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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 37 records · Page 2
All sourcesNASA NTRSDOE OSTI
NASA NTRS1975

Atmospheric science facility pallet-only mode space transportation system payload (feasibility study), Volume 1

The economic and technical feasibility is assessed of employing a pallet-only mode for conducting Atmospheric Magnetospheric Plasmas-in-Space experiments. A baseline design incorporating the experiment and instrument descriptions is developed. The prime instruments are packaged into four pallets in a physical and functional manner compatible with the Space Transportation System capabilities and/or constraints and an orbiter seven-day mission timeline. Operational compatibility is verified between the orbiter/payload and supporting facilities. The development status and the schedule requirements applicable to the Atmospheric Science Facility mission are identified. Conclusions and recommendations are presented and discussed.

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NASA NTRS1983

Portable Pallet-Weighing Apparatus

Portable apparatus intended for standard four-trunnion pallets readily adaptable to any large payload or other loads where shifting of cargo is to be avoided. Device lifts trunnion of pallet short distance above its resting place. Weight at trunnion applied to load cell. Similar units placed at all four trunnions.

Day, R. M.↗
NASA NTRS1982

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

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

Keegan, W. B.↗
NASA NTRS1995

The BMDO Thruster-on-a-Pallet Program

The Ballistic Missile Defense Organization sponsors an aggressive program to develop and demonstrate electric propulsion and space power technologies for future missions. This program supports a focused effort to design, fabricate, and space qualify a Russian Hall thruster system-on-a-pallet ready to take advantage of a near-term flight opportunity. The Russian Hall Effect Thruster Technology (RHETT) program will demonstrate an integrated pallet design in late FY95. The program also includes a parallel effort to develop advanced Solar Concentrator Arrays with Refractive Linear Element Technology (SCARLET). This synergistic technology will be demonstrated in a flight experiment this summer on the Comet satellite. This paper provides an overview of the RHETT and SCARLET programs with an emphasis on electric propulsion, recent progress, and near-term program plans.

Caveny, Leonard H.↗
NASA NTRS1974

TERSSE: Definition of the Total Earth Resources System for the Shuttle Era. Volume 6: An Early Shuttle Pallet Concept for the Earth Resources Program

A space shuttle sortie mission which can be performed inexpensively in the early shuttle era and which, if the necessary intermediate steps are accomplished provides a major technological advance for the user organization-the U.S. Bureau of Census is described. The orbital configuration created for the Urban Land Use/1980 Census mission is illustrated including sensors and ground support equipment along with the information flow for the mission. Factors discussed include: specific Census Bureau functions to be supported by the mission; hardware and flight operations necessary for implementation of the mission; and integration of the TERSSE pallet into a shuttle mission.

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NASA NTRS1976

Addendum report to atmospheric science facility pallet-only mode space transportation system payload feasibility study, volume 3, revision A

The feasibility of accomplishing selected atmospheric science mission using a pallet-only mode was studied. Certain unresolved issues were identified. The first issue was that of assuring that the on-board computer facility was adequate to process scientific data, control subsystems such as instrument pointing, provide mission operational program capability, and accomplish display and control. The second issue evolved from an investigation of the availability of existing substitute instruments that could be used instead of the prime instrumentation where the development tests and schedules are incompatible with the realistic budgets and shuttle vehicle schedules. Some effort was expended on identifying candidate substitute instruments, and the performance, cost, and development schedule trade-offs found during that effort were significant enough to warrant a follow-on investigation. This addendum documents the results of that follow-on effort, as it applies to the Atmospheric Sciences Facility.

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NASA NTRS1976

Preliminary feasibility study of pallet-only mode for magnetospheric and plasmas in space payloads, volume 4

Results of studies performed on the magnetospheric and plasma portion of the AMPS are presented. Magnetospheric and plasma in space experiments and instruments are described along with packaging (palletization) concepts. The described magnetospheric and plasma experiments were considered as separate entities. Instrumentation ospheric and plasma experiments were considered as separate entities. Instrumentation requirements and operations were formulated to provide sufficient data for unambiguous interpretation of results without relying upon other experiments of the series. Where ground observations are specified, an assumption was made that large-scale additions or modifications to existing facilities were not required.

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NASA NTRS1982

Spacelab Mission 2 pallet-only mode verification flight

The first two flights of Spacelab are intended to verify the utility and flexibility of all elements of the Spacelab inventory, incorporating an array of interchangeable components including pressurized manned laboratories, unpressurized platforms, and related support systems, which can be assembled in several different configurations of pallets and pressurized modules depending on the specific requirements of the mission. System performance will be monitored by flight instrumentation. Attention is given to Mission 2's unique payload-integration equipment and the general problem of mission planning.

Lester, R. C.↗
NASA NTRS1984

Development of baseline random vibration environment criteria for Shuttle pallet payload subsystems

This paper presents a statistical evaluation of measured random vibration response data obtained from the Office of Space Science-1 (OSS-1) pallet payload. The data were measured during the acoustic test simulation (September 1980) and the ascent phase of the flight of STS-3, Orbiter 102 (launched from the Kennedy Space Center on March 22, 1982). Acoustic test efficiency factors are evaluated based on the Dynamic, Acoustic and Thermal Environments (DATE) instrumentation as the source of the measured vibration data. Test efficiency correction to test data is applied in the extrapolation of non-DATE acoustic test data to increase sample population size for improved statistical evaluation. For baseline criteria evaluation and development, data are grouped in accordance with the payload zone in which the component is mounted.

On, F. J.↗
NASA NTRS1983

Development of baseline random vibration criteria for STS pallet payloads

This paper presents a statistical evaluation of measured random vibration response data obtained from the Office of Space Science-1 (OSS-1) pallet payload. The data were measured during the acoustic test simulation (September 1980) and the ascent phase of the flight of STS-3, Orbiter 102 (launched from the Kennedy Space Center on March 22, 1982). Acoustic test efficiency factors are evaluated based on the Dynamic, Acoustic and Thermal Environments (DATE) instrumentation as the source of the measured vibration data. Test efficiency correction to test data is applied in the extrapolation of non-DATE acoustic test data to increase sample population size for improved statistical evaluation. For baseline criteria evaluation and development, data are grouped in accordance with the payload 'zone' in which the component is mounted.

On, F. J.↗
NASA NTRS1995

International Space Station EXPRESS Pallet. Ground Demonstration Baseline Design Review

This publication is comprised of the viewgraphs from the presentations of the EXPRESS Pallet Baseline Design Review meeting held July 20, 1995. Individual presentations addressed general requirements and objectives; mechanical, electrical, and data systems; software; operations and KSC (Kennedy Space Center) integration; payload candidates; thermal considerations; ground vs. flight demo; and recommended actions.

Schaffer, James R.↗
NASA NTRS2014

Optimization of a Lunar Pallet Lander Reinforcement Structure Using a Genetic Algorithm

This paper presents a design automation process using optimization via a genetic algorithm to design the conceptual structure of a Lunar Pallet Lander. The goal is to determine a design that will have the primary natural frequencies at or above a target value as well as minimize the total mass. Several iterations of the process are presented. First, a concept optimization is performed to determine what class of structure would produce suitable candidate designs. From this a stiffened sheet metal approach was selected leading to optimization of beam placement through generating a two-dimensional mesh and varying the physical location of reinforcing beams. Finally, the design space is reformulated as a binary problem using 1-dimensional beam elements to truncate the design space to allow faster convergence and additional mechanical failure criteria to be included in the optimization responses. Results are presented for each design space configuration. The final flight design was derived from these results.

Burt, Adam O.↗
NASA NTRS2019

Mission Design for the Lunar Pallet Lander

Marshall Space Flight Center is developing a small lunar lander capable of delivering up to 300 kg of payload to the lunar surface near the North or South Pole. Originally designed as a lander for a small rover, the Lunar Pallet Lander, has seen several design iterations over the last couple of years. This paper will cover how the vehicle and mission design changed from being a co-manifested payload candidate in NASA’s Space Launch System to its current design, which could be launched with an Evolved Expendable Launch Vehicle (EELV), and reach a wide range of polar landing sites.

Craig, A. S.↗
NASA NTRS2019

Guidance, Navigation, and Control for NASA Lunar Pallet Lander

The NASA Lander Technology project is leading the development and integration of the Lunar Pallet Lander (LPL) concept. The objective is to demonstrate precision landing by delivering a payload to the lunar surface within 100 meters of a landing target. Potential landing sites are selected near the lunar pole where water may be present in permanently shadowed regions that could enable future in-situ resource utilization. The LPL is part of a sequence of missions aimed at maturing the necessary technologies, such as lunar precision landing sensors, that will enable the next generation of multi-ton lunar payloads and human landers. This paper provides an overview of the Mission Design, Guidance Navigation and Control (GNC) algorithms, and sensor suite. The results show the LPL simulated trajectory and landing precision performance under nominal and dispersed conditions. The landing precision simulation confirms the need to rely on high-accuracy navigation techniques and sensors such as Terrain Relative Navigation (TRN) and the Navigation Doppler Lidar (NDL), currently being developed for space applications. The results also demonstrate the ability of the guidance and control system to perform a soft lunar touchdown by combining thrust vector control during the solid rocket motor deceleration phase, and pulse engine control, for the liquid powered descent phase.

Orphee, Juan↗
NASA NTRS2019

Guidance and Navigation Design Trades for the Lunar Pallet Lander

This paper provides an overview of a series of design trades in support of the NASA Lunar Pallet Lander (LPL) project. The vehicle is being designed to enable a high mass landing capability on the Lunar surface with a high precision. In order to provide clear requirements definition and preliminary design, the Guidance and Navigation Teams are assessing areas such as algorithm development, sensor architectures, and system-level sensitivities. These trades are enabled by the de-tailed six degree of freedom analysis tools. This mature simulation with the capability for closed- and open-loop simulation modes allows for high fidelity modeling and understanding of the system under design. The results show the feasibility and performance of the current vehicle to meet high accuracy landing requirements.

Anzaline, Evan↗