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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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The initial and growth modular space station configurations are described, and the evolutionary steps arriving at the final configuration are outlined. Supporting tradeoff studies and analyses such as stress, radiation dosage, and micrometeoroid and thermal protection are included.
Guidelines are presented for incorporation of the onboard checkout and monitoring function (OCMF) into the designs of the space shuttle propulsion systems. The guidelines consist of and identify supporting documentation; requirements for formulation, implementation, and integration of OCMF; associated compliance verification techniques and requirements; and OCMF terminology and nomenclature. The guidelines are directly applicable to the incorporation of OCMF into the design of space shuttle propulsion systems and the equipment with which the propulsion systems interface. The techniques and general approach, however, are also generally applicable to OCMF incorporation into the design of other space shuttle systems.
An analysis was conducted of the space shuttle propulsion systems to define the onboard checkout and monitoring function. A baseline space shuttle vehicle and mission were used to establish the techniques and approach for defining the requirements. The requirements were analyzed to formulate criteria for implementing the functions of preflight checkout, performance monitoring, fault isolation, emergency detection, display, data storage, postflight evaluation, and maintenance retest.
The design and development of the communications terminal breadboard for the modular space station are discussed. The subjects presented are: (1) history of communications terminal breadboard, (2) requirements analysis, (3) technology goals in terminal design, and (4) communications terminal board integration tests.
The computation and logical functions which are performed by the data processing assembly of the modular space station are defined. The subjects discussed are: (1) requirements analysis, (2) baseline data processing assembly configuration, (3) information flow study, (4) throughput simulation, (5) redundancy study, (6) memory studies, and (7) design requirements specification.
The development of uniform computer program standards and conventions for the modular space station is discussed. The accomplishments analyzed are: (1) development of computer program specification hierarchy, (2) definition of computer program development plan, and (3) recommendations for utilization of all operating on-board space station related data processing facilities.
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The MSS system, capable of supporting a six-man crew, is described as consisting of four common station modules, two special modules (core and power), and a cargo module arranged in a cruciform. The station buildup, and space station subsystems including environmental control life support, electrical power, guidance and control are also described. The MSS system weights are presented for design-to-weight, closeout weights, and shuttle payload weights.
An analysis of the factors affecting the cost effectiveness of space shuttle operations is presented. The subjects discussed are: (1)payload data bank, (2) program risk analysis, (3)navigation satellite program, and (4) reusable launch systems.
Problematic causes and characteristics of light colored sinuous markings on the lunar surface are explored. Two processes, exogenetic and endogenetic, are examined in detailed. During the endogenetic process it is suggested that impact ejecta deposition and surface disturbances cause the markings. During the endogenetic process, it is suggested that extrusive volcanism and sublimation and/or alteration cause the markings.
The erratic operation of the mapping camera assemblies on board Apollo 15, 16, 17 is investigated. The exact causes of the problems with the scientific equipment module deployment mechanisms are not identified. However, the possibility of increased friction in hard vacuum is implied. It is suggested that since hard vacuum conditions are not attainable in large chambers, realistically loaded components could be tested in small chambers capable of vacuums to 10 to the minus 14th power torr. It is concluded that this technique carries with it the greatest promise for future investigations.
An analysis of alternate space shuttle concepts is presented. The two main program alternatives are: (1) phased booster development with an interim solid rocket engine cluster preceding the reusable booster and (2) phased orbiter development with modified avionics, vehicle subsystems, thermal protection system, and redesigned rocket engines. Diagrams of the various concepts are provided. The predicted spacecraft performance capabilities are reported. Project management proposals are submitted.
A recommended baseline system is presented along with alternate avionics systems, Mark 2 avionics, booster avionics, and a cost summary. Analyses and discussions are included on the Mark 1 orbiter avionics subsystems, electrical ground support equipment, and the computer programs. Results indicate a need to define all subsystems of the baseline system, an installation study to determine the impact on the crew station, and a study on access for maintenance.
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An equation governing the prior-to-failure crack propagation is proposed. For a rate-sensitive solid containing a two-dimensional crack and subject to the tensile mode of fracture the differential equations are integrated numerically for loads increasing monotonically in time. The resulting integral curves of load vs crack length and length vs time indicate that the growth of cracks in the subcritical range is strongly rate-dependent. The fatigue growth, viewed as a sequence of slow growth periods, is simulated on an EAI 380 analog computer. The fourth-power law proposed by Paris is confirmed only within certain range of high-cycle fatigue propagation and for a rate-insensitive solid. Otherwise, i.e., for a more pronounced rate dependence induced by viscosity of a solid and/or in the proximity of the final instability point, the growth is markedly enhanced.
Some of the features of synchrotron radiation are examined which occur when relativistic particles move at small pitch angles in a magnetic field. The emission from individual particles is computed. The general properties of the emission from distributions of particles with small pitch angles is discussed, and the emissivities and degrees of polarization for several specific source models are presented. For sources which mainly contain particles with small pitch angles, the degree of circular polarization will normally be high, whereas, if the magnetic field is somewhat irregular, the degree of linear polarization will be small. If the particle distribution also has a low-energy cutoff, the emissivity will vary linearly with frequency at low frequencies.
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