CN113819023A - Propellant supply device of magnetic plasma power propulsion system - Google Patents
Propellant supply device of magnetic plasma power propulsion system Download PDFInfo
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- CN113819023A CN113819023A CN202111014938.5A CN202111014938A CN113819023A CN 113819023 A CN113819023 A CN 113819023A CN 202111014938 A CN202111014938 A CN 202111014938A CN 113819023 A CN113819023 A CN 113819023A
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- propellant
- module
- flow
- pressure
- propulsion system
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0012—Means for supplying the propellant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0006—Details applicable to different types of plasma thrusters
- F03H1/0031—Thermal management, heating or cooling parts of the thruster
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0081—Electromagnetic plasma thrusters
Abstract
A propellant supply device of a magnetic plasma power propulsion system comprises a propellant low-temperature storage module, a pressure regulation module and a flow regulation module; the propellant low-temperature storage module is used for cooling, compressing and storing the propellant; the propellant output by the propellant low-temperature storage module is sequentially supplied to the cathode and the anode of the propulsion system through the pressure regulation module and the flow regulation module; the pressure regulating module is used for reducing the pressure of the propellant; the flow regulating module is used for regulating the flow output to the cathode and the anode of the propulsion system. The invention adopts an active refrigeration zero-evaporation scheme, so that the volume and the weight of the propellant storage tank are greatly reduced; the large-range propellant flow adjusting module is adopted, so that the precise control of the propellant flow can be completed simultaneously; the propellant low-temperature storage module, the pressure regulating module and the flow regulating module are integrated, so that the volume weight of the propellant supply system is greatly reduced; the use of argon as the propellant saves the propellant cost.
Description
Technical Field
The invention relates to a propellant supply device of a magnetic plasma power propulsion system, in particular to a low-temperature propellant supply device of a high-power magnetic plasma power propulsion system, belonging to the technical field of design of an electric propulsion power system of a space spacecraft.
Background
The high-power magnetic plasma power electric thruster (MPDT) is an advanced power device for accelerating the high-speed ejection of plasma by utilizing the ultra-strong electromagnetic force, has the technical advantages of ultra-high specific impulse, high thrust density, compact structure and the like, has core indexes such as specific impulse and the like far higher than the existing space propulsion technology, and is one of key technologies for determining the success or failure of important space missions such as manned Mars detection, ultra-large space-based weapon platform deployment and the like in the future.
The traditional ion and Hall electric propulsion technology is an electrostatic field acceleration working mode, the acceleration voltage is relatively high, xenon with a heavier molecular weight is generally used as a propellant, so that the high specific impulse performance is obtained, and the propellant adopts a high-pressure normal-temperature storage scheme during the on-orbit working. In contrast, in the MPDT, the plasma is in a complex electromagnetic acceleration mode, the acceleration voltage is relatively small, and a gas with a relatively light molecular weight is used as a propellant, so that high specific impulse and efficiency can be obtained. However, compared with the gas with relatively light molecular weight, the gas is stored at high pressure and normal temperature, and the storage density is low, so that the volume of a propellant storage box required during on-track operation is greatly increased, and the on-track application of a high-power magnetic plasma power propulsion system is greatly limited.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the propellant supply device of the magnetic plasma power propulsion system comprises a propellant low-temperature storage module, a pressure regulation module and a flow regulation module; the propellant low-temperature storage module is used for cooling, compressing and storing the propellant; the propellant output by the propellant low-temperature storage module is sequentially supplied to the cathode and the anode of the propulsion system through the pressure regulation module and the flow regulation module; the pressure regulating module is used for reducing the pressure of the propellant; the flow regulating module is used for regulating the flow output to the cathode and the anode of the propulsion system. The invention adopts an active refrigeration zero-evaporation scheme, so that the volume and the weight of the propellant storage tank are greatly reduced; the large-range propellant flow adjusting module is adopted, so that the precise control of the propellant flow can be completed simultaneously; the propellant low-temperature storage module, the pressure regulating module and the flow regulating module are integrated, so that the volume weight of the propellant supply system is greatly reduced; the use of argon as the propellant saves the propellant cost.
The purpose of the invention is realized by the following technical scheme:
a propellant supply device of a magnetic plasma power propulsion system comprises a propellant low-temperature storage module, a pressure regulation module and a flow regulation module;
the propellant low-temperature storage module is used for cooling, compressing and storing the propellant;
the propellant output by the propellant low-temperature storage module is sequentially supplied to the cathode and the anode of the propulsion system through the pressure regulation module and the flow regulation module;
the pressure regulating module is used for reducing the pressure of the propellant to the working pressure required by the flow regulating module;
the flow regulating module is used for regulating the flow output to the cathode and the anode of the propulsion system.
Preferably, the propellant low-temperature storage module cools and compresses the propellant by adopting an active refrigeration zero-evaporation method.
Preferably, argon is used as the propellant.
Preferably, the propellant output pipeline in the pressure regulating module is divided into two parts, wherein one part supplies propellant to the cathode of the propulsion system through the flow regulating module, and the other part supplies propellant to the anode of the propulsion system through the flow regulating module; the pressures in the two propellant output lines are different.
Preferably, the pressure regulation module comprises upstream of 4 high pressure latching valves, the 4 upstream high pressure latching valves being in parallel series for safely isolating the high pressure zone from the low pressure zone.
Preferably, the propellant low-temperature storage module comprises a refrigerator and a storage tank;
the refrigerating machine is used for cooling the propellant;
the storage tank is used for storing the cooled propellant.
Preferably, the outlet of the propellant low-temperature storage module is welded with the inlet of the pressure regulating module through a titanium pipe; the outlet of the pressure regulating module and the inlet and outlet of the flow control module are standard M8 screw joints, and are installed in a screw connection mode through a stainless steel pipe and a ball head.
Preferably, the pressure regulating module includes a high pressure sensor for monitoring the pressure in the reservoir of the cryogenic storage module of propellant to estimate the remaining amount of propellant.
Preferably, the flow regulating module comprises a flow control self-locking valve and a flow controller;
the flow control self-locking valve is used for controlling the flow on-off of each path of thruster, and the flow controller is used for controlling the output flow.
Preferably, the flow rate is adjusted in the range of 50mg/s to 150 mg/s.
Compared with the prior art, the invention has the following beneficial effects:
(1)the invention adopts the active refrigeration zero-evaporation scheme of the Stirling refrigerator, can cool the argon to 85K from normal temperature, has the storage pressure of the storage tank of 1.5MPa, and further can store the argon with the density of 23.15kg/m3Increased to 1413.4kg/m3Thereby greatly reducing the volume and weight of the propellant storage tank.
(2) The invention adopts a large-range propellant flow adjusting module, can simultaneously complete the accurate control of the flow of the magnetic plasma power thruster cathode and anode propellants, realize the optimal matching of the cathode and anode gas supply flow, and complete the large-range adjustable working power (50 kW-100 kW) of the thruster by matching with the thruster.
(3) The invention adopts the integrated solution of the propellant low-temperature storage module, the pressure regulating module and the flow regulating module, and the system can rapidly finish low-temperature storage, high-pressure to low-pressure regulation and large-range flow control, thereby greatly reducing the volume weight of the propellant supply system.
(4) Compared with the traditional method of selecting xenon as the propellant, the method of the invention adopts argon as the propellant and has the following advantages: compared with xenon, the argon can improve the propelling specific impulse of the MPDT from about 3000 seconds to about 6000 seconds by one time, and the consumption of the propellant of the spacecraft can be greatly saved. Secondly, the molecular weight (39.95g/mol) of argon is far lower than that (131.29g/mol) of xenon, the specific impulse is about twice of xenon, and further, under the condition of the same propulsion carrying mass, the total impulse of argon is increased by two times relative to xenon, so that the power efficiency of the spacecraft is greatly improved. And about 30 yuan/1 kg of argon gas cost and about 12000 yuan/1 kg of xenon gas cost, and the consumption cost of the propellant can be greatly saved by adopting the argon gas as the propellant.
Drawings
FIG. 1 is a schematic diagram of the composition of the apparatus of the present invention (where C represents the cathode and the part with the symbol C is the part on the cathode branch; A represents the anode and the part with the symbol A is the part on the anode branch).
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
A propellant supply device of a magnetic plasma power propulsion system comprises a propellant low-temperature storage module, a pressure regulation module and a flow regulation module; the propellant low-temperature storage module is used for cooling, compressing and storing the propellant; the propellant output by the propellant low-temperature storage module is sequentially supplied to the cathode and the anode of the propulsion system through the pressure regulation module and the flow regulation module; the pressure regulating module is used for reducing the pressure of the propellant to the working pressure required by the flow regulating module; the flow regulating module is used for regulating the flow output to the cathode and the anode of the propulsion system.
The propellant low-temperature storage module cools and compresses the propellant by adopting an active refrigeration zero-evaporation method. Argon is used as propellant.
The propellant output pipeline in the pressure regulating module is divided into two parts, wherein one part supplies propellant for the cathode of the propulsion system through the flow regulating module, and the other part supplies propellant for the anode of the propulsion system through the flow regulating module; the pressures in the two propellant output lines are different.
The upstream of the pressure regulating module comprises 4 upstream high pressure latching valves, the 4 upstream high pressure latching valves being in parallel series for safely isolating the high pressure zone from the low pressure zone.
The propellant low-temperature storage module comprises a refrigerator and a storage box; the refrigerating machine is used for cooling the propellant; the storage tank is used for storing the cooled propellant.
The outlet of the propellant low-temperature storage module is welded with the inlet of the pressure regulating module through a titanium pipe; the outlet of the pressure regulating module and the inlet and outlet of the flow control module are standard M8 screw joints, and are installed in a screw connection mode through a stainless steel pipe and a ball head.
The pressure regulating module comprises a high-pressure sensor which is used for monitoring the pressure in a storage tank in the propellant low-temperature storage module and estimating the residual quantity of the propellant.
The flow regulating module comprises a flow control self-locking valve and a flow controller; the flow control self-locking valve is used for controlling the flow on-off of each path of thruster, and the flow controller is used for controlling the output flow. The flow regulating range is 50 mg/s-150 mg/s.
More specifically:
the invention relates to a low-temperature high-density propellant supply device of a high-power magnetic plasma power propulsion system, in particular to a propellant supply device of a magnetic plasma power propulsion system, which mainly comprises 1 set of propellant low-temperature storage module, 1 set of pressure regulation module and 4 sets of flow regulation module, and can provide precision flow supply for a high-power magnetic plasma power thruster, as shown in figure 1.
The pressure regulating module is used for reducing the high-pressure gas to the working pressure required by the flow controller, and comprises 4 upstream high-pressure latching valves (HLV1, HLV2, HLV3 and HLV4), 2 adding and discharging valves (MV1 and MV2), 1 high-pressure sensor (HPT), 4 midstream high-pressure latching valves (C-HLV1, C-HLV2, A-HLV1 and A-HLV2), 2 low-pressure adding and discharging valves (C-MV and A-MV), 4 proportional control valves (C-PPV1, C-PPV2, A-PPV1 and A-PPV2), and 4 low-pressure sensors (C-LPT1, C-LPT2, A-LPT1 and A-LPT 2). The upstream high-pressure self-locking valve mainly plays a role in safety isolation, separates a high-pressure area from a low-pressure area in a launching stage and is normally open in an on-orbit working state; the high-pressure sensor monitors the pressure in the storage tank and estimates the residual gas; the charging and discharging valve is an external interface for ground test and charging; the midstream high-pressure self-locking valves (C-HLV1, C-HLV2, A-HLV1 and A-HLV2) have the functions of safety isolation and pressure branch selection, a high-pressure area is separated from a low-pressure area when the storage and supply subsystem is in a non-working state, one of each pressure branch is opened by sending a command before the electric thruster works every time, and the pressure branch is closed by sending a command after the electric thruster works; the proportional valve and the low-pressure sensor jointly form a proportional electronic pressure reducer under the control of the control unit, and the upstream high-pressure gas is regulated and controlled within a required range. The module is independently packaged before delivery, a system joint test is carried out, delivery is carried out in a module form, and the module is arranged close to a gas cylinder on the satellite.
The flow regulating module is used for regulating the flow output to the cathode and the anode of the propulsion system, and 4 identical modules are defined as flow regulating modules N1, N2, S1 and S2, and each module comprises 4 flow control latching valves (N1C-FLVA, N1C-FLVB, N1A-FLVA, N1A-FLVB) and 2 flow control controllers (N1C-FC, N1A-FC). The flow control self-locking valve is used for controlling the flow on-off of each path of thruster; the flow controller outputs rated flow under the control of the control unit, the flow regulation range is 50-150 mg/s, and the flow range of each branch of the anode and the cathode can reach 20-80 mg/s. The module is delivered in a module form with the individual packages prior to delivery.
The invention relates to a low-temperature high-density propellant supply device of a high-power magnetic plasma power propulsion system, wherein three modules are connected through a satellite pipeline, an outlet of a propellant low-temperature storage module is welded with an inlet of a pressure regulating module through a titanium pipe, an outlet of the pressure regulating module and an inlet and outlet of a flow control module are standard M8 screw joints, and the three modules are installed through a stainless steel pipe and a ball head in a screw connection mode. The high-pressure part pipeline adopts a titanium alloy pipeline with the wall thickness of 1mm and the outer diameter of 6mm, and the low-pressure part pipeline can adopt a stainless steel pipeline with the wall thickness of 0.8mm and the outer diameter of 4 mm.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. The propellant supply device of the magnetic plasma power propulsion system is characterized by comprising a propellant low-temperature storage module, a pressure regulation module and a flow regulation module;
the propellant low-temperature storage module is used for cooling, compressing and storing the propellant;
the propellant output by the propellant low-temperature storage module is sequentially supplied to the cathode and the anode of the propulsion system through the pressure regulation module and the flow regulation module;
the pressure regulating module is used for reducing the pressure of the propellant to the working pressure required by the flow regulating module;
the flow regulating module is used for regulating the flow output to the cathode and the anode of the propulsion system.
2. A propellant supply system for a magnetic plasma power propulsion system as claimed in claim 1 wherein the propellant cryogenic storage module cools and compresses the propellant by active refrigeration with zero evaporation.
3. A propellant supply for a magnetic plasma powered propulsion system as claimed in claim 1 wherein the propellant is argon.
4. A propellant supply arrangement for a magnetic plasma powered propulsion system as claimed in claim 1 wherein the propellant output line in the pressure regulating module is divided into two parts, one part supplying propellant to the cathode of the propulsion system via the flow regulating module and the other part supplying propellant to the anode of the propulsion system via the flow regulating module; the pressures in the two propellant output lines are different.
5. A propellant feed arrangement for a magnetic plasma dynamic propulsion system as claimed in claim 1 wherein the pressure regulation module comprises 4 upstream high pressure latching valves, the 4 upstream high pressure latching valves being in parallel series for safely isolating the high pressure zone from the low pressure zone.
6. A propellant supply for a magnetic plasma powered propulsion system as claimed in claim 1 wherein the propellant cryogenic storage module includes a refrigerator and a tank;
the refrigerating machine is used for cooling the propellant;
the storage tank is used for storing the cooled propellant.
7. A propellant supply system for a magnetic plasma power propulsion system as claimed in claim 1 wherein the outlet of the propellant cryogenic storage module is welded to the inlet of the pressure regulating module by a titanium tube; the outlet of the pressure regulating module and the inlet and outlet of the flow control module are standard M8 screw joints, and are installed in a screw connection mode through a stainless steel pipe and a ball head.
8. A propellant supply system for a magnetic plasma dynamic propulsion system as claimed in any one of claims 1 to 7 wherein the pressure regulation module includes a high pressure sensor for monitoring the pressure in the reservoir of the cryogenic storage module of propellant to provide an estimate of the remaining amount of propellant.
9. A propellant supply arrangement of a magnetic plasma dynamic propulsion system as claimed in any one of claims 1 to 7 wherein the flow regulation module comprises a flow control latching valve, a flow controller;
the flow control self-locking valve is used for controlling the flow on-off of each path of thruster, and the flow controller is used for controlling the output flow.
10. A propellant supply for a magnetic plasma dynamic propulsion system as claimed in claim 9, wherein the flow rate adjustment range is 50mg/s to 150 mg/s.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111014938.5A CN113819023B (en) | 2021-08-31 | 2021-08-31 | Propellant supply device of magnetic plasma power propulsion system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111014938.5A CN113819023B (en) | 2021-08-31 | 2021-08-31 | Propellant supply device of magnetic plasma power propulsion system |
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| CN113819023A true CN113819023A (en) | 2021-12-21 |
| CN113819023B CN113819023B (en) | 2023-04-14 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH116473A (en) * | 1997-06-16 | 1999-01-12 | Ishikawajima Harima Heavy Ind Co Ltd | Dc arc thrustor |
| CN102678500A (en) * | 2012-05-10 | 2012-09-19 | 北京航空航天大学 | Magnetic plasma propeller |
| US9334855B1 (en) * | 2005-12-01 | 2016-05-10 | Busek Company, Inc. | Hall thruster for use with a condensable propellant |
| CN109983217A (en) * | 2016-11-23 | 2019-07-05 | 乔治洛德方法研究和开发液化空气有限公司 | Device and method for adjusting gas flow |
| CN110081301A (en) * | 2019-05-17 | 2019-08-02 | 中国科学院理化技术研究所 | A kind of cryogenic liquid Zero emission device and method |
| EP3620646A1 (en) * | 2018-09-06 | 2020-03-11 | Airbus Defence and Space Limited | A propellant |
-
2021
- 2021-08-31 CN CN202111014938.5A patent/CN113819023B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH116473A (en) * | 1997-06-16 | 1999-01-12 | Ishikawajima Harima Heavy Ind Co Ltd | Dc arc thrustor |
| US9334855B1 (en) * | 2005-12-01 | 2016-05-10 | Busek Company, Inc. | Hall thruster for use with a condensable propellant |
| CN102678500A (en) * | 2012-05-10 | 2012-09-19 | 北京航空航天大学 | Magnetic plasma propeller |
| CN109983217A (en) * | 2016-11-23 | 2019-07-05 | 乔治洛德方法研究和开发液化空气有限公司 | Device and method for adjusting gas flow |
| EP3620646A1 (en) * | 2018-09-06 | 2020-03-11 | Airbus Defence and Space Limited | A propellant |
| CN110081301A (en) * | 2019-05-17 | 2019-08-02 | 中国科学院理化技术研究所 | A kind of cryogenic liquid Zero emission device and method |
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| CN113819023B (en) | 2023-04-14 |
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