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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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Environmental requirements, spacecraft system evaluation, and mission characteristics in comet and close-approach asteroid mission study
Cost estimate model for manned spacecraft systems
The use of low cost, off the shelf prefabricated enclosures for spacecraft system thermal cycling applications was indicated. The enclosures are erected in the satellite integration areas without disturbing the test article, electrical test set, or RF interfaces. They are assembled by metal clad, modular urethane panels. These panels are self supporting, and are locked and sealed to each other on assembly. Penetrations for interconnecting cables, coaxial and waveguide services; and temperature conditioning inlet and outlet ducts are easily incorporated where required. The facility and its advantages and intrinsic benefits are described.
Problems associated with the in-orbit repair and maintenance of spacecraft systems are examined with reference to experience gained from three servicing missions: in-orbit capture, repair, and reflight of the Solar Maximum Mission satellite, capture and return to earth of the Palapa and Westar communications satellites, and in-orbit repair of Syncom 3. It is then shown how the lessons learned from the three servicing missions are applied to current and future servicing activities. In particular, planned servicing missions for the Hubble Space Telescope, tools and servicing facilities development, and the development of the Explorer Platform are discussed.
This presentation provides and overview of the products, technology demonstration missions, and efforts of NASA's Small Spacecraft Systems Virtual Institute and Small Spacecraft Technology Program.
Telecommunication system requirements and design for Voyager spacecraft 1971
Voyager spacecraft system using Saturn V launch vehicle - summary of parametric studies for unmanned exploration of Mars by landing module
Research concerned with automating the monitoring and control of spacecraft systems is discussed. In particular, the application of SRI's Procedural Reasoning System (PRS) to the handling of malfunctions in the Reaction Control System (RCS) of NASA's Space Shuttle is examined. Unlike traditional monitoring and control systems, PRS is able to reason about and perform complex tasks in a very flexible and robust manner, somewhat in the manner of a human assistant. Using various RCS malfunctions as examples (including sensor faults, leaking components, multiple alarms, and regulator and jet failures), it is shown how PRS manages to combine both goal-directed reasoning and the ability to react rapidly to unanticipated changes in its environment. In conclusion, some important issues in the design of PRS are reviewed and future enhancements are indicated.
Spacecraft design for Voyager mission
Subsystems development in proposed Voyager spacecraft design
Design for 1969 test flight options and spacecraft configurations, and two launch vehicles - Voyager project
Hardware subsystems for flight spacecraft, design reliability, interface control, and mission objectives - Voyager project
Preferred Voyager spacecraft design rationale - alternate mission objectives and spacecraft designs
Functional descriptions of subsystems for 1971 Voyager flight spacecraft
The Atmosphere Explorer Spacecraft incorporates an orbiting aeronomy laboratory designed to operate in the lower thermosphere. A three-axis stabilized platform capable of operating over a wide range of orbital altitudes, inclinations, solar aspect angles, and spin rates satisfies the science requirements for instrument orientation. An on-board propulsion subsystem allows operations at low-perigee altitudes without severe limitation of orbital lifetime. Programmable high-speed digital command and data handling, together with power supplied by solar cells and batteries, allows the spacecraft to be operated remotely in daylight or darkness. This configuration of spacecraft support subsystems fulfills the requirements for the various phases of the scientific mission.
Voyager spacecraft system - Titan III C launch vehicle
Alternate designs for guidance and control, power, controller and sequencer systems for Voyager spacecraft - effect of alternate designs on schedule and implementation
Spacecraft TV system for topographic reconnaissance of Mars surface consisting of single camera and slow-scan vidicon shutter system