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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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Doppler shift measurements derived from closed-loop radio tracking of distant spacecraft by ground stations of the Deep Space Network (DSN) are one of the principal means used for interplanetary navigation.
The ultimate objective of this work is to design, build, and fly a dual-purpose, piggyback payload whose function is to produce a large volume, low intensity magnetic field and to test the concept of using such a magnetic field (1) to protect spacecraft against solar flare protons, (2) to produce a thrust of sufficient magnitude to stabilize low satellite orbits against orbital decay from atmospheric drag, and (3) to test the magsail concept. These all appear to be capable of being tested using the same deployed high temperature superconducting coil. In certain orbits, high temperature superconducting wire, which has now been developed to the point where silver-sheathed high T sub c wires one mm in diameter are commercially available, can be used to produce the magnetic moments required for shielding without requiring any mechanical cooling system. The potential benefits of this concept apply directly to both earth-orbital and interplanetary missions. The usefulness of a protective shield for manned missions needs scarcely to be emphasized. Similarly, the usefulness of increasing orbit perigee without expenditure of propellant is obvious. This payload would be a first step in assessing the true potential of large volume magnetic fields in the US space program. The objective of this design research is to develop an innovative, prototype deployed high temperature superconducting coil (DHTSC) system.
Unmanned spacecraft guidance from earth based station - optimal control and orbit calculations
Meteoroid flux - nature and distribution of & micrometeoroid model for meteoroid hazard study
Spacecraft attitude control system optimization by parametric analysis of the magnitudes and directions of solar pressure torques
Helium-oxygen mixture for microatmosphere of spacecraft cabins - animal study
Operation results of Mariner and Pioneer telecommunication systems, including system design and future capabilities
Structural engineering to control thermal problems in spacecraft design
Signal attenuation, signal distortion, and radio noise generation due to ion engine exhaust beam
Preliminary parametric analyses on earth orbital storage of liquid hydrogen propellant for manned Mars vehicle
Planning handbook for flexible manned planetary mission system for Mars and Venus flights
All nuclear space acceleration system and basic spacecraft consisting of biconic earth entry module, mission module, vehicle control, experiment laboratories, and excursion module
Trajectory optimization for Mars and Venus flights by manned spacecraft
Scientific payloads for manned space flights common to Mars and Venus missions
Radio propagation considered for solar system exploration, discussing spacecraft role
Technical analyses and computer programs in support of optimization of liquid hydrogen thermal protection systems for nuclear Mars spacecraft
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The power subsystems planned for missions in the 70s have relied heavily on earlier hardware technology and represent an extension of technology conceived in the 60s. Solar panels and primary rechargeable silver-zinc batteries were used throughout the series as power sources. However, because of the increase in battery discharge-charge cycles required, subsequent spacecraft beginning with the Mariner Mars 1971 will use nickel-cadmium batteries. Spacecraft missions to Mars and Venus will continue to use the solar panel and the battery as primary and secondary power sources. The use of the radioisotope thermoelectric generator as the primary power source appears mandatory for missions to the outer planets.