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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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Dynamic structural analysis, statistical analysis, and Rayleigh-Ritz methods applied to Skylab and Apollo/Saturn problems including pogo effects, vibration damping, and noise reduction
Design and testing of solid state TV camera, FM TV transmitter, and AM baseband telemetry for space application and X ray source for solar energy measurements - data reduction techniques
Mass properties of space station and logistic module
The Apollo Lunar Roving Vehicle (LRV) mobility system is described. Special emphasis is given to the redundancy aspects and to the selection of the drive motors. A summary chart of the performance on the lunar surface during the Apollo 15 flight is included. An appendix gives details on some development work on high efficiency drive systems and compares these systems to the selected system.
Experimental aerodynamic investigations were conducted in the 14 x 14 inch trisonic wind tunnel during early December 1971 on 0.003366 scale models of the space shuttle pressure fed booster configurations. The basic configurations tested were a 40 deg cone/cylinder/13 deg flare designated the pressure fed booster and a 35 deg cone/cylinder designated the pressure fed booster configuration x. Six component aerodynamic force and moment data were recorded over a Mach number range from 0.6 to 5.0 at angles of attack from +20 to +60 deg at 0 deg sideslip and over a sideslip range from -10 to +10 deg at 31 and 52 deg angles of attack. Primary configuration variables for the two basic pressure fed booster configurations were fin size and fin dihedral position.
The dust problem and fender design for the LRV were studied under reduced gravity with a lunar soil simulant. The test equipment, soil characteristics of the lunar soil simulant, and the test procedures are described. It is concluded: (1) The fender plus flap design is adequate. (2) Vacuum conditions tend to eliminate or reduce suspended dust clouds. (3) Reduced gravity conditions tend to increase the dust problems. (4) Slow starting speeds are necessary to minimize slip and reduce initial dust generation.
Contract engineering item specifications for the modular space station are presented. These specifications resulted from the development and allocations of requirements which are concise statements of performance or constraints on performance. Specifications contain requirements for functional performance and for the verification of design solutions.
The interface and support performance, design and confirmation requirements are defined for the modular space station and space shuttle programs. The requirements are treated as separate obligations against each modular program and are presented for the following: shuttle orbiter, shuttle booster, launch operations, mission operations, and the research applications module.
The orbiting laboratory which can take many forms and can be configured to house a crew of up to 12 men is discussed. The initial study of the 33-foot-diameter Space Station, launched by the Saturn INT-21 and supporting a complement of 12 crewmen, has been completed and documented. A Modular Space Station comprised of smaller, shuttle-launched modules is described. These modules could ultimately be configured to provide for a crew of the same size as envisioned for the 33-foot-diameter Space Station-but buildup would be gradual, beginning with a small initial crew and progressing toward greater capability by adding modules and crewmen on a flexible schedule.
The design plan requirements define the design implementation and control requirements for Phase C/D of the Modular Space Station Project and specifically address the Initial Space Station phase of the Space Station Program (modular). It is based primarily on the specific objective of translating the requirements of the Space Station Program, Project, Interface, and Support Requirements and preliminary contract end x item specifications into detail design of the operational systems which comprise the initial space station. This document is designed to guide aerospace contractors in the planning and bidding for Phase C/D.
Cryogenic research applicable to Skylab, space station, and space shuttle programs
Experimental aerodynamic investigations were conducted in the 14-inch trisonic wind tunnel during early February 1972 on a 0.00340 scale model of the 33-foot diameter space shuttle pump fed booster configuration. The basic configuration tested was a 40-deg cone/cylinder. Six component aerodynamic force and moment data were recorded over a Mach number range from 0.6 to 5.0, angles-of-attack from 50 to 90 deg at 0 deg sideslip and over a sideslip range from -10 to +10 deg at 60 and 80 deg angles-of-attack. Primary configuration variables were fin area and body cutout size.
Advanced methods of reliability engineering and quality assurance for aerospace application
Performance tests to determine the thermodynamic properties of thermal control coatings for application to the Skylab corollary experiments under preflight, inflight, and postflight conditions are described. Malfunction analyses and procedures for working around contingency situations are discussed. The specifications for various sensors and instruments are presented in tables of data.
All program options and a detailed definition of the format of each input card (with examples) are given. Output options and their applications are detailed. A listing of the main program is provided and all update points are explained. All information required for a designer/draftsman (for program use) is provided, and it will not be necessary to become intimately familiar with the internal operations to effectively use the extensive capability it has to offer.
Performance, stability, and design of aerospike engines and engine system components
Results are presented for an experimental space shuttle stage separation plume impingement program conducted in the NASA-Marshall Space Flight Center's impulse base flow facility (IBFF). Major objectives of the investigation were to: (1)determine the degree of dual engine exhaust plume simulation obtained using the equivalent engine; (2) determine the applicability of the analytical techniques; and (3) obtain data applicable for use in full-scale studies. The IBFF tests determined the orbiter rocket motor plume impingement loads, both pressure and heating, on a 3 percent General Dynamics B-15B booster configuration in a quiescent environment simulating a nominal staging altitude of 73.2 km (240,00 ft). The data included plume surveys of two 3 percent scale orbiter nozzles, and a 4.242 percent scaled equivalent nozzle - equivalent in the sense that it was designed to have the same nozzle-throat-to-area ratio as the two 3 percent nozzles and, within the tolerances assigned for machining the hardware, this was accomplished.
Research projects conducted as part of NASA programs during period May 1970 through May 1972