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Author

Wang Haoming

Bio: Wang Haoming is an academic researcher. The author has contributed to research in topics: Propulsion & Storage tank. The author has an hindex of 2, co-authored 7 publications receiving 11 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
16 Apr 2019
TL;DR: In this paper, an integrated space marching system based on an electric pump is presented, which consists of a high-pressure air bottle, an oxidizing agent storage tank, a fuel storage tank and an electric pumps system.
Abstract: The invention discloses an orbit and attitude control integrated space marching system based on an electric pump. The orbit and attitude control integrated space marching system comprises a high-pressure air bottle, an oxidizing agent storage tank, a fuel storage tank, an electric pump system, an oxidizing agent pressure accumulator, a fuel pressure accumulator, an orbit-control engine and attitude-control engines; the high-pressure air bottle is connected with the oxidizing agent storage tank and the fuel storage tank through a pipeline I, the oxidizing agent storage tank and the fuel storagetank are connected with the electric pump system through a pipeline II and a pipeline III correspondingly, the electric pump system is connected with the orbit-control engine and the oxidizing agentpressure accumulator and the fuel pressure accumulator through a pipeline V and a pipeline VI correspondingly, and the oxidizing agent pressure accumulator and the fuel pressure accumulator are connected with the attitude-control engines through a pipeline VII and a pipeline VIII correspondingly. The electric pump system controls the rotating speed and the lift of a motor pump through an actuator,the pressure and flow of an oxidizing agent and fuel supplied for the engines are controlled, the adjustment is convenient, and the supplying requirements for a propellant of large-range thrust adjustment and multi-time starting and stopping of the orbit-control engine can be met.

2 citations

Patent
09 Oct 2020
TL;DR: In this article, a ground test system for an electric pump pressure type liquid rocket engine is presented, which is suitable for testing of variable-thrust and multi-start liquid rocket engines.
Abstract: The invention provides a liquid rocket electric pump engine ground test system. The system comprises a fuel supply system, an oxidizing agent supply system, an electric pump pressure type engine system, a power supply and a control system. The fuel supply system and the oxidizing agent supply system are connected with the electric pump pressure type engine system through a first pipeline and a second pipeline respectively, and pressurization and supply of fuel and an oxidizing agent are achieved through a fuel pump and an oxidizing agent pump. Start and stop of the fuel pump and the oxidizingagent pump are controlled through a motor driver in the power supply and the control system to achieve start and stop performance of the electric pump pressure type engine system. The system is suitable for an electric pump pressure type liquid rocket engine, and particularly has remarkable application advantages in the aspect of testing of a variable-thrust and multi-start liquid rocket engine.

1 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.

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
28 Apr 2020
TL;DR: In this article, an in-orbit autonomous management method and an autonomous management system for a planetary probe propulsion system is presented. But the method comprises the steps: enabling a propulsion management unit to collect the working parameters of the propulsion system in real-time, and judging and identifying fault modes of propulsion system according to a preset pressure or temperature threshold value; and completing corresponding fault mode autonomous management functions through the identified fault modes.
Abstract: The invention provides an in-orbit autonomous management method and an in-orbit autonomous management system for a planetary probe propulsion system. The method comprises the steps: enabling a propulsion management unit to collect the working parameters of the propulsion system in real time, and judging and identifying fault modes of the propulsion system according to a preset pressure or temperature threshold value; and completing corresponding fault mode autonomous management functions through the identified fault modes, wherein the propulsion system fault modes comprise judgment and identification of fault modes of rail entering control pipeline overpressure, posture control pipeline overpressure, pressure reducing valve overpressure, propulsion system underpressure and thruster leakage; and the self-management functions comprise rail control pipeline pressure relief self-management, posture control pipeline pressure relief self-management, pressure reducing valve overpressure self-management, propulsion system underpressure self-management and thruster leakage self-management. The problems of five main propulsion system fault modes and long-distance deep space detection instruction time delay are solved, and a guarantee is provided for high-reliability work of the long-distance planetary detector propulsion system.

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.