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Author

You Gang

Bio: You Gang is an academic researcher. The author has contributed to research in topics: Propulsion & Electrically powered spacecraft propulsion. The author has an hindex of 1, co-authored 1 publications receiving 3 citations.

Papers
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Patent
26 Apr 2019
TL;DR: In this article, a spatial high-power nuclear power system based on a closed Brayton cycle was proposed, which consists of a spatial nuclear reactor, a Brayton thermoelectric conversion subsystem, heat dissipation subsystem, a cycle working medium storage and supply subsystem, an electric propulsion subsystem and an electric loading subsystem.
Abstract: The invention provides a spatial high-power nuclear power system based on a closed Brayton cycle. The spatial high-power nuclear power system comprises a spatial nuclear reactor, a Brayton thermoelectric conversion subsystem, a heat dissipation subsystem, a cycle working medium storage and supply subsystem, an electric propulsion subsystem and an electric loading subsystem. Helium-xenon mixed gasis taken as a cycle working medium so as to realize efficient thermoelectric conversion, and a high-specific-impulse high-thrust electric thruster directly driven by high voltage is utilized for realizing efficient propulsion. According to the spatial high-power nuclear power system, the efficient thermoelectric conversion problem of a nuclear power air vehicle and the large-range electric power adjusting problem are solved, and the problem that the high voltage of a motor end is not matched with the lower voltage of the electric thruster is solved.

3 citations


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Patent
22 Nov 2019
TL;DR: In this article, a space solar thermal power generation system consisting of a heat source, a thermoelectric conversion subsystem, a radiation heat dissipation subsystem, and a power management subsystem was proposed.
Abstract: The invention provides a space solar thermal power generation system. The space solar thermal power generation system comprises a heat source subsystem, a thermoelectric conversion subsystem, a radiation heat dissipation subsystem, and a power management subsystem, wherein the heat source subsystem is used for gathering solar radiation, converting solar energy into heat energy and storing part ofthe heat energy through a phase change energy storage mode; the thermoelectric conversion subsystem is connected with the heat source subsystem and used for converting part of heat energy of the heatsource subsystem into the electric energy; the radiation heat dissipation subsystem is connected with the thermoelectric conversion subsystem and used for discharging redundant waste heat generated inthe thermoelectric conversion process into the space in a radiation heat dissipation manner; and the power management subsystem is connected with the thermoelectric conversion subsystem and used forsupplying power to a spacecraft and simultaneously supplying power to each unit on a power supply system. According to the solar thermal power generation system, a traditional power generation deviceutilizing solar panels for photovoltaic conversion is replaced with a thermoelectric conversion power generation device, the weight of the power supply system can be effectively reduced by adopting the solar thermal power generation system, and the solar thermal power generation system has remarkable advantages when being applied to a spacecraft with the power requirements of 30 Kw or more.

1 citations

Patent
08 Oct 2019
TL;DR: In this paper, a thermoelectric conversion integrated reactor with a turbine is presented, where a turbine engine is added based on a Stirling type thermocoronium conversion integrated this paper.
Abstract: The invention discloses a thermoelectric conversion integrated reactor with a turbine. A turbine engine is added based on a Stirling type thermoelectric conversion integrated reactor, so that output power is remarkably improved. A reactor internal comprises a reactor pressure vessel, reactor internals, a reactor core, an inner shield, an electric generator, a starting engine, a turbine and a gas compressor, the reactor pressure vessel comprises a cylinder, a cover and a bottom sealing head, the cylinder is similar to a cylindrical shape, the cover is arranged at the top of the cylinder in a covering manner, the bottom sealing head is supported at the bottom of the cylinder, and a reactor external comprises a drum control rod and a heat pipe cooler. A basic idea of the reactor is applicableto fast reactors, also applicable to thermal reactor and further applicable to other persistent heat sources such as isotope heat sources.
Patent
05 Nov 2019
TL;DR: In this paper, a propulsion and power generation integrated device for a space power system and an operation method thereof is presented, which includes an attitude and orbit control engine module, a combustion gas generator module and a turbine-motor module.
Abstract: The invention provides a propulsion and power generation integrated device used for a space power system and an operation method thereof. The device includes an attitude and orbit control engine module, a combustion gas generator module and a turbine-motor module; the attitude and orbit control engine module and the combustion gas generator module are respectively connected to a propellant supplysystem; the outlet of the combustion gas generator module is connected to the turbine-motor module, and gas flows a turbine to work to output shaft power to drive a motor to generate power; and the downstream of the turbine-motor module is connected to power utilization equipment, so that large power electric energy can be provided for the power utilization equipment. The device can simultaneouslymeet demands of the spacecraft for power and large power electric energy; except for providing power required by the aircraft, the device can provide large power electric energy when the aircraft haslarge power electric energy demands, so that the integrated design of an aircraft propulsion system and a power generation system can be realized; and propellant supplement can be performed on the device based on a propellant on-track supplement technology, so that the long-term on-track service of the device can be realized.