy, R. L.; Cahill, L. J., Jr.; Kintner, P. M.; Moore, T. E.; Pollock, C. J.

1992-01-01

Data from ARCS rocket ion beam injection experiments are primarily discussed. There are three results from this series of active experiments that are of particular interest in space plasma physics. These are the transverse acceleration of ambient ions in the large beam volume, the scattering of beam ions near the release payload, and the possible acceleration of electrons very close to the plasma generator which produce intense high frequency waves. The ability of 100 ma ion beam injections into the upper E and F regions of the ionosphere to produce these phenomena appear to be related solely to the process by which the plasma release payload and the ion beam are neutralized. Since the electrons in the plasma release do not convect with the plasma ions, the neutralization of both the payload and beam must be accomplished by large field-aligned currents (milliamperes/square meter) which are very unstable to wave growth of various modes.

Robotic Lunar Landers for Science and Exploration

NASA Technical Reports Server (NTRS)

Cohen, Barbara A.

2012-01-01

The MSFC/APL Robotic Lunar Landing Project (RLLDP) team has developed lander concepts encompassing a range of mission types and payloads for science, exploration, and technology demonstration missions: (1) Developed experience and expertise in lander systems, (2) incorporated lessons learned from previous efforts to improve the fidelity of mission concepts, analysis tools, and test beds Mature small and medium lander designs concepts have been developed: (1) Share largely a common design architecture. (2) Flexible for a large number of mission and payload options. High risk development areas have been successfully addressed Landers could be selected for a mission with much of the concept formulation phase work already complete

Primary propulsion/large space system interaction study

NASA Technical Reports Server (NTRS)

Coyner, J. V.; Dergance, R. H.; Robertson, R. I.; Wiggins, J. V.

1981-01-01

An interaction study was conducted between propulsion systems and large space structures to determine the effect of low thrust primary propulsion system characteristics on the mass, area, and orbit transfer characteristics of large space systems (LSS). The LSS which were considered would be deployed from the space shuttle orbiter bay in low Earth orbit, then transferred to geosynchronous equatorial orbit by their own propulsion systems. The types of structures studied were the expandable box truss, hoop and column, and wrap radial rib each with various surface mesh densities. The impact of the acceleration forces on system sizing was determined and the effects of single point, multipoint, and transient thrust applications were examined. Orbit transfer strategies were analyzed to determine the required velocity increment, burn time, trip time, and payload capability over a range of final acceleration levels. Variables considered were number of perigee burns, delivered specific impulse, and constant thrust and constant acceleration modes of propulsion. Propulsion stages were sized for four propellant combinations; oxygen/hydrogen, oxygen/methane, oxygen/kerosene, and nitrogen tetroxide/monomethylhydrazine, for pump fed and pressure fed engine systems. Two types of tankage configurations were evaluated, minimum length to maximize available payload volume and maximum performance to maximize available payload mass.

Ground Systems Integration Domain (GSID) Materials for Ground Platforms

DTIC Science & Technology

2010-09-20

Vehicles • Heavy Brigade Combat Team • Strykers • MRAPs • Ground Combat Vehicles (Future) Tactical Vehicles • HMMWVs • Trailers • Heavy, Medium and...efficient structural material solutions • Signature management, electromagnetic shielding over potentially non-metallic surfaces • Diagnostics...Occupant-Centric Survivability Focused): 1. 4500 lbs + trailer towing capacity; 4-6 man crew compartmentPayload 2. 14,000 lb curb vehicle weightPerformance

2016 Summer Series - Kenneth Cheung: Building Blocks for Aerospace Structures

NASA Image and Video Library

2016-06-16

Strong, ultra-lightweight materials are expected to play a key role in the design of future aircraft and space vehicles. Lower structural mass leads to improved performance, maneuverability, efficiency, range and payload capacity. Dr. Kenneth Cheung is developing cellular composite building blocks, or digital materials, to create transformable aerostructures. In his presentation, Dr. Cheung will discuss the implications of the digital materials and morphing structures.

Microprocessor-Based Systems Control for the Rigidized Inflatable Get-Away-Special Experiment

DTIC Science & Technology

2004-03-01

communications and faster data throughput increase, satellites are becoming larger. Larger satellite antennas help to provide the needed gain to...increase communications in space. Compounding the performance and size trade-offs are the payload weight and size limit imposed by the launch vehicles...increased communications capacity, and reduce launch costs. This thesis develops and implements the computer control system and power system to

Infrastructure considerations

NASA Astrophysics Data System (ADS)

Lovelace, Uriel; Sumrall, Phil; Pritchard, Brian

1989-04-01

An evaluation is made of performance requirements and technology development prospects for the logistical capacity entailed by manned space exploration. While the Space Shuttle will suffice for the launch of crews to a LEO Space Station, in support of such exploration missions, cargo transport will require 500-1000 tonne annual payload capacity launchers. As a first step toward satisfaction of such requirements, NASA has undertaken the development of the Shuttle-C unmanned Space Shuttle derivative. This will be followed by the Shuttle-Z derivative-family, aimed at meeting the needs of Mars missions. Joint USAF/NASA Advanced Launch System development will allow a given launch to place 91 tonnes in LEO.

WISDOM, a polarimetric GPR for the shallow subsurface characterization

NASA Astrophysics Data System (ADS)

Ciarletti, V.; Plettemeier, D.; Hassen-Kodja, R.; Clifford, S. M.; Wisdom Team

2011-12-01

WISDOM (Water Ice and Subsurface Deposit Observations on Mars) is a polarimetric Ground Penetrating Radar (GPR) that has been selected to be part of the Pasteur payload onboard the Rover of the 2018 ExoMars mission. It will perform large-scale scientific investigations of the sub-surface of the landing site and provide precise information about the subsurface structure prior to drilling. WISDOM has been designed to provide accurate information on the sub-surface structure down to a depth in excess to 2 meters (commensurate to the drill capacities) with a vertical resolution of a several centimetres. It will give access to the geological structure, electromagnetic nature, and, possibly, to the hydrological state of the shallow subsurface by retrieving the layering and properties of the layers and buried reflectors. The data will also be used to determine the most promising locations to collect underground samples with the drilling system mounted on board the rover. Polarimetric measurements have been recently acquired on perfectly known targets as well as in natural environments. They demonstrated the ability to provide a better understanding of sub-surface structure and significantly reduce the ambiguity associated with identifying the location of off-nadir reflectors, relative to the rover path. This work describes the instrument and its operating modes with particular emphasis on its polarimetric capacities.

Utilizing the US Lab Nadir Research Window for Remote Sensing Operations with The Window Observational Research Facility (WORF)

NASA Technical Reports Server (NTRS)

Turner, Richard; Barley, Bryan; Gilbert, Paul A. (Technical Monitor)

2002-01-01

The Window Observational Research Facility (WORF) is an ISPR-based rack facility designed to take advantage of the high optical quality US Lab Nadir research window. The WORF is based on the ISS Expedite the Processing of Experiments to Space Station (EXPRESS) rack mechanical structure and electronic systems. The WORF has a unique payload volume located at the center of the rack that provides access to the window. The interior dimensions of the payload volume are 34-in. (86.36 cm) wide by 33-in. (83.82 cm) high by 23-in. (58.42 cm) deep. This facility supports the deployment of payloads such as 9 in. aerial photography cameras and 12 in. diameter optical equipment. The WORF coupled with the optical quality of the United States Lab window support the deployment of various payload disciplines. The WORF provides payloads with power, data command and control, air cooling, water cooling, and video processing. The WORF's payload mounting surfaces and interfaces include the interior payload mounting shelf and the interior and exterior aircraft-like seat tracks. The payload mounting shelf is limited to a maximum mass of 136 kg (299 pounds). The WORF can accommodate large payloads such as the commonly used Leica-Heerbrug RC-30 aerial photography camera (whose dimensions are 53.3 cm (21-in.) wide by 50.8 cm (20-in.) deep by 76.2 cm (30-in.) long). The performance characteristics of the WORF allow it to support an array of payload disciplines. The WORF provides a maximum of 3 Kw at 28 Vdc and has a maximum data rate of 10 Mbps. The WORF's unique payload volume is designed to be light-tight, down to 2.8 x 10(exp -11) Watts/cm2/steradian, and have low-reflective surfaces. This specially designed WORF interior supports payload investigations that observe low-light-level phenomenon such as aurora. Although the WORF rack does not employ any active rack isolation (i.e., vibration dampening) technology, the rack provides a very stable environment for payload operations (on the order of X microradians). The facility's software is capable of being updated during its period of deployment. The WORF project also includes a Suitcase Simulator to allow for a payload developer to verify data interfaces at his development site, a trainer rack for astronauts to learn how to operate the WORF prior to flight, and the use of the EXPRESS Functional Checkout Units to allow for payload checkout at the KSC prior to launch.

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.

SPACEHAB is lowered by crane in the SSPF into the payload canister

NASA Technical Reports Server (NTRS)

1998-01-01

The SPACEHAB Single Module is lowered into the payload canister in KSC's Space Station Processing Facility. It will be joined in the canister by the Alpha Magnetic Spectrometer-01 payload before being moved to Launch Pad 39A for the STS-91 mission, scheduled to launch June 2 at around 6:04 p.m. EDT. SPACEHAB is used mainly as a large pressurized cargo container for science, logistical equipment and supplies to be exchanged between the orbiter Discovery and the Russian Space Station Mir. The nearly 10-day flight of STS-91 also is scheduled to return the sixth American, Mission Specialist Andrew Thomas, Ph.D., aboard the Russian orbiting outpost safely to Earth.

Capture-ejector satellites

NASA Technical Reports Server (NTRS)

Macconochie, I. O.; Eldred, C. H.; Martin, J. A.

1983-01-01

A satellite in the form of a large rotating rim which can be used to boost spacecraft from low-Earth orbit to higher orbits is described. The rim rotates in the plane of its orbit such that the lower portion of the rim is traveling at suborbital velocity, while the upper portion is travelling at greater than orbital velocity. Ascending spacecraft or payloads arrive at the lowest portion of the rim at suborbital velocities, where the payloads are released on a trajectory for higher orbits; descending payloads employ the reverse procedure. Electric thrusters placed on the rim maintain rim rotational speed and altitude. From the standpoint of currently known materials, the capture-ejector concept may be useful for relatively small velocity increments.

Science Planning for the Solar Probe Plus NASA Mission

NASA Astrophysics Data System (ADS)

Kusterer, M. B.; Fox, N. J.; Turner, F. S.; Vandegriff, J. D.

2015-12-01

With a planned launch in 2018, there are a number of challenges for the Science Planning Team (SPT) of the Solar Probe Plus mission. The geometry of the celestial bodies and the spacecraft during some of the Solar Probe Plus mission orbits cause limited uplink and downlink opportunities. The payload teams must manage the volume of data that they write to the spacecraft solid-state recorders (SSR) for their individual instruments for downlink to the ground. The aim is to write the instrument data to the spacecraft SSR for downlink before a set of data downlink opportunities large enough to get the data to the ground and before the start of another data collection cycle. The SPT also intend to coordinate observations with other spacecraft and ground based systems. To add further complexity, two of the spacecraft payloads have the capability to write a large volumes of data to their internal payload SSR while sending a smaller "survey" portion of the data to the spacecraft SSR for downlink. The instrument scientists would then view the survey data on the ground, determine the most interesting data from their payload SSR, send commands to transfer that data from their payload SSR to the spacecraft SSR for downlink. The timing required for downlink and analysis of the survey data, identifying uplink opportunities for commanding data transfers, and downlink opportunities big enough for the selected data within the data collection period is critical. To solve these challenges, the Solar Probe Plus Science Working Group has designed a orbit-type optimized data file priority downlink scheme to downlink high priority survey data quickly. This file priority scheme would maximize the reaction time that the payload teams have to perform the survey and selected data method on orbits where the downlink and uplink availability will support using this method. An interactive display and analysis science planning tool is being designed for the SPT to use as an aid to planning. The tool will integrate the data file priority downlink scheme, payload data volume allocations, spacecraft ephemeris, attitude, downlink and uplink schedules, spacecraft and payload activities, and other spacecraft ephemeris. A prototype of the tool is in development using notional inputs obtained from the spacecraft engineering teams.

Flight Testing of Terrain-Relative Navigation and Large-Divert Guidance on a VTVL Rocket

NASA Technical Reports Server (NTRS)

Trawny, Nikolas; Benito, Joel; Tweddle, Brent; Bergh, Charles F.; Khanoyan, Garen; Vaughan, Geoffrey M.; Zheng, Jason X.; Villalpando, Carlos Y.; Cheng, Yang; Scharf, Daniel P.;

Science Enabled by the Ares V: A Large Monolithic Telescope Placed at the Second Sun-Earth Lagrange Point

NASA Technical Reports Server (NTRS)

Hopkins, Randall C.; Stahl, H. Philip

2007-01-01

The payload mass and volume capabilities of the planned Ares V launch vehicle provide the science community with unprecedented opportunities to place large science payloads into low earth orbit and beyond. One example, the outcome of a recent study conducted at the NASA Marshall Space Flight Center, is a large, monolithic telescope with a primary mirror diameter of 6.2 meters placed into a halo orbit about the second Sun-Earth Lagrange point, or L2, approximately 1.5 million kin beyond Earth's orbit. Operating in the visible and ultraviolet regions of the electromagnetic spectrum, such a large telescope would allow astronomers to detect bio-signatures and characterize the atmospheres of transiting exoplanets, provide high resolution imaging three or more times better than the Hubble Space Telescope and the James Webb Space Telescope, and observe the ultraviolet light from warm baryonic matter.

A Fully Implemented 12 × 12 Data Vortex Optical Packet Switching Interconnection Network

NASA Astrophysics Data System (ADS)

Shacham, Assaf; Small, Benjamin A.; Liboiron-Ladouceur, Odile; Bergman, Keren

2005-10-01

A fully functional optical packet switching (OPS) interconnection network based on the data vortex architecture is presented. The photonic switching fabric uniquely capitalizes on the enormous bandwidth advantage of wavelength division multiplexing (WDM) wavelength parallelism while delivering minimal packet transit latency. Utilizing semiconductor optical amplifier (SOA)-based switching nodes and conventional fiber-optic technology, the 12-port system exhibits a capacity of nearly 1 Tb/s. Optical packets containing an eight-wavelength WDM payload with 10 Gb/s per wavelength are routed successfully to all 12 ports while maintaining a bit error rate (BER) of 10-12 or better. Median port-to-port latencies of 110 ns are achieved with a distributed deflection routing network that resolves packet contention on-the-fly without the use of optical buffers and maintains the entire payload path in the optical domain.

Capacity-optimized mp2 audio watermarking

NASA Astrophysics Data System (ADS)

Steinebach, Martin; Dittmann, Jana

2003-06-01

Today a number of audio watermarking algorithms have been proposed, some of them at a quality making them suitable for commercial applications. The focus of most of these algorithms is copyright protection. Therefore, transparency and robustness are the most discussed and optimised parameters. But other applications for audio watermarking can also be identified stressing other parameters like complexity or payload. In our paper, we introduce a new mp2 audio watermarking algorithm optimised for high payload. Our algorithm uses the scale factors of an mp2 file for watermark embedding. They are grouped and masked based on a pseudo-random pattern generated from a secret key. In each group, we embed one bit. Depending on the bit to embed, we change the scale factors by adding 1 where necessary until it includes either more even or uneven scale factors. An uneven group has a 1 embedded, an even group a 0. The same rule is later applied to detect the watermark. The group size can be increased or decreased for transparency/payload trade-off. We embed 160 bits or more in an mp2 file per second without reducing perceived quality. As an application example, we introduce a prototypic Karaoke system displaying song lyrics embedded as a watermark.

Autonomous Acqisition of Science Grade Spectra From UAS's

NASA Astrophysics Data System (ADS)

Mandl, D.; Campbell, P. K. E.; Sohlberg, R. A.; Ong, L.; Cappelaere, P. G.

2017-12-01

We assembled a payload box which contains a QE Pro and a Flame hyperspectral instruments. The payload was mounted on a DJI Matrice 600 drone. The total weight of the drone and the payload was 38 lbs. It was flown over a United States Department of Agricultural (USDA) research field where corn and soybeans were grown. The fields were subdivided into areas that had a variety of treatments such as low nitrogen and high nitrogen. The research is centered on correlating the treatments with the year-end crop yields. Our effort was to monitor spectral data to recognize photosynthetic activity via proxies such as solar induced fluorescence (SIF). To detect SIF requires optimized spectra which is normalized into reflectance. We perform the optimization routine onboard. The intent is to demonstrate a viable measurement campaign that would enable a researcher to measure the fields diurnally over a growing season. What we found out is that there was more complexity to trying to make this happen then we originally thought. For one thing, we had limited battery life, limited payload capacity and sometimes the cloud cover did not cooperate. So the question was how to intelligently apply the resources using some onboard processing and software. Our long term vision is to have multiple drones act as an intelligent cluster and self-manage their own deployment at multiple locations and multiple altitudes, auto-adjustments and intelligent management of errors. This presentation will go over lessons learned, achievements and future directions.

SLS launched missions concept studies for LUVOIR mission

NASA Astrophysics Data System (ADS)

Stahl, H. Philip; Hopkins, Randall C.

2015-09-01

NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. The multi-center ATLAST Team is working to meet these needs. The MSFC Team is examining potential concepts that leverage the advantages of the SLS (Space Launch System). A key challenge is how to affordably get a large telescope into space. The JWST design was severely constrained by the mass and volume capacities of its launch vehicle. This problem is solved by using an SLS Block II-B rocket with its 10-m diameter x 30-m tall fairing and estimated 45 mt payload to SE-L2. Previously, two development study cycles produced a detailed concept called ATLAST-8. Using ATLAST-8 as a point of departure, this paper reports on a new ATLAST-12 concept. ATLAST-12 is a 12-m class segmented aperture LUVOIR with an 8-m class center segment. Thus, ATLAST-8 is now a de-scope option.

SLS Launched Missions Concept Studies for LUVOIR Mission

NASA Technical Reports Server (NTRS)

Stahl, H. Philip; Hopkins, Randall C.

2015-01-01

NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-meter Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-meter class High-Definition Space Telescope to pursue transformational scientific discoveries. The multi-center ATLAST Team is working to meet these needs. The MSFC Team is examining potential concepts that leverage the advantages of the SLS (Space Launch System). A key challenge is how to affordably get a large telescope into space. The JWST design was severely constrained by the mass and volume capacities of its launch vehicle. This problem is solved by using an SLS Block II-B rocket with its 10-m diameter x 30-m tall fairing and 45 mt payload to SE-L2. Previously, two development study cycles produced a detailed concept called ATLAST-8. Using ATLAST-8 as a point of departure, this paper reports on a new ATLAST-12 concept. ATLAST-12 is a 12-meter class segmented aperture LUVOIR with an 8-m class center segment. Thus, ATLAST-8 is now a de-scope option.

Tuning Material and Component Properties to Reduce Weight and Increase Blastworthiness of a Notional V-Hull Structure

DTIC Science & Technology

2015-04-24

for designing blast-resistant structures [16]. The failure mechanisms in unidirectional fiber -reinforced composites of delamination, fiber -matrix...Batra, R.C., and Hassan, N.M., “Blast resistance of unidirectional fiber reinforced composites ,” Composites Part B: Engineering, 2008 18. Liu, X...feature a lighter weight structure, because this enables faster transport, higher mobility, greater fuel conservation, higher payload capacity, and

Advanced Tactical Booster Technologies: Applications for Long-Range Rocket Systems

DTIC Science & Technology

2016-09-07

Applications for Long-Range Rocket Systems 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) Matthew McKinna, Jason Mossman 5d...technology advantages currently under development for tactical rocket motors which have direct application to land-based long-range rocket systems...increased rocket payload capacity, improved rocket range or increased rocket loadout from the volumetrically constrained environment of a land-based

Destruction of Opportunistic Pathogens via Polymer Nanoparticle-Mediated Release of Plant-Based Antimicrobial Payloads.

PubMed

Amato, Dahlia N; Amato, Douglas V; Mavrodi, Olga V; Braasch, Dwaine A; Walley, Susan E; Douglas, Jessica R; Mavrodi, Dmitri V; Patton, Derek L

2016-05-01

The synthesis of antimicrobial thymol/carvacrol-loaded polythioether nanoparticles (NPs) via a one-pot, solvent-free miniemulsion thiol-ene photopolymerization process is reported. The active antimicrobial agents, thymol and carvacrol, are employed as "solvents" for the thiol-ene monomer phase in the miniemulsion to enable facile high capacity loading (≈50% w/w), excellent encapsulation efficiencies (>95%), and elimination of all postpolymerization purification processes. The NPs serve as high capacity reservoirs for slow-release and delivery of thymol/carvacrol-combination payloads that exhibit inhibitory and bactericidal activity (>99.9% kill efficiency at 24 h) against gram-positive and gram-negative bacteria, including both saprophytic (Bacillus subtilis ATCC 6633 and Escherichia coli ATCC 25922) and pathogenic species (E. coli ATCC 43895, Staphylococcus aureus RN6390, and Burkholderia cenocepacia K56-2). This report is among the first to demonstrate antimicrobial efficacy of essential oil-loaded nanoparticles against B. cenocepacia - an innately resistant opportunistic pathogen commonly associated with debilitating respiratory infections in cystic fibrosis. Although a model platform, these results point to promising pathways to particle-based delivery of plant-derived extracts for a range of antimicrobial applications, including active packaging materials, topical antiseptics, and innovative therapeutics. © 2016 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

Advanced System Design Requirements for Large and Small Fixed-wing Aerial Application Systems for Agriculture

NASA Technical Reports Server (NTRS)

Hinely, J. T., Jr.; Boyles, R. Q., Jr.

1979-01-01

Several candidate aircraft configurations were defined over the range of 1000 to 10,000 pounds payload and evaluated over a broad spectrum of agricultural missions. From these studies, baseline design points were selected at 3200 pounds payload for the small aircraft and 7500 pounds for the large aircraft. The small baseline aircraft utilizes a single turboprop powerplant while the large aircraft utilizes two turboprop powerplants. These configurations were optimized for wing loading, aspect ratio, and power loading to provide the best mission economics in representative missions. Wing loading of 20 lb/sq ft was selected for the small aircraft and 25 lb/sq ft for the large aircraft. Aspect ratio of 8 was selected for both aircraft. It was found that a 10% reduction in engine power from the original configurations provided improved mission economics for both aircraft by reducing the cost of the turboprop. Refined configurations incorporate a 675 HP engine in the small aircraft and two 688 HP engines in the large aircraft.

Aerodynamic flight control to increase payload capability of future launch vehicles

NASA Technical Reports Server (NTRS)

Cochran, John E., Jr.

1995-01-01

The development of new launch vehicles will require that designers use innovative approaches to achieve greater performance in terms of pay load capability. The objective of the work performed under this delivery order was to provide technical assistance to the Contract Officer's Technical Representative (COTR) in the development of ideas and concepts for increasing the payload capability of launch vehicles by incorporating aerodynamic controls. Although aerodynamic controls, such as moveable fins, are currently used on relatively small missiles, the evolution of large launch vehicles has been moving away from aerodynamic control. The COTR reasoned that a closer investigation of the use of aerodynamic controls on large vehicles was warranted.

External Payload Carrier (XPC) - A Novel Platform for Suborbital Research

NASA Technical Reports Server (NTRS)

Schallhorn, Paul; Groves, Curtis; Tatro, Charles; Kutter, Bernard; Szatkowski, Gerald; Bulk, Tim; Pitchford, Brian

2010-01-01

ULA, SAS, and NASA LSP are examining a new platform for suborbital research utilizing the Atlas V Launch Vehicle. The new platform, XPC, fills a new niche within the suborbital realm Large Heavy Lift (approximately 1200 cubic feet, 5000 lb payload). It will not compete with the commercial suborbital launch sector. The XPC will utilize excess performance on Atlas V missions. The Preliminary Design phase is recently underway. The XPC team is soliciting input from potential users.

The First Large Balloon Launch from Antarctica

DTIC Science & Technology

1988-09-26

On 31 December 1987 the payload and the operations were shifted to Williams Field. The gondola was housed in the garage at Williams Field. Operations...were complete and the system was flight ready. The launch was reconfirmed for 0600 hours 8 January 1988. The gondola was returned to the garage to...0000 hours LST. 13 January. The payload was off-loaded and stored In the garage at Williams Field. At this point the mission was complete except for

SPACEHAB is moved by crane in the SSPF before installation in the payload canister

NASA Technical Reports Server (NTRS)

1998-01-01

The SPACEHAB Single Module is moved by crane over the payload canister in KSC's Space Station Processing Facility. It will be joined in the canister by the Alpha Magnetic Spectrometer-01 payload before being moved to Launch Pad 39A for the STS-91 mission, scheduled to launch June 2 at around 6:04 p.m. EDT. SPACEHAB is used mainly as a large pressurized cargo container for science, logistical equipment and supplies to be exchanged between the orbiter Discovery and the Russian Space Station Mir. The nearly 10-day flight of STS-91 also is scheduled to return the sixth American, Mission Specialist Andrew Thomas, Ph.D., aboard the Russian orbiting outpost safely to Earth.

Modeling and control of flexible space platforms with articulated payloads

NASA Technical Reports Server (NTRS)

Graves, Philip C.; Joshi, Suresh M.

1989-01-01

The first steps in developing a methodology for spacecraft control-structure interaction (CSI) optimization are identification and classification of anticipated missions, and the development of tractable mathematical models in each mission class. A mathematical model of a generic large flexible space platform (LFSP) with multiple independently pointed rigid payloads is considered. The objective is not to develop a general purpose numerical simulation, but rather to develop an analytically tractable mathematical model of such composite systems. The equations of motion for a single payload case are derived, and are linearized about zero steady-state. The resulting model is then extended to include multiple rigid payloads, yielding the desired analytical form. The mathematical models developed clearly show the internal inertial/elastic couplings, and are therefore suitable for analytical and numerical studies. A simple decentralized control law is proposed for fine pointing the payloads and LFSP attitude control, and simulation results are presented for an example problem. The decentralized controller is shown to be adequate for the example problem chosen, but does not, in general, guarantee stability. A centralized dissipative controller is then proposed, requiring a symmetric form of the composite system equations. Such a controller guarantees robust closed loop stability despite unmodeled elastic dynamics and parameter uncertainties.

Bantam System Technology Project Ground System Operations Concept and Plan

NASA Technical Reports Server (NTRS)

Moon, Jesse M.; Beveridge, James R.

1997-01-01

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

Design of a spanloader cargo aircraft

NASA Technical Reports Server (NTRS)

1989-01-01

With a growing demand for fast international freight service, the slow-moving cargo ships currently in use will soon find a substantial portion of their clients looking elsewhere. One candidate for filling this expected gap in the freight market is a span-loading aircraft (or 'flying wing') capable of long-range operation with extremely large payloads. This report summarizes the design features of an aircraft capable of fulfilling a long-haul, high-capacity cargo mission. The spanloader seeks to gain advantage over conventional aircraft by eliminating the aircraft fuselage and thus reducing empty weight. The primary disadvantage of this configuration is that the cargo-containing wing tends to be thick, thus posing a challenge to the airfoil designer. It also suffers from stability and control problems not encountered by conventional aircraft. The result is an interesting, challenging exercise in unconventional design. The report that follows is a student written synopsis of an effort judged to be the best of eight designs developed during the year 1988-1989.

Geostationary platform systems concepts definition study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1980-01-01

The results of a geostationary platform concept analysis are summarized. Mission and payloads definition, concept selection, the requirements of an experimental platform, supporting research and technology, and the Space Transportation System interface requirements are addressed. It is concluded that platforms represent a logical extension of current trends toward larger, more complex, multifrequency satellites. Geostationary platforms offer significant cost savings compared to individual satellites, with the majority of these economies being realized with single Shuttle launched platforms. Further cost savings can be realized, however, by having larger platforms. Platforms accommodating communications equipment that operates at multiple frequencies and which provide larger scale frequency reuse through the use of large aperture multibeam antennas and onboard switching maximize the useful capacity of the orbital arc and frequency spectrum. Projections of market demand indicate that such conservation measures are clearly essential if orderly growth is to be provided for. In addition, it is pointed out that a NASA experimental platform is required to demonstrate the technologies necessary for operational geostationary platforms of the 1990's.

A comparison of Frequency Domain Multiple Access (FDMA) and Time Domain Multiple Access (TDMA) approaches to satellite service for low data rate Earth stations

NASA Technical Reports Server (NTRS)

Stevens, G.

1983-01-01

A technological and economic assessment is made of providing low data rate service to small earth stations by satellite at Ka-band. Various Frequency Domain Multiple Access (FDMA) and Time Domain Multiple Access (TDMA) scenarios are examined and compared on the basis of cost to the end user. Very small stations (1 to 2 meters in diameter) are found not to be viable alternatives to available terrestrial services. However, medium size (3 to 5 meters) earth stations appear to be very competitive if a minimum throughput of about 1.5 Mbs is maintained. This constrains the use of such terminals to large users and shared use by smaller users. No advantage was found to the use of FDMA. TDMA had a slight advantage from a total system viewpoint and a very significant advantage in the space segment (about 1/3 the required payload weight for an equivalent capacity).

Optimizing communication satellites payload configuration with exact approaches

NASA Astrophysics Data System (ADS)

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

2015-12-01

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

Communications platform payload definition study

NASA Technical Reports Server (NTRS)

Clopp, H. W.; Hawkes, T. A.; Bertles, C. R.; Pontano, B. A.; Kao, T.

1986-01-01

Large geostationary communications platforms were investigated in a number of studies since 1974 as a possible means to more effectively utilize the geostationary arc and electromagnetic spectrum and to reduce overall satellite communications system costs. The commercial feasibility of various communications platform payload concepts circa 1998 was addressed. Promising payload concepts were defined, recurring costs were estimated, and critical technologies needed to enable eventual commercialization were identified. Ten communications service aggregation scenarios describing potential groupings of service were developed for a range of conditions. Payload concepts were defined for four of these scenarios: (1) Land Mobile Satellite Service (LMSS) meets 100% of Contiguous United States (CONUS) plus Canada demand with a single platform; (2) Fixed Satellite Service (FSS) (trunking + Customer Premises Service (CPS)), meet 20% of CONUS demand;(3) FSS (trunking + CPS + video distribution), 10 to 13% of CONUS demand; and (4) FSS (20% of demand) + Inter Satellite Links (ISL) + Tracking and Data Relay Satellite System (TDRSS)/Tracking and Data Acquisition System (TDAS) Data Distribution.

Near-Earth Object Interception Using Nuclear Thermal Rock Propulsion

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

X-L. Zhang; E. Ball; L. Kochmanski

Planetary defense has drawn wide study: despite the low probability of a large-scale impact, its consequences would be disastrous. The study presented here evaluates available protection strategies to identify bottlenecks limiting the scale of near-Earth object that could be deflected, using cutting-edge and near-future technologies. It discusses the use of a nuclear thermal rocket (NTR) as a propulsion device for delivery of thermonuclear payloads to deflect or destroy a long-period comet on a collision course with Earth. A ‘worst plausible scenario’ for the available warning time (10 months) and comet approach trajectory are determined, and empirical data are used tomore » make an estimate of the payload necessary to deflect such a comet. Optimizing the tradeoff between early interception and large deflection payload establishes the ideal trajectory for an interception mission to follow. The study also examines the potential for multiple rocket launch dates. Comparison of propulsion technologies for this mission shows that NTR outperforms other options substantially. The discussion concludes with an estimate of the comet size (5 km) that could be deflected usingNTRpropulsion, given current launch capabilities.« less

An alternate concept for expanding man's presence in space

NASA Technical Reports Server (NTRS)

Hook, W. R.; Osborne, R. S.

1983-01-01

A logical next step after shuttle is a manned orbital service system (MOSS) consisting of a two-man crew module mated with a propulsion module. The resulting spacecraft would remain in low Earth orbit for months or years at a time conducting civil or military satellite servicing, experimental, or applications missions while being periodically supplied and refueled by Shuttle flights from the ground. The system would accumulate experience invaluable to the design of future large and more expensive spacecraft. Key features of the vehicle are versatility and mobility. With Centaur-type propulsion and a large payload, the MOSS could leave an initial orbit of 370 km (200 nmi) altitude and inclinations up to 56 deg, make a plane change of up to + or - 14 deg, reach altitudes to 5500 km (2970 nmi), and then return the payload to the original orbit altitude and inclination. Obviously, the size of the performance envelope varies with the payload and propulsion-unit selected. The MOSS can reach orbits and perform tasks not possible with Shuttle alone or with the much larger space stations currently being proposed.

Adaptive glide slope control for parafoil and payload aircraft

NASA Astrophysics Data System (ADS)

Ward, Michael

Airdrop systems provide a unique capability of delivering large payloads to undeveloped and inaccessible locations. Traditionally, these systems have been unguided, requiring large landing zones and drops from low altitude. The invention of the steerable, gliding, ram-air parafoil enabled the possibility of precision aerial payload delivery. In practice, the gliding ability of the ram-air parafoil can actually create major problems for airdrop systems by making them more susceptible to winds and allowing them to achieve far greater miss distances than were previously possible. Research and development work on guided airdrop systems has focused primarily on evolutionary improvements to the guidance algorithm, while the navigation and control algorithms have changed little since the initial autnomous systems were developed. Furthermore, the control mechanisms have not changed since the invention of the ram-air canopy in the 1960’s. The primary contributions of this dissertation are: (1) the development of a reliable and robust method to identify a flight dynamic model for a parafoil and payload aircraft using minimal sensor data; (2) the first demonstration in flight test of the ability to achieve large changes in glide slope over ground using coupled incidence angle variation and trailing edge brake deflection; (3) the first development of a control law to implement glide slope control on an autonomous system; (4) the first flight tests of autonomous landing with a glide slope control mechanism demonstrating an improvement in landing accuracy by a factor of 2 or more in especially windy conditions, and (5) the first demonstrations in both simulation and flight test of the ability to perform in-flight system identification to adapt the internal control mappings to flight data and provide dramatic improvements in landing accuracy when there is a significant discrepancy between the assumed and actual flight characteristics.

Bayesian networks for satellite payload testing

NASA Astrophysics Data System (ADS)

Przytula, Krzysztof W.; Hagen, Frank; Yung, Kar

1999-11-01

Satellite payloads are fast increasing in complexity, resulting in commensurate growth in cost of manufacturing and operation. A need exists for a software tool, which would assist engineers in production and operation of satellite systems. We have designed and implemented a software tool, which performs part of this task. The tool aids a test engineer in debugging satellite payloads during system testing. At this stage of satellite integration and testing both the tested payload and the testing equipment represent complicated systems consisting of a very large number of components and devices. When an error is detected during execution of a test procedure, the tool presents to the engineer a ranked list of potential sources of the error and a list of recommended further tests. The engineer decides this on this basis if to perform some of the recommended additional test or replace the suspect component. The tool has been installed in payload testing facility. The tool is based on Bayesian networks, a graphical method of representing uncertainty in terms of probabilistic influences. The Bayesian network was configured using detailed flow diagrams of testing procedures and block diagrams of the payload and testing hardware. The conditional and prior probability values were initially obtained from experts and refined in later stages of design. The Bayesian network provided a very informative model of the payload and testing equipment and inspired many new ideas regarding the future test procedures and testing equipment configurations. The tool is the first step in developing a family of tools for various phases of satellite integration and operation.

A narrowband CDMA communications payload for little LEOS applications

NASA Astrophysics Data System (ADS)

Michalik, H.; Hävecker, W.; Ginati, A.

1996-09-01

In recent years Code Division Multiple Access (CDMA) techniques have been investigated for application in Local Area Networks [J. A. Salehi, IEEE Trans. Commun. 37 (1989)]as well as in Mobile Communications [R. Kohno et al., IEEE Commun. Mag. Jan (1995)]. The main attraction of these techniques is due to potential higher throughput and capacity of such systems under certain conditions compared to conventional multi-access schemes like frequency and time division multiplexing. Mobile communication over a Satellite Link represents in some terms the "worst case" for operating a CDMA-system. Considering e.g. the uplink case from mobile to satellite, the imperfections due to different and time varying channel conditions will add to the well known effects of Multiple Access Interference (MAI) between the simultaneously active users at the satellite receiver. In addition, bandwidth constraints due to the non-availability of large bandwidth channels in the interesting frequency bands, exist for small systems. As a result, for a given service in terms of user data rates, the practical code sequence lengths are limited as well as the available number of codes within a code set. In this paper a communications payload for Small Satellite Applications with CDMA uplink and C/TDMA downlink under the constraint of bandwidth limitations is proposed. To optimise the performance under the above addressed imperfections the system provides ability for power control and synchronisation for the CDMA uplink. The major objectives of this project are studying, development and testing of such a system for educational purposes and technology development at Hochschule Bremen.

A system concept for gradual deployment of geostationary lightsats

NASA Astrophysics Data System (ADS)

Peters, Graham C.; Garry, James R. C.

1993-10-01

Small satellites provide an attractive option for developing countries wishing to own and operate a satellite for the first time. It is proposed that space segment capacity could be built-up in response to increasing traffic requirements by launching small satellites at intervals into a single orbital slot to form a cluster. This paper, which results from an ESA study, reviews the various system aspects which must be considered and develops a suitable approach for multi-satellite deployment and collocation. Particular attention is paid to the system and payload configuration required to achieve effective mutual sparing between the satellites' payloads as the constellation is expanded. Mission and operational aspects are examined to obtain an acceptable risk of collisions between the satellites in a single orbit slot. The complexity and cost of operations are investigated to obtain the optimum size of satellite required to satisfy different demand requirements taken from real market scenarios.

Cost and Business Analysis Module (CABAM). Revision A

NASA Technical Reports Server (NTRS)

Lee, Michael Hosung

1997-01-01

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

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

NASA Astrophysics Data System (ADS)

Friis, Jan W., Jr.

2000-11-01

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

Deployable pressurized cell structure for a micrometeoroid detector

NASA Technical Reports Server (NTRS)

Kinard, W. H. (Inventor)

1974-01-01

This disclosure comprises a plurality of individual pressurized cells which are caused to leak in response to a micrometeoroid penetration, the leak being sensed by appropriate instrumentation. The plurality of cells may be rolled into a compact arrangement such that the volume of the micrometeoroid detector is small and therefore readily packed in a payload of a launch vehicle. Once the payload is placed in orbit, the rolled up cells can be released, pressurized and provide a relatively rigid, large surface area for detecting micrometeoroid penetration.

Interactions measurement payload for Shuttle

NASA Technical Reports Server (NTRS)

Guidice, D. A.; Pike, C. P.

1985-01-01

The Interactions Measurement Payload for Shuttle (IMPS) consisted of engineering experiments to determine the effects of the space environment on projected Air Force space systems. Measurements by IMPS on a polar-orbit Shuttle flight will lead to detailed knowledge of the interaction of the low-altitude polar-auroral environment on materials, equipment and technologies to be used in future large, high-power space systems. The results from the IMPS measurements will provide direct input to MIL-STD design guidelines and test standards that properly account for space-environment effects.

Environmental Assessment for the National Museum of the United States Air Force Addition, Wright-Patterson Air Force Base, Ohio

DTIC Science & Technology

2013-02-01

telephone, local computer systems, long-haul communications , and land mobile radio systems (WPAFB 2001). There are over 100 miles of communication cable...10. SPONSOR/MONITOR’S ACRONYM(S) 11 . SPONSOR/MONITOR’S REPORT NUMBER(S) 12. DISTRIBUTION/AVAILABILITY STATEMENT Approved for public release...Air Force technologies and would include unique characteristics in design, propulsion, payload capacity, buman factors, communication , range, speed

On LSB Spatial Domain Steganography and Channel Capacity

DTIC Science & Technology

2008-03-21

reveal the hidden information should not be taken as proof that the image is now clean. The survivability of LSB type spatial domain steganography ...the mindset that JPEG compressing an image is sufficient to destroy the steganography for spatial domain LSB type stego. We agree that JPEGing...modeling of 2 bit LSB steganography shows that theoretically there is non-zero stego payload possible even though the image has been JPEGed. We wish to

Mars Rotorcraft: Possibilities, Limitations, and Implications For Human/Robotic Exploration

NASA Technical Reports Server (NTRS)

Young, Larry A.; Aiken, Edwin; Lee, Pascal; Briggs, Geoffrey

2005-01-01

Several research investigations have examined the challenges and opportunities in the use of small robotic rotorcraft for the exploration of Mars. To date, only vehicles smaller than 150 kg have been studied. This paper proposes to examine the question of maximum Mars rotorcraft size, range, and payload/cargo capacity. Implications for the issue of whether or not (from an extreme design standpoint) a manned Mars rotorcraft is viable are also discussed.

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

NASA Technical Reports Server (NTRS)

1978-01-01

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

Applications of a new mass-driver concept

NASA Technical Reports Server (NTRS)

Oneill, G. K.

1981-01-01

A description of the operating principles and requirements of a novel mass-driver concept is presented. The design obtains acceleration of payload bucket coils by means of transverse focussing from strong, off-axis restoring forces that are produced by drive coils operating in a 'pull-only' mode. The concept offers the unprecedented possibility of operating high-performance mass-drivers entirely within the limitations of existing commercial switching devices, such as silicon-controlled rectifiers, spark gaps, vacuum-triggered arcs or vacuum mechanical switches. Representative applications of the concept described are: (1) a large-diameter magnetic lunar launcher for payloads having autonomous maneuvering; (2) an intermediate-diameter launcher with long operational life; and (3) a reaction engine for orbit transfer of large, massive objects.

Analysis and Improvement of Large Payload Bidirectional Quantum Secure Direct Communication Without Information Leakage

NASA Astrophysics Data System (ADS)

Liu, Zhi-Hao; Chen, Han-Wu

2018-02-01

As we know, the information leakage problem should be avoided in a secure quantum communication protocol. Unfortunately, it is found that this problem does exist in the large payload bidirectional quantum secure direct communication (BQSDC) protocol (Ye Int. J. Quantum. Inf. 11(5), 1350051 2013) which is based on entanglement swapping between any two Greenberger-Horne-Zeilinger (GHZ) states. To be specific, one half of the information interchanged in this protocol is leaked out unconsciously without any active attack from an eavesdropper. Afterward, this BQSDC protocol is revised to the one without information leakage. It is shown that the improved BQSDC protocol is secure against the general individual attack and has some obvious features compared with the original one.

Finding 'paydirt' on the moon and asteroids

NASA Technical Reports Server (NTRS)

Staehle, R. L.

1983-01-01

Lunar polar region water ice, the Trojan asteroids of the earth, accessible, volatile substance-rich near-earth asteroids, and lunar gas deposits, are theoretically identified extraterrestrial resources for application to space transportation whose existence and economical exploitability could be confirmed by explorations conducted with relatively simple spacecraft. Any of these resources could improve the economics of interorbit transportation, thereby permitting launch vehicle payloads to be devoted to the transport of revenue-generating or services-providing equipment, rather than to the large propellant volumes required for the placing of large payloads on station. Among the verification missions cited is a simple lunar prospector orbiter, carrying a gamma-ray spectrometer and an electromagnetic sounder, which could ascertain the presence of water ice at the lunar poles.

SPACEHAB is raised by crane in the SSPF before installation in the payload canister

NASA Technical Reports Server (NTRS)

1998-01-01

The SPACEHAB Single Module is raised by crane from a transporter in KSC's Space Station Processing Facility, where it will be moved to the payload canister. It will be joined in the canister by the Alpha Magnetic Spectrometer-01 payload before being moved to Launch Pad 39A for the STS-91 mission, scheduled to launch June 2 at around 6:04 p.m. EDT. SPACEHAB is used mainly as a large pressurized cargo container for science, logistical equipment and supplies to be exchanged between the orbiter Discovery and the Russian Space Station Mir. The nearly 10-day flight of STS-91 also is scheduled to return the sixth American, Mission Specialist Andrew Thomas, Ph.D., aboard the Russian orbiting outpost safely to Earth.

The SALSA Project - High-End Aerial 3d Camera

NASA Astrophysics Data System (ADS)

Rüther-Kindel, W.; Brauchle, J.

2013-08-01

The ATISS measurement drone, developed at the University of Applied Sciences Wildau, is an electrical powered motor glider with a maximum take-off weight of 25 kg including a payload capacity of 10 kg. Two 2.5 kW engines enable ultra short take-off procedures and the motor glider design results in a 1 h endurance. The concept of ATISS is based on the idea to strictly separate between aircraft and payload functions, which makes ATISS a very flexible research platform for miscellaneous payloads. ATISS is equipped with an autopilot for autonomous flight patterns but under permanent pilot control from the ground. On the basis of ATISS the project SALSA was undertaken. The aim was to integrate a system for digital terrain modelling. Instead of a laser scanner a new design concept was chosen based on two synchronized high resolution digital cameras, one in a fixed nadir orientation and the other in a oblique orientation. Thus from every object on the ground images from different view angles are taken. This new measurement camera system MACS-TumbleCam was developed at the German Aerospace Center DLR Berlin-Adlershof especially for the ATISS payload concept. Special advantage in comparison to laser scanning is the fact, that instead of a cloud of points a surface including texture is generated and a high-end inertial orientation system can be omitted. The first test flights show a ground resolution of 2 cm and height resolution of 3 cm, which underline the extraordinary capabilities of ATISS and the MACS measurement camera system.

Development and Characteristics of a Mobile, Semi-Autonomous Floating Platform for in situ Lake Measurements

NASA Astrophysics Data System (ADS)

Barry, D.; Lemmin, U.; Le Dantec, N.; Zulliger, L.; Rusterholz, M.; Bolay, M.; Rossier, J.; Kangur, K.

2013-12-01

In the development of sustainable management strategies of lakes more insight into their physical, chemical and ecological dynamics is needed. Field data obtained from various types of sensors with adequate spatial and temporal sampling rate are essential to understand better the processes that govern fluxes and pathways of water masses and transported compounds, whether for model validation or for monitoring purposes. One advantage of unmanned platforms is that they limit the disturbances typically affecting the quality of data collected on small vessels, including perturbations caused by movements of onboard crew. We have developed a mobile, semi-autonomous floating platform with 8 h power autonomy using a 5 m long by 2.5 m wide catamaran. Our approach focused on modularity and high payload capacity in order to accommodate a large number of sensors both in terms of electronic (power and data) and mechanical constraints of integration. Software architecture and onboard electronics use National Instruments technology to simplify and standardize integration of sensors, actuators and communication. Piecewise-movable deck sections allow optimizing platform stability depending on the payload. The entire system is controlled by a remote computer located on an accompanying vessel and connected via a wireless link with a range of over 1 km. Real-time transmission of GPS-stamped measurements allows immediate modifications in the survey plan if needed. The displacement of the platform is semi-autonomous, with the options of either autopilot mode following a pre-planned course specified by waypoints or remote manual control from the accompanying vessel. Maintenance of permanent control over the platform displacement is required for safety reasons with respect to other users of the lake. Currently, the sensor payload comprises an array of fast temperature probes, a bottom-tracking ADCP and atmospheric sensors including a radiometer. A towed CTD with additional water quality sensors operated from a remotely controlled winch is presently being integrated. Field tests have shown that the platform is reliable, capable of collecting long transects of 2D lake and collocated atmospheric boundary layer data and adaptable to integrate new sensors.

Preliminary Analysis for an Optimized Oil-Free Rotorcraft Engine Concept

NASA Technical Reports Server (NTRS)

Howard, Samuel A.; Bruckner, Robert J.; DellaCorte, Christopher; Radil, Kevin C.

2008-01-01

Recent developments in gas foil bearing technology have led to numerous advanced high-speed rotating system concepts, many of which have become either commercial products or experimental test articles. Examples include Oil-Free microturbines, motors, generators and turbochargers. The driving forces for integrating gas foil bearings into these high-speed systems are the benefits promised by removing the oil lubrication system. Elimination of the oil system leads to reduced emissions, increased reliability, and decreased maintenance costs. Another benefit is reduced power plant weight. For rotorcraft applications, this would be a major advantage, as every pound removed from the propulsion system results in a payload benefit. Implementing foil gas bearings throughout a rotorcraft gas turbine engine is an important long-term goal that requires overcoming numerous technological hurdles. Adequate thrust bearing load capacity and potentially large gearbox applied radial loads are among them. However, by replacing the turbine end, or hot section, rolling element bearing with a gas foil bearing many of the above benefits can be realized. To this end, engine manufacturers are beginning to explore the possibilities of hot section gas foil bearings in propulsion engines. This paper presents a logical follow-on activity by analyzing a conceptual rotorcraft engine to determine the feasibility of a foil bearing supported core. Using a combination of rotordynamic analyses and a load capacity model, it is shown to be reasonable to consider a gas foil bearing core section.

The Lunar Crater Observation and Sensing Satellite (LCROSS) Payload Development and Performance in Flight

NASA Astrophysics Data System (ADS)

Ennico, Kimberly; Shirley, Mark; Colaprete, Anthony; Osetinsky, Leonid

2012-05-01

The primary objective of the Lunar Crater Observation and Sensing Satellite (LCROSS) was to confirm the presence or absence of water ice in a permanently shadowed region (PSR) at a lunar pole. LCROSS was classified as a NASA Class D mission. Its payload, the subject of this article, was designed, built, tested and operated to support a condensed schedule, risk tolerant mission approach, a new paradigm for NASA science missions. All nine science instruments, most of them ruggedized commercial-off-the-shelf (COTS), successfully collected data during all in-flight calibration campaigns, and most importantly, during the final descent to the lunar surface on October 9, 2009, after 112 days in space. LCROSS demonstrated that COTS instruments and designs with simple interfaces, can provide high-quality science at low-cost and in short development time frames. Building upfront into the payload design, flexibility, redundancy where possible even with the science measurement approach, and large margins, played important roles for this new type of payload. The environmental and calibration approach adopted by the LCROSS team, compared to existing standard programs, is discussed. The description, capabilities, calibration and in-flight performance of each instrument are summarized. Finally, this paper goes into depth about specific areas where the instruments worked differently than expected and how the flexibility of the payload team, the knowledge of instrument priority and science trades, and proactive margin maintenance, led to a successful science measurement by the LCROSS payload's instrument complement.

Fabrication of Calcium Phosphate-Based Nanocomposites Incorporating DNA Origami, Gold Nanorods, and Anticancer Drugs for Biomedical Applications.

PubMed

Zhang, Hongbo; Qu, Xiangmeng; Chen, Hong; Kong, Haixin; Ding, Ruihua; Chen, Dong; Zhang, Xu; Pei, Hao; Santos, Hélder A; Hai, Mingtan; Weitz, David A

2017-10-01

DNA origami is designed by folding DNA strands at the nanoscale with arbitrary control. Due to its inherent biological nature, DNA origami is used in drug delivery for enhancement of synergism and multidrug resistance inhibition, cancer diagnosis, and many other biomedical applications, where it shows great potential. However, the inherent instability and low payload capacity of DNA origami restrict its biomedical applications. Here, this paper reports the fabrication of an advanced biocompatible nano-in-nanocomposite, which protects DNA origami from degradation and facilities drug loading. The DNA origami, gold nanorods, and molecular targeted drugs are co-incorporated into pH responsive calcium phosphate [Ca 3 (PO 4 ) 2 ] nanoparticles. Subsequently, a thin layer of phospholipid is coated onto the Ca 3 (PO 4 ) 2 nanoparticle to offer better biocompatibility. The fabricated nanocomposite shows high drug loading capacity, good biocompatibility, and a photothermal and pH-responsive payload release profile and it fully protects DNA origami from degradation. The codelivery of DNA origami with cancer drugs synergistically induces cancer cell apoptosis, reduces the multidrug resistance, and enhances the targeted killing efficiency toward human epidermal growth factor receptor 2 positive cells. This nanocomposite is foreseen to open new horizons for a variety of clinical and biomedical applications. © 2017 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim.

CRYOTE (Cryogenic Orbital Testbed) Concept

NASA Technical Reports Server (NTRS)

Gravlee, Mari; Kutter, Bernard; Wollen, Mark; Rhys, Noah; Walls, Laurie

2009-01-01

Demonstrating cryo-fluid management (CFM) technologies in space is critical for advances in long duration space missions. Current space-based cryogenic propulsion is viable for hours, not the weeks to years needed by space exploration and space science. CRYogenic Orbital TEstbed (CRYOTE) provides an affordable low-risk environment to demonstrate a broad array of critical CFM technologies that cannot be tested in Earth's gravity. These technologies include system chilldown, transfer, handling, health management, mixing, pressure control, active cooling, and long-term storage. United Launch Alliance is partnering with Innovative Engineering Solutions, the National Aeronautics and Space Administration, and others to develop CRYOTE to fly as an auxiliary payload between the primary payload and the Centaur upper stage on an Atlas V rocket. Because satellites are expensive, the space industry is largely risk averse to incorporating unproven systems or conducting experiments using flight hardware that is supporting a primary mission. To minimize launch risk, the CRYOTE system will only activate after the primary payload is separated from the rocket. Flying the testbed as an auxiliary payload utilizes Evolved Expendable Launch Vehicle performance excess to cost-effectively demonstrate enhanced CFM.

Simulating Vibrations in a Complex Loaded Structure

NASA Technical Reports Server (NTRS)

Cao, Tim T.

2005-01-01

The Dynamic Response Computation (DIRECT) computer program simulates vibrations induced in a complex structure by applied dynamic loads. Developed to enable rapid analysis of launch- and landing- induced vibrations and stresses in a space shuttle, DIRECT also can be used to analyze dynamic responses of other structures - for example, the response of a building to an earthquake, or the response of an oil-drilling platform and attached tanks to large ocean waves. For a space-shuttle simulation, the required input to DIRECT includes mathematical models of the space shuttle and its payloads, and a set of forcing functions that simulates launch and landing loads. DIRECT can accommodate multiple levels of payload attachment and substructure as well as nonlinear dynamic responses of structural interfaces. DIRECT combines the shuttle and payload models into a single structural model, to which the forcing functions are then applied. The resulting equations of motion are reduced to an optimum set and decoupled into a unique format for simulating dynamics. During the simulation, maximum vibrations, loads, and stresses are monitored and recorded for subsequent analysis to identify structural deficiencies in the shuttle and/or payloads.

Results of a laboratory experiment that tests rotating unbalanced-mass devices for scanning gimbaled payloads and free-flying spacecraft

NASA Technical Reports Server (NTRS)

Alhorn, D. C.; Polites, M. E.

1994-01-01

Rotating unbalanced-mass (RUM) devices are a new way to scan space-based, balloon-borne, and ground-based gimbaled payloads, like x-ray and gamma-ray telescopes. They can also be used to scan free-flying spacecraft. Circular scans, linear scans, and raster scans can be generated. A pair of RUM devices generates the basic scan motion and an auxiliary control system using torque motors, control moment gyros, or reaction wheels keeps the scan centered on the target and produces some complementary motion for raster scanning. Previous analyses and simulation results show that this approach offers significant power savings compared to scanning only with the auxiliary control system, especially with large payloads and high scan frequencies. However, these claims have never been proven until now. This paper describes a laboratory experiment which tests the concept of scanning a gimbaled payload with RUM devices. A description of the experiment is given and test results that prove the concept are presented. The test results are compared with those from a computer simulation model of the experiment and the differences are discussed.

14 CFR 420.19 - Launch site location review-general.

Code of Federal Regulations, 2011 CFR

2011-01-01

... nm orbit Weight class Small Medium Medium large Large 28 degrees inclination * ≤4400 >4400 to ≤11100.... Orbital expendable launch vehicles are further classified by weight class, based on the weight of payload... class of orbital expendable launch vehicles flown from a launch point, the applicant shall demonstrate...

Preliminary study of a very large catamaran freighter as a derivative of a current wide-body aircraft

NASA Technical Reports Server (NTRS)

Heyson, H. H.

1976-01-01

The development of a very large cargo aircraft by combining, in catamaran fashion, two existing wide body transports was studied. Advantages of this system include: lighter weight and increased payload; increased fuel economy; and reduction in direct operating costs.

Lessons Learned From the Development, Operation, and Review of Mechanical Systems on the Space Shuttle, International Space Station, and Payloads

NASA Technical Reports Server (NTRS)

Dinsel, Alison; Jermstad, Wayne; Robertson, Brandan

2006-01-01

The Mechanical Design and Analysis Branch at the Johnson Space Center (JSC) is responsible for the technical oversight of over 30 mechanical systems flying on the Space Shuttle Orbiter and the International Space Station (ISS). The branch also has the responsibility for reviewing all mechanical systems on all Space Shuttle and International Space Station payloads, as part of the payload safety review process, through the Mechanical Systems Working Group (MSWG). These responsibilities give the branch unique insight into a large number of mechanical systems, and problems encountered during their design, testing, and operation. This paper contains narrative descriptions of lessons learned from some of the major problems worked on by the branch during the last two years. The problems are grouped into common categories and lessons learned are stated.

Design and systems analysis of a chemical interorbital shuttle. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Nissim, W.

1972-01-01

An interorbital shuttle that can be utilized to carry payloads between low earth orbit (180 n mi, 37.6 deg) and lunar or geosynchronous orbits, and also to interplanetary trajectories is discussed. After each mission the stage returns to its earth parking orbit where it delivers the inbound payloads, and where it is maintained and refueled for the subsequent missions. The stage can also be utilized to carry large payloads (150 to 200 KLBS) to the Space Station orbit (270 n mi, 55 deg) when it is used as a second or parallel burn stage to the space shuttle booster. The mission and systems analysis, as well as the results of structural, mechanical and propulsion, and avionics subsystems analysis and design are described. A development plan and cost estimates are also included.

Control-structure interaction/mirror motion compensation

NASA Technical Reports Server (NTRS)

Mclaren, Mark; Chu, Peter; Price, Xen

1992-01-01

Space Systems/Loral (formerly Ford Aerospace, Space Systems Division) has implemented a rigid-body Mirror Motion Compensation (MMC) scheme for the GOES-I/M spacecraft currently being built for NASA and NOAA. This has resulted in a factor of 15 reduction in pointing error due to rigid-body spacecraft motion induced by the periodic black-body calibration maneuvers required for the instruments. For GOES the spacecraft and the payload mirrors are considered as rigid bodies. The structural flexibility effects are small and are included in the total pointing budget as a separate item. This paper extends the MMC technique to include structural flexibility. For large multi-payload platforms, the structural flexibility effects can be more important in sensor pointing jitter as the result of payload motion. Sensitivity results are included to show the importance of the dynamic model fidelity.

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

NASA Technical Reports Server (NTRS)

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

1980-01-01

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

Advanced power systems for EOS

NASA Technical Reports Server (NTRS)

Bailey, Sheila G.; Weinberg, Irving; Flood, Dennis J.

1991-01-01

The Earth Observing System, which is part of the International Mission to Planet Earth, is NASA's main contribution to the Global Change Research Program. Five large platforms are to be launched into polar orbit: two by NASA, two by the European Space Agency, and one by the Japanese. In such an orbit the radiation resistance of indium phosphide solar cells combined with the potential of utilizing 5 micron cell structures yields an increase of 10 percent in the payload capability. If further combined with the Advanced Photovoltaic Solar Array, the total additional payload capability approaches 12 percent.

Boeing 747 aircraft with large external pod for transporting outsize cargo

NASA Technical Reports Server (NTRS)

Price, J. E.; Quartero, C. B.; Smith, P. M.; Washburn, G. F.

1979-01-01

The effect on structural arrangement, system weight, and range performance of the cargo pod payload carrying capability was determined to include either the bridge launcher or a spacelab module on a Boeing 747 aircraft. Modifications to the carrier aircraft and the installation time required to attach the external pod to the 747 were minimized. Results indicate that the increase in pod size was minimal, and that the basic 747 structure was adequate to safely absorb the load induced by ground or air operation while transporting either payload.

Large Diameter Shuttle Launched-AEM (LDSL-AEM) study

NASA Technical Reports Server (NTRS)

1976-01-01

A technical description of a Large Diameter Shuttle Launched-AEM (LDSL-AEM), an AEM base module adapted to carry 5 ft diameter payloads in the shuttle with propulsion for carrying payloads to higher altitude orbits from a 150 NM shuttle orbit, is described. The AEM is designed for launch on the scout launch vehicle. Onboard equipment provides capability to despin, acquire the earth, and control the vehicle in an earth pointing mode using reaction wheels for torque with magnets for all attitude acquisition, wheel desaturation, and nutation damping. Earth sensors in the wheels provide pitch and roll attitude. This system provides autonomous control capability to 1 degree in pitch and roll and 2 degrees in yaw. The attitude can be determined to .5 degrees in pitch and roll and 2 degrees in yaw.

NASA/MSFC ground experiment for large space structure control verification

NASA Technical Reports Server (NTRS)

Waites, H. B.; Seltzer, S. M.; Tollison, D. K.

1984-01-01

Marshall Space Flight Center has developed a facility in which closed loop control of Large Space Structures (LSS) can be demonstrated and verified. The main objective of the facility is to verify LSS control system techniques so that on orbit performance can be ensured. The facility consists of an LSS test article which is connected to a payload mounting system that provides control torque commands. It is attached to a base excitation system which will simulate disturbances most likely to occur for Orbiter and DOD payloads. A control computer will contain the calibration software, the reference system, the alignment procedures, the telemetry software, and the control algorithms. The total system will be suspended in such a fashion that LSS test article has the characteristics common to all LSS.

Space Launch System Spacecraft and Payload Elements: Progress Toward Crewed Launch and Beyond

NASA Technical Reports Server (NTRS)

Schorr, Andrew A.; Smith, David Alan; Holcomb, Shawn; Hitt, David

2017-01-01

While significant and substantial progress continues to be accomplished toward readying the Space Launch System (SLS) rocket for its first test flight, work is already underway on preparations for the second flight - using an upgraded version of the vehicle - and beyond. Designed to support human missions into deep space, SLS is the most powerful human-rated launch vehicle the United States has ever undertaken, and is one of three programs being managed by the National Aeronautics and Space Administration's (NASA's) Exploration Systems Development division. The Orion spacecraft program is developing a new crew vehicle that will support human missions beyond low Earth orbit (LEO), and the Ground Systems Development and Operations (GSDO) program is transforming Kennedy Space Center (KSC) into a next-generation spaceport capable of supporting not only SLS but also multiple commercial users. Together, these systems will support human exploration missions into the proving ground of cislunar space and ultimately to Mars. For its first flight, SLS will deliver a near-term heavy-lift capability for the nation with its 70-metric-ton (t) Block 1 configuration. Each element of the vehicle now has flight hardware in production in support of the initial flight of the SLS, which will propel Orion around the moon and back. Encompassing hardware qualification, structural testing to validate hardware compliance and analytical modeling, progress is on track to meet the initial targeted launch date. In Utah and Mississippi, booster and engine testing are verifying upgrades made to proven shuttle hardware. At Michoud Assembly Facility (MAF) in Louisiana, the world's largest spacecraft welding tool is producing tanks for the SLS core stage. Providing the Orion crew capsule/launch vehicle interface and in-space propulsion via a cryogenic upper stage, the Spacecraft/Payload Integration and Evolution (SPIE) element serves a key role in achieving SLS goals and objectives. The SPIE element marked a major milestone in 2014 with the first flight of original SLS hardware, the Orion Stage Adapter (OSA) which was used on Exploration Flight Test-1 with a design that will be used again on the first flight of SLS. The element has overseen production of the Interim Cryogenic Propulsion Stage (ICPS), an in-space stage derived from the Delta Cryogenic Second Stage, which was manufactured at United Launch Alliance (ULA) in Decatur, Alabama, prior to being shipped to Florida for flight preparations. Manufacture of the OSA and the Launch Vehicle Stage Adapter (LVSA) took place at the Friction Stir Facility located at Marshall Space Flight Center (MSFC) in Huntsville, Alabama. Marshall is also home to the Integrated Structural Test of the ICPS, LVSA, and OSA, subjecting the stacked components to simulated stresses of launch. The SPIE Element is also overseeing integration of 13 "CubeSat" secondary payloads that will fly on the first flight of SLS, providing access to deep space regions in a way currently not available to the science community. At the same time as this preparation work is taking place toward the first launch of SLS, however, the Space Launch System Program is actively working toward its second launch. For its second flight, SLS will be upgraded to the more-capable Block 1B configuration. While the Block 1 configuration is capable of delivering more than 70 t to LEO, the Block 1B vehicle will increase that capability to 105 t. For that flight, the new configuration introduces two major new elements to the vehicle - an Exploration Upper Stage (EUS) that will be used for both ascent and in-space propulsion, and a Universal Stage Adapter (USA) that serves as a "payload bay" for the rocket, allowing the launch of large exploration systems along with the Orion spacecraft. Already, flight hardware is being prepared for the Block 1B vehicle. Welding is taking place on the second rocket's core stage. Flight hardware production has begun on booster components. An RS-25 engine slated for that flight has been tested. Development work is taking place on the EUS, with contracts in place for both the stage and the RL10 engines which will power it. (The EUS will use four RL10 engines, an increase from one on the ICPS.) For the crew configuration of the Block 1B vehicle, the SLS SPIE element is managing the USA and accompanying Payload Adapter, which will accommodate both large payloads co-manifested with Orion and small-satellite secondary payloads. This co-manifested payload capacity will be instrumental for missions into the proving ground around the moon, where NASA will test new systems and demonstrate new capabilities needed for human exploration farther into deep space.

Space Launch System Spacecraft and Payload Elements: Progress Toward Crewed Launch and Beyond

NASA Technical Reports Server (NTRS)

Schorr, Andrew A.; Creech, Stephen D.

2017-01-01

While significant and substantial progress continues to be accomplished toward readying the Space Launch System (SLS) rocket for its first test flight, work is already also underway on preparations for the second flight - using an upgraded version of the vehicle - and beyond. Designed to support human missions into deep space, Space Launch System (SLS), is the most powerful human-rated launch vehicle the United States has ever undertaken, and is one of three programs being managed by the National Aeronautics and Space Administration's (NASA's) Exploration Systems Development division. The Orion spacecraft program is developing a new crew vehicle that will support human missions beyond low Earth orbit (LEO), and the Ground Systems Development and Operations program is transforming Kennedy Space Center into a next-generation spaceport capable of supporting not only SLS but also multiple commercial users. Together, these systems will support human exploration missions into the proving ground of cislunar space and ultimately to Mars. For its first flight, SLS will deliver a near-term heavy-lift capability for the nation with its 70-metric-ton (t) Block 1 configuration. Each element of the vehicle now has flight hardware in production in support of the initial flight of the SLS, which will propel Orion around the moon and back. Encompassing hardware qualification, structural testing to validate hardware compliance and analytical modeling, progress in on track to meet the initial targeted launch date. In Utah and Mississippi, booster and engine testing are verifying upgrades made to proven shuttle hardware. At Michoud Assembly Facility in Louisiana, the world's largest spacecraft welding tool is producing tanks for the SLS core stage. Providing the Orion crew capsule/launch vehicle interface and in-space propulsion via a cryogenic upper stage, the Spacecraft/Payload Integration and Evolution (SPIE) element serves a key role in achieving SLS goals and objectives. The SPIE element marked a major milestone in 2014 with the first flight of original SLS hardware, the Orion Stage Adapter (OSA) which was used on Exploration Flight Test-1 with a design that will be used again on the first flight of SLS. The element has overseen production of the Interim Cryogenic Propulsion Stage (ICPS), an in-space stage derived from the Delta Cryogenic Second Stage, which was manufactured at United Launch Alliance in Decatur, Alabama, prior to being shipped to Florida for flight preparations. Manufacture of the Orion Stage Adapter and the Launch Vehicle Stage Adapter (LVSA) took place at the Friction Stir Facility located at Marshall Space Flight Center in Huntsville, Alabama. Marshall is also home to the Integrated Structural Test of the ICPS, LVSA, and OSA, subjecting the stacked components to simulated stresses of launch. The SPIE Element is also overseeing integration of 13 "CubeSat" secondary payloads that will fly on the first flight of SLS, providing access to deep space regions in a way currently not available to the science community. At the same time as this preparation work is taking place toward the first launch of SLS, however, the Space Launch System Program is actively working toward its second launch. For its second flight, SLS will be upgraded to the more-capable Block 1B configuration. While the Block 1 configuration is capable of delivering more than 70 metric tons to low Earth orbit, the Block 1B vehicle will increase that capability to 105 t. For that flight, the new configuration introduces two major new elements to the vehicle - an Exploration Upper Stage (EUS) that will be used for both ascent and in-space propulsion, and a Universal Stage Adapter (USA) that serves as a "payload bay" for the rocket, allowing the launch of large exploration systems along with the Orion spacecraft. Already, flight hardware is being prepared for the Block 1B vehicle. Welding is taking place on the second rocket's core stage. Flight hardware production has begun on booster components. An RS-25 engine slated for that flight has been tested. Development work is taking place on the Exploration Upper Stage, with contracts in place for both the stage and the RL10 engines which will power it. (The EUS will use four RL10 engines, an increase from one on the ICPS.) For the crew configuration of the Block 1B vehicle, the SLS SPIE element is managing the USA and accompanying Payload Adapter, which will accommodate both large payloads co-manifested with Orion and small-satellite secondary payloads. This co-manifested payload capacity will be instrumental for missions into the Proving Ground around the moon, where NASA will test new systems and demonstrate new capabilities needed for human exploration farther into deep space.

The AstroSat Production Line: From AstroSat 100 to AstroSat 1000

NASA Astrophysics Data System (ADS)

Maliet, E.; Pawlak, D.; Koeck, C.; Beaufumé, E.

2008-08-01

From the late 90s onward, Astrium Satellites has developed and improved several classes of high resolution optical Earth Observation satellites. The resulting product line ranges from micro-satellites (about 120 kg) type to the large satellites (in the range of 1 200 kg). They all make uses of state of the art technologies for optical payloads, as well as for avionics. Several classes of platforms have thus been defined and standardised: AstroSat 100 for satellites up to 150 kg, allowing affordable but fully operational missions, AstroSat 500 for satellites up to 800 kg, allowing complex high resolution missions, and AstroSat 1000 for satellites up to 1 200 kg, providing very high resolution and outstanding imaging and agility capabilities. A new class, AstroSat 250, has been developed by Astrium Satellites, and is now proposed, offering a state-of-the-art 3-axis agile platform for high- resolution missions, with a launch mass below 550 kg. The Astrosat platforms rely on a centralised architecture avionics based on an innovative AOCS hybridising of measurements from GPS, stellar sensors and inertial reference unit. Operational safety has been emphasised through thruster free safe modes. All optical payloads make use of all Silicon Carbide (SiC) telescopes. High performance and low consumption linear CCD arrays provide state of the art images. The satellites are designed for simple flight operations, large data collection capability, and large versatility of payload and missions. They are adaptable to a large range of performances. Astrium satellites have already been selected by various customers worldwide.

NASA's advanced space transportation system launch vehicles

NASA Technical Reports Server (NTRS)

Branscome, Darrell R.

1991-01-01

Some insight is provided into the advanced transportation planning and systems that will evolve to support long term mission requirements. The general requirements include: launch and lift capacity to low earth orbit (LEO); space based transfer systems for orbital operations between LEO and geosynchronous equatorial orbit (GEO), the Moon, and Mars; and Transfer vehicle systems for long duration deep space probes. These mission requirements are incorporated in the NASA Civil Needs Data Base. To accomplish these mission goals, adequate lift capacity to LEO must be available: to support science and application missions; to provide for construction of the Space Station Freedom; and to support resupply of personnel and supplies for its operations. Growth in lift capacity must be time phased to support an expanding mission model that includes Freedom Station, the Mission to Planet Earth, and an expanded robotic planetary program. The near term increase in cargo lift capacity associated with development of the Shuttle-C is addressed. The joint DOD/NASA Advanced Launch System studies are focused on a longer term new cargo capability that will significantly reduce costs of placing payloads in space.

EXPRESS Rack Mockup

NASA Technical Reports Server (NTRS)

2002-01-01

The EXPRESS Rack is a standardized payload rack system that transports, stores, and supports experiments aboard the International Space Station (ISS). EXPRESS stands for EXpedite the PRocessing of Experiments to the Space Station, reflecting the fact that this system was developed specifically to maximize the Station's research capabilities. The EXPRESS Rack system supports science payloads in several disciplines, including biology, chemistry, physics, ecology, and medicine. With the EXPRESS Rack, getting experiments to space has never been easier or more affordable. With its standardized hardware interfaces and streamlined approach, the EXPRESS Rack enables quick, simple integration of multiple payloads aboard the ISS. The system is comprised of elements that remain on the ISS, as well as elements that travel back and forth between the ISS and Earth via the Space Shuttle. The Racks stay on orbit continually, while experiments are exchanged in and out of the EXPRESS Racks as needed, remaining on the ISS for three months to several years, depending on the experiment's time requirements. A refrigerator-sized Rack can be divided into segments, as large as half of an entire rack or as small as a bread box. Payloads within EXPRESS Racks can operate independently of each other, allowing for differences in temperature, power levels, and schedules. Experiments contained within EXPRESS Racks may be controlled by the ISS crew or remotely by the Payload Rack Officer at the Payload Operations Center at the Marshall Space Flight Center (MSFC). The EXPRESS Rack system was developed by MSFC and built by the Boeing Co. in Huntsville, Alabama. Eight EXPRESS Racks are being built for use on the ISS.

A Systems Approach to Lower Cost Missions: Following the Rideshare Paradigm

NASA Technical Reports Server (NTRS)

Herrell, L.

2009-01-01

Small-satellite rideshare capabilities and opportunities for low-cost access to space have been evolving over the past 10 years. Small space launch vehicle technology is rapidly being developed and demonstrated, including the Minotaur series and the Space X Falcon, among others, along with the lower cost launch facilities at Alaska's Kodiak Launch Complex, NASA's Wallops Flight Facility, and the Reagan Test Site in the Pacific. Demonstrated capabilities for the launch of multiple payloads have increased (and continue to increase) significantly. This will allow more efficient and cost-effective use of the various launch opportunities, including utilizing the excess capacity of the emerging Evolved Expendable Launch Vehicle (EELV)-based missions. The definition of standardized interfaces and processes, along with various user guides and payload implementation plans, has been developed and continues to be refined. Top-level agency policies for the support of low-cost access to space for small experimental payloads, such as the DoD policy structure on auxiliary payloads, have been defined and provide the basis for the continued refinement and implementation of these evolving technologies. Most importantly, the coordination and cooperative interfaces between the various stakeholders continues to evolve. The degree of this coordination and technical interchange is demonstrated by the wide stakeholder participation at the recent 2008 Small Payload Rideshare Workshop, held at NASA's Wallops Flight Facility. This annual workshop has been the major platform for coordination and technical interchange within the rideshare community and with the various sponsoring agencies. These developments have provided the foundation for a robust low-cost small payload rideshare capability. However, the continued evolution, sustainment, and utilization of these capabilities will require continued stakeholder recognition, support, and nourishing. Ongoing, coordinated effort, partnering, and support between stakeholders is essential to acquire the improved organizational processes and efficiencies required to meet the needs of the growing small payload community for low-cost access to space. Further, a mix of capabilities developed within the space community for Operationally Responsive Space, an international committee investigating space systems cross-compatibility, and an industry-based organization seeking small satellite "standardization" all work toward a new paradigm: sharing or leveraging resources amongst multiple users. The challenge: where are those users, and what is the best way to leverage them? What is leveraged-mass, power, cost-sharing? And how does one sort through these options? What policies may prevent the use of some options? Who are the "other users" that might share or leverage capabilities? This paper presents a systematic look at both the users and the launch options, and suggests a way forward.

Space Situational Awareness of Large Numbers of Payloads From a Single Deployment

NASA Astrophysics Data System (ADS)

Segerman, A.; Byers, J.; Emmert, J.; Nicholas, A.

2014-09-01

The nearly simultaneous deployment of a large number of payloads from a single vehicle presents a new challenge for space object catalog maintenance and space situational awareness (SSA). Following two cubesat deployments last November, it took five weeks to catalog the resulting 64 orbits. The upcoming Kicksat mission will present an even greater SSA challenge, with its deployment of 128 chip-sized picosats. Although all of these deployments are in short-lived orbits, future deployments will inevitably occur at higher altitudes, with a longer term threat of collision with active spacecraft. With such deployments, individual scientific payload operators require rapid precise knowledge of their satellites' locations. Following the first November launch, the cataloguing did not initially associate a payload with each orbit, leaving this to the satellite operators. For short duration missions, the time required to identify an experiment's specific orbit may easily be a large fraction of the spacecraft's lifetime. For a Kicksat-type deployment, present tracking cannot collect enough observations to catalog each small object. The current approach is to treat the chip cloud as a single catalog object. However, the cloud dissipates into multiple subclouds and, ultimately, tiny groups of untrackable chips. One response to this challenge may be to mandate installation of a transponder on each spacecraft. Directional transponder transmission detections could be used as angle observations for orbit cataloguing. Of course, such an approach would only be employable with cooperative spacecraft. In other cases, a probabilistic association approach may be useful, with the goal being to establish the probability of an element being at a given point in space. This would permit more reliable assessment of the probability of collision of active spacecraft with any cloud element. This paper surveys the cataloguing challenges presented by large scale deployments of small spacecraft, examining current methods. Potential new approaches are discussed, including simulations to evaluate their utility. Acknowledgement: This work was supported by the Office of the Assistant Secretary of Defense for R&E, via the Data-to-Decisions program.

The Dynairship. [structural design criteria and feasibility analysis of an airplane - airship

NASA Technical Reports Server (NTRS)

Miller, W. M., Jr.

1975-01-01

A feasibility analysis for the construction and use of a combination airplane-airship named 'Dynairship' is undertaken. Payload capacities, fuel consumption, and the structural design of the craft are discussed and compared to a conventional commercial aircraft (a Boeing 747). Cost estimates of construction and operation of the craft are also discussed. The various uses of the craft are examined (i.e, in police work, materials handling, and ocean surveillance), and aerodynamic configurations and photographs are shown.

Lightsats and their attraction to budget oriented Federal agencies

NASA Technical Reports Server (NTRS)

Bonsall, Charles A.

1988-01-01

The term Lightsats refers to low volume, low mass, low Earth orbit, satellites suitable for launch from Get Away Special canisters, or as secondary payloads on expendable launch vehicles. New or existing technology that offers potential to improve the safety, capacity and efficiency of the National Airspace System is discussed. The discussion is presented from the point of view of an individual within a government agency who wants to see a new technology to enhance the mission of that agency.

KSC-98pc265

NASA Image and Video Library

1998-02-03

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is moved on a barge by two tug boats toward a pier at Port Canaveral, Fla. The tank is scheduled to undergo processing at Kennedy Space Center for flight on STS-91, targeted for launch in late May. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. The tank was sent from the NASA Michoud Assembly Facility in New Orleans

Onboard experiment data support facility. Task 2 report: Definition of onboard processing requirements

NASA Technical Reports Server (NTRS)

1976-01-01

The onboard experiment data support facility (OEDSF) will provide data processing support to various experiment payloads on board the space shuttle. The OEDSF study will define the conceptual design and generate specifications for an OEDSF which will meet the following objectives: (1) provide a cost-effective approach to end-to-end processing requirements, (2) service multiple disciplines (3) satisfy user needs, (4) reduce the amount and improve the quality of data collected, stored and processed, and (5) embody growth capacity.

Mission Report on the Orbiter Camera Payload System (OCPS) Large Format Camera (LFC) and Attitude Reference System (ARS)

NASA Technical Reports Server (NTRS)

Mollberg, Bernard H.; Schardt, Bruton B.

1988-01-01

The Orbiter Camera Payload System (OCPS) is an integrated photographic system which is carried into earth orbit as a payload in the Space Transportation System (STS) Orbiter vehicle's cargo bay. The major component of the OCPS is a Large Format Camera (LFC), a precision wide-angle cartographic instrument that is capable of producing high resolution stereo photography of great geometric fidelity in multiple base-to-height (B/H) ratios. A secondary, supporting system to the LFC is the Attitude Reference System (ARS), which is a dual lens Stellar Camera Array (SCA) and camera support structure. The SCA is a 70-mm film system which is rigidly mounted to the LFC lens support structure and which, through the simultaneous acquisition of two star fields with each earth-viewing LFC frame, makes it possible to determine precisely the pointing of the LFC optical axis with reference to the earth nadir point. Other components complete the current OCPS configuration as a high precision cartographic data acquisition system. The primary design objective for the OCPS was to maximize system performance characteristics while maintaining a high level of reliability compatible with Shuttle launch conditions and the on-orbit environment. The full-up OCPS configuration was launched on a highly successful maiden voyage aboard the STS Orbiter vehicle Challenger on October 5, 1984, as a major payload aboard mission STS 41-G. This report documents the system design, the ground testing, the flight configuration, and an analysis of the results obtained during the Challenger mission STS 41-G.

High-throughput optical inter-board interconnects for next-generation on-board digital transparent processors

NASA Astrophysics Data System (ADS)

Venet, N.; Sotom, M.; Gachon, H.; Foucal, V.; Pez, M.; Heikkinen, V.; Tuominen, T.; Pantoja, S.

2017-11-01

The satellite telecommunication sector is continuously facing new challenges. Operators turn towards increasing capacity payloads with higher number of beams and broader bandwidth, in order to cope with exhausting orbital positions and to lower the cost of in-orbit delivery of bit. Only satellites able to provide high data rate connections to numerous users are expected to achieve affordable communication prices. On the other hand, as the telecom market grows and the range of offered services (HDTV, Video On Demand, Triple Play), operators call for more versatile solutions to quickly grasp new markets and to adapt to these evolutions over the average 15 years of a satellite lifetime. Flexible payloads have found an increasing interest for a number of years. Flexibility is considered as a means for a better commercial exploitation of a satellite fleet and a better allocation of resource in response to traffic evolution and/or changing business plans, with potential advantages such as a wider range of applications, less customization for specific missions, increased production runs of equipment, enhancement of reliability, reduction of equipment cost, reduction of program schedules [1]. Flexibility is expected to be offered in spectrum management and frequency plan, in coverage, or in the repeater power allocation. The industry is taking up the challenge both by improving current telecom satellites and offering new payload technology, more flexible and able to address the new markets. From a system integrator perspective, flexibility is as an opportunity to design more generic payloads, that can be customized during or after fabrication only, thus shortening the design-to-manufacturing cycle, and improving the industry competitiveness.

Status report on the activities of National Balloon Facility at Hyderabad

NASA Astrophysics Data System (ADS)

Shankarnarayan, Sreenivasan; S, Sreenivasan; Shankarnarayan, Sreenivasan; Manchanda, R. K.; Subba Rao Jonnalagadda, Venkata; Buduru, Suneelkumar

National balloon facility at Hyderabad has been mandated to provide launch support for Indian and International scientific balloon experiments and also perform the necessary research and development in the design and fabrication of plastic balloons. In the last 4 years, since our last report, NBF has launched many successful balloon flights for the astronomy payloads and a large number of high altitude GPS Sonde flights at different places in the country. We have also continued our efforts on qualification of raw materials for zero-failure performance of our balloons and major focus on upgrading of various facilities and load-line instrumentation for launching from remote sites. We foresee a surge of balloon based experimental activity for in-situ measurements in atmospheric sciences and concept validation payloads for future space based instruments. A new centre for research in Environmental Sciences and Payload Engineering (ESPE) has also been set up at the National Balloon Facility campus to develop and conduct research in various aspects of Environmental sciences in collaboration with other groups, with a specific goal to identify, development of advanced technologies leading to an improved understanding of the earth system. The Payload Engineering facility is geared to the Design and Fabrication of Micro and Nano Satellites and will act as Inter -University Centre for payload fabrication. In this paper we present an overview of the present and planned activities in scientific ballooning at National Balloon Facility Hyderabad.

Orbital Payload Reductions Resulting from Booster and Trajectory Modifications for Recovery of a Large Rocket Booster

NASA Technical Reports Server (NTRS)

Levin, Alan D.; Hopkins, Edward J.

1961-01-01

An analysis was made to determine the reduction in payload for a 300 nautical mile orbit resulting from the addition of inert weight, representing recovery gear, to the first-stage booster of a three-stage rocket vehicle. The values of added inert weight investigated ranged from 0 to 18 percent of gross weight at lift off. The study also included the effects on the payload in orbit and the distance from the launch site at burnout and at impact caused by variation in the vertical rise time before the programmed tilt. The vertical rise times investigated ranged from 16-7 to 100 percent of booster burning time. For a vertical rise of 16.7 percent of booster burning time it was found that a 50-percent increase in the weight of the empty booster resulted in only a 10-percent reduction of the payload in orbit. For no added booster weight, increasing vertical rise time from 16-7 to 100 percent of booster burning time (so that the spent booster would impact in the launch area) reduced the payload by 37 percent. Increasing the vertical rise time from 16-7 to 50 percent of booster burning time resulted in about a 15-percent reduction in the impact distance, and for vertical rise times greater than 50-percent the impact distance decreased rapidly.

Relative tracking control of constellation satellites considering inter-satellite link

NASA Astrophysics Data System (ADS)

Fakoor, M.; Amozegary, F.; Bakhtiari, M.; Daneshjou, K.

2017-11-01

In this article, two main issues related to the large-scale relative motion of satellites in the constellation are investigated to establish the Inter Satellite Link (ISL) which means the dynamic and control problems. In the section related to dynamic problems, a detailed and effective analytical solution is initially provided for the problem of satellite relative motion considering perturbations. The direct geometric method utilizing spherical coordinates is employed to achieve this solution. The evaluation of simulation shows that the solution obtained from the geometric method calculates the relative motion of the satellite with high accuracy. Thus, the proposed analytical solution will be applicable and effective. In the section related to control problems, the relative tracking control system between two satellites will be designed in order to establish a communication link between the satellites utilizing analytical solution for relative motion of satellites with respect to the reference trajectory. Sliding mode control approach is employed to develop the relative tracking control system for body to body and payload to payload tracking control. Efficiency of sliding mode control approach is compared with PID and LQR controllers. Two types of payload to payload tracking control considering with and without payload degree of freedom are designed and suitable one for practical ISL applications is introduced. Also, Fuzzy controller is utilized to eliminate the control input in the sliding mode controller.

NASA/DOD Control/Structures Interaction Technology, 1986

NASA Technical Reports Server (NTRS)

Wright, Robert L. (Compiler)

1986-01-01

Control/structures interactions, deployment dynamics and system performance of large flexible spacecraft are discussed. Spacecraft active controls, deployable truss structures, deployable antennas, solar power systems for space stations, pointing control systems for space station gimballed payloads, computer-aided design for large space structures, and passive damping for flexible structures are among the topics covered.

Preliminary analysis of long-range aircraft designs for future heavy airlift missions

NASA Technical Reports Server (NTRS)

Nelms, W. P., Jr.; Murphy, R.; Barlow, A.

1976-01-01

A computerized design study of very large cargo aircraft for the future heavy airlift mission was conducted using the Aircraft Synthesis program (ACSYNT). The study was requested by the Air Force under an agreement whereby Ames provides computerized design support to the Air Force Flight Dynamics Laboratory. This effort is part of an overall Air Force program to study advanced technology large aircraft systems. Included in the Air Force large aircraft program are investigations of missions such as heavy airlift, airborne missile launch, battle platform, command and control, and aerial tanker. The Ames studies concentrated on large cargo aircraft of conventional design with payloads from 250,000 to 350,000 lb. Range missions up to 6500 n.mi. and radius missions up to 3600 n.mi. have been considered. Takeoff and landing distances between 7,000 and 10,000 ft are important constraints on the configuration concepts. The results indicate that a configuration employing conventional technology in all disciplinary areas weighs approximately 2 million pounds to accomplish either a 6500-n.mi. range mission or a 3600-n.mi. radius mission with a 350,000-lb payload.

Combined in-situ and ground-based observations of quasi-periodic radar echoes

NASA Astrophysics Data System (ADS)

Pfaff, R.; Kudeki, E.; Larsen, M.; Clemmons, J.; Earle, G.

A series of combined rocket/radar investigation of the electrodynamics and neutralplasma coupling associated with sporadic-E layers and quasi-periodic backscatter radar echoes has been carried out from launch sites at both Puerto Rico and the Wallops Flight Facility, Virginia (USA) between 1998-2001. The instrumented rockets consisted of main and sub-payloads and were launched while strong quasiperiodic VHF echoes were observed simultaneously with the Univ. of Illinois 50 MHz backscatter radar. The rocket apogee was purposely limited so that the payloads would dwell in the sporadic-E region (90-115 km). The main payload included vector DC and AC electric field detectors, a DC magnetometer, an ion mass spectrometer, an ionization gauge, and spaced-electric field receivers to measure the wavelength and phase velocity of the unstable plasma waves. The sub-payload was instrumented to measure DC and wave electric fields and plasma density. In one case, a separate rocket was launched a few minutes later which released luminous TMA trails to measure the neutral wind, its velocity shear, and embedded neutral structures. In this experiment, the payloads successfully pierced a well-defined, 2-3 km thick metallic sporadic-E layer of approximately 10**5 e/cc near 103 km altitude. In-situ DC electric field measurements revealed ~5mV/m ambient meridional fields above and below the layer with 1-2 mV/m amplitude, large scale structures superimposed. The wavelengths of these structures were approximately 2-4 km and may be related to the seat of the quasiperiodic echoes. Intense (~5 mV/m), higher frequency (shorter scale) broadband waves were also observed in-situ, both above and below the layer, consistent with the VHF backscatter observations during the time of the launch. Neither the large scale nor short scale plasma waves appeared to be distinctly organized by the sporadic-E density layer. The TMA release showed large amplitude (~ 100 m/s) meridional winds near 102-105 km, with the most intense shears directly below these altitudes, where the short scale electric field fluctuations were most intense. We summarize the observations from the different experiments and discuss them in the context of current theories regarding quasi-periodic echoes.

Combined In-situ and Ground-based Observations of Quasi-periodic Radar Echoes

NASA Astrophysics Data System (ADS)

Pfaff, R.; Kudeki, E.; Larsen, M.; Clemmons, J.; Earle, G.

A series of combined rocket/radar investigation of the electrodynamics and neutral- plasma coupling associated with sporadic-E layers and quasi-periodic backscatter radar echoes has been carried out from launch sites at both Puerto Rico and the Wallops Flight Facility, Virginia (USA) between 1998-2001. The instrumented rock- ets consisted of main and sub-payloads and were launched while strong quasi- periodic VHF echoes were observed simultaneously with the Univ. of Illinois 50 MHz backscatter radar. The rocket apogee was purposely limited so that the payloads would dwell in the sporadic-E region (90-115 km). The main payload included vector DC and AC electric field detectors, a DC magnetometer, an ion mass spectrometer, an ioniza- tion gauge, and spaced-electric field receivers to measure the wavelength and phase velocity of the unstable plasma waves. The sub-payload was instrumented to measure DC and wave electric fields and plasma density. In one case, a separate rocket was launched a few minutes later which released luminous TMA trails to measure the neu- tral wind, its velocity shear, and embedded neutral structures. In this experiment, the payloads successfully pierced a well-defined, 2-3 km thick metallic sporadic-E layer of approximately 10**5 e/cc near 103 km altitude. In-situ DC electric field measure- ments revealed ~5mV/m ambient meridional fields above and below the layer with 1-2 mV/m amplitude, large scale structures superimposed. The wavelengths of these structures were approximately 2-4 km and may be related to the seat of the quasi- periodic echoes. Intense (~5 mV/m), higher frequency (shorter scale) broadband waves were also observed in-situ, both above and below the layer, consistent with the VHF backscatter observations during the time of the launch. Neither the large scale nor short scale plasma waves appeared to be distinctly organized by the sporadic-E den- sity layer. The TMA release showed large amplitude (~ 100 m/s) meridional winds near 102-105 km, with the most intense shears directly below these altitudes, where the short scale electric field fluctuations were most intense. We summarize the ob- servations from the different experiments and discuss them in the context of current theories regarding quasi-periodic echoes.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

This STS-98 Shuttle mission image shows an overall interior view of the newly attached U.S. Laboratory, Destiny. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the International Space Station (ISS), where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

International Space Station (ISS)

NASA Image and Video Library

2001-02-11

This STS-98 mission photograph shows astronauts Thomas D. Jones (foreground) and Kerneth D. Cockrell floating inside the newly installed Laboratory aboard the International Space Station (ISS). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

Peptide-Drug Conjugate: A Novel Drug Design Approach.

PubMed

Ma, Liang; Wang, Chao; He, Zihao; Cheng, Biao; Zheng, Ling; Huang, Kun

2017-01-01

More than 100 years ago, German physician Paul Ehrlich first proposed the concept of selectively delivering "magic bullets" to tumors through targeting agents. The targeting therapy with antibody-drug conjugates (ADCs) and peptide-drug conjugate (PDCs), which are usually composed of monoclonal antibodies or peptides, toxic payloads and cleavage/ noncleavage linkers, has been extensively studied for decades. The conjugates enable selective delivery of cytotoxic payloads to target cells, which results in improved efficacy, reduced systemic toxicity and improved pharmacokinetics (PK)/pharmacodynamics (PD) compared with traditional chemotherapy. PDC and ADC share similar concept, but with vastly different structures and properties. Humanized antibodies introduce high specificity and prolonged half-life, while small molecule weight peptides exhibit higher drug loading and enhanced tissue penetration capacity, and the flexible linear or cyclic peptides are also modified more easily. In this review, the principles of design, synthesis approaches and the latest advances of PDCs are summarized. Copyright© Bentham Science Publishers; For any queries, please email at epub@benthamscience.org.

KSC-2009-1212

NASA Image and Video Library

2009-01-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a ballast assembly is moved above the Ares I-X segment 7. Ballast assemblies will be installed in the upper stage 1 and 7 segments and will mimic the mass of the fuel. Their total weight is approximately 160,000 pounds. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ares I is the essential core of a safe, reliable, cost-effective space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system. Ares I may also use its 25-ton payload capacity to deliver resources and supplies to the International Space Station, or to "park" payloads in orbit for retrieval by other spacecraft bound for the moon or other destinations. The Ares I-X is targeted for launch in July 2009. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-1214

NASA Image and Video Library

2009-01-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a ballast assembly is lowered into the Ares I-X segment 7. Ballast assemblies are being installed in the upper stage 1 and 7 segments and will mimic the mass of the fuel. Their total weight is approximately 160,000 pounds. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ares I is the essential core of a safe, reliable, cost-effective space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system. Ares I may also use its 25-ton payload capacity to deliver resources and supplies to the International Space Station, or to "park" payloads in orbit for retrieval by other spacecraft bound for the moon or other destinations. The Ares I-X is targeted for launch in July 2009. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-1211

NASA Image and Video Library

2009-01-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a ballast assembly is lifted toward the Ares I-X segments for installation. These ballast assemblies will be installed in the upper stage 1 and 7 segments and will mimic the mass of the fuel. Their total weight is approximately 160,000 pounds. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ares I is the essential core of a safe, reliable, cost-effective space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system. Ares I may also use its 25-ton payload capacity to deliver resources and supplies to the International Space Station, or to "park" payloads in orbit for retrieval by other spacecraft bound for the moon or other destinations. The Ares I-X is targeted for launch in July 2009. Photo credit: NASA/Dimitri Gerondidakis

KSC-2009-1213

NASA Image and Video Library

2009-01-16

CAPE CANAVERAL, Fla. – In high bay 4 of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a ballast assembly is lowered into the Ares I-X segment 7. Ballast assemblies are being installed in the upper stage 1 and 7 segments and will mimic the mass of the fuel. Their total weight is approximately 160,000 pounds. Ares I-X is the test vehicle for the Ares I, which is part of the Constellation Program to return men to the moon and beyond. Ares I is the essential core of a safe, reliable, cost-effective space transportation system that eventually will carry crewed missions back to the moon, on to Mars and out into the solar system. Ares I may also use its 25-ton payload capacity to deliver resources and supplies to the International Space Station, or to "park" payloads in orbit for retrieval by other spacecraft bound for the moon or other destinations. The Ares I-X is targeted for launch in July 2009. Photo credit: NASA/Dimitri Gerondidakis

Developing a Ruggedized User-Friendly UAS for Monitoring Volcanic Emissions

NASA Astrophysics Data System (ADS)

Wardell, L. J.; Elston, J. S.; Stachura, M.

2017-12-01

Using lessons learned from a history of airborne volcano measurements and a range of UAS R&D, a reliable and ruggedized UAS is being developed specifically for volcano monitoring and response. A key feature is the user interface (UI) that allows for a menu of automated flight plans that will account for terrain and sensor requirements. Due to variation in response times of miniaturized airborne the sensors, flight plan options are extended to account for sensor lag when needed. By automating such complicating variables into the UI, the amount of background and training needed for operation is further minimized. Payload options include simultaneous in situ gas and particle sensors combined with downward-looking imagers to provide a wide range of data products. Currently under development by Black Swift Technologies, the latest updates and test results will be presented. Specifications of the Superswift airframe include a 6,000 m flight ceiling, 2.4 kg payload capacity, and 2 hr endurance.

The protective capacity of high payload FMDV A22 IRQ vaccine in sheep against direct-contact challenge with a heterologous, contemporary FMDV A strain from South East Asia.

PubMed

Horsington, Jacquelyn; Nfon, Charles; Bittner, Hilary; Durr, Peter A; Singanallur, Nagendrakumar; Alexandersen, Soren; Vosloo, Wilna

2018-01-01

Foot-and-mouth disease (FMD) is an acute, highly contagious viral disease of domestic and wild cloven-hoofed animals, caused by FMD virus (FMDV). An FMD outbreak can cause major production losses and have significant implications for trade. Vaccination can assist in controlling the disease, and emergency vaccination using high antigen payload vaccines (>6 PD50/dose) is considered an important control approach in the event of an outbreak. In recent years there has been a divergence of serotype A viruses in South East Asia (SEA) into several distinct genetic and antigenic clusters. Numerous variants were found to poorly match serotype A vaccines commonly included in international antigen banks. This study examined the ability of single vaccination with high-potency monovalent A22 IRQ vaccine to protect sheep following challenge with the A/VIT/15/2012 strain, just four days following vaccination. The vaccine proved effective at limiting clinical disease but did not prevent infection.

Science and Applications Space Platform (SASP) End-to-End Data System Study

NASA Technical Reports Server (NTRS)

Crawford, P. R.; Kasulka, L. H.

1981-01-01

The capability of present technology and the Tracking and Data Relay Satellite System (TDRSS) to accommodate Science and Applications Space Platforms (SASP) payload user's requirements, maximum service to the user through optimization of the SASP Onboard Command and Data Management System, and the ability and availability of new technology to accommodate the evolution of SASP payloads were assessed. Key technology items identified to accommodate payloads on a SASP were onboard storage devices, multiplexers, and onboard data processors. The primary driver is the limited access to TDRSS for single access channels due to sharing with all the low Earth orbit spacecraft plus shuttle. Advantages of onboard data processing include long term storage of processed data until TRDSS is accessible, thus reducing the loss of data, eliminating large data processing tasks at the ground stations, and providing a more timely access to the data.

Tether Transportation System Study

NASA Technical Reports Server (NTRS)

Bangham, M. E.; Lorenzini, E.; Vestal, L.

1998-01-01

The projected traffic to geostationary earth orbit (GEO) is expected to increase over the next few decades. At the same time, the cost of delivering payloads from the Earth's surface to low earth orbit (LEO) is projected to decrease, thanks in part to the Reusable Launch Vehicle (RLV). A comparable reduction in the cost of delivering payloads from LEO to GEO is sought. The use of in-space tethers, eliminating the requirement for traditional chemical upper stages and thereby reducing the launch mass, has been identified as such an alternative. Spinning tethers are excellent kinetic energy storage devices for providing the large delta vee's required for LEO to GEO transfer. A single-stage system for transferring payloads from LEO to GEO was proposed some years ago. The study results presented here contain the first detailed analyses of this proposal, its extension to a two-stage system, and the likely implementation of the operational system.

Technology Overview and Assessment for Small-Scale EDL Systems

NASA Technical Reports Server (NTRS)

Heidrich, Casey R.; Smith, Brandon P.; Braun, Robert D.

2016-01-01

Motivated by missions to land large rovers and humans at Mars and other bodies, high-mass EDL technologies are a prevalent trend in the research community. In contrast, EDL systems for low-mass payloads have attracted less attention. Significant potential in science and discovery exists in small-scale EDL systems. Payloads acting secondary to a flagship mission are a currently under-utilzed resource. Before taking advantage of these opportunities, further developed of scaled EDL technologies is required. The key limitations identified in this study are compact decelerators and deformable impact systems. Current technologies may enable rough landing of small payloads, with moderate restrictions in packaging volume. Utilization of passive descent and landing stages will greatly increase the applicability of small systems, allowing for vehicles robust to entry environment uncertainties. These architectures will provide an efficient means of achieving science and support objectives while reducing cost and risk margins of a parent mission.

KSC-08pd2333

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane moves the Cosmic Origins Spectrograph, or COS, toward a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2336

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Cosmic Origins Spectrograph, or COS, toward a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2332

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane moves the Cosmic Origins Spectrograph, or COS, toward a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2334

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Cosmic Origins Spectrograph, or COS, toward a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2335

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Cosmic Origins Spectrograph, or COS, toward a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2338

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Cosmic Origins Spectrograph, or COS, into a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2337

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Cosmic Origins Spectrograph, or COS, into a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2339

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane settles the Cosmic Origins Spectrograph, or COS, in a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

A white paper: Operational efficiency. New approaches to future propulsion systems

NASA Technical Reports Server (NTRS)

Rhodes, Russel; Wong, George

1991-01-01

Advanced launch systems for the next generation of space transportation systems (1995 to 2010) must deliver large payloads (125,000 to 500,000 lbs) to low earth orbit (LEO) at one tenth of today's cost, or 300 to 400 $/lb of payload. This cost represents an order of magnitude reduction from the Titan unmanned vehicle cost of delivering payload to orbit. To achieve this sizable reduction, the operations cost as well as the engine cost must both be lower than current engine system. The Advanced Launch System (ALS) is studying advanced engine designs, such as the Space Transportation Main Engine (STME), which has achieved notable reduction in cost. The results are presented of a current study wherein another level of cost reduction can be achieved by designing the propulsion module utilizing these advanced engines for enhanced operations efficiency and reduced operations cost.

A New Large Vibration Test Facility Concept for the James Webb Space Telescope

NASA Technical Reports Server (NTRS)

Ross, Brian P.; Johnson, Eric L.; Hoksbergen, Joel; Lund, Doug

2014-01-01

The James Webb Space Telescope consists of three main components, the Integrated Science Instrument Module (ISIM) Element, the Optical Telescope Element (OTE), and the Spacecraft Element. The ISIM and OTE are being assembled at the National Aeronautics and Space Administration's Goddard Spaceflight Center (GSFC). The combined OTE and ISIM Elements, called OTIS, will undergo sine vibration testing before leaving Goddard. OTIS is the largest payload ever tested at Goddard and the existing GSFC vibration facilities are incapable of performing a sine vibration test of the OTIS payload. As a result, a new large vibration test facility is being designed. The new facility will consist of a vertical system with a guided head expander and a horizontal system with a hydrostatic slip table. The project is currently in the final design phase with installation to begin in early 2015 and the facility is expected to be operational by late 2015. This paper will describe the unique requirements for a new large vibration test facility and present the selected final design concepts.

Going mobile

NASA Astrophysics Data System (ADS)

Brus, Eric

1987-12-01

By 1990, all metropolitan areas in the U.S. and rural areas close to major cities or towns are expected to have cellular telephone service; 22 Canadian cities also feature cellular service. To supply mobile telecommunication services to sparsely-populated rural areas, a mobile satellite service (MSS) is now being developed. In this paper the projected possibilities of the MSS system are discussed, including a possibility that a piggyback-MSS payload be added to the GSTAR-4 satellite which is scheduled for a launch in 1988 or 1989; one in which some of the hardware from aborted direct-broadcast satellites would be used; and the possibility of building a new MSS satellite with large servicing capacity. Canada is planning to launch its own mobile satellite, MSAT, in the early 1990s. The MSS is expected to be 'generic', serving not only people on land but maritime and aeronautical users as well. It will also offer major benefits to truck and automobile drivers, making it possible for them to conduct business or to call for assistance from locations beyond the range of cellular systems.

The next generation balloon-borne large aperture submillimeter telescope (BLAST-TNG)

NASA Astrophysics Data System (ADS)

Dober, Bradley Jerald

Large areas of astrophysics, such as precision cosmology, have benefited greatly from large maps and datasets, yielded by telescopes of ever-increasing number and ability. However, due to the unique challenges posed by submillimeter polarimetry, the study of molecular cloud dynamics and star formation remain stunted. Previously, polarimetry data was limited to a few vectors on only the brightest areas of molecular clouds. This made drawing statistically-driven conclusions a daunting task. However, the successful flight of the Balloon-born Large Aperture Submillimeter Telescope for Polarimetry (BLASTPol) generated maps with thousands of independent polarization measurements of molecular clouds, and ushered in a new era of empirical modeling of molecular cloud dynamics. Now that the potential benefits from large-scale maps of magnetic fields in molecular clouds had been identified, a successor that would truly unlock the secrets must be born. The Next Generation Balloon-borne Large Aperture Submillimeter Telescope (BLAST-TNG), the successor to BLASTPol, has the ability to make larger and more detailed maps of magnetic fields in molecular clouds. It will push the field of star formation into a statistics-driven, empirical realm. With these large, detailed datasets, astronomers will be able to find new relationships between the dust dynamics and the magnetic fields. The field will surge to a new level of understanding. One of the key enabling technologies of BLAST-TNG is its three arrays of polarization-sensitive Microwave Kinetic Inductance Detectors (MKIDs). MKIDs are superconducting RLC circuits with a resonant frequency that shifts proportionally to the amount of incident radiation. The key feature of MKIDs is that thousands of detectors, each with their own unique resonant frequency, can be coupled to the same readout line. This technology will be able to drive the production of large-scale monolithic arrays, containing tens or hundreds of thousands of detectors, resulting in an ever-increasing rate of scientific progress. The current limiting factor that determines how many MKIDs can be placed on the same readout line is the bandwidth and processing limitations of the readout hardware. BLAST-TNG has pushed this technology forward by implementing the first Reconfigurable Open-Architecture Computing Hardware (ROACH2) based readout system. This has significantly raised the processing abilities of the MKID readout electronics, enabling over 1000 MKIDs to be read out on a single line. It is also the first ever ROACH (1 or 2) based system to ever be flown on a long duration balloon (LDB) payload. This thesis documents the first-ever deployment of MKIDs on a balloon payload. This is a significant technological step towards an MKID-based satellite payload. This thesis overviews the balloon payload, details the underlying detector physics, catalogs the detector and full-scale array development, and ends with the room-temperature readout electronics.

Entry, Descent and Landing Systems Analysis: Exploration Class Simulation Overview and Results

NASA Technical Reports Server (NTRS)

DwyerCianciolo, Alicia M.; Davis, Jody L.; Shidner, Jeremy D.; Powell, Richard W.

2010-01-01

NASA senior management commissioned the Entry, Descent and Landing Systems Analysis (EDL-SA) Study in 2008 to identify and roadmap the Entry, Descent and Landing (EDL) technology investments that the agency needed to make in order to successfully land large payloads at Mars for both robotic and exploration or human-scale missions. The year one exploration class mission activity considered technologies capable of delivering a 40-mt payload. This paper provides an overview of the exploration class mission study, including technologies considered, models developed and initial simulation results from the EDL-SA year one effort.

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

NASA Technical Reports Server (NTRS)

1972-01-01

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

STS-47 PS Mohri uses Spacelab Japan microscope to study cells aboard OV-105

NASA Image and Video Library

1992-09-20

STS047-05-025 (12 - 20 Sept 1992) --- Payload specialist Mamoru Mohri, representing Japan's National Space Development Agency (NASDA), uses a microscope to produce photomicrographs of mammalian cells. The mammal cell structure experiment is one of a large number of tests that were performed during the eight-day Spacelab-J mission. On his back, Dr. Mohri totes a health monitoring experiment. The primary objective of the physiological monitoring system is to observe the health condition of the Japanese payload specialist so that good health can be maintained during and after the spaceflight.

ESA's CCD test bench for the PLATO mission

NASA Astrophysics Data System (ADS)

Beaufort, Thierry; Duvet, Ludovic; Bloemmaert, Sander; Lemmel, Frederic; Prod'homme, Thibaut; Verhoeve, Peter; Smit, Hans; Butler, Bart; van der Luijt, Cornelis; Heijnen, Jerko; Visser, Ivo

2016-08-01

PLATO { PLAnetary Transits and Oscillations of stars { is the third medium-class mission to be selected in the European Space Agency (ESA) Science and Robotic Exploration Cosmic Vision programme. Due for launch in 2025, the payload makes use of a large format (8 cm x 8 cm) Charge-Coupled Devices (CCDs), the e2v CCD270 operated at 4 MHz and at -70 C. To de-risk the PLATO CCD qualification programme initiated in 2014 and support the mission definition process, ESA's Payload Technology Validation section from the Future Missions Office has developed a dedicated test bench.

Application of superconducting technology to earth-to-orbit electromagnetic launch systems

NASA Technical Reports Server (NTRS)

Hull, J. R.; Carney, L. M.

1988-01-01

Benefits may occur by incorporating superconductors, both existing and those currently under development, in one or more parts of a large-scale electromagnetic launch (EML) system that is capable of delivering payloads from the surface of the Earth to space. The use of superconductors for many of the EML components results in lower system losses; consequently, reductions in the size and number of energy storage devices are possible. Applied high-temperature superconductivity may eventually enable novel design concepts for energy distribution and switching. All of these technical improvements have the potential to reduce system complexity and lower payload launch costs.

A Water Vapor Differential Absorption LIDAR Design for Unpiloted Aerial Vehicles

NASA Technical Reports Server (NTRS)

DeYoung, Russell J.; Mead, Patricia F.

2004-01-01

This system study proposes the deployment of a water vapor Differential Absorption LIDAR (DIAL) system on an Altair unmanned aerial vehicle (UAV) platform. The Altair offers improved payload weight and volume performance, and longer total flight time as compared to other commercial UAV's. This study has generated a preliminary design for an Altair based water vapor DIAL system. The design includes a proposed DIAL schematic, a review of mechanical challenges such as temperature and humidity stresses on UAV deployed DIAL systems, an assessment of the available capacity for additional instrumentation (based on the proposed design), and an overview of possible weight and volume improvements associated with the use of customized electronic and computer hardware, and through the integration of advanced fiber-optic and laser products. The results of the study show that less than 17% of the available weight, less than 19% of the volume capacity, and approximately 11% of the electrical capacity is utilized by the proposed water vapor DIAL system on the Altair UAV.

Automated Derivation of Complex System Constraints from User Requirements

NASA Technical Reports Server (NTRS)

Foshee, Mark; Murey, Kim; Marsh, Angela

2010-01-01

The Payload Operations Integration Center (POIC) located at the Marshall Space Flight Center has the responsibility of integrating US payload science requirements for the International Space Station (ISS). All payload operations must request ISS system resources so that the resource usage will be included in the ISS on-board execution timelines. The scheduling of resources and building of the timeline is performed using the Consolidated Planning System (CPS). The ISS resources are quite complex due to the large number of components that must be accounted for. The planners at the POIC simplify the process for Payload Developers (PD) by providing the PDs with a application that has the basic functionality PDs need as well as list of simplified resources in the User Requirements Collection (URC) application. The planners maintained a mapping of the URC resources to the CPS resources. The process of manually converting PD's science requirements from a simplified representation to a more complex CPS representation is a time-consuming and tedious process. The goal is to provide a software solution to allow the planners to build a mapping of the complex CPS constraints to the basic URC constraints and automatically convert the PD's requirements into systems requirements during export to CPS.

An Innovative Short Arm Centrifuge for Future Studies on the Effects of Artificial Gravity on the Human Body

NASA Astrophysics Data System (ADS)

Frett, Timo; Mayrhofer, Michael; Schwandtner, Johann; Anken, Ralf; Petrat, Guido

2014-11-01

In July 2013, the German Aerospace Center (DLR) in Cologne, Germany, commissioned its new medical research facility :envihab. One central element of the facility is a new type of short radius centrifuge called DLR-SAHC 1 (formerly known as :enviFuge), which has been developed in collaboration with AMST Systemtechnik GmbH, Ranshofen, Austria. The shift of subjects above heart-level on a short arm centrifuge allows unique studies on, e.g., the cardiovascular regulation in surroundings with a high gradient of artificial gravity. Equipped with the capacity to move the four nacelles along the acceleration axis simultaneously and independently from each other, the centrifuge allows the possibility to perform up to four complex trials in parallel. The maximal acceleration is 6 g at the foot level and each nacelle can accomodate an up to 150kg payload. Additional equipment can be mounted on two payload bays with a capacity of 100kg each. Standard features of the centrifuge include a motion capturing system with six cameras and two triaxial force plates to study the kinematics of physical exercise (e.g., squatting, jumping or vibration training) under increased gravity. Future projects involving SAHC 1 will allow the development and testing of potential countermeasures and training methods against the negative effects of weightlessness in space on human physiology. Due to the centrifuge's capability to hold heavy equipment, carrying out a variety of non-human life science experiments requiring complex and heavy hardware is also fully feasible.

Trans Atlantic Infrasound Payload (TAIP) Operation Plan.

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

Bowman, Daniel; Lees, Jonathan M.

The Carolina Infrasound package, added as a piggyback to the 2016 ULDB ight, recorded unique acoustic signals such as the ocean microbarom and a large meteor. These data both yielded unique insights into the acoustic energy transfer from the lower to the upper atmosphere as well as highlighted the vast array of signals whose origins remain unknown. Now, the opportunity to y a payload across the north Atlantic offers an opportunity to sample one of the most active ocean microbarom sources on Earth. Improvements in payload capabilities should result in characterization of the higher frequency range of the stratospheric infrasoundmore » spectrum as well. Finally, numerous large mining and munitions disposal explosions in the region may provide \\ground truth" events for assessing the detection capability of infrasound microphones in the stratosphere. The flight will include three different types of infrasound sensors. One type is a pair of polarity reversed InfraBSU microphones (standard for high altitude flights since 2016), another is a highly sensitive Chaparral 60 modified for a very low corner period, and the final sensor is a lightweight, low power Gem infrasound package. By evaluating these configurations against each other on the same flight, we will be able to optimize future campaigns with different sensitivity and mass constraints.« less

Planning and Scheduling of Payloads of AstroSat During Initial and Normal Phase Observations

NASA Astrophysics Data System (ADS)

Pandiyan, R.; Subbarao, S. V.; Nagamani, T.; Rao, Chaitra; Rao, N. Hari Prasad; Joglekar, Harish; Kumar, Naresh; Dumpa, Surya Ratna Prakash; Chauhan, Anshu; Dakshayani, B. P.

2017-06-01

On 28th September 2015, India launched its first astronomical space observatory AstroSat, successfully. AstroSat carried five astronomy payloads, namely, (i) Cadmium Zinc Telluride Imager (CZTI), (ii) Large Area X-ray Proportional Counter (LAXPC), (iii) Soft X-ray Telescope (SXT), (iv) Ultra Violet Imaging Telescope (UVIT) and (v) Scanning Sky Monitor (SSM) and therefore, has the capability to observe celestial objects in multi-wavelength. Four of the payloads are co-aligned along the positive roll axis of the spacecraft and the remaining one is placed along the positive yaw axis direction. All the payloads are sensitive to bright objects and specifically, require avoiding bright Sun within a safe zone of their bore axes in orbit. Further, there are other operational constraints both from spacecraft side and payloads side which are to be strictly enforced during operations. Even on-orbit spacecraft manoeuvres are constrained to about two of the axes in order to avoid bright Sun within this safe zone and a special constrained manoeuvre is exercised during manoeuvres. The planning and scheduling of the payloads during the Performance Verification (PV) phase was carried out in semi-autonomous/manual mode and a complete automation is exercised for normal phase/Guaranteed Time Observation (GuTO) operations. The process is found to be labour intensive and several operational software tools, encompassing spacecraft sub-systems, on-orbit, domain and environmental constraints, were built-in and interacted with the scheduling tool for appropriate decision-making and science scheduling. The procedural details of the complex scheduling of a multi-wavelength astronomy space observatory and their working in PV phase and in normal/GuTO phases are presented in this paper.

Orbital Propagation of Momentum Exchange Tether Systems

NASA Technical Reports Server (NTRS)

Westerhoff, John

2002-01-01

An advanced concept in in-space transportation currently being studied is the Momentum-Exchange/Electrodynamic Reboost Tether System (MXER). The system acts as a large momentum wheel, imparting a Av to a payload in low earth orbit (LEO) at the expense of its own orbital energy. After throwing a payload, the system reboosts itself using an electrodynamic tether to push against Earth's magnetic field and brings itself back up to an operational orbit to prepare for the next payload. The ability to reboost itself allows for continued reuse of the system without the expenditure of propellants. Considering the cost of lifting propellant from the ,ground to LEO to do the same Av boost at $10000 per pound, the system cuts the launch cost of the payload dramatically, and subsequently, the MXER system pays for itself after a small number of missions.1 One of the technical hurdles to be overcome with the MXER concept is the rendezvous maneuver. The rendezvous window for the capture of the payload is on the order of a few seconds, as opposed to traditional docking maneuvers, which can take as long ets necessary to complete a precise docking. The payload, therefore, must be able to match its orbit to meet up with the capture device on the end of the tether at a specific time and location in the future. In order to be able to determine that location, the MXER system must be numerically propagated forward in time to predict where the capture device will be at that instant. It should be kept in mind that the propagation computation must be done faster than real-time. This study focuses on the efforts to find and/or build the tools necessary to numerically propagate the motion of the MXER system as accurately as possible.

Thermal Design, Test and Analysis of PharmaSat, a Small Class D Spacecraft with a Biological Experiment

NASA Technical Reports Server (NTRS)

Diaz-Aguado, Millan F.; VanOutryve, Cassandra; Ghassemiah, Shakib; Beasley, Christopher; Schooley, Aaron

2009-01-01

Small spacecraft have been increasing in popularity because of their low cost, short turnaround and relative efficiency. In the past, small spacecraft have been primarily used for technology demonstrations, but advances in technology have made the miniaturization of space science possible [1,2]. PharmaSat is a low cost, small three cube size spacecraft, with a biological experiment on board, built at NASA (National Aeronautics and Space Administration) Ames Research Center. The thermal design of small spacecraft presents challenges as their smaller surface areas translate into power and thermal constraints. The spacecraft is thermally designed to run colder in the Low Earth Orbit space environment, and heated to reach the temperatures required by the science payload. The limited power supply obtained from the solar panels on small surfaces creates a constraint in the power used to heat the payload to required temperatures. The pressurized payload is isolated with low thermally conductance paths from the large ambient temperature changes. The thermal design consists of different optical properties of section surfaces, Multi Layer Insulation (MLI), low thermal conductance materials, flexible heaters and thermal spreaders. The payload temperature is controlled with temperature sensors and flexible heaters. Finite Element Analysis (FEA) and testing were used to aid the thermal design of the spacecraft. Various tests were conducted to verify the thermal design. An infrared imager was used on the electronic boards to find large heat sources and eliminate any possible temperature runaways. The spacecraft was tested in a thermal vacuum chamber to optimize the thermal and power analysis and qualify the thermal design of the spacecraft for the mission.

Evaluation philosophy for shuttle launched payloads

NASA Technical Reports Server (NTRS)

Heuser, R. E.

1975-01-01

Potential benefits of factory-to-pad testing constitute major cost savings and increase test effectiveness. Overall flight performance will be improved. The factory-to-pad approach is compatible with space shuttle processing and the large space telescope program.

Development of deployable structures for large space platform systems, part 1

NASA Technical Reports Server (NTRS)

Cox, R. L.; Nelson, R. A.

1982-01-01

Eight deployable platform design objectives were established: autodeploy/retract; fully integrated utilities; configuration variability; versatile payload and subsystem interfaces; structural and packing efficiency; 1986 technology readiness; minimum EVA/RMS; and Shuttle operational compatibility.

ESA study of XEUS, a potential follow-on to XMM-Newton

NASA Astrophysics Data System (ADS)

Rando, N.; Lyngvi, A.; Gondoin, P.; Lumb, D.; Bavdaz, M.; Verhoeve, P.; de Wilde, D.; Parmar, A.; Peacock, A.

2017-11-01

In October 2005, based on a massive response by the Science Community to ESA's call for themes in space science, a large aperture X-ray Observatory (XRO) was identified as a candidate project for Europe within the frame of the 2015-2025 Cosmic Vision program. Such a mission would represent the natural follow-on to XMM Newton, providing a large aperture X-ray telescope combined with high spectral and time resolution instruments, capable of investigating matter under extreme conditions and the evolution of the early universe. The paper summarises the results of the most recent ESA internal study activities, leading to an updated mission configuration, with a mirror and a detector spacecraft flying in formation around L2 and a consolidated scientific payload design. The paper also describes the ongoing technology development activities for the payload and for the spacecraft that will play a crucial role in case ESA would decide to develop such a mission.

A 16-m Telescope for the Advanced Technology Large Aperture Telescope (ATLAST) Mission

NASA Astrophysics Data System (ADS)

Lillie, Charles F.; Dailey, D. R.; Polidan, R. S.

2010-01-01

Future space observatories will require increasingly large telescopes to study the earliest stars and galaxies, as well as faint nearby objects. Technologies now under development will enable telescopes much larger than the 6.5-meter diameter James Webb Space Telescope (JWST) to be developed at comparable costs. Current segmented mirror and deployable optics technology enables the 6.5 meter JWST telescope to be folded for launch in the 5-meter diameter Ariane 5 payload fairing, and deployed autonomously after reaching orbit. Late in the next decade, when the Ares V Cargo Launch Vehicle payload fairing becomes operational, even larger telescope can be placed in orbit. In this paper we present our concept for a 16-meter JWST derivative, chord-fold telescope which could be stowed in the 10-m diameter Ares V fairing, plus a description of the new technologies that enable ATLAST to be developed at an affordable price.

On-Board Software Reference Architecture for Payloads

NASA Astrophysics Data System (ADS)

Bos, Victor; Rugina, Ana; Trcka, Adam

2016-08-01

The goal of the On-board Software Reference Architecture for Payloads (OSRA-P) is to identify an architecture for payload software to harmonize the payload domain, to enable more reuse of common/generic payload software across different payloads and missions and to ease the integration of the payloads with the platform.To investigate the payload domain, recent and current payload instruments of European space missions have been analyzed. This led to a Payload Catalogue describing 12 payload instruments as well as a Capability Matrix listing specific characteristics of each payload. In addition, a functional decomposition of payload software was prepared which contains functionalities typically found in payload systems. The definition of OSRA-P was evaluated by case studies and a dedicated OSRA-P workshop to gather feedback from the payload community.

Thermal management of instruments on space platforms using a high capacity two-phase heat transport system

NASA Technical Reports Server (NTRS)

Ollendorf, S.; Fowle, A.; Almgren, D.

1981-01-01

A system utilizing a pumped, two-phase single component working fluid for heat exchange and transport services necessary to meet the temperature control requirements of typical orbiting instrument payloads on space platforms is described. The design characteristics of the system is presented, together with a presentation of a laboratory apparatus for demonstration of proof of concept. Results indicate that the pumped two-phase design concept can meet a wide range of thermal performance requirements with the only penalty being the requirement for a small liquid pump.

Enhanced EOS photovoltaic power system capability with InP solar cells

NASA Technical Reports Server (NTRS)

Bailey, Sheila G.; Weinberg, Irving; Flood, Dennis J.

1991-01-01

The Earth Observing System (EOS), which is part of the International Mission to Planet Earth, is NASA's main contribution to the Global Change Research Program which opens a new era in international cooperation to study the Earth's environment. Five large platforms are to be launched into polar orbit, two by NASA, two by ESA, and one by the Japanese. In such an orbit the radiation resistance of indium phosphide solar cells combined with the potential of utilizing five micron cell structures yields an increase of 10 percent in the payload capability. If further combined with the advanced photovoltaic solar array the payload savings approaches 12 percent.

STS-52 Mission Insignia

NASA Technical Reports Server (NTRS)

1992-01-01

The STS-52 insignia, designed by the mission's crew members, features a large gold star to symbolize the crew's mission on the frontiers of space. A gold star is often used to symbolize the frontier period of the American West. The red star in the shape of the Greek letter lambda represents both the laser measurements taken from the Laser Geodynamic Satellite (LAGEOS II) and the Lambda Point Experiment, which was part of the United States Microgravity Payload (USMP-l). The remote manipulator and maple leaf are emblematic of the Canadian payload specialist who conducted a series of Canadian flight experiments (CANEX-2), including the Space Vision System test.

Space Shuttle Projects

NASA Image and Video Library

1992-10-20

The STS-52 insignia, designed by the mission’s crew members, features a large gold star to symbolize the crew's mission on the frontiers of space. A gold star is often used to symbolize the frontier period of the American West. The red star in the shape of the Greek letter lambda represents both the laser measurements taken from the Laser Geodynamic Satellite (LAGEOS II) and the Lambda Point Experiment, which was part of the United States Microgravity Payload (USMP-l). The remote manipulator and maple leaf are emblematic of the Canadian payload specialist who conducted a series of Canadian flight experiments (CANEX-2), including the Space Vision System test.

A study of cooling time reduction of interferometric cryogenic gravitational wave detectors using a high-emissivity coating

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

Sakakibara, Y.; Yamamoto, K.; Chen, D.

In interferometric cryogenic gravitational wave detectors, there are plans to cool mirrors and their suspension systems (payloads) in order to reduce thermal noise, that is, one of the fundamental noise sources. Because of the large payload masses (several hundred kg in total) and their thermal isolation, a cooling time of several months is required. Our calculation shows that a high-emissivity coating (e.g. a diamond-like carbon (DLC) coating) can reduce the cooling time effectively by enhancing radiation heat transfer. Here, we have experimentally verified the effect of the DLC coating on the reduction of the cooling time.

OSTA-3 Shuttle payload

NASA Technical Reports Server (NTRS)

Dillman, R. D.; Eav, B. B.; Baldwin, R. R.

1984-01-01

The Office of Space and Terrestrial Applications-3 payload, scheduled for flight on STS Mission 17, consists of four earth-observation experiments. The Feature Identification and Location Experiment-1 will spectrally sense and numerically classify the earth's surface into water, vegetation, bare earth, and ice/snow/cloud-cover, by means of spectra ratio techniques. The Measurement of Atmospheric Pollution from Satellite experiment will measure CO distribution in the middle and upper troposphere. The Imaging Camera-B uses side-looking SAR to create two-dimensional images of the earth's surface. The Large Format Camera/Attitude Reference System will collect metric quality color, color-IR, and black-and-white photographs for topographic mapping.

Entry, Descent and Landing Systems Analysis Study: Phase 1 Report

NASA Technical Reports Server (NTRS)

DwyerCianciolo, Alicia M.; Davis, Jody L.; Komar, David R.; Munk, Michelle M.; Samareh, Jamshid A.; Powell, Richard W.; Shidner, Jeremy D.; Stanley, Douglas O.; Wilhite, Alan W.; Kinney, David J.;

Sounding rockets in Antarctica

NASA Technical Reports Server (NTRS)

Alford, G. C.; Cooper, G. W.; Peterson, N. E.

1982-01-01

Sounding rockets are versatile tools for scientists studying the atmospheric region which is located above balloon altitudes but below orbital satellite altitudes. Three NASA Nike-Tomahawk sounding rockets were launched from Siple Station in Antarctica in an upper atmosphere physics experiment in the austral summer of 1980-81. The 110 kg payloads were carried to 200 km apogee altitudes in a coordinated project with Arcas rocket payloads and instrumented balloons. This Siple Station Expedition demonstrated the feasibility of launching large, near 1,000 kg, rocket systems from research stations in Antarctica. The remoteness of research stations in Antarctica and the severe environment are major considerations in planning rocket launching expeditions.

NASA's Space Launch System: A Transformative Capability for Deep Space Missions

NASA Technical Reports Server (NTRS)

Creech, Stephen D.

2017-01-01

Already making substantial progress toward its first launches, NASA’s Space Launch System (SLS) exploration-class launch vehicle presents game-changing new opportunities in spaceflight, enabling human exploration of deep space, as well as a variety of missions and mission profiles that are currently impossible. Today, the initial configuration of SLS, able to deliver more than 70 metric tons of payload to low Earth orbit (LEO), is well into final production and testing ahead of its planned first flight, which will send NASA’s new Orion crew vehicle around the moon and will deploy 13 CubeSats, representing multiple disciplines, into deep space. At the same time, production work is already underway toward the more-capable Block 1B configuration, planned to debut on the second flight of SLS, and capable of lofting 105 tons to LEO or of co-manifesting large exploration systems with Orion on launches to the lunar vicinity. Progress being made on the vehicle for that second flight includes initial welding of its core stage and testing of one of its engines, as well as development of new elements such as the powerful Exploration Upper Stage and the Universal Stage Adapter “payload bay.” Ultimately, SLS will evolve to a configuration capable of delivering more than 130 tons to LEO to support humans missions to Mars. In order to enable human deep-space exploration, SLS provides unrivaled mass, volume, and departure energy for payloads, offering numerous benefits for a variety of other missions. For robotic science probes to the outer solar system, for example, SLS can cut transit times to less than half that of currently available vehicles or substantially increased spacecraft mass. In the field of astrophysics, SLS’ high payload volume, in the form of payload fairings with a diameter of up to 10 meters, creates the opportunity for launch of large-aperture telescopes providing an unprecedented look at our universe. This presentation will give an overview of SLS’ capabilities and its current status, and discuss the vehicle’s potential for human exploration of deep space and other game-changing utilization opportunities.

The Space Shuttle orbiter payload retention systems

NASA Technical Reports Server (NTRS)

Hardee, J. H.

1982-01-01

Payloads are secured in the orbiter payload bay by the payload retention system or are equipped with their own unique retention systems. The orbiter payload retention mechanisms provide structural attachments for each payload by using four or five attachment points to secure the payload within the orbiter payload bay during all phases of the orbiter mission. The payload retention system (PRS) is an electromechanical system that provides standarized payload carrier attachment fittings to accommodate up to five payloads for each orbiter flight. The mechanisms are able to function under either l-g or zero-g conditions. Payload berthing or deberthing on orbit is accomplished by utilizing the remote manipulator system (RMS). The retention mechanisms provide the capability for either vertical or horizontal payload installation or removal. The payload support points are selected to minimize point torsional, bending, and radial loads imparted to the payloads. In addition to the remotely controlled latching system, the passive system used for nondeployable payloads performs the same function as the RMS except it provides fixed attachments to the orbiter.

Test and User Facilities | NREL

Science.gov Websites

| L | M | N | O | P | Q | R | S | T | U | V | W | X | Y | Z B Battery Thermal and Life Test Facility High-Flux Solar Furnace I Integrated Biorefinery Research Facility L Large Payload Solar Tracker M

Future lunar exploration activities in ESA

NASA Astrophysics Data System (ADS)

Houdou, B.; Carpenter, J. D.; Fisackerly, R.; Koschny, D.; Pradier, A.; di Pippo, S.; Gardini, B.

2009-04-01

Introduction Recent years have seen a resurgence of interest in the Moon and various recent and coming orbital missions including Smart-1, Kaguya, Chandrayaan-1and Lunar Reconnaissance Orbiter are advancing our understanding. In 2004 the US announced a new Vision for Space Exploration [1], whose objectives are focused towards human missions to the Moon and Mars. The European Space Agency has established similar objectives for Europe, described in [2] and approved at the ESA ministerial council (2009). There is considerable potential for international cooperation in these activities, as formulated in the recently agreed Global Exploration Strategy [3]. Present lunar exploration activities at ESA emphasise the development of European technologies and capabilities, to enable European participation in future international human exploration of the Moon. A major element in this contribution has been identified as a large lunar cargo lander, which would fulfill an ATV-like function, providing logistical support to human activities on the Moon, extending the duration of sorties and the capabilities of human explorers. To meet this ultimate goal, ESA is currently considering various possible development approaches, involving lunar landers of different sizes. Lunar Lander Mission Options A high capacity cargo lander able to deliver consumables, equipment and small infrastructure, in both sortie and outpost mission scenarios, would use a full Ariane 5 launch and is foreseen in the 2020-2025 timeframe. ESA is also considering an intermediate, smaller-scale mission beforehand, to mature the necessary landing technologies, to demonstrate human-related capabilities in preparation of human presence on the Moon and in general to gain experience in landing and operating on the lunar surface. Within this frame, ESA is currently leading several feasibility studies of a small lunar lander mission, also called "MoonNEXT". This mission is foreseen to be to be launched from Kourou with a Soyuz in the 2015-2018 timeframe. The mission would be a first step to-wards mastering the automated precision landing with hazard avoidance required for a future cargo lander and essential for landing at the South Pole Aitken basin (SPA), the provisional MoonNEXT landing site. In addition the mission carries a strawman payload with several technology demonstration and testing packages, which will investigate advanced fuel cell and life sup-port technologies. A small MoonNEXT-like lander (Soyuz-launched) constitutes one of several possible mission types for a first landing on the Moon. The coming year will see additional investigations into other possibilities, including a medium-size lander, launched in a shared Ariane 5 configuration, which could provide a better level of validation of the landing technologies with respect to the targeted large lunar lander, as well as a more significant payload mass. Ultimately, the candidate intermediate mission options will be traded off to find the best balance of cost, mission implementation timeframe, development effort and representability. The reference intermediate lunar lander mission will be established so as to proceed with industrial Phase B1 activities in late 2009. It is also planned to study the large lunar lander based on a full Ariane 5 launch, in order to elaborate the design and to enter in more detailed discussion with the international partners. Possible Payload Packages: Multiple domains can be covered, depending also on the available pay-load mass (thus on the lander size): • Environmental characterization and monitoring: radiation, dust, micrometeorite impacts, temperature etc. (medium TRL) • Technology experiments for exploration preparation: e.g. life support and life sciences, small-scale or subsystem for ISRU, fuel cell etc. (low TRL) • Mobility • Payload transportation and manipulation • Logistics: infrastructure, equipment, consumables etc. The primary objective of any European Moon lander will be to enhance European capabilities for human exploration. It is expected that there will be provision for a significant inclusion of scientific interests. References: [1] National Aeronautics and Space Administration (NASA), The Vision for Space Exploration, NP-2004-01-334-HQ, NASA, Washington D.C, (2004). [2] ESA declaration on Transporation and Human Exploration (2008). [3] The Global Exploration Strategy, available at http://www.esa.int/SPECIALS/Space_Exploration_Strategy/SEMDAM0YUFF_0.html.

CREW TRAINING (CONTINOUS FLOW ELECTROPHORESIS [CFES]) - STS-14/41D - MCDONNELL-DOUGLAS AIRCRAFT CORP. (MDAC), MO

NASA Image and Video Library

1984-06-18

S84-35757 (May 1984) --- Astronaut Judith A. Resnik, 41-D mission specialist, and Charles Walker, payload specialist for that June 1984 flight, prepare for some scheduled intravehicular activity involving the continuous flow electrophoresis systems (CFES) experiment. CFES will join the six-member crew aboard the Earth-orbiting Discovery for a seven day mission. The two share in preparing a sample to be processed by the CFES. In the background are stowage lockers and a CFES trainer-- part of the Shuttle one-g trainer at NASA's Johnson Space Center (JSC). Walker, an engineer at McDonnell Douglas Astronautics Co. in St. Louis, Missouri, will be the first Shuttle payload specialist to represent a project designed for commercial purposes. As payload specialist, his job will be to run the materials electrophoresis-operations-in-space project. The project is aimed at separating large quantities of biological materials in space for ultimate use in new pharmaceuticals. The photo was taken by a McDonnell Douglas photographer.

MSAT signalling and network management architectures

NASA Technical Reports Server (NTRS)

Garland, Peter; Keelty, J. Malcolm

1989-01-01

Spar Aerospace has been active in the design and definition of Mobile Satellite Systems since the mid 1970's. In work sponsored by the Canadian Department of Communications, various payload configurations have evolved. In addressing the payload configuration, the requirements of the mobile user, the service provider and the satellite operator have always been the most important consideration. The current Spar 11 beam satellite design is reviewed, and its capabilities to provide flexibility and potential for network growth within the WARC87 allocations are explored. To enable the full capabilities of the payload to be realized, a large amount of ground based Switching and Network Management infrastructure will be required, when space segment becomes available. Early indications were that a single custom designed Demand Assignment Multiple Access (DAMA) switch should be implemented to provide efficient use of the space segment. As MSAT has evolved into a multiple service concept, supporting many service providers, this architecture should be reviewed. Some possible signalling and Network Management solutions are explored.

KSC-08pd2326

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, workers prepare to attach an overhead crane to the Cosmic Origins Spectrograph, or COS. The COS will be lifted and moved to a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2327

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, workers attach an overhead crane to the Cosmic Origins Spectrograph, or COS. The COS is being lifted and moved to a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2330

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lifts the Cosmic Origins Spectrograph, or COS. The COS is being lifted and moved to a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2331

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lifts the Cosmic Origins Spectrograph, or COS. The COS is being lifted and moved to a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2328

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lifts the Cosmic Origins Spectrograph, or COS. The COS is being lifted and moved to a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

KSC-08pd2329

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – In the clean room of the Payload Hazardous Processing Facility at NASA's Kennedy Space Center, an overhead crane lifts the Cosmic Origins Spectrograph, or COS. The COS is being lifted and moved to a protective enclosure on the Orbital Replacement Unit Carrier, part of the payload for the fifth and final Hubble servicing mission, STS-125. Other payloads include the Flight Support System, the Super Lightweight Interchangeable Carrier and the Multi-Use Lightweight Equipment, or MULE, carrier. COS will be the most sensitive ultraviolet spectrograph ever flown on Hubble and will probe the "cosmic web" - the large-scale structure of the universe whose form is determined by the gravity of dark matter and is traced by galaxies and intergalactic gas. The COS far-ultraviolet channel has a sensitivity 30 times greater than that of previous spectroscopic instruments for the detection of extremely low light levels. Launch of Atlantis on the STS-125 mission is targeted for Oct. 8. Photo credit: NASA/Kim Shiflett

Development of the Hawk/Nike Hawk sounding rocket vehicles

NASA Technical Reports Server (NTRS)

Flowers, B. J.

1976-01-01

A new sounding rocket family, the Hawk and Nike-Hawk Vehicles, have been developed, flight tested and added to the NASA Sounding Rocket Vehicle Stable. The Hawk is a single-stage vehicle that will carry 35.6 cm diameter payloads weighing 45.5 kg to 91 kg to altitudes of 78 km to 56 km, respectively. The two-stage Nike-Hawk will carry payloads weighing 68 kg to 136 kg to altitudes of 118 km to 113 km, respectively. Both vehicles utilize the XM22E8 Hawk rocket motor which is available in large numbers as a surplus item from the U.S. Army. The Hawk fin and tail can hardware were designed in-house. The Nike tail can and fin hardware are surplus Nike-Ajax booster hardware. Development objectives were to provide a vehicle family with a larger diameter, larger volume payload capability than the Nike-Apache and Nike-Tomahawk vehicles at comparable cost. Both vehicles performed nominally in flight tests.

A System For Load Isolation And Precision Pointing

NASA Astrophysics Data System (ADS)

Keckler, Claude R.; Hamilton, Brian J.

1983-11-01

A system capable of satisfying the accuracy and stability requirements dictated by Shuttle-borne payloads utilizing large optics has been under joint NASA/Sperry development. This device, denoted the Annular Suspension and Pointing System, employs a unique combination of conventional gimbals and magnetic bearing actuators, thereby providing for the "complete" isolation of the payload from its external environment, as well as for extremely accurate and stable pointing (≍0.01 arcseconds). This effort has been pursued through the fabrication and laboratory evaluation of engineering model hardware. Results from these tests have been instrumental in generating high fidelity computer simulations of this load isolation and precision pointing system, and in permitting confident predictions of the system's on-orbit performance. Applicability of this system to the Solar Optical Telescope mission has been examined using the computer simulation. The worst case pointing error predicted for this payload while subjected to vernier reaction control system thruster firings and crew motions aboard Shuttle was approximately 0.006 arcseconds.

Modal Testing of Seven Shuttle Cargo Elements for Space Station

NASA Technical Reports Server (NTRS)

Kappus, Kathy O.; Driskill, Timothy C.; Parks, Russel A.; Patterson, Alan (Technical Monitor)

2001-01-01

From December 1996 to May 2001, the Modal and Control Dynamics Team at NASA's Marshall Space Flight Center (MSFC) conducted modal tests on seven large elements of the International Space Station. Each of these elements has been or will be launched as a Space Shuttle payload for transport to the International Space Station (ISS). Like other Shuttle payloads, modal testing of these elements was required for verification of the finite element models used in coupled loads analyses for launch and landing. The seven modal tests included three modules - Node, Laboratory, and Airlock, and four truss segments - P6, P3/P4, S1/P1, and P5. Each element was installed and tested in the Shuttle Payload Modal Test Bed at MSFC. This unique facility can accommodate any Shuttle cargo element for modal test qualification. Flexure assemblies were utilized at each Shuttle-to-payload interface to simulate a constrained boundary in the load carrying degrees of freedom. For each element, multiple-input, multiple-output burst random modal testing was the primary approach with controlled input sine sweeps for linearity assessments. The accelerometer channel counts ranged from 252 channels to 1251 channels. An overview of these tests, as well as some lessons learned, will be provided in this paper.

High Tonnage Forest Biomass Production Systems from Southern Pine Energy Plantations

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

Taylor, Steve; McDonald, Timothy; Fasina, Oladiran

In this study, a high-tonnage harvesting system designed specifically to operate efficiently in the expected stand types of a bioenergy scenario was built, deployed, and evaluated in a production setting. Stands on which the system was evaluated exhibited the heavy stocking levels (> 600 stems per acre) and tree size distributions with significant volume in small stems (down to 2” DBH) that were expected in the modified energy plantation silvicultural approach. The harvest system also was designed to be functional in the traditional plantation stands dominating the commercial forestry landscape in the region. The Tigercat 845D feller buncher, which wasmore » a prototype machine designed for the high tonnage harvest system, used a boom-mounted prototype DT1802 shear felling head and incorporated a number of options intended to maximize its small-stem productivity, including: a high-speed shear severing system that was cheaper to operate than a saw; a large-pocket felling head that allowed larger accumulations of small stems to be built before expending the time to drop them for the skidder; efficient, low ground pressure, tracked carrier system to decrease the amount of maneuvering, saving time and minimizing soil disturbance; and various energy-saving devices to lower fuel costs and minimize air quality impacts. Overall, the feller buncher represented a quantum advance in small-stem harvesting technology. Extensive testing showed the machine’s production rate to be relatively insensitive to piece size, much less so than comparable traditional equipment. In plantation stands, the feller buncher was able to produce approximately 100 green tons of biomass per productive machine hour (PMH), and in natural stands, it produced nearly 120 green tons per PMH. The ability of the high tonnage feller buncher to maintain high productivity in stands with smaller diameter stems is something that has not been achieved in previous feller buncher designs. The Tigercat 845D feller buncher is now a production machine for Tigercat and is being sold in their current product line. The high-speed felling system was paired with a Tigercat 630D skidder and high-capacity grapple; one that could match the felling productivity when pulling small stems. The harvesting system minimized hourly costs using a single, high-capacity skidder (with a single operator), rather than two smaller ones, which is the traditional practice. The skidder itself can be considered a mid-range size and had an engine no larger than other machines in its class, but it incorporated a very large capacity 25 ft2 grapple. The large grapple is well suited to grabbing and hauling a large bunch of small-diameter trees, as produced by the high tonnage feller buncher. The grapple worked effectively in larger stems as well, but its ability to carry large numbers of small stems meant the average payload did not drop as stand DBH decreased. Tests with the machine indicated its travel speeds were nearly the same as, or perhaps slightly better than, conventionally equipped skidders, but grapple capacity was 75% larger. Productivity and cost per ton of the new skidder were better than conventional skidders for average skid distances of any length greater than 100 feet. Measured skidder productivity was as high as 143 gt/PMH. Its productivity exceeded that of the high-capacity feller buncher for skid distances out to nearly 700 feet, so system productivity could be expected to remain high for stands of a size typical in the southern U.S. The Tigercat 630D skidder is a production machine for Tigercat and the large grapple can now be ordered by customers using it for small diameter trees. When the feller buncher and skidder are analyzed as a two-machine system, overall productivity is fixed at the level of the least productive machine. Results from a set of side-by-side tests in the same density stand with conventional feller bunchers and skidders showed that the high tonnage system produced 97 gt/PMH versus 68 gt/PMH for a comparable conventional system. Machine rate costs for felling and skidding were $2.31/gt and $3.72/gt for the high tonnage, and conventional systems, respectively. However, the most significant result of the project is that the high tonnage system was shown to be relatively insensitive to tree size. This ability to maintain felling and skidding productivity and cost as tree size decreases is a breakthrough in harvesting systems for southern pine plantations. The concept of transpirational drying of woody biomass was tested at an industrial scale at multiple locations during this project. Felled trees were allowed to dry in two scenarios: 1) in bunches where they were felled, and 2) in roadside piles. Although the wood piled in large piles at roadside did experience drying, the wood left in bunches experienced a greater moisture reduction. Drying times of 72 days in the late summer resulted in mean wood moisture content of 26% for skidder bunches and 39% for the large pile at roadside as compared to moisture contents of 55% to 58% for freshly cut trees. An existing whole-tree chipper, Precision 2675, was modified to allow production of chips smaller than the traditional pulp size chip (i.e. “microchips”). Feed rates and knife placements were retained in the new design, while additional pockets were incorporated in the chipper disk to allow the attachment of either four knives for pulp chips or eight knives for microchips. This design facilitated switching between the energy and pulp chip product options at relatively low expense (about ½ day downtime). Chipping of whole-trees into pulp chips and microchips with the Precision 2675 disk chipper resulted in average productivities of 79.5 gt/PMH and 70.7 gt/PMH, respectively. Production rates of the chipper were lower when producing microchips by about 10% relative to producing pulp chips, but rates were similar to those achievable when making clean pulp chips. Particle size analysis for clean pine microchips revealed 26.6% retention on a 13 mm (slightly less than 3/8-inch) round hole screen and 25.9% retention for whole-tree pine microchips. For comparison, clean pine pulp chips had 52.2% retained. Ash content (% dry basis) was 0.54% for clean pine microchips and 0.62% for whole-tree pine microchips. Ash content for clean pine pulp chips was 0.39%. For transpirationally-dried material there was 38.1% retention for whole-tree microchips on a 13mm screen compared to 70.1% for dried clean pulp chips. Ash content was 0.78% and 0.44% respectively for these two chip types. Clean pine microchips stored at roadside had 25.2% retention on a 13 mm screen and 0.50% ash content. For mixed species (pine and hardwood), whole-tree microchips had 25.1% retention on a 13 mm screen compared to 50.6% for whole-tree pulp chips. Ash content was 2.12% and 2.74% respectively for these two chip types. Clean hardwood microchips stored at roadside had 35.0% retention on a 13 mm screen and an ash content of 1.24%. There are two significant advantages to using transpirational drying: reduced transportation costs, and reduced drying costs (capital and operating costs) for the biorefinery. This project evaluated the potential to reduce transportation costs through transpirational drying, and it included a component that tested higher capacity chip trailers (23% larger volume) to be able to transport dry wood with a lower bulk density. For transpirationally-dried chips at 35% MC, the high-capacity trailers achieved loads with a mean payload of 24 tons with maximum payloads of 29 tons. The typical legal payload on this trailer is 28.5 tons. Therefore, the project demonstrated that it is possible to achieve maximum legal payloads on chip trailers with transpirationally dried wood. Assuming that the truck is loaded to the legal payload limit, the transportation costs of chips can be reduced from $15.91/dry ton (dt) for 56% MC wood to $10.77/dt for transpirationally dried wood at 35% MC (for an example 50-mile haul distance at $0.14 per one-way ton-mile). For longer haul distances, these savings in trucking costs become even more significant. These results have demonstrated how significant savings in transportation costs can be achieved through transpirational drying. Also, these results show that it may be possible to increase the procurement radius for a biorefinery by using transpirational drying. Further cost reductions can be realized by the biorefinery when drying costs are reduced. The goal of this study was development of a timber harvesting system as productive in stands optimized for biomass production as it was in stands grown for roundwood markets. If that goal is achieved, a logger can invest in a single suite of equipment and operate efficiently in any future silvicultural regime that might include energy feedstocks as an output. It was the premise of the study that a future biomass market would shift the age distribution and stem size in stands grown for energy downward, and the key strategy in developing a harvest system for that scenario would be creating one with logging costs relatively insensitive to tree size. Our vision for such a system included a felling machine with a large capacity head to minimize time spent building bunches, plus a skidder capable of moving large volumes of small trees. The study proposed building the system and testing it against existing equipment in stands similar to those envisioned as resulting from biomass-optimized silviculture. As stated previously, the new feller buncher and skidder evaluated on their own merits showed their designs were clearly a step in the right direction - their productivity was indeed high and less sensitive to reductions in stem size. Cost projections based on extensive time and production studies of the high tonnage and benchmark operations showed modest advantages in FOB costs of the new system in both ‘average’ and simulated ‘energy’ stands (7.7% and 9.5%, respectively). But it was clear, when coupled into a traditional logging system, the in-woods productivity advantage of the modified equipment was easily overwhelmed by inefficiencies in chipping or trucking. Some additional savings can be achieved by spreading the cost of the feller buncher over multiple chipping operations (another 7.5%), but generally, in stands with average DBH above 6 inches, the in-woods equipment was not limiting productivity, and costs were driven by chipping and transport. Our results were a positive step in lowering delivered cost of trees grown for energy purposes, but they also argue strongly for a more comprehensive approach in solving this issue. The procurement system in its entirety has to be optimized to take full advantage of the productivity gains achieved with the machines and transpirational drying techniques developed in this project. We have to understand the true costs of all logistical options, particularly those of the choice in chipping strategy and in truck allocation, both of which seemed, in this study, to be the greatest source of variability in cost, and often the most expensive operations as well.« less

Design, testing and demonstration of a small unmanned aircraft system (sUAS) and payload for measuring wind speed and particulate matter in the atmospheric boundary layer

NASA Astrophysics Data System (ADS)

Riddell, Kevin Donald Alexander

The atmospheric boundary layer (ABL) is the layer of air directly influenced by the Earth's surface and is the layer of the atmosphere most important to humans as this is the air we live in. Methods for measuring the properties of the ABL include three general approaches: satellite based, ground based and airborne. A major research challenge is that many contemporary methods provide a restricted spatial resolution or coverage of variations of ABL properties such as how wind speed varies across a landscape with complex topography. To enhance our capacity to measure the properties of the ABL, this thesis presents a new technique that involves a small unmanned aircraft system (sUAS) equipped with a customized payload for measuring wind speed and particulate matter. The research presented herein outlines two key phases in establishing the proof of concept of the payload and its integration on the sUAS: (1) design and testing and (2) field demonstration. The first project focuses on measuring wind speed, which has been measured with fixed wing sUASs in previous research. but not with a helicopter sUAS. The second project focuses on the measurement of particulate matter, which is a major air pollutant typically measured with ground-based sensors. Results from both proof of concept projects suggest that ABL research could benefit from the proposed techniques. .

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

NASA Technical Reports Server (NTRS)

1971-01-01

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

Inhalable microparticles containing large payload of anti-tuberculosis drugs.

PubMed

Muttil, Pavan; Kaur, Jatinder; Kumar, Kaushlendra; Yadav, Awadh Bihari; Sharma, Rolee; Misra, Amit

2007-10-01

Microparticles containing large payloads of two anti-tuberculosis (TB) drugs were prepared and evaluated for suitability as a dry powder inhalation targeting alveolar macrophages. A solution containing one part each of isoniazid and rifabutin, plus two parts poly(lactic acid) (L-PLA) was spray-dried. Drug content and in vitro release were assayed by HPLC, and DSC was used to elucidate release behaviour. Particle size was measured by laser scattering and aerosol characteristics by cascade impaction using a Lovelace impactor. Microparticles were administered to mice using an in-house inhalation apparatus or by intra-tracheal instillation. Drugs in solution were administered orally and by intra-cardiac injection. Flow cytometry and HPLC were used to investigate the specificity and magnitude of targeting macrophages. Microparticles having drug content approximately 50% (w/w), particle size approximately 5 microm and satisfactory aerosol characteristics (median mass aerodynamic diameter, MMAD=3.57 microm; geometric standard deviation, GSD=1.41 microm; fine particle fraction, FPF(<4.6 microm)=78.91+/-8.4%) were obtained in yields of >60%. About 70% of the payload was released in vitro in 10 days. Microparticles targeted macrophages and not epithelial cells on inhalation. Drug concentrations in macrophages were approximately 20 times higher when microparticles were inhaled rather than drug solutions administered. Microparticles were thus deemed suitable for enhanced targeted drug delivery to lung macrophages.

Controllability of Large SEP for Earth Orbit Raising

NASA Technical Reports Server (NTRS)

Woodcock, Gordon

2004-01-01

A six-degree-of-freedom (6DOF) simulation was constructed and exercised for a large solar electric propulsion (SEP) vehicle operating in low Earth orbit Nominal power was 500 kWe, with the large array sizes implied. Controllability issues, including gravity gradient, roll maneuvering for Sun tracking, and flexible arrays, and flight control methods, were investigated. Initial findings are that a SEP vehicle of this size is controllable and could be used for orbit raising of heavy payloads.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

This STS-98 mission photograph shows astronauts Thomas D. Jones (foreground) and Kerneth D. Cockrell floating inside the newly installed Laboratory aboard the International Space Station (ISS). The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

U.S. Laboratory Module (Destiny) for the International Space Station

NASA Technical Reports Server (NTRS)

1997-01-01

In this photograph, the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS) is shown under construction in the West High Bay of the Space Station manufacturing facility (building 4708) at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

U.S. Laboratory Module (Destiny) for the International Space Station

NASA Technical Reports Server (NTRS)

1998-01-01

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), in the Space Station manufacturing facility at the Marshall Space Flight Center, being readied for shipment to the Kennedy Space Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

U.S. Laboratory Module (Destiny) for the International Space Station

NASA Technical Reports Server (NTRS)

1997-01-01

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), under construction in the Space Station manufacturing facility at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two end cones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

STS-98 Onboard Photograph-U.S. Laboratory, Destiny

NASA Technical Reports Server (NTRS)

2001-01-01

This closer image of the International Space Station (ISS) showing the newly installed U.S. Laboratory, Destiny (left), was taken from the departing Space Shuttle Atlantis. The American-made Destiny module is the cornerstone for space-based research aboard the orbiting platform and the centerpiece of the ISS, where unprecedented science experiments will be performed in the near-zero gravity of space. Destiny will also serve as the command and control center for the ISS. The aluminum module is 8.5-meters (28-feet) long and 4.3-meters (14-feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations. Payload racks will occupy 15 locations especially designed to support experiments. The Destiny module was built by the Boeing Company under the direction of the Marshall Space Flight Center.

Injection of a microsatellite in circular orbits using a three-stage launch vehicle

NASA Astrophysics Data System (ADS)

Marchi, L. O.; Murcia, J. O.; Prado, A. F. B. A.; Solórzano, C. R. H.

2017-10-01

The injection of a satellite into orbit is usually done by a multi-stage launch vehicle. Nowadays, the space market demonstrates a strong tendency towards the use of smaller satellites, because the miniaturization of the systems improve the cost/benefit of a mission. A study to evaluate the capacity of the Brazilian Microsatellite Launch Vehicle (VLM) to inject payloads into Low Earth Orbits is presented in this paper. All launches are selected to be made to the east side of the Alcântara Launch Center (CLA). The dynamical model to calculate the trajectory consists of the three degrees of freedom (3DOF) associated with the translational movement of the rocket. Several simulations are performed according to a set of restrictions imposed to the flight. The altitude reached in the separation of the second stage, the altitude and velocity of injection, the flight path angle at the moment of the activation of the third stage and the duration of the ballistic flight are presented as a function of the payload carried.

International Space Station (ISS)

NASA Image and Video Library

1998-11-01

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), in the Space Station manufacturing facility at the Marshall Space Flight Center, being readied for shipment to the Kennedy Space Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

International Space Station (ISS)

NASA Image and Video Library

1997-01-01

In this photograph, the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS) is shown under construction in the West High Bay of the Space Station manufacturing facility (building 4708) at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

International Space Station (ISS)

NASA Image and Video Library

1997-11-01

In this photograph, the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS) is shown under construction in the West High Bay of the Space Station manufacturing facility (building 4708) at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-98 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two endcones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

International Space Station (ISS)

NASA Image and Video Library

1997-11-26

This photograph shows the U.S. Laboratory Module (also called Destiny) for the International Space Station (ISS), under construction in the Space Station manufacturing facility at the Marshall Space Flight Center. The U.S. Laboratory module is the centerpiece of the ISS, where science experiments will be performed in the near-zero gravity of space. The Destiny Module was launched aboard the Space Shuttle orbiter Atlantis (STS-67 mission) on February 7, 2001. The aluminum module is 8.5 meters (28 feet) long and 4.3 meters (14 feet) in diameter. The laboratory consists of three cylindrical sections and two end cones with hatches that will be mated to other station components. A 50.9-centimeter- (20-inch-) diameter window is located on one side of the center module segment. This pressurized module is designed to accommodate pressurized payloads. It has a capacity of 24 rack locations, and payload racks will occupy 13 locations especially designed to support experiments. The ISS is a multidisciplinary laboratory, technology test bed, and observatory that will provide unprecedented undertakings in scientific, technological, and international experimentation.

Status of the assessment phase of the ESA M3 mission candidate LOFT

NASA Astrophysics Data System (ADS)

Corral van Damme, Carlos; Ayre, Mark; Lumb, David; Short, Alexander D.; Rando, Nicola

2012-09-01

LOFT (Large Observatory For x-ray Timing) is one of four candidates for the M3 slot (launch in 2024, with the option of a launch in 2022) of ESAs Cosmic Vision 2015 - 2025 Plan, and as such it is currently undergoing an initial assessment phase lasting one year. The objective of the assessment phase is to provide the information required to enable the down selection process, in particular: the space segment definition for meeting the assigned science objectives; consideration of and initial definition of the implementation schedule; an estimate of the mission Cost at Completion (CaC); an evaluation of the technology readiness evaluation and risk assessment. The assessment phase is divided into two interleaved components: (i) A payload assessment study, performed by teams funded by member states, which is primarily intended for design, definition and programmatic/cost evaluation of the payload, and (ii) A system industrial study, which has essentially the same objectives for the space segment of the mission. This paper provides an overview of the status of the LOFT assessment phase, both for payload and platform. The initial focus is on the payload design status, providing the reader with an understanding of the main features of the design. Then the space segment assessment study status is presented, with an overview of the principal challenges presented by the LOFT payload and mission requirements, and a presentation of the expected solutions. Overall the mission is expected to enable cutting-edge science, is technically feasible, and should remain within the required CaC for an M3 candidate.

The Story of the Nuclear Rocket: Back to the Future

NASA Astrophysics Data System (ADS)

Dewar, James A.

2002-01-01

The United States had a nuclear rocket development program from 1955-1973 called Project Rover/NERVA. Twenty reactor tests demonstrated conclusively the superiority, flexibility and reliability of nuclear rocket engines over their chemical counterparts. This paper surveys the technical accomplishments from that perspective, to help illustrate why many call for the program's reestablishment. Most focus on the large NERVA, but this review will consider the little known Small Nuclear Engine. KIWI-B1B was one of the first tests in which nuclear rockets demonstrated their superiority. It ejected its core as it rose to 1000MW (a megawatt equals 50 pounds of thrust). This seems contradictory, how can a `failure' demonstrate superiority? Precisely in this: the reactor remained controllable going to and from 1000MW, still ejecting its core, but still turning out power. That gave insurance to a mission. A solid or liquid chemical engine suffering similar damage would likely shutdown or blow up. KIWI-TNT and Phoebus-1A had planned and unplanned accidents. That verified the safety of nuclear engines in launch operations. NRX/EST and XE-Prime proved they could startup reliably under their own power in a simulated space environment and change power without loss of specific impulse or control, from 20MW to 1000MW and back. That gave flexibility for mid-course corrections, maneuvering between orbits or breaking into orbit. Pewee and the Nuclear Furnace tested fuels to achieve 10 hours of engine operation with 60 recycles (stops and starts). That meant an engine could perform multiple missions. Work started on fuels promising1000 seconds of specific impulse. That meant increased power and payload capacity and speed. This contrasts with the 450 seconds of LOX/LH2. The NERVA of 1971 would be 1500MW, with 10/60 capability and 825 seconds of a specific impulse. Later generation NERVAs would be in excess of 1000 seconds, 3000MW and 10/60. The Nixon Administration cancelled it in 1971. After its demise, the Small Nuclear Engine appeared for unmanned missions. To fit in the space shuttle's 15 by 60 foot cargo bay, the 10 foot long engine would be 400MW, weigh 5600 pounds and use slush hydrogen. That left 50 feet and almost 60,000 pounds for the tank, propellant and payload that could vary in size, but it was nominally 5 tons. It would cost 500 million (in1972 dollars) and take a decade to develop. It had NERVA's operating characteristics, but subsequent generation systems envisioned longer engine life and recycle capability and specific impulses of 1000+ seconds. Nixon ended this in 1973. By reconsidering it instead of a nuclear electric engine that serves only space science, the nation could gain a fast, powerful system that would radically change most future unmanned space missions. With its recycle capability, a single engine could ferry large scientific payloads swiftly throughout the solar system. Yet it also could propel heavy national security and commercial payloads to geo-synchronous orbit. NASA might even offer a satellite retrieval service. Thus, one lesson is clear: it is 1960s era technology, but the Small Engine is not obsolete. If developed, it would serve not just one, but three users yet have growth potential for decades for an ever more expansive space program.

NASA's Space Launch System: SmallSat Deployment to Deep Space

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Creech, Stephen D.

2017-01-01

Leveraging the significant capability it offers for human exploration and flagship science missions, NASA's Space Launch System (SLS) also provides a unique opportunity for lower-cost deep-space science in the form of small-satellite secondary payloads. Current plans call for such opportunities to begin with the rocket's first flight; a launch of the vehicle's Block 1 configuration, capable of delivering 70 metric tons (t) to Low Earth Orbit (LEO), which will send the Orion crew vehicle around the moon and return it to Earth. On that flight, SLS will also deploy 13 CubeSat-class payloads to deep-space destinations. These secondary payloads will include not only NASA research, but also spacecraft from industry and international partners and academia. The payloads also represent a variety of disciplines including, but not limited to, studies of the moon, Earth, sun, and asteroids. While the SLS Program is making significant progress toward that first launch, preparations are already under way for the second, which will see the booster evolve to its more-capable Block 1B configuration, able to deliver 105t to LEO. That configuration will have the capability to carry large payloads co-manifested with the Orion spacecraft, or to utilize an 8.4-meter (m) fairing to carry payloads several times larger than are currently possible. The Block 1B vehicle will be the workhorse of the Proving Ground phase of NASA's deep-space exploration plans, developing and testing the systems and capabilities necessary for human missions into deep space and ultimately to Mars. Ultimately, the vehicle will evolve to its full Block 2 configuration, with a LEO capability of 130 metric tons. Both the Block 1B and Block 2 versions of the vehicle will be able to carry larger secondary payloads than the Block 1 configuration, creating even more opportunities for affordable scientific exploration of deep space. This paper will outline the progress being made toward flying smallsats on the first flight of SLS, and discuss future opportunities for smallsats on subsequent flights.

Adaptive beamforming in a CDMA mobile satellite communications system

NASA Technical Reports Server (NTRS)

Munoz-Garcia, Samuel G.

1993-01-01

Code-Division Multiple-Access (CDMA) stands out as a strong contender for the choice of multiple access scheme in these future mobile communication systems. This is due to a variety of reasons such as the excellent performance in multipath environments, high scope for frequency reuse and graceful degradation near saturation. However, the capacity of CDMA is limited by the self-interference between the transmissions of the different users in the network. Moreover, the disparity between the received power levels gives rise to the near-far problem, this is, weak signals are severely degraded by the transmissions from other users. In this paper, the use of time-reference adaptive digital beamforming on board the satellite is proposed as a means to overcome the problems associated with CDMA. This technique enables a high number of independently steered beams to be generated from a single phased array antenna, which automatically track the desired user signal and null the unwanted interference sources. Since CDMA is interference limited, the interference protection provided by the antenna converts directly and linearly into an increase in capacity. Furthermore, the proposed concept allows the near-far effect to be mitigated without requiring a tight coordination of the users in terms of power control. A payload architecture will be presented that illustrates the practical implementation of this concept. This digital payload architecture shows that with the advent of high performance CMOS digital processing, the on-board implementation of complex DSP techniques -in particular digital beamforming- has become possible, being most attractive for Mobile Satellite Communications.

Adaptive beamforming in a CDMA mobile satellite communications system

NASA Astrophysics Data System (ADS)

Munoz-Garcia, Samuel G.

Code-Division Multiple-Access (CDMA) stands out as a strong contender for the choice of multiple access scheme in these future mobile communication systems. This is due to a variety of reasons such as the excellent performance in multipath environments, high scope for frequency reuse and graceful degradation near saturation. However, the capacity of CDMA is limited by the self-interference between the transmissions of the different users in the network. Moreover, the disparity between the received power levels gives rise to the near-far problem, this is, weak signals are severely degraded by the transmissions from other users. In this paper, the use of time-reference adaptive digital beamforming on board the satellite is proposed as a means to overcome the problems associated with CDMA. This technique enables a high number of independently steered beams to be generated from a single phased array antenna, which automatically track the desired user signal and null the unwanted interference sources. Since CDMA is interference limited, the interference protection provided by the antenna converts directly and linearly into an increase in capacity. Furthermore, the proposed concept allows the near-far effect to be mitigated without requiring a tight coordination of the users in terms of power control. A payload architecture will be presented that illustrates the practical implementation of this concept. This digital payload architecture shows that with the advent of high performance CMOS digital processing, the on-board implementation of complex DSP techniques -in particular digital beamforming- has become possible, being most attractive for Mobile Satellite Communications.

27 CFR 478.153 - Semiautomatic assault weapons and large capacity ammunition feeding devices manufactured or...

Code of Federal Regulations, 2011 CFR

2011-04-01

... weapons and large capacity ammunition feeding devices manufactured or imported for the purposes of testing... AMMUNITION Exemptions, Seizures, and Forfeitures § 478.153 Semiautomatic assault weapons and large capacity... weapon, and § 478.40a with respect to large capacity ammunition feeding devices, shall not apply to the...

27 CFR 478.153 - Semiautomatic assault weapons and large capacity ammunition feeding devices manufactured or...

Code of Federal Regulations, 2013 CFR

2013-04-01

... weapons and large capacity ammunition feeding devices manufactured or imported for the purposes of testing... AMMUNITION Exemptions, Seizures, and Forfeitures § 478.153 Semiautomatic assault weapons and large capacity... weapon, and § 478.40a with respect to large capacity ammunition feeding devices, shall not apply to the...

27 CFR 478.153 - Semiautomatic assault weapons and large capacity ammunition feeding devices manufactured or...

Code of Federal Regulations, 2014 CFR

2014-04-01

... weapons and large capacity ammunition feeding devices manufactured or imported for the purposes of testing... AMMUNITION Exemptions, Seizures, and Forfeitures § 478.153 Semiautomatic assault weapons and large capacity... weapon, and § 478.40a with respect to large capacity ammunition feeding devices, shall not apply to the...

27 CFR 478.153 - Semiautomatic assault weapons and large capacity ammunition feeding devices manufactured or...

Code of Federal Regulations, 2012 CFR

2012-04-01

... weapons and large capacity ammunition feeding devices manufactured or imported for the purposes of testing... AMMUNITION Exemptions, Seizures, and Forfeitures § 478.153 Semiautomatic assault weapons and large capacity... weapon, and § 478.40a with respect to large capacity ammunition feeding devices, shall not apply to the...

27 CFR 478.153 - Semiautomatic assault weapons and large capacity ammunition feeding devices manufactured or...

Code of Federal Regulations, 2010 CFR

2010-04-01

... weapons and large capacity ammunition feeding devices manufactured or imported for the purposes of testing... AMMUNITION Exemptions, Seizures, and Forfeitures § 478.153 Semiautomatic assault weapons and large capacity... weapon, and § 478.40a with respect to large capacity ammunition feeding devices, shall not apply to the...

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

NASA Technical Reports Server (NTRS)

Calvert, John; Freas, George, II

2017-01-01

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

Earth Viewing Applications Laboratory (EVAL). Dedicated payload, standard test rack payload, sensor modifications

NASA Technical Reports Server (NTRS)

1976-01-01

The preliminary analysis of strawman earth-viewing shuttle sortie payloads begun with the partial spacelab payload was analyzed. The payloads analyzed represent the two extremes of shuttle sortie application payloads: a full shuttle sortie payload dedicated to earth-viewing applications, and a small structure payload which can fly on a space available basis with another primary shuttle payload such as a free flying satellite. The intent of the dedicated mission analysis was to configure an ambitious, but feasible, payload; which, while rich in scientific return, would also stress the system and reveal any deficiences or problem areas in mission planning, support equipment, and operations. Conversely, the intent of the small structure payload was to demonstrate the ease with which a small, simple, flexible payload can be accommodated on shuttle flights.

Planning Inmarsat's second generation of spacecraft

NASA Astrophysics Data System (ADS)

Williams, W. P.

1982-09-01

The next generation of studies of the Inmarsat service are outlined, such as traffic forecasting studies, communications capacity estimates, space segment design, cost estimates, and financial analysis. Traffic forecasting will require future demand estimates, and a computer model has been developed which estimates demand over the Atlantic, Pacific, and Indian ocean regions. Communications estimates are based on traffic estimates, as a model converts traffic demand into a required capacity figure for a given area. The Erlang formula is used, requiring additional data such as peak hour ratios and distribution estimates. Basic space segment technical requirements are outlined (communications payload, transponder arrangements, etc), and further design studies involve such areas as space segment configuration, launcher and spacecraft studies, transmission planning, and earth segment configurations. Cost estimates of proposed design parameters will be performed, but options must be reduced to make construction feasible. Finally, a financial analysis will be carried out in order to calculate financial returns.

A normal incidence X-ray telescope sounding rocket payload

NASA Technical Reports Server (NTRS)

Golub, L.

1985-01-01

Progress is reported on the following major activities on the X-ray telescope: (1) complete design of the entire telescope assembly and fabrication of all front-end components was completed; (2) all rocket skin sections, including bulkheads, feedthroughs and access door, were specified; (3) fabrication, curing and delivery of the large graphite-epoxy telescope tube were completed; (4) an engineering analysis of the primary mirror vibration test was completed and a decision made to redesign the mirror attachment system to a kinematic three-point mount; (5) detail design of the camera control, payload and housekeeping electronics were completed; and (6) multilayer mirror plates with 2d spacings of 50 A and 60 A were produced.

Costs and benefits of future heavy Space Freighters

NASA Astrophysics Data System (ADS)

Arend, H.

1987-10-01

A class of two-stage reusable ballistic Space Freighters with nominal launch masses of 7000 metric tons for transport of heavy payloads into low earth orbits is investigated in this paper with spcial regard to vehicle cost efficiency. A life-cycle cost analysis shows that Space Freighters with a conventional aluminum structure offer significantly lower specific transportation costs than today's systems for large payload markets and high launch rates. Advanced structural materials and thermal protection systems offer further important reductions not only with regard to vehicle mass but also with respect to specific transportation cost. A phased introduction of these technologies is cost efficient for larger programs with more than 100 vehicles.

The LEAN Payload Integration Process

NASA Technical Reports Server (NTRS)

Jordan, Lee P.; Young, Yancy; Rice, Amanda

2011-01-01

It is recognized that payload development and integration with the International Space Station (ISS) can be complex. This streamlined integration approach is a first step toward simplifying payload integration; making it easier to fly payloads on ISS, thereby increasing feasibility and interest for more research and commercial organizations to sponsor ISS payloads and take advantage of the ISS as a National Laboratory asset. The streamlined integration approach was addressed from the perspective of highly likely initial payload types to evolve from the National Lab Pathfinder program. Payloads to be accommodated by the Expedite the Processing of Experiments for Space Station (EXPRESS) Racks and Microgravity Sciences Glovebox (MSG) pressurized facilities have been addressed. It is hoped that the streamlined principles applied to these types of payloads will be analyzed and implemented in the future for other host facilities as well as unpressurized payloads to be accommodated by the EXPRESS Logistics Carrier (ELC). Further, a payload does not have to be classified as a National Lab payload in order to be processed according to the lean payload integration process; any payload that meets certain criteria can follow the lean payload integration process.

Conceptual Design and Feasibility of Foil Bearings for Rotorcraft Engines: Hot Core Bearings

NASA Technical Reports Server (NTRS)

Howard, Samuel A.

2007-01-01

Recent developments in gas foil bearing technology have led to numerous advanced high-speed rotating system concepts, many of which have become either commercial products or experimental test articles. Examples include oil-free microturbines, motors, generators and turbochargers. The driving forces for integrating gas foil bearings into these high-speed systems are the benefits promised by removing the oil lubrication system. Elimination of the oil system leads to reduced emissions, increased reliability, and decreased maintenance costs. Another benefit is reduced power plant weight. For rotorcraft applications, this would be a major advantage, as every pound removed from the propulsion system results in a payload benefit.. Implementing foil gas bearings throughout a rotorcraft gas turbine engine is an important long-term goal that requires overcoming numerous technological hurdles. Adequate thrust bearing load capacity and potentially large gearbox applied radial loads are among them. However, by replacing the turbine end, or hot section, rolling element bearing with a gas foil bearing many of the above benefits can be realized. To this end, engine manufacturers are beginning to explore the possibilities of hot section gas foil bearings in propulsion engines. This overview presents a logical follow-on activity by analyzing a conceptual rotorcraft engine to determine the feasibility of a foil bearing supported core. Using a combination of rotordynamic analyses and a load capacity model, it is shown to be reasonable to consider a gas foil bearing core section. In addition, system level foil bearing testing capabilities at NASA Glenn Research Center are presented along with analysis work being conducted under NRA Cooperative Agreements.

Kinematics and dynamics analysis of a quadruped walking robot with parallel leg mechanism

NASA Astrophysics Data System (ADS)

Wang, Hongbo; Sang, Lingfeng; Hu, Xing; Zhang, Dianfan; Yu, Hongnian

2013-09-01

It is desired to require a walking robot for the elderly and the disabled to have large capacity, high stiffness, stability, etc. However, the existing walking robots cannot achieve these requirements because of the weight-payload ratio and simple function. Therefore, Improvement of enhancing capacity and functions of the walking robot is an important research issue. According to walking requirements and combining modularization and reconfigurable ideas, a quadruped/biped reconfigurable walking robot with parallel leg mechanism is proposed. The proposed robot can be used for both a biped and a quadruped walking robot. The kinematics and performance analysis of a 3-UPU parallel mechanism which is the basic leg mechanism of a quadruped walking robot are conducted and the structural parameters are optimized. The results show that performance of the walking robot is optimal when the circumradius R, r of the upper and lower platform of leg mechanism are 161.7 mm, 57.7 mm, respectively. Based on the optimal results, the kinematics and dynamics of the quadruped walking robot in the static walking mode are derived with the application of parallel mechanism and influence coefficient theory, and the optimal coordination distribution of the dynamic load for the quadruped walking robot with over-determinate inputs is analyzed, which solves dynamic load coupling caused by the branches’ constraint of the robot in the walk process. Besides laying a theoretical foundation for development of the prototype, the kinematics and dynamics studies on the quadruped walking robot also boost the theoretical research of the quadruped walking and the practical applications of parallel mechanism.

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

NASA Astrophysics Data System (ADS)

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

2017-11-01

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

Quaternion-Based Conversion Formulas for Kinematic Attitude of Floating Offshore Wind Turbines (FOWT)

NASA Astrophysics Data System (ADS)

Li, Yugang; Fu, Gaoyong

2018-01-01

A floater allowing large-angle motion supporting a large payload (wind turbine and nacelle) with large aerodynamic loads high above the water surface is a great challenge because of the raised center of gravity and large overturning moment. In this paper, the conversion formulas between Euler angles and quaternions were derived, the research offered an efficient methodology without singularity to compute large-angle rigid body rotations of a FOWT, which laid the foundation for quaternion-based attitude kinematic model introduced to describe the dynamic response of the FOWT system and further solution.

Payload Configurations for Efficient Image Acquisition - Indian Perspective

NASA Astrophysics Data System (ADS)

Samudraiah, D. R. M.; Saxena, M.; Paul, S.; Narayanababu, P.; Kuriakose, S.; Kiran Kumar, A. S.

2014-11-01

The world is increasingly depending on remotely sensed data. The data is regularly used for monitoring the earth resources and also for solving problems of the world like disasters, climate degradation, etc. Remotely sensed data has changed our perspective of understanding of other planets. With innovative approaches in data utilization, the demands of remote sensing data are ever increasing. More and more research and developments are taken up for data utilization. The satellite resources are scarce and each launch costs heavily. Each launch is also associated with large effort for developing the hardware prior to launch. It is also associated with large number of software elements and mathematical algorithms post-launch. The proliferation of low-earth and geostationary satellites has led to increased scarcity in the available orbital slots for the newer satellites. Indian Space Research Organization has always tried to maximize the utility of satellites. Multiple sensors are flown on each satellite. In each of the satellites, sensors are designed to cater to various spectral bands/frequencies, spatial and temporal resolutions. Bhaskara-1, the first experimental satellite started with 2 bands in electro-optical spectrum and 3 bands in microwave spectrum. The recent Resourcesat-2 incorporates very efficient image acquisition approach with multi-resolution (3 types of spatial resolution) multi-band (4 spectral bands) electro-optical sensors (LISS-4, LISS-3* and AWiFS). The system has been designed to provide data globally with various data reception stations and onboard data storage capabilities. Oceansat-2 satellite has unique sensor combination with 8 band electro-optical high sensitive ocean colour monitor (catering to ocean and land) along with Ku band scatterometer to acquire information on ocean winds. INSAT- 3D launched recently provides high resolution 6 band image data in visible, short-wave, mid-wave and long-wave infrared spectrum. It also has 19 band sounder for providing vertical profile of water vapour, temperature, etc. The same system has data relay transponders for acquiring data from weather stations. The payload configurations have gone through significant changes over the years to increase data rate per kilogram of payload. Future Indian remote sensing systems are planned with very high efficient ways of image acquisition. This paper analyses the strides taken by ISRO (Indian Space research Organisation) in achieving high efficiency in remote sensing image data acquisition. Parameters related to efficiency of image data acquisition are defined and a methodology is worked out to compute the same. Some of the Indian payloads are analysed with respect to some of the system/ subsystem parameters that decide the configuration of payload. Based on the analysis, possible configuration approaches that can provide high efficiency are identified. A case study is carried out with improved configuration and the results of efficiency improvements are reported. This methodology may be used for assessing other electro-optical payloads or missions and can be extended to other types of payloads and missions.

Spacelab Level 4 Programmatic Implementation Assessment Study. Volume 1: Representative payload definition

NASA Technical Reports Server (NTRS)

1978-01-01

Four types of Spacelab payloads were analyzed; these were considered to be representative of the Spacelab traffic model. The payloads were: (1) space processing - a single pallet payload; (2) combined astronomy - a five pallet payload; (3) life sciences - a long module payload; and (4) advanced technology lab - a short module plus train payload.

Shuttle payload interface verification equipment study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1976-01-01

A preliminary design analysis of a stand alone payload integration device (IVE) is provided that is capable of verifying payload compatibility in form, fit and function with the shuttle orbiter prior to on-line payload/orbiter operations. The IVE is a high fidelity replica of the orbiter payload accommodations capable of supporting payload functional checkout and mission simulation. A top level payload integration analysis developed detailed functional flow block diagrams of the payload integration process for the broad spectrum of P/L's and identified degree of orbiter data required by the payload user and potential applications of the IVE.

Integrating International Space Station payload operations

NASA Technical Reports Server (NTRS)

Noneman, Steven R.

1996-01-01

The payload operations support for the International Space Station (ISS) payload is reported on, describing payload activity planning, payload operations control, payload data management and overall operations integration. The operations concept employed is based on the distribution of the payload operations responsibility between the researchers and ISS partners. The long duration nature of the ISS mission dictates the geographical distribution of the payload operations activities between the different national centers. The coordination and integration of these operations will be assured by NASA's Payload Operations Integration Center (POIC). The prime objective of the POIC is the achievement of unified operations through communication and collaboration.

National geotechnical centrifuge

NASA Technical Reports Server (NTRS)

Hallam, J. A.; Kunz, N.; Vallotton, W. C.

1982-01-01

A high G-ton centrifuge, able to take a 2700 kg (6000 lb) payload up to 300 G, is described. The stability of dams and embankments, the bearing capacity of soil foundations, and the dynamic behavior of foundations due to vibration of machinery are examples of applications. A power rating of 6,000 kW (9,000 hp) was established for the motor. An acceptable maximum speed of 70 rpm was determined. A speed increase with a ratio of 1:3 is discussed. The isolated tension straps, the anti-spreader bar and the flexwall bucket, and safety precautions are also discussed.

Resin Transfer Moldable Polyimides Developed for High-Temperature Applications

NASA Technical Reports Server (NTRS)

Meador, Mary Ann

2000-01-01

High-temperature polyimides, such as PMR 15 (which was developed at the NASA Glenn Research Center at Lewis Field), are becoming an increasingly important class of materials for a variety of aerospace applications, such as aircraft engine components and propulsion and airframe components for reusable launch vehicles (RLV s). Because of their high specific strength and low density, use of these materials in place of more traditional aerospace materials, such as titanium, can significantly reduce component and vehicle weight, leading to reductions in fuel consumption (and pollutants), increases in payload and passenger capacity, and improvements in vehicle performance.

Suborbital Applications in Astronomy and Astrophysics

NASA Technical Reports Server (NTRS)

Unwin, Steve; Werner, Mike; Goldsmith, Paul

2012-01-01

Suborbital flights providing access to zero-g in a space environment - Demonstrating new technologies in a relevant environment. - Flight testing of individual elements of a constellation. - Raising the TRL of critical technologies for subsystems on future large missions High-altitude balloons (up to 10 kg payload) -Access to near-space for wavelengths not observable from the ground. -Raising the TRL of critical technologies for subsystems on future large missions. -UV Detector testing.

Interior of Spacewedge #3

NASA Image and Video Library

1996-01-22

This photo shows the instrumentation and equipment inside the Spacewedge #3, a remotely-piloted research vehicle flown at the Dryden Flight Research Center, Edwards, California, to help develop technology for autonomous return systems for spacecraft as well as methods to deliver large Army cargo payloads to precise landings.

Basic relationships for LTA technical analysis

NASA Technical Reports Server (NTRS)

Ausrotas, R. A.

1975-01-01

An introduction to airship performance is presented. Static lift equations are shown which, when combined with power requirements for conventional airships, allow parametric studies of range, payload, speed and airship size. It is shown that very large airships are required to attain reasonable speeds at transoceanic ranges.

Hybrid Propulsion Technology Program

NASA Technical Reports Server (NTRS)

Jensen, G. E.; Holzman, A. L.

1990-01-01

Future launch systems of the United States will require improvements in booster safety, reliability, and cost. In order to increase payload capabilities, performance improvements are also desirable. The hybrid rocket motor (HRM) offers the potential for improvements in all of these areas. The designs are presented for two sizes of hybrid boosters, a large 4.57 m (180 in.) diameter booster duplicating the Advanced Solid Rocket Motor (ASRM) vacuum thrust-time profile and smaller 2.44 m (96 in.), one-quater thrust level booster. The large booster would be used in tandem, while eight small boosters would be used to achieve the same total thrust. These preliminary designs were generated as part of the NASA Hybrid Propulsion Technology Program. This program is the first phase of an eventual three-phaes program culminating in the demonstration of a large subscale engine. The initial trade and sizing studies resulted in preferred motor diameters, operating pressures, nozzle geometry, and fuel grain systems for both the large and small boosters. The data were then used for specific performance predictions in terms of payload and the definition and selection of the requirements for the major components: the oxidizer feed system, nozzle, and thrust vector system. All of the parametric studies were performed using realistic fuel regression models based upon specific experimental data.

Places Only Sails Can Go

NASA Technical Reports Server (NTRS)

Montgomery, Edward E., IV; Heaton, Andrew F.; Garbe, Gregory P.

2003-01-01

Solar sails are a near term, low thrust, propellantless propulsion technology suitable for orbital maneuvering, station keeping, and attitude control applications for small payloads. Furthermore, these functions can be highly integrated, reducing mass, cost and complexity. The solar sail concept is based on momentum exchange with solar flux reflected from a large, deployed thin membrane. Thrust performance increases as the square of the distance to the sun. In comparison to conventional chemical systems, there are missions where solar sails are vastly more and less economical. The less attractive applications involve large payloads, outer solar system transfers, and short trip times. However, for inclination changes and station keeping at locations requiring constant thrust, the solar sail is the only economical option for missions of more than a few weeks duration. We compare the location and energies required for these applications between solar sails, advanced electric propulsion, and conventional rockets. We address the effect on mass fraction to understand solar sail mission cost and capability. Finally, the benefit of potential applications to near term science missions is reported.

Structures-propulsion interactions and requirements. [large space structures

NASA Technical Reports Server (NTRS)

Coyner, J. V.

1982-01-01

The effects of low-thrust primary propulsion system characteristics on the mass, area, and orbit transfer characteristics of large space systems (LSS) were determined. Three general structural classes of LSS were considered, each with a broad range of diameters and nonstructural surface densities. While transferring the deployed structure from LEO and to GEO, an acceleration range of 0.02 to 0.1 g's was found to maximize deliverable payload based on structural mass impact. After propulsion system parametric analyses considering four propellant combinations produced values for available payload mass, length and volume, a thrust level range which maximizes deliverable LSS diameter was determined corresponding to a structure and propulsion vehicle. The engine start and/or shutdown thrust transients on the last orbit transfer (apogee) burn can impose transient loads which would be greater than the steady-state loads at the burnout acceleration. The effect of the engine thrust transients on the LSS was determined from the dynamic models upon which various engine ramps were imposed.

Status of advanced orbital transfer propulsion

NASA Technical Reports Server (NTRS)

Cooper, L. P.

1985-01-01

A new Orbital Transfer Vehicle (OTV) propulsion system that will be used in conjunction with the Space Shuttle, Space Station and Orbit Maneuvering Vehicle is discussed. The OTV will transfer men, large space structures and conventional payloads between low Earth and higher energy orbits. Space probes carried by the OTV will continue the exploration of the solar system. When lunar bases are established, the OTV will be their transportation link to Earth. Critical engine design considerations based upon the need for low cost payload delivery, space basing, reusability, aeroassist maneuvering, low g transfers of large space structures and man rating are described. The importance of each of these to propulsion design is addressed. Specific propulsion requirements discussed are: (1) high performance H2/O2 engine; (2) multiple engine configurations totalling no more than 15,000 lbf thrust 15 to 20 hr life; (3) space maintainable modular design; (4) health monitoring capability; and (5) safety and mission success with backup auxiliary propulsion.

Selection of shuttle payload data processing drivers for the data system new technology study

NASA Technical Reports Server (NTRS)

1976-01-01

An investigation of all payloads in the IBM disciplines and the selection of driver payloads within each discipline are described. The driver payloads were selected on the basis of their data processing requirements. These requirements are measured by a weighting scheme. The total requirements for each discipline are estimated by use of the technology payload model. The driver selection process which was both a payload by payload comparison and a comparison of expected groupings of payloads was examined.

SRM-Assisted Trajectory for the GTX Reference Vehicle

NASA Technical Reports Server (NTRS)

Riehl, John; Trefny, Charles; Kosareo, Daniel

2002-01-01

A goal of the GTX effort has been to demonstrate the feasibility of a single stage- to- orbit (SSTO) vehicle that delivers a small payload to low earth orbit. The small payload class was chosen in order to minimize the risk and cost of development of this revolutionary system. A preliminary design study by the GTX team has resulted in the current configuration that offers considerable promise for meeting the stated goal. The size and gross lift-off weight resulting from scaling the current design to closure however may be considered impractical for the small payload. In lieu of evolving the project's reference vehicle to a large-payload class, this paper offers the alternative of using solid-rocket motors in order to close the vehicle at a practical scale. This approach offers a near-term, quasi-reusable system that easily evolves to reusable SSTO following subsequent development and optimization. This paper presents an overview of the impact of the addition of SRM's to the GTX reference vehicle's performance and trajectory. The overall methods of vehicle modeling and trajectory optimization will also be presented. A key element in the trajectory optimization is the use of the program OTIS 3.10 that provides rapid convergence and a great deal of flexibility to the user. This paper will also present the methods used to implement GTX requirements into OTIS modeling.

SRM-Assisted Trajectory for the GTX Reference Vehicle

NASA Technical Reports Server (NTRS)

Riehl, John; Trefny, Charles; Kosareo, Daniel (Technical Monitor)

2002-01-01

A goal of the GTX effort has been to demonstrate the feasibility of a single stage-to-orbit (SSTO) vehicle that delivers a small payload to low earth orbit. The small payload class was chosen in order to minimize the risk and cost of development of this revolutionary system. A preliminary design study by the GTX team has resulted in the current configuration that offers considerable promise for meeting the stated goal. The size and gross lift-off weight resulting from scaling the current design to closure however may be considered impractical for the small payload. In lieu of evolving the project' reference vehicle to a large-payload class, this paper offers the alternative of using solid-rocket motors in order to close the vehicle at a practical scale. This approach offers a near-term, quasi-reusable system that easily evolves to reusable SSTO following subsequent development and optimization. This paper presents an overview of the impact of the addition of SRM's to the GTX reference vehicle#s performance and trajectory. The overall methods of vehicle modeling and trajectory optimization will also be presented. A key element in the trajectory optimization is the use of the program OTIS 3.10 that provides rapid convergence and a great deal of flexibility to the user. This paper will also present the methods used to implement GTX requirements into OTIS modeling.

A Vibration Isolation System for Use in a Large Thermal Vacuum Test Facility

NASA Technical Reports Server (NTRS)

Hershfeld, Donald; VanCampen, Julie

2002-01-01

A thermal vacuum payload platform that is isolated from background vibration is required to support the development of future instruments for Hubble Space Telescope (HST) and the Next Generation Space Telescope (NGST) at the Goddard Space Flight Center (GSFC). Because of the size and weight of the thermal/vacuum facility in which the instruments are tested, it is not practical to isolate the entire facility externally. Therefore, a vibration isolation system has been designed and fabricated to be installed inside the chamber. The isolation system provides a payload interface of 3.05 m (10 feet) in diameter and is capable of supporting a maximum payload weight of 4536 kg (10,000 Lbs). A counterweight system has been included to insure stability of payloads having high centers of gravity. The vibration isolation system poses a potential problem in that leakage into the chamber could compromise the ability to maintain vacuum. Strict specifications were imposed on the isolation system design to minimize leakage. Vibration measurements, obtained inside the chamber, prior to installing the vibration isolation system, indicated levels in all axes of approximately 1 milli-g at about 20 Hz. The vibration isolation system was designed to provide a minimum attenuation of 40 dB to these levels. This paper describes the design and testing of this unique vibration isolation system. Problems with leakage and corrective methods are presented. Isolation performance results are also presented.

Glutathione-mediated release of Bodipy® from PEG cofunctionalized gold nanoparticles

PubMed Central

Kumar, Dhiraj; Meenan, Brian J; Dixon, Dorian

2012-01-01

Gold nanoparticles synthesized via sodium citrate reduction of chloroauric acid (HAuCl4) were functionalized with either various concentrations of thiol-terminated Bodipy® FL L-cystine (0.5, 1.0, 1.5, and 2.0 μg/mL) or Bodipy-poly(ethylene glycol) at concentrations of 0.5–18.75, 1.0–12.50, and 1.5–6.25 μg/mL to form a mixed monolayer of BODIPY-PEG. Thiol-terminated Bodipy, a fluorescing molecule, was used as the model drug, while PEG is widely used in drug-delivery applications to shield nanoparticles from unwanted immune responses. Understanding the influence of PEG-capping on payload release is critical because it is the most widely used type of nanoparticle functionalization in drug delivery studies. It has been previously reported that glutathione can trigger release of thiol-bound payloads from gold nanoparticles. Bodipy release from Bodipy capped and from Bodipy-PEG functionalized gold nanoparticles was studied at typical intracellular glutathione levels. It was observed that the addition of PEG capping inhibits the initial burst release observed in gold nanoparticles functionalized only with Bodipy and inhibits nanoparticle aggregation. Efficient and controlled payload release was observed in gold nanoparticles cofunctionalized with only a limited amount of PEG, thus enabling the coattachment of large amounts of drug, targeting groups or other payloads. PMID:22915847

High Pressure Earth Storable Rocket Technology Program: Basic Program

NASA Technical Reports Server (NTRS)

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

1995-01-01

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

MACSAT - A Near Equatorial Earth Observation Mission

NASA Astrophysics Data System (ADS)

Kim, B. J.; Park, S.; Kim, E.-E.; Park, W.; Chang, H.; Seon, J.

MACSAT mission was initiated by Malaysia to launch a high-resolution remote sensing satellite into Near Equatorial Orbit (NEO). Due to its geographical location, Malaysia can have large benefits from NEO satellite operation. From the baseline circular orbit of 685 km altitude with 7 degrees of inclination, the neighboring regions around Malaysian territory can be frequently monitored. The equatorial environment around the globe can also be regularly observed with unique revisit characteristics. The primary mission objective of MACSAT program is to develop and validate technologies for a near equatorial orbit remote sensing satellite system. MACSAT is optimally designed to accommodate an electro-optic Earth observation payload, Medium-sized Aperture Camera (MAC). Malaysian and Korean joint engineering teams are formed for the effective implementation of the satellite system. An integrated team approach is adopted for the joint development for MACSAT. MAC is a pushbroom type camera with 2.5 m of Ground Sampling Distance (GSD) in panchromatic band and 5 m of GSD in four multi-spectral bands. The satellite platform is a mini-class satellite. Including MAC payload, the satellite weighs under 200 kg. Spacecraft bus is designed optimally to support payload operations during 3 years of mission life. The payload has 20 km of swath width with +/- 30 o of tilting capability. 32 Gbits of solid state recorder is implemented as the mass image storage. The ground element is an integrated ground station for mission control and payload operation. It is equipped with S- band up/down link for commanding and telemetry reception as well as 30 Mbps class X-band down link for image reception and processing. The MACSAT system is capable of generating 1:25,000-scale image maps. It is also anticipated to have capability for cross-track stereo imaging for Digital elevation Model (DEM) generation.

Commercial investigation results for the generic bioprocessing apparatus flown on United States Microgravity Laboratory-1

NASA Technical Reports Server (NTRS)

Stodieck, Louis S.; Robinson, M. C.; Luttges, M. W.

1994-01-01

The Generic Bioprocessing Apparatus (BPA) payload was developed by BioServe to support the commercial flight development needs of our specialized consortia comprised of business, academic, and government entities. The consortia have commitments to explore commercial opportunities in bioprocessing, biomedical models, and closed agricultural systems. In addition, some members of BioServe have interests in the development and/or qualification of enabling flight hardware used in life sciences space flight testing. Some business and academic entities have interests in more than one of these consortia. To aid in payload development, flight, and analysis, each consortium member contributes resources ranging from proprietary expertise and materials, to hardware and cash. Professionals from business, academia, and government often interact with each other via graduate research assistants who do much of the 'hands-on' payload preparation and subsequent data analyses. The GBA supported research, testing, and development activities for each different BioServe consortium. It produced an environment in which professionals from diverse backgrounds came together with a single focus. And, it provided a truly novel learning environment for a youthful new cadre of space professionals committed to the exploration of commercial opportunities presented by space. Since the GBA supported a large number of different experiments, this paper briefly describes the payload characteristics and the essential operations of the payload. A summary of the experiments is presented. Finally, a few of the experiments are described in detail highlighting some novel effects of space flight on life science systems. Portions of the reported work have or will appear in appropriate archival journals as cited in the bibliography. In several instances, data collected from USML-1 have been supplemented with related data collected on more recent STS missions.

Control system and method for payload control in mobile platform cranes

DOEpatents

Robinett, III, Rush D.; Groom, Kenneth N.; Feddema, John T.; Parker, Gordon G.

2002-01-01

A crane control system and method provides a way to generate crane commands responsive to a desired payload motion to achieve substantially pendulation-free actual payload motion. The control system and method apply a motion compensator to maintain a payload in a defined payload configuration relative to an inertial coordinate frame. The control system and method can further comprise a pendulation damper controller to reduce an amount of pendulation between a sensed payload configuration and the defined payload configuration. The control system and method can further comprise a command shaping filter to filter out a residual payload pendulation frequency from the desired payload motion.

Lightweight Liquid Helium Dewar for High-Altitude Balloon Payloads

NASA Technical Reports Server (NTRS)

Kogut, Alan; James, Bryan; Fixsen, Dale

2013-01-01

Astrophysical observations at millimeter wavelengths require large (2-to-5- meter diameter) telescopes carried to altitudes above 35 km by scientific research balloons. The scientific performance is greatly enhanced if the telescope is cooled to temperatures below 10 K with no emissive windows between the telescope and the sky. Standard liquid helium bucket dewars can contain a suitable telescope for telescope diameter less than two meters. However, the mass of a dewar large enough to hold a 3-to-5-meter diameter telescope would exceed the balloon lift capacity. The solution is to separate the functions of cryogen storage and in-flight thermal isolation, utilizing the unique physical conditions at balloon altitudes. Conventional dewars are launched cold: the vacuum walls necessary for thermal isolation must also withstand the pressure gradient at sea level and are correspondingly thick and heavy. The pressure at 40 km is less than 0.3% of sea level: a dewar designed for use only at 40 km can use ultra thin walls to achieve significant reductions in mass. This innovation concerns new construction and operational techniques to produce a lightweight liquid helium bucket dewar. The dewar is intended for use on high-altitude balloon payloads. The mass is low enough to allow a large (3-to-5-meter) diameter dewar to fly at altitudes above 35 km on conventional scientific research balloons without exceeding the lift capability of the balloon. The lightweight dewar has thin (250- micron) stainless steel walls. The walls are too thin to support the pressure gradient at sea level: the dewar launches warm with the vacuum space vented continuously during ascent to eliminate any pressure gradient across the walls. A commercial 500-liter storage dewar maintains a reservoir of liquid helium within a minimal (hence low mass) volume. Once a 40-km altitude is reached, the valve venting the vacuum space of the bucket dewar is closed to seal the vacuum space. A vacuum pump then evacuates the dewar vacuum space to provide the necessary thermal isolation. Liquid helium may then be transferred from the storage dewar into the bucket dewar to cool the telescope inside the bucket dewar. By splitting the functions of helium storage and in-flight thermal isolation, the parasitic mass associated with the dewar pressure vessel is eliminated to achieve factor-of-five or better reduction in mass. The lower mass allows flight on conventional scientific research balloons, even for telescopes 3 to 5 meters in diameter.

Commercial suborbital reusable launch vehicles: ushering in a new era for turbopause exploration (Invited)

NASA Astrophysics Data System (ADS)

Smith, H. T.

2013-12-01

Multiple companies are in the process of developing commercial suborbital reusable launch vehicles (sRLV's). While these companies originally targeted space tourism as the primary customer base, it is rapidly becoming apparent that this dramatic increase in low cost access to space could provide revolutionary opportunities for scientific research, engineering/instrument development and STEM education. These burgeoning capabilities will offer unprecedented opportunities regarding access to space with frequent low-cost access to the region of space from the ground to the boundary of near-Earth space at ~100 km. In situ research of this region is difficult because it is too high for aircraft and balloons and yet too low for orbital satellites and spacecraft. However, this region is very significant because it represents the tenuous boundary of Earth's Atmosphere and Space. It contains a critical portion of the atmosphere where the regime transitions from collisional to non-collisional physics and includes complex charged and neutral particle interactions. These new launch vehicles are currently designed for manned and unmanned flights that reach altitudes up to 110 km for 5K-500K per flight with payload capacity exceeding 600 kg. Considering the much higher cost per flight for a sounding rocket with similar capabilities, high flight cadence, and guaranteed return of payload, commercial spacecraft has the potential to revolutionize access to near space. This unprecedented access to space allows participation at all levels of research, engineering, education and the public at large. For example, one can envision a model where students can conduct complete end to end projects where they design, build, fly and analyze data from individual research projects for thousands of dollars instead of hundreds of thousands. Our community is only beginning to grasp the opportunities and impactions of these new capabilities but with operational flights anticipated in 2014, it is important for our community to start exploring possible applications for these new spacecraft.

Use of Remotely Piloted Aircraft System and LiDAR for Alpine forested Landslide

NASA Astrophysics Data System (ADS)

Borgniet, Laurent; Lachenal, Philippe; Berger, Frédéric

2017-04-01

In the last decade Remotely Piloted Aircraft Systems (RPAS) technologies considerably evolved, improving flight stability, GPS positioning and payload. Recent researches shown that RPAS-SfM framework, combining high volumes data acquisition and fast treatments capacity, make it suitable for environmental monitoring. However, monitoring, in a short period, an active landslide with major land displacements in a context of unstable and vegetated mountainous area still represent a real challenge. In this study, we aimed at developing a reproducible and optimized cost-efficiency method to accurately survey active terrain movements. The combined use of two RPAS allows to i)better visualize at large scale (1km2) the phenomenon dimensions and velocity in order to ii) focus our efforts on a safe topographic and photogrammetric data acquisition. The study area is a re-activated landslide previously reported in 1966 by forest management services located near Beaufort in the French Alps. For six time steps between April and September 2017, we acquired aerial photos with two reflex camera (Visible and Near Infra-Red Bands) mounted on a hexacopter with a payload up to 4kg. A validation campaign with aerial LiDAR and Terrestrial Laser Scanner took place on June 2017. Comparison of the digital Surface models and orthophotos derived from RPAS flights gave satisfactory results. Spatial analysis in a GIS allowed a quantitative evaluation of heterogeneous behaviors and dynamic distributions of materials (mineral and vegetal) along the slope. Estimations of displaced volumes (500 000 m3) constitute a precious information for improving in emergency crisis the calibration of deposits place in order to avoid jam and flood on the road network. In this research, we demonstrate the feasibility of a repetitive RPAS based data acquisition method but some limitations still remain. Research efforts will now focus on DEM under vegetation cover determination combining RPAS adapted LiDAR, improved RTK differential positioning systems and miniaturized Hyperspectral sensor.

14 CFR 415.59 - Information requirements for payload review.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Information requirements for payload review... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LAUNCH LICENSE Payload Review and Determination § 415.59 Information requirements for payload review. (a) A person requesting review of a particular payload or payload...

14 CFR 431.7 - Payload and payload reentry determinations.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Payload and payload reentry determinations. 431.7 Section 431.7 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... payload reentry determination is required to reenter a payload to Earth on an RLV unless the proposed...

The Micro-Instrumentation Package: A Solution to Lightweight Ballooning

NASA Astrophysics Data System (ADS)

Juneau, Jill

This paper discusses the design and testing of an over the horizon (OTH) light weight telemetry and termination system that can be used for small ballooning payloads. Currently, the Columbia Scientific Balloon Facility (CSBF) provides telemetry for the science payload by integrating one of two types of support packages. The type of support package integrated depends on whether the flight will stay in range of line of sight (LOS) or will exceed LOS requiring the use of over the horizon (OTH) telemetry. The weights of these systems range from 100 pounds to 350 pounds depending upon the use of redundant systems, equipment for high data rates, and batteries and/or solar panels for power requirements. These weight values are not as significant for larger payloads but can be crippling for smaller payloads. In addition, these support package systems are fairly expensive, placing a high importance on recovery. A lightweight and inexpensive telemetry system could be beneficial for various reasons. First, it would allow scientists to fly lightweight payloads on large balloons reaching even higher altitudes. Second, scientists could fly lightweight payloads on less expensive balloons such as meteorological balloons. Depending on the payload, these flights could be fairly inexpensive and even disposable. Third, a compact telemetry system on any balloon will free up more room for the science portion of the payload. In response, a compact telemetry/termination system called the Micro-Instrumentation Package (MIP) was developed. The MIP provides uplink and downlink communications, an interface to the science, housekeeping information including global positioning system (GPS) position, and relays. Instead of a power-hungry microprocessor, the MIP's central consists of a microcontroller. Microcontrollers are lower power, easily programmed, and can be purchased for less than ten dollars. For uplink and downlink telemetry, the MIP uses an LOS serial transceiver and an Iridium unit for OTH flights. A relay deck is also included for powering subsystems and for flight termination. Furthermore, the science will be able to interface to the MIP through a serial connection, although the data rates for the science interface will be limited compared to those of standard telemetry support packages. Overall, the MIP provides the basic necessities for the safe operation of a balloon flight without the weight and the expense of the current CSBF telemetry support packages. This paper will explain more about CSBF operations and delve further into the MIP development, testing and capabilities.

14 CFR 415.57 - Payload review.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Payload review. 415.57 Section 415.57... TRANSPORTATION LICENSING LAUNCH LICENSE Payload Review and Determination § 415.57 Payload review. (a) Timing. A payload review may be conducted as part of a license application review or may be requested by a payload...

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

NASA Technical Reports Server (NTRS)

Uhran, Mark L.; Timm, Marc G.

1993-01-01

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

Satellite situation report, volume 33, number 4

NASA Technical Reports Server (NTRS)

1993-01-01

The Satellite Situation Report is a listing of those satellites (objects) currently in orbit and those which have previously orbited the Earth. Some objects are too small or too far from the Earth's surface to be detected; therefore, the Satellite Situation Report does not include all manmade objects orbiting the Earth. Generally, satellites are classified as follows: (1) Payloads may contain one or more functioning or nonfunctioning experiments. Usually only the owners of the satellites know if the experiments are functioning, and there is no one source which indicates the operational status of all payloads and/or experiments. Payloads are normally the first listed in the Satellite Situation Report, i.e., 1982 087A, unless there are multiple payloads for the launch. In which case, the first objects cataloged are usually all payloads, unless a subsequent payload is later identified after objects other than payloads have been cataloged. (2) Platforms are used to support a payload while it is being placed into orbit. A platform may remain in orbit long after its purpose is served, usually longer than rocket bodies. It is usually the first object identified in the Satellite Situation Report listing after the payload(s), i.e., 1982 087B (when a platform is not used, the first object after the payload(s) is usually the rocket body). (3) Rocket bodies are used to place the payload and platform (if one is used) into orbit. Some launches may have more than one rocket body because of the payload weight or the type of orbit or experiment. Most rocket bodies decay within a short time after the payload (and platform) have achieved orbit. Rocket bodies are usually the third object listed in the Satellite Situation Report after the payload(s), i.e., 1982 087C. (4) Debris in orbit occurs when parts (nose cone shrouds, lens or hatch covers) are separated from the payload, when rocket bodies or payloads disintegrate or explode, or when objects are placed into free space from manned orbiting spacecraft during operations. Debris is detected by its size and distance from the Earth. Debris objects are the last objects after payload(s), platform, and rocket body(s) listed in the Satellite Situation Report, i.e., 1982 087D, 1982 087E, 1982 087F.

Measurement of Solar Neutrons on 05 March 2012, Using a Fiber-Type Neutron Monitor Onboard the Attached Payload to the ISS

NASA Astrophysics Data System (ADS)

Koga, K.; Muraki, Y.; Masuda, S.; Shibata, S.; Matsumoto, H.; Kawano, H.

2017-08-01

The solar neutron detector Space Environment Data Acquisition Equipment - Attached Payload (SEDA-FIB) onboard the International Space Station (ISS) detected several events from the solar direction associated with three large solar flares observed on 05 (X1.1), 07 (X5.4), and 09 (M6.3) March 2012. In this study, we focus on the interesting event of 05 March, present the temporal profiles of the neutrons, and discuss the physics that may be related to a possible acceleration scenario for ions above the solar surface. We compare our data with images of the flares obtained by the ultraviolet telescope Atmospheric Imaging Assembly (AIA) onboard the Solar Dynamics Observatory (SDO).

A reconfigurable robot with tensegrity structure using nylon artificial muscle

NASA Astrophysics Data System (ADS)

Wu, Lianjun; de Andrade, Monica Jung; Brahme, Tarang; Tadesse, Yonas; Baughman, Ray H.

2016-04-01

This paper describes the design and experimental investigation of a self-reconfigurable icosahedral robot for locomotion. The robot consists of novel and modular tensegrity structures, which can potentially maneuver in unstructured environments while carrying a payload. Twisted and Coiled Polymer (TCP) muscles were utilized to actuate the tensegrity structure as needed. The tensegrity system has rigid struts and flexible TCP muscles that allow keeping a payload in the central region. The TCP muscles provide large actuation stroke, high mechanical power per fiber mass and can undergo millions of highly reversible cycles. The muscles are electrothermally driven, and, upon stimulus, the heated muscles reconfigure the shape of the tensegrity structure. Here, we present preliminary experimental results that determine the rolling motion of the structure.

KSC-08pd2340

NASA Image and Video Library

2008-08-07

CAPE CANAVERAL, Fla. – The Fine Guidance Sensor, or FGS, is being prepared for backlight inspection and cleaning in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The FGS is part of the payload for the fifth and final Hubble servicing mission, STS-125, aboard space shuttle Atlantis. An FGS consists of a large structure housing a collection of mirrors, lenses, servos, prisms, beam splitters and photomultiplier tubes. There are three fine guidance sensors on Hubble located at 90-degree intervals around the circumference of the telescope. Along with the gyroscopes, the optical sensors are a key component of Hubble’s highly complex but extraordinarily effective “pointing control system.” Atlantis is targeted to launch Oct. 8. Photo credit: NASA/Jack Pfaller

KSC-98pc542

NASA Image and Video Library

1998-04-28

The SPACEHAB Single Module is raised by crane from a transporter in KSC's Space Station Processing Facility, where it will be moved to the payload canister. It will be joined in the canister by the Alpha Magnetic Spectrometer-01 payload before being moved to Launch Pad 39A for the STS-91 mission, scheduled to launch June 2 at around 6:04 p.m. EDT. SPACEHAB is used mainly as a large pressurized cargo container for science, logistical equipment and supplies to be exchanged between the orbiter Discovery and the Russian Space Station Mir. The nearly 10-day flight of STS-91 also is scheduled to return the sixth American, Mission Specialist Andrew Thomas, Ph.D., aboard the Russian orbiting outpost safely to Earth

KSC-08pd1359

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, technicians lower NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft toward the payload attach fitting. The fitting will eventually be used to mate GLAST to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1358

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, technicians lower NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft toward the payload attach fitting. The fitting will eventually be used to mate GLAST to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1360

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, technicians check the placement of NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft on the payload attach fitting. The fitting will eventually be used to mate GLAST to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1352

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft is being prepared for a move to an payload attach fitting that will eventually be used to mate GLAST to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1354

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft will be installed on this payload attach fitting that will eventually be mated to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1356

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, technicians prepare the payload attach fitting that will receive NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft. The fitting will eventually be used to mate GLAST to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1361

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, technicians check the attachment of NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft on the payload attach fitting. The fitting will eventually be used to mate GLAST to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1355

NASA Image and Video Library

2008-05-14

CAPE CANAVERAL, Fla. -- At the Astrotech payload processing facility, technicians prepare NASA's Gamma-Ray Large Area Space Telescope, or GLAST, spacecraft for its move to the payload attach fitting that will eventually be used to mate GLAST to the Delta II launch vehicle. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date still is to be determined. Photo credit: NASA/Jim Grossmann

Technical and economic assessment of span-distributed loading cargo aircraft concepts

NASA Technical Reports Server (NTRS)

Whitlow, D. H.; Whitner, P. C.

1976-01-01

A preliminary design study of the performance and economics resulting from the application of the distributed load concept to large freighter aircraft was made. The study was limited to configurations having the payload entirely contained in unswept wings of constant chord with conventional tail surfaces supported from the wing by twin booms. A parametric study based on current technology showed that increases in chord had a similar effect on the economics as increases in span. Increases in both span and chord or airplane size had the largest and most favorable effect. At 600,000 lbs payload a configuration was selected and refined to incorporate advanced technology that could be in production by 1990 and compared with a reference conventional airplane having similar technology.

KSC-08pd3323

NASA Image and Video Library

2008-10-22

CAPE CANAVERAL, Fla. - In the Payload Changeout Room, or PCR, on Launch Pad 39A at NASA's Kennedy Space Center in Florida, workers use the payload ground-handling mechanism to transfer space shuttle Endeavour's STS-126 mission payload from the payload canister. The payload is the Multi-Purpose Logistics Module Leonardo and the Lightweight Multi-Purpose Experiment Support Structure Carrier. The payload later will be installed in Endeavour's payload bay. Endeavour is targeted for launch on Nov. 14. Photo credit: NASA/Kim Shiflett

Space Construction Experiment Definition Study (SCEDS), part 2. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1982-01-01

A baseline Space Construction Experiment (SCE) concept is defined. Five characteristics were incorporated: (1) large space system (LSS) element test, (2) shuttle mission payload of opportunity, (3) attachment to Orbiter with jettison capability, (4) Orbiter flight control capabilities, and (5) LSS construction and assembly operations.

KSC-02pd0103

NASA Image and Video Library

2002-01-29

KENNEDY SPACE CENTER, FLA. -- Workers in the Vertical Processing Facility get the Large Orbital Protective Enclosure (LOPE) ready to move to the Multi-Use Lightweight Equipment (MULE) carrier. The LOPE contains part of the payload on the Hubble Space Telescope Servicing Mission, STS-109, scheduled to launch Feb. 28 from Launch Pad 39A

KSC-02pd0102

NASA Image and Video Library

2002-01-29

KENNEDY SPACE CENTER, FLA. -- Workers in the Vertical Processing Facility get the Large Orbital Protective Enclosure (LOPE) ready to move to the Multi-Use Lightweight Equipment (MULE) carrier. The LOPE contains part of the payload on the Hubble Space Telescope Servicing Mission, STS-109, scheduled to launch Feb. 28 from Launch Pad 39A

KSC-02pd0101

NASA Image and Video Library

2002-01-29

KENNEDY SPACE CENTER, FLA. -- Workers in the Vertical Processing Facility get the Large Orbital Protective Enclosure (LOPE) ready to move to the Multi-Use Lightweight Equipment (MULE) carrier. The LOPE contains part of the payload on the Hubble Space Telescope Servicing Mission, STS-109, scheduled to launch Feb. 28 from Launch Pad 39A