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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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THEORETICAL CONSIDERATIONS FOR A PRELIMINARY DESIGN OF A SOLAR CELL GENERATOR ON A SATELLITE
Solar cell generators for satellite power supply - design theory
THE NASA NUCLEAR ELECTRIC POWER PROGRAM
Description of nasa nuclear electric power program with special emphasis on power supplies in the surveyor program and the snap 8 project
GEMINI FUEL CELL POWER SOURCE - FIRST SPACECRAFT APPLICATION
Design and development of the ion-exchange membrane fuel cell intended to furnish electric power and drinking water to the gemini spacecraft
The integration of radioisotope thermoelectric systems and spacecraft.
Radioisotope thermoelectric power supply effects on satellite design
Nuclear power supplies.
SNAP, Rankine-cycle reactor and radioisotopes auxiliary power sources for spacecraft
Spacecraft power system architecture to mitigate spacecraft charging effects
A power system architecture for a spacecraft and a method of a power supply for a spacecraft are presented which take advantage of the reduced plasma interaction associated with positive ground high voltage photovoltaic arrays and provide a negative ground power supply for electrical loads of the spacecraft. They efficiently convert and regulate power to the load bus and reduce power system mass and complexity. The system and method ground the positive terminal of the solar arrays to the spacecraft hull, and using a power converter to invert the electric sign, permit a negative ground for the electrical distribution bus and electrical components. A number of variations including a load management system and a battery management system having charging and recharging devices are presented.
Heat-Exchanger/Heat-Pipe Interface
Monolithic assembly reliable and light in weight. Heat exchanger and evaporator ends of heat pipes integrated in monolithic halves welded together. Interface assembly connects heat exchanger of furnace, reactor, or other power source with heat pipes carrying heat to radiator or power-consuming system. One of several concepts proposed for nuclear power supplies aboard spacecraft, interface useful on Earth in solar thermal power systems, heat engines, and lightweight cooling systems.
Analysis of the advanced Nimbus power systems
Solar-conversion power-supply subsystem for Nimbus B, using pulse width modulated voltage regulator
ATS-4 study program, volume 4 Final report
Power supply system, orbital analyses, and propulsion and guidance of Applications Technology Satellite-4
Buoyant Venus station feasibility study. Volume IV - Communications and power Final report
Telecommunication and power supply requirements for inflatable buoyant Venus station
THE SOLAR POWER SUPPLY SYSTEM FOR THE ORBITING ASTRONOMICAL OBSERVATORIES
Solar power supply system for orbiting astronomical observatory
Nimbus power systems - 1960-1969.
Nimbus power supply subsystems 1960-1969, discussing regulation techniques, battery and maximum power point tracking
Motor/generator and electronic control considerations for energy storage flywheels
A spacecraft electric power supply system is described. Requirements of the system are to accelerate a momentum wheel to a fixed maximum speed when solar energy is available and to maintain a constant voltage on the spacecraft bus under varying loads when solar energy is not available. Candidate motor types, pulse width modulated current control systems, and efficiency considerations are discussed. In addition, the Lunar Roving Vehicle motors are described along with their respective efficiencies.
Power Converter Design for the Europa Lander Motor Controller
This paper will outline the design and test results for the Europa Lander motor controller’s Power Conversion Slice. Europa Lander is a proposed NASA mission concept to send a stationary spacecraft to Jupiter’s Icy Moon, Europa, to search for subsurface biosignatures. The Power Conversion Card is one of the many technologies designed for this mission. The Power Conversion Card’s primary function is to convert the power supplied by the spacecraft battery to usable power for use within the motor controller. In addition, this card provides power system telemetry to the spacecraft computer. This card tolerates Europa’s harsh radiation environment within a protected vault to enable it to survive the external temperatures which can be as low as -184°C during the three-week mission. This design makes use of multiple commercially available radiation hardened electronics, including Cobham’s UT32M0R500 Arm Microcontroller along with VPT’s DC-DC Converters for power conversion. The microcontroller is used to collect local power system telemetry and assess card health autonomously without intervention from the spacecraft’s main computer. This paper will showcase the design behind the prototype and electrical testing results.
Summary results of the first United States manned orbital space flight
This paper describes the principal findings of the first United States manned orbital space flight in light of the flight mission. Consideration is given to the coordinated tracking network, recovery forces and to the spacecraft and its several functional systems. These include mechanisms for heat protection, escape maneuvers, spacecraft control, power supply, communications, life support and landing. A few difficulties encountered in the flight and deviations from the planned sequence are described. Craft preparation, aeromedical studies, flight plan and particularly flight observations--including the color, light, horizon visibility by day and by night, cloud formations and sunrise and sunset effects are given in some detail. The general conclusion from the MA-6 flight is that man can adapt well to new conditions encountered in space flight and that man can contribute importantly to mission reliability and toward mission achievement through his capacities to control the spacecraft and its multiple systems contribute to decision making and adaptation of programming as well as to direct exploratory and experimental observations.
THE DESIGN OF THE UNITED KINGDOM SCIENTIFIC SATELLITE SOLAR POWER SYSTEM
Solar power system for the ariel satellite /uk-1/
THE NASA NUCLEAR ELECTRIC POWER PROGRAM
The aim of the NASA nuclear electric power program is to provide long-lived reliable nuclear power sources in the range from tens of watts to tens of megawatts for advanced missions. The work is conducted in corporation with the U.S. Atomic Energy Commission which is developing isotope power sources and the reactor for the SNAP-8 project. Isotopes are considered for missions requiring up to several hundred watts of power. SNAP-8 will provide about 35 to 60 kilowatts for missions requiring tens of kilowatts and lifetimes of about one year. SNAP-8 has been redesigned to emphasize reliability and performance. This decision permits many components to operate at lower, more nearly state-of-the -art temperatures at the sacrifice of greater cooling requirements and increased weight. Beyond SNAP-8, an extensive applied research program has been conducted since 1959 to provide the technology required for the sound development of light weight nuclear electric systems in the megawatt range for lifetimes of up to several years. The work is accomplished in university, industrial and government laboratories.