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Author

Tian Gui

Bio: Tian Gui is an academic researcher. The author has contributed to research in topics: Propulsion & Heat exchanger. The author has an hindex of 2, co-authored 4 publications receiving 8 citations.

Papers
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Patent
29 Jan 2019
TL;DR: In this paper, an electric pump pressure type liquid oxygen methane space propelling system is proposed for a space aircraft propulsion system, which is suitable for a large propellant filling amount and whose track control engine needs to be started for a plurality of times.
Abstract: The invention provides an electric pump pressure type liquid oxygen methane space propelling system. The electric pump pressure type liquid oxygen methane space propelling system comprises a high-pressure gas cylinder, a liquid oxygen storage tank, a methane storage tank, an electric pump system, an oxygen heat exchange injection rod, a methane heat exchange injection rod and a track control engine; the high-pressure gas cylinder is connected with the liquid oxygen storage tank and the methane storage tank through a first pipeline; the liquid oxygen storage tank and the methane storage tank are connected with an electric pump system through a second pipeline and a third pipeline; the oxygen heat exchange injection rod is arranged in the liquid oxygen storage tank; the methane heat exchangeinjection rod is arranged in the methane storage tank; the electric pump system is connected with the oxygen heat exchange injection rod and the track control engine through a fourth pipeline; and the electric pump system is connected with the methane heat exchange injection rod and the track control engine through a fifth pipeline. The electric pump pressure type liquid oxygen methane space propelling system is suitable for a space aircraft propulsion system, and particularly has obvious application advantages on a space propelling system which has large propellant filling amount and whose track control engine needs to be started for a plurality of times..

5 citations

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

Patent
13 Dec 2019
TL;DR: In this article, an annular flow channel structure between a shielded motor stator and a rotor is proposed. But the structure comprises a stator shielding sleeve, a rotor shielding sleeve and a flow-guide convex ribs.
Abstract: The invention discloses an annular flow channel structure between a shielded motor stator and a rotor. The structure comprises a stator shielding sleeve, a rotor shielding sleeve and an annular flow channel between the stator shielding sleeve and the rotor shielding sleeve. An inner cylindrical surface of the stator shielding sleeve and/or an outer cylindrical surface of the rotor shielding sleeve are/is provided with flow guide convex ribs, and a section shape, a size, a number, layout and the like of the flow guide convex ribs can be set according to specific technical requirements and application environments. By using the annular flow channel structure between the shielded motor stator and the rotor, on one hand, working efficiency, a rotating speed and power density of the shielded motor are improved; and on the other hand, a fault probability caused by motor overheating, cooling medium vaporization and the like can be reduced.
Patent
17 Sep 2019
TL;DR: In this article, an engine injector based on laminate diffusion welding, a manufacturing method and an engine is presented. And the injector comprises laminates (11) are provided with set laminate passageway structure units separately.
Abstract: The invention provides an engine injector based on laminate diffusion welding, a manufacturing method and an engine. The injector comprises laminates (11). The Nm laminates (11) are provided with set laminate passageway structure units separately. The Nm laminates (11) are sequentially connected through diffusion welding. The Nm laminate passageway structure units are connected in a set manner to form an injector passageway, wherein Nm is an integer larger than 1. According to the injector based on laminate diffusion welding, the problems that in the prior art, a low-temperature orbit/attitude control engine injector is provided with multiple parts, and a low-temperature propellant easily suffers from phase change on the head of the engine can be solved, and meanwhile the engine injector has the beneficial effects of being compact in structure and high in working reliability and achieving uniform and fine atomization of the propellant, and can meet the use requirements of the low-temperature orbit/attitude control engine.

Cited by
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Patent
16 Aug 2019
TL;DR: In this article, the authors proposed a space propelling system for large-capacity storage tank filling. But, their scheme is composed of a filling gas path system and a filling liquid path system.
Abstract: The invention provides a space propelling system suitable for large-capacity storage tank filling. The propelling system scheme is composed of a filling gas path system and a filling liquid path system. The filling gas path system is composed of an oxidizing agent filling gas sub-system and a fuel filling gas sub-system, the upstream of the oxidizing agent filling gas sub-system and the upstream of the fuel filling gas sub-system are in communication with each other and then are connected to a pressurizing gas path, and the downstream of the oxidizing agent filling gas sub-system and the downstream of the fuel filling gas sub-system are mutually independent and are correspondingly connected to the filling liquid path system; and the filling liquid path system is composed of an oxidizing agent storage tank pipeline sub-system and a fuel storage tank pipeline sub-system, the oxidizing storage tank pipeline sub-system and the fuel storage tank pipeline sub-system are mutually independentand physically isolated, and are correspondingly connected to the filling gas path system. According to the space propelling system, the safety of the space propelling system can be improved, the reverse flow of the oxidizing agent and the fuel can be effectively prevented so that explosion due to chemical reaction can be avoided; and the filling efficiency of a propellant is improved, the fillingtime of the propellant is shortened, and it is ensured that the propellant fill a conventional surface tension storage tank in place.

2 citations

Patent
14 Apr 2020
TL;DR: In this paper, a closed expansion circulation system was used to combine liquid oxygen and liquid methane as a propellant combination, and the system is simple, the inherent reliability is high, the specific impulse performance is high and repeated starting is easy to achieve.
Abstract: An expansion cycle liquid oxygen and methane upper-stage engine system comprises a propellant supply system, an ignition system and a thrust chamber The propellant supply system comprises a methane supply system and a liquid oxygen supply system, the methane supply system pressurizes low-temperature liquid methane from an external storage tank and then supplies the low-temperature liquid methaneto the thrust chamber; the liquid oxygen supply system pressurizes the low-temperature liquid oxygen from the external storage tank and then supplies the low-temperature liquid oxygen to the thrust chamber; and the ignition system is located at the head of the thrust chamber and ignites under the control of a control system, liquid oxygen and methane entering the thrust chamber are ignited, and generated high-temperature gas is sprayed out of the nozzle of the thrust chamber to generate thrust force The liquid oxygen and liquid methane are used as a propellant combination, and a closed expansion circulation system scheme is adopted, so the system is simple, the inherent reliability is high, the specific impulse performance is high, and repeated starting is easy to achieve

1 citations

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
17 Nov 2020
TL;DR: In this article, a fuel gas generator pressurization module based on an electric pump was proposed for attitude and orbit control propulsion system, which was used to avoid potential safety hazards and leakage risks existing in long-term storage of high pressure gas.
Abstract: The invention provides a fuel gas pressurization attitude and orbit control propulsion system based on an electric pump. The fuel gas pressurization attitude and orbit control propulsion system comprises a fuel gas generator pressurization module based on the electric pump, an oxidizing agent storage tank, a fuel storage tank, an orbit control engine, an attitude control engine and an electric explosion valve. The fuel gas generator pressurization module based on the electric pump is connected with an inlet of the oxidizing agent storage tank and an inlet of the fuel storage tank respectively;an outlet of the oxidizing agent storage tank is connected with the orbit control engine and the attitude control engine respectively after passing through the electric explosion valve; and an outletof the fuel storage tank is connected with the orbit control engine and the attitude control engine after passing through the electric explosion valve. Pressurized gas needed in the attitude and orbit control propulsion system is provided by the fuel gas generator pressurization module based on the electric pump, normal-pressure long-term storage of the pressurized gas can be achieved before thesystem does not work, and potential safety hazards and leakage risks existing in long-term storage of high-pressure gas are avoided.
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.