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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 487 records · Page 27
All sourcesNASA NTRSDOE OSTI
NASA NTRS1973

Capabilities of electrodynamic shakers when used for mechanical shock testing

The results of a research task to investigate the capabilities of electrodynamic vibrators (shakers) to perform mechanical shock tests are presented. The simulation method employed was that of developing a transient whose shock response spectrum matched the desired shock response spectrum. Areas investigated included the maximum amplitude capabilities of the shaker systems, the ability to control the shape of the resultant shock response spectrum, the response levels induced at frequencies outside the controlled bandwidth, and the nonlinearities in structural response induced by a change in test level.

Keegan, W. B.↗
NASA NTRS1974

Propulsion system tests on a full scale Centaur vehicle to investigate 3-burn mission capability of the D-lT configuration

Propulsion system tests were conducted on a full scale Centaur vehicle to investigate system capability of the proposed D-lT configuration for a three-burn mission. This particular mission profile requires that the engines be capable of restarting and firing for a final maneuver after a 5-1/2-hour coast to synchronous orbit. The thermal conditioning requirements of the engine and propellant feed system components for engine start under these conditions were investigated. Performance data were also obtained on the D-lT type computer controlled propellant tank pressurization system. The test results demonstrated that the RL-10 engines on the Centaur vehicle could be started and run reliably after being thermally conditioned to predicted engine start conditions for a one, two and three burn mission. Investigation of the thermal margins also indicated that engine starts could be accomplished at the maximum predicted component temperature conditions with prestart durations less than planned for flight.

Groesbeck, W. A.↗
NASA NTRS1973

The Space Shuttle System description, operations, and payload capabilities

General characteristics of the Space Shuttle System are presented with overall capabilities and operating characteristics detailed. Mission operations and performance baselines are presented. The relationships between orbital parameters and payload capabilities are highlighted. On-orbit scientific and applications operating modes are briefly reviewed and methods of achieving a versatile payloads program using standard payload carriers are discussed.

Heberlig, J. C.↗
NASA NTRS1974

Error protection capability of space shuttle data bus designs

Error protection assurance in the reliability of digital data communications is discussed. The need for error protection on the space shuttle data bus system has been recognized and specified as a hardware requirement. The error protection techniques of particular concern are those designed into the Shuttle Main Engine Interface (MEI) and the Orbiter Multiplex Interface Adapter (MIA). The techniques and circuit design details proposed for these hardware are analyzed in this report to determine their error protection capability. The capability is calculated in terms of the probability of an undetected word error. Calculated results are reported for a noise environment that ranges from the nominal noise level stated in the hardware specifications to burst levels which may occur in extreme or anomalous conditions.

Proch, G. E.↗
NASA NTRS1965

NASA agenda D mission capabilities and restraints catalog, volume 1

The purpose of this document is to provide a single source of information regarding Agena D mission capabilities and restraints which affect spacecraft design. Utilized as a handbook during conceptual design and program planning, this catalog is intended to supplement the designer's knowledge of the Agena D and specify guidelines that enable him to design a spacecraft configuration which is: - Compatible with the booster system - Designed to realize maximum capabilities of the existing launch vehicle and associated equipment

Lockheed Missiles and Space Company↗
NASA NTRS1976

A distributed data base management capability for the deep space network

The Configuration Control and Audit Assembly (CCA) is reported that has been designed to provide a distributed data base management capability for the DSN. The CCA utilizes capabilities provided by the DSN standard minicomputer and the DSN standard nonreal time high level management oriented programming language, MBASIC. The characteristics of the CCA for the first phase of implementation are described.

Bryan, A. I.↗
NASA NTRS1975

Orbital lifetime capabilities of digital programs RMDAP and Monster

The orbital lifetime study capabilities of the Reference Mission Design and Analysis Program (RMDAP) and the Apollo Mission Planning and Real-Time Rendezvous Support Program (ARRS or Monster) were studied. Output and program versatility, that is, the methods with which each program permits user definition of the major factors affecting orbital lifetimes, are discussed. In addition, orbit maintenance is examined and sample runs are compared. Since each program has special capabilities in different areas, it is left to the investigator's discretion as to the preferable program to employ for his lifetime study purposes.

Source record↗
NASA NTRS1976

The GSFC NASTRAN thermal analyzer new capabilities

An overview of four analysis capabilities, which developed and integrated into the NASTRAN Thermal Analyzer, is given. To broaden the scope of applications, these additions provide the NTA users with the following capabilities: (1) simulating a thermal louver as a means of the passive thermal control, (2) simulating a fluid loop for transporting energy as a means of the active thermal control, (3) condensing a large sized finite element model for an efficient transient thermal analysis, and (4) entering multiple boundary condition sets in a single submission for execution in steady state thermal analyses.

Lee, H. P.↗
NASA NTRS1977

Development of a curved pipe capability for the NASTRAN finite element program

A curved pipe element capability for the NASTRAN structural analysis program is developed using the NASTRAN dummy element feature. A description is given of the theory involved in the subroutines which describe stiffness, mass, thermal and enforced deformation loads, and force and stress recovery for the curved pipe element. Incorporation of these subroutines into NASTRAN is discussed. Test problems are proposed. Instructions on use of the new element capability are provided.

Jeter, J. W., Jr.↗
NASA NTRS1977

Remote manipulator system steering capability for SVDS

Details of the remote manipulator system steering capability to be implemented into the space vehicle dynamics simulator are reported. The resolve rate law is included as part of the overall steering capability. The steering model includes three automatic modes, four manual augmented modes, and a single joint rate mode.

Martin, D. T.↗
NASA NTRS1976

The challenge for improved air cargo capability

Requirements for a strategic air cargo capability are considered. Practical national resource investment considerations dictate that future military strategic airlift planners regard civil capabilities as an integral part of the solution. Attention is given to the military needs for airlift, the civil-military airlift commonality, the present air cargo business, growth projections for civil air cargo, future air cargo business, the introduction date for a dedicated airfreighter, and the demands for transport aircraft.

Vaughan, J.↗
NASA NTRS1977

Modifying the NASTRAN system with a new capability

The need for a new capability/maintenance interface specification for the NASTRAN system was discussed. Those problems are highlighted which are most difficult to resolve when a new capability is delivered for inclusion into an archive level. The guidelines presented show the objectives of new capability integration as they relate to design and development, delivery, checkout, and documentation. Examples of new capability/maintenance interface already done on an informal basis are presented to illustrate the 'test conditions' of the idea of defining implementation objectives.

Mcdonough, J. R.↗
NASA NTRS1977

Capabilities of the Navy variable stability X-22A for V/STOL flying qualities R and D

The X-22A V/STOL Flight Research Facility which provides in-flight simulation capability applicable to hover, low speed, and transition flight investigation of fixed wing V/STOL flying is described. The variable stability system, the guidance and display equipment, the data acquisition and processing system, and the ground simulator are included. Research programs involving the STOL flying qualities for landing approach, the control system, display, and guidance requirements for VTOL aircraft instrument approach and landing, and the expansion of the adverse weather operation capabilities of the Navy's VTOL aircraft are briefly summarized.

Aiken, E. W.↗
NASA NTRS1978

Potential SSME modifications to provide extended capabilities for future applications

Expendable launch vehicles will be phased out during the first years of shuttle operation and the payloads currently carried to orbit by these vehicles will be placed in low earth orbit by the reusable shuttle. In connection with limitations regarding the weight of the payload which can be launched by the Space Shuttle in its present form, approaches have been considered for increasing the payload capability of the Shuttle. Propulsion systems for Shuttle derived vehicles with larger payload capabilities have been studied. Such systems can potentially be obtained from modifications of the Space Shuttle Main Engine (SSME). Concepts based on modifications to the basic engine include an SSME-35 for low altitude operation with liquid rocket boosters and an SSME-150 for operation over the complete altitude range as might be required in a single-stage-to-orbit vehicle application. Another modification would provide operation with a hydrocarbon fuel instead of hydrogen.

Kirby, F. M.↗
NASA NTRS1978

Flight research capabilities of the NASA/Army Rotor Systems Research Aircraft

After a brief description of the Rotor Systems Research Aircraft (RSRA), the paper reviews their flight capabilities and limitations. A favorable assessment is given to the expected research capabilities of the RSRA. The structural limitations should not significantly constrain the flight envelope for research operations; the handling qualities, though not optimum, are within the parameters originally predicted; and there are no fundamental dynamics problems. Although the accuracy of the force and moment measurement system has not yet been quantified by calibration, it is expected to be acceptable after calibration.

White, S., Jr.↗
NASA NTRS1978

Satellite measurement capabilities for environmental and resource observations

The report summarizes the measurement needs of the major earth applications disciplines which have been culled from a wide range of documental sources. These measurement needs are matched against present or funded-for-launch space-borne measurement capabilities. A brief prognosis of this program's abilities to eliminate or reduce the voids and gaps in performance between the measurement needs and the existing capability is included, based on the author's present understanding of technology.

Nagler, R. G.↗
NASA NTRS1978

Nimbus 6 satellite vs rawinsonde capabilities

The paper establishes rms errors in Nimbus 6 satellite data from discrepancies between satellite and rawinsonde data, compares rms errors in Nimbus 6 with those in rawinsonde data, and examines the capability of Nimbus 6 satellite data to depict such quantities as horizontal gradients of basic variables and computed variables such as vorticity and lapse rate of temperature. The capability of Nimbus 6 data is illustrated by comparisons of rms errors in computed variables obtained through a propagation-of-error method with average and near-extreme values of the variables obtained from two of NASA's Atmospheric Variability Experiments (AVE II and AVE IV). It is shown that the rms errors in Nimbus 6 basic variables (temperature, mixing ratio, geopotential height, and wind speed) are between 2 and 12 times larger than the corresponding errors in rawinsonde data. For all variables examined, the magnitude of the rms errors are smaller than the near-extreme values of the variables determined from AVE II and AVE IV data.

Scoggins, J. R.↗