Design of subsystems in large structures
Approximation methods for design of spacecraft subsystems in large structures
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Approximation methods for design of spacecraft subsystems in large structures
GCF DSS communications equipment subsystem high-speed data assembly for data conversion to suitable form for transmission
Capabilities and 4800-bps data circuits of GCF SFOF communications terminal subsystem high-speed data assembly
GCF area communications terminal subsystem high-speed data regeneration assembly for routing and conditioning all communications entering and leaving
Gas management subsystem using xenon-helium working fluid designed for Brayton space power system
Design and development of subsystem interface unit, bus control unit, and supporting equipment for space shuttle data processing equipment
Failure effects analysis of guidance, navigation, and control, data management, and communications subsystems
Environmental control and life support subsystem for space shuttle orbiter
Design and fabrication of flight-concept prototype electrochemical water recovery subsystem
Evaluation of oxygen-hydrogen auxiliary propulsion subsystems for space shuttle booster and orbiter baseline vehicles
Brayton power system electrical subsystem and component performance tests, discussing engine control package, DC supply, inverters and instrumentation
Electrical subsystem of 2-15 kW Brayton power conversion system consisting of speed controller, alternator voltage regulator, DC power supply, etc
The thermoelectric outer-planet spacecraft (TOPS) attitude propulsion subsystem effort is summarized. It includes the tradeoff rationale that went into the selection of anhydrous hydrazine as the propellant, and a brief description of three types of 0.445-N (100-mlbf) thrusters that were purchased for in-house evaluation. A discussion is also included of the 0.2224-N (50-mlbf)-developed thrusters and their integration with a portable, completely enclosed, propulsion module that was designed and developed to support the TOPS single-axis attitude control tests in the celestarium.
One of the problems inherent in the use of optical communication systems is the exceedingly high Doppler shift which can be expected. With the recent development of stable, linear, octavebandwidth, voltage-tunable oscillators, this problem has been solved. A laboratory tracking receiver which is capable of tracking a 1-GHz frequency shift at rates up to 12 MHz/s with subsequent coherent data demodulation was designed and tested. This work demonstrates that the design and fabrication of an RF subsystem, utilizing coherent demodulation of data, for wideband communications systems is now both feasible and practical.
Design and operation of the primate life support subsystem for the Biosatellite Program as used during the flight of Biosatellite 3 are discussed. Included are preflight changes necessitated by the primate's (a Macaca nemistrina monkey) influence on the initial equipment design.
Design, fabrication, and testing of the Mariner Mars 1971 pyrotechnic subsystem are reviewed. Emphasis is placed on those changes from the Mariner Mars 1969 configuration. Major problems occurring in the developmental and testing phases are discussed.
An oscillation in the OGO-3 roll control channel, resulting from the EP-5 and EP-6 boom motion coupling into the control channel and causing loss of attitude control, is investigated. The study includes (1) an analysis of the OGO-3 and OGO-2 flight data to determine the nature and extent of the roll oscillation phenomena, (2) design analysis of the complete attitude control subsystem (ACS) to evolve changes which would prevent recurrences of the coupled ACS boom oscillation observed on OGO-3, and (3) analog simulations to verify the performance of the design changes selected. Portions of OGO-3 and OGO-2 flight data are illustrated and the major flexible body oscillation are identified. A model of the major flexible appendage dynamics is developed and is shown analytically and through analog simulations to reproduce the OGO-3 oscillation phenomena. The design changes which were found necessary are: a reversal delay logic for the roll reaction wheels, widening of the solar array dead zone from 0.5 to 1.0 deg, and modification of the OPEP control loop to include a filter and stabilizing feedback loops.
Performance characteristics of electrical subsystem for 2 to 15 kilowatt Brayton power conversion system