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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 451 records · Page 25
All sourcesNASA NTRSDOE OSTI
NASA NTRS1973

Study for identification of Beneficial Uses of Space (BUS) (phase 2). Volume 1: Executive summary

A study was conducted to analyze the benefits to the world which can be realized from space manufacturing processes. The study envisaged the use of the space shuttle and manned space stations for the purpose. For each proposed operation a data base and rationale were established for those processes or portions of processes which would be improved by performance in the orbital environment. The four experiments which were recommended for the initial investigation are identified. The procedures for conducting the weightless manufacturing processes are outline.

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NASA NTRS1972

Space shuttle system program definition. Volume 1: Executive summary

A study for the selection of a low cost shuttle system for design and development was conducted. The objective of the final study was to examine and penetrate the major technical and cost issues affecting the choice of the following: (1) liquid propulsion recoverable or solid propulsion recoverable booster, (2) parallel burn/parallel mount or series burn/tandem mount configurations, and (3) payload weight and payload bay size of the orbiter. The matrix of program options which were considered in the study is developed.

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NASA NTRS1974

Reusable Agena study. Volume 1: Executive summary

The shuttle Agena upper stage interim tug concept is based on a building block approach. These building block concepts are extensions of existing ascent Agena configurations. Several current improvements, have been used in developing the shuttle/Agena upper stage concepts. High-density acid is used as the Agena upper stage oxidizer. The baffled injector is used in the main engine. The DF-224 is a fourth generation computer currently in development and will be flight proven in the near future. The Agena upper stage building block concept uses the current Agena as a baseline, adds an 8.5-inch (21.6 cm) extension to the fuel tank for optimum mixture ratio, uses monomethyl hydrazine as fuel, exchanges a 150:1 nozzle extension for the existing 45:1, exchanges an Autonetics DF-224 for the existing Honeywell computer, and adds a star sensor for guidance update. These modifications to the current Agena provide a 5-foot (1.52m) diameter shuttle/Agena upper stage that will fly all Vandenberg Air Force Base missions in the reusable mode without resorting to a kick motor. The delta V velocity of the Agena is increased by use of a strap-on propellant tank option. This option provides a shuttle/Agena upper stage with the capability to place almost 3900 pounds (1769 kg) into geosynchronous orbit (24 hour period) without the aid of kick motors.

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NASA NTRS1972

Space shuttle phase B. Volume 1: Executive summary

A study was conducted to identify the differences among total system concepts of space shuttle configurations. Emphasis was placed on concepts that lead to selection of a system that performs the missions within budget and schedule constraints. The spectrum of launch vehicle configurations is illustrated. An inboard profile of the spacecraft is presented to show the interior arrangement of the major subsystems. The performance prediction of the spacecraft during specified portions of the mission is analyzed. A cost comparison of the various concepts is included.

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NASA NTRS1974

Reusable Centaur study. Volume 1: Executive summary

A study of the Reusable Centaur for use as an initial upper stage with the space shuttle was conducted. The currently operative Centaur stage, with modifications for space shuttle orbiter compatibility and for improved performance, represents a cost effective development solution. The performance needs and available development funds are discussed. The main features of three Reusable Centaur configurations with increasing capability at increasing development costs are summarized.

Heald, D. A.↗
NASA NTRS1974

Configuration and design study of manipulator systems applicable to the free flying teleoperator. Volume 1: Executive summary

A preliminary design of a manipulator system, applicable to a free flying teleoperator spacecraft operating in conjunction with the shuttle or tug, is presented. A new control technique is proposed for application to the manipulator system. This technique, a range/azimuth/elevation rate-rate mode, was selected based upon the results of man-in-the-loop simulations. Several areas are identified in which additional emphasis must be placed prior to the development of the manipulator system. The study results in a manipulator system which will provide an effective method for servicing, maintaining, and repairing satellites to increase their useful life.

Tewell, J. R.↗
NASA NTRS1974

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

The definition and integration tasks involved in the development of design concepts for a carry-on laboratory (COL), to be compatible with Spacelab operations, were divided into the following study areas: (1) identification of research and equipment requirements of the COL; (2) development of a number of conceptual layouts for COL based on the defined research of final conceptual designs; and (4) development of COL planning information for definition of COL/Spacelab interface data, cost data, and program cost schedules, including design drawings of a selected COL to permit fabrication of a functional breadboard.

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NASA NTRS1974

Space processing applications payload equipment study. Volume 1: Executive summary

A study was conducted to derive and collect payload information on the anticipated space processing payload requirements for the Spacelab and space shuttle orbiter planning activities. The six objectives generated by the study are defined. Concepts and requirements for space processing payloads to accommodate the performance of the shuttle-supported research phase are analyzed. Diagrams and tables of data are developed to show the experiments involved, the power requirements, and the payloads for shared missions.

Hammel, R. L.↗
NASA NTRS1973

Payload design requirements analysis (study 2.2). Volume 1: Executive summary

Research was conducted to provide data on ways to effectively realize the projected cost reductions for payloads to be developed and operated in the shuttle era. Prior studies have indicated that the Shuttle concept of satellite operations will lead to a large reduction in overall payload cost. This study provides the data and insight into the methods of accomplishing these economic benefits. The study examined only payloads that will be launched on the shuttle/tug/sortie lab combinations. These payloads are of four types: (1) expendable; (2) ground refurbishable; (3) on-orbit maintainable; and (4) sortie. The expendable payloads are intended specifically for the shuttle/tug and not for expendable launch vehicles. Economic comparisons were made only between these four types of shuttle payloads and not between these payloads and current expendable launch vehicle payloads.

Shiokari, T.↗
NASA NTRS1973

Design fabrication, testing, and delivery of shuttle heat pipe leading edge test modules. Volume 1: Executive summary

The construction of two test modules is presented for a feasibility demonstration of a concept for reusable space shuttle wing leading edge surfaces. In this leading edge concept high temperature heat pipes were incorporated into the structure to cool the stagnation region, allowing the use of super-alloys in place of refractory metal, ablator protected, or carbon-carbon structures. The program included the analysis and design of the heat pipes, their integration into the test module structure, heat pipe development testing, construction of the test modules and a facility adapter, and formulation of recommended testing conditions. The results of the heat pipe and leading edge module thermal analyses indicate the test modules will meet the design goal; reducing the leading edge temperature at the stagnation line from 1315 C (2400 F) to less than 1010 C (1850 F). The development tests demonstrated that the module assembly could be brazed with active heat pipes, as was borne out by the subsequent successful brazing of both modules with active heat pipes loaded with sodium.

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NASA NTRS1974

Cost-effectiveness of integrated analysis/design systems /IPAD/ An executive summary. II

Evaluation of the cost-effectiveness of integrated analysis/design systems with particular attention to Integrated Program for Aerospace-Vehicle Design (IPAD) project. An analysis of all the ingredients of IPAD indicates the feasibility of a significant cost and flowtime reduction in the product design process involved. It is also concluded that an IPAD-supported design process will provide a framework for configuration control, whereby the engineering costs for design, analysis and testing can be controlled during the air vehicle development cycle.

Miller, R. E., Jr.↗
NASA NTRS1973

Space shuttle sortie payload crew safety and systems compatibility criteria. Volume 1: Executive summary

As part of the effort to reduce the costs of shuttle payloads, this study was performed to determine the minimum, mandatory design and verification criteria necessary to insure that sortie payloads are compatible with the space shuttle system; distinguishing them from those criteria related primarily to mission success, configuration choices, management prerogatives, or other cost-benefit variables which are, therefore, discretionary to payload project management. It was concluded that utilization of the mandatory design criteria, presented in this report, as the basis for sortie payload specifications will produce basic systems compatibility between the orbiter and its sortie payloads at reduced costs. Also, when additional criteria are generated due to changes in subsystems, designs, or guidelines, the categorization methodology developed can aid managerial decision-making concerning these criteria. To a limited degree, the compatibility criteria as defined in this study reflect a portion of the total system safety effort involved in a manned space program.

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NASA NTRS1974

Advanced space program studies: Overall executive summary

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

Sitney, L. R.↗
NASA NTRS1974

The DLG processor: A data management executive for the engineering design integration (EDIN) system. Volume 1: Engineering description and utilization manual

The DLG processor is a Univac 1100 series computer program designed to read, modify, manipulate, and replace symbolic images. DLG is controlled by a set of user supplied directives and operates from a data base of stratified information which can be merged with the symbolic images. Data bases can be constructed and maintained in the mass storage media using the DLG directive language.

Glatt, C. R.↗
NASA NTRS1975

Tug fleet and ground operations schedules and controls. Volume 1: Executive summary

This study presents Tug Fleet and Ground Operations Schedules and Controls plan. This plan was developed and optimized out of a combination of individual Tug program phased subplans, special emphasis studies, contingency analyses and sensitivity analyses. The subplans cover the Tug program phases: (1) Tug operational, (2) Interim Upper Stage (IUS)/Tug fleet utilization, (3) and IUS/Tug payload integration, (4) Tug site activation, (5) IUS/Tug transition, (6) Tug acquisition. Resource requirements (facility, GSE, TSE, software, manpower, logistics) are provided in each subplan, as are appropriate Tug processing flows, active and total IUS and Tug fleet requirements, fleet management and Tug payload integration concepts, facility selection recommendations, site activation and IUS to Tug transition requirements. The impact of operational concepts on Tug acquisition is assessed and the impact of operating Tugs out of KSC and WTR is analyzed and presented showing WTR as a delta. Finally, cost estimates for fleet management and ground operations of the DDT&E and operational phases of the Tug program are given.

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NASA NTRS1975

Mission roles for the Solar Electric Propulsion Stage (SEPS) with the space transportation system. Volume 1: Executive summary

A study was conducted to determine the characteristics of solar electric propulsion stage (SEPS) for the space transportation system. Emphasis is placed on the rationale leading to the concepts for the development and operations program which enhances the cost effectiveness of the SEPS operating with the space transportation system. The approach in describing design concepts and configurations is concerned with the decision controlling factors and selection criteria. The mission roles for the SEPS in accomplishing proposed space activities are defined.

Hammock, D. M.↗