Trajectories of unmanned spacecraft.
Unmanned spacecraft trajectories, discussing flight mechanics of solar system exploration
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Unmanned spacecraft trajectories, discussing flight mechanics of solar system exploration
Unmanned space mission to determine Martian environmental factors influencing design of systems for manned space mission to Mars - unmanned spacecraft design
Unmanned spacecraft program costs estimation through empirical studies of past and current NASA programs
Unmanned spacecraft program costs estimation through empirical studies of past and current NASA programs
Nonmetallic materials for unmanned spacecraft
Unmanned spacecraft guidance and control technology for lunar and planetary exploration
Unmanned spacecraft - deep space probes and scientific and applications satellites
Advanced propulsion systems for unmanned spacecraft making simple pressure-fed systems, using storable propellants, thrust chambers and flexible propellant barriers
Characteristics of OAO-A1 unmanned spacecraft and Atlas-Agena launch vehicle
Design of unmanned spacecraft for interplanetary travel and scientific observations
A historical overview of electrical power systems used in the U.S. manned spacecraft and some of the U.S. unmanned spacecraft is presented in this investigation. A time frame of approximately 25 years, the period for 1959 to 1984, is covered in this report. Results indicate that the nominal bus voltage was 28 volts dc in most spacecraft and all other voltage levels were derived from this voltage through such techniques as voltage inversion or rectification, or a combination. Most spacecraft used solar arrays for the main source of power except for those spacecraft that had a relatively short flight duration, or deep spaceprobes that were designed for very long flight duration. Fuel cells were used on Gemini, Apollo, and Space Shuttle (short duration flights) while radioisotope thermoelectric generators were employed on the Pioneer, Jupiter/Saturn, Viking Lander, and Voyager spacecraft (long duration flights). The main dc bus voltage was unregulated on the manned spacecraft with voltage regulation provided at the user loads. A combination of regulated, semiregulated, and unregulated buses were used on the unmanned spacecraft depending on the type of load. For example, scientific instruments were usually connected to regulated buses while fans, relays, etc. were energized from an unregulated bus. Different forms of voltage regulation, such as shunt, buck/boot, and pulse-width modulated regulators, were used. This report includes a comprehensive bibliography on spacecraft electrical power systems for the space programs investigated.
Data compression feasibility for data transmission from unmanned spacecraft in deep space
Systems safety for unmanned spacecraft, considering power supply, equipment operation, trajectory correction, etc
Unmanned spacecraft for earth resources survey, investigating ERTS payload, performance characteristics and ground station
The applications of unmanned spacecraft for research purposes are discussed. Specific applications of the Communication and Navigation satellites and the Earth Observations satellites are described. Diagrams of communications on world-wide basis using synchronous satellites are developed. Photographs of earth resources and geology obtained from space vehicles are included.
Reliability in unmanned spacecraft by environmental testing, specifically of Ariel I, Echo II and Relay I
Avoidance of contamination of extraterrestrial planets with earth organisms by sterilization of unmanned spacecraft
Mechanical positive expulsion devices for earth- storable liquid rocket propellants in unmanned spacecraft