Electric propulsion vacuum system

Abstract

The invention discloses an electric propulsion vacuum system, and relates to a vacuum system. The invention aims to solve the problem that the test and use cost is increased due to the fact that an existing electric propulsion system cannot recover rare gas. The device comprises a vacuum chamber, an outlet of the vacuum chamber is connected with an inlet of a vacuum pump, an outlet of the vacuum pump is connected with an inlet of a gas storage tank through a pipeline, an outlet of the gas storage tank is connected with an inlet of a membrane pressure pump through a pipeline, and an outlet of the membrane pressure pump is connected with an inlet of a gas cylinder through a pipeline; the vacuum pump is used for pumping out gas in the vacuum chamber; the gas storage tank is used for storing gas pumped from the vacuum chamber by the vacuum pump; the membrane pressure pump is used for compressing gas in the gas storage tank; the gas cylinder is used for storing gas compressed by the film pressure pump. The invention belongs to the technical field of aerospace.

Description

TECHNICAL FIELD

[0001] The present application relates to a vacuum system, belonging to the field of aerospace technology. BACKGROUND

[0002] In the field of space electric propulsion (such as satellite electric propulsion system), xenon gas is usually used as the propellant. However, high-purity xenon gas is difficult to obtain and has high cost. In addition, xenon gas needs to be stored in a supercritical state at high pressure, which has high requirements for the storage container and occupies a large volume. With the development of new space technologies, the propellant of electric propulsion is gradually diversified.

[0003] Among them, iodine propellant as a solid propellant has the advantages of low cost, high storage density, no pressure container storage, and easy control, and is the preferred choice for small satellite electric propulsion system propellant. In practical applications, iodine propellant is directly stored in an iodine tank, and then iodine vapor is generated by external heating or radiation heating and delivered to the downstream thruster. When the iodine propellant is heated, there is often a problem of uneven heating and slow heat transfer, which leads to pressure response lag in system flow control. At the same time, the iodine propellant in the iodine tank often does not fully vaporize, resulting in waste of iodine and difficulties in igniting the iodine propellant system. In addition, in some radiation-type iodine storage and supply methods, the mechanical cavity occupies a large space and the iodine propellant loading rate is low.

[0004] The invention patent with publication number EP890739B1 and application date July 9, 1998 discloses an electrostatic propulsion system (140, 220) for a spacecraft including a plurality of electrostatic thrusters is serially connected to a power forming power supply system. Ionizable gas is supplied to a selected one of the thrusters to selectively activate the electrostatic thrusters. In other embodiments, heater power forming is coupled only to the selected thrusters to reduce power consumption and increase the lifetime of the cathode. The propulsion system has a reduced complexity and its only one thruster is particularly suitable for use in a spacecraft that is once fired at a given time.

[0005] The invention patent with publication number US11945606B1 and application date October 18, 2022 discloses a spacecraft propulsion system and method, characterized by a first tank containing a metallic propellant and a second tank containing a non-metallic propellant. Depending on the operational mode of the spacecraft, a selected one of the metallic propellant and the non-metallic propellant is supplied to an electric propulsion thruster. The metallic propellant is stored at a relatively high density, while the non-metallic propellant is stored at a lower density than the metallic propellant. In addition, the non-metallic propellant is preferably used to generate thrust by the electric propulsion thruster during operational maneuvers, while the metallic propellant is reserved for generating thrust by the electric propulsion thruster during end-of-life maneuvers, such as de-orbiting maneuvers.

[0006] But the above-mentioned technology can not be recovered to rare gas, resulting in test and use cost increase. SUMMARY

[0007] The present application is to solve the problem that the existing electric propulsion system cannot recover rare gas, resulting in test and use cost increase, and further proposes an electric propulsion vacuum system.

[0008] The technical scheme adopted by the present application to solve the above-mentioned problem is: the present application comprises a vacuum chamber, the outlet of the vacuum chamber is connected with the inlet of a vacuum pump, the outlet of the vacuum pump is connected with the inlet of a gas storage tank through a pipeline, the outlet of the gas storage tank is connected with the inlet of a membrane pressure pump through a pipeline, and the outlet of the membrane pressure pump is connected with the inlet of a gas cylinder through a pipeline. The vacuum pump is used to extract the gas in the vacuum chamber; The gas storage tank is used to store the gas extracted from the vacuum chamber by the vacuum pump; The membrane pressure pump is used to compress the gas in the gas storage tank; The gas cylinder is used to store the gas compressed by the membrane pressure pump.

[0009] Further, a first filter is arranged on the pipeline between the outlet of the vacuum pump and the gas storage tank.

[0010] Further, a branch pipeline is arranged on the pipeline between the vacuum pump and the first filter, and a first vacuum ball valve is installed on the branch pipeline.

[0011] Further, a second vacuum ball valve and a vacuum check valve are installed in sequence on the pipeline between the branch pipeline and the first filter.

[0012] Further, a branch pipeline is arranged on the pipeline between the gas storage tank and the membrane pressure pump, and a third vacuum ball valve is installed on the branch pipeline.

[0013] Further, a first stop valve is arranged between the branch pipeline and the membrane pressure pump.

[0014] Further, a second filter is installed on the pipeline between the membrane pressure pump and the gas cylinder.

[0015] Further, a second stop valve is installed on the pipeline between the membrane pressure pump and the second filter.

[0016] The beneficial effects of the present application are: 1. The present application can recover the tail gas generated in the electric propulsion system test into the gas cylinder, and then utilize the tail gas twice, avoiding the waste of rare gas and reducing the test cost; 2. The present application has high maintenance and repair performance, and the technical parameters of the equipment meet the technical index requirements. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 This is a schematic diagram of the principle structure of the present invention; Figure 2 This is a structural diagram of the gas storage tank; Figure 1 In the diagram, 1-vacuum chamber, 2-vacuum pump, 3-first vacuum ball valve, 4-second vacuum ball valve, 5-vacuum check valve, 6-first filter, 7-gas storage tank, 8-third vacuum ball valve, 9-first shut-off valve, 10-diaphragm pump, 11-second shut-off valve, 12-second filter, 13-gas cylinder. Detailed Implementation

[0018] Specific implementation method one: as follows Figure 1 As shown, an electric propulsion vacuum system includes a vacuum chamber 1, the outlet of the vacuum chamber 1 is connected to the inlet of a vacuum pump 2, the outlet of the vacuum pump 2 is connected to the inlet of a gas storage tank 7 through a pipeline, the outlet of the gas storage tank 7 is connected to the inlet of a diaphragm pump 10 through a pipeline, and the outlet of the diaphragm pump 10 is connected to the inlet of a gas cylinder 13 through a pipeline. Vacuum pump 2 is used to extract gas from vacuum chamber 1; Gas storage tank 7 is used to store the gas extracted from vacuum chamber 1 by vacuum pump 2; The diaphragm pump 10 is used to compress the gas in the gas storage tank 7; Gas cylinder 13 is used to store gas compressed by diaphragm pump 10.

[0019] Among them, such as Figure 2 As shown, the gas storage tank 7 is mainly used for gas storage and buffering, collecting the test exhaust gas discharged from the vacuum pump. While ensuring the outlet pressure of the vacuum pump, it can also provide a stable system pressure for the diaphragm pump. Considering the exhaust volume, a Shanghai Shenjiang gas storage tank with a volume of 1... Withstands pressure of 0.8 MPa.

[0020] Among them, the diaphragm pump adopts an advanced oil-distributorless cylinder block component structure, which reduces the difficulty of assembly process; reduces the sealing surface and improves sealing performance; the compressed medium does not come into contact with any lubricant, making it suitable for compressing extremely pure gases; the cylinder has good heat dissipation performance, allowing for higher compression ratios. Taking all factors into consideration, the Zhongding Hengsheng diaphragm pump was selected.

[0021] In some embodiments, such as Figure 1 As shown, a first filter 6 is installed on the pipeline between the outlet of vacuum pump 2 and gas storage tank 7.

[0022] In some embodiments, such as Figure 1 As shown, a branch pipe is provided on the pipeline between the vacuum pump 2 and the first filter 6, and a first vacuum ball valve 3 is installed on the branch pipe.

[0023] In some embodiments, such as Figure 1As shown, a branch pipeline is provided between the pipeline between the second vacuum ball valve 4 and the vacuum one-way valve 5.

[0024] In some embodiments, as shown, Figure 1 As shown, a branch pipeline is provided between the pipeline between the gas tank 7 and the membrane pressure pump 10, and the third vacuum ball valve 8 is installed on the branch pipeline.

[0025] In some embodiments, as shown, Figure 1 As shown, the first stop valve 9 is provided between the branch pipeline and the membrane pressure pump 10.

[0026] In some embodiments, as shown, Figure 1 As shown, the second filter 12 is installed on the pipeline between the membrane pressure pump 10 and the gas cylinder 13.

[0027] In some embodiments, as shown, Figure 1 As shown, the second stop valve 11 is installed on the pipeline between the membrane pressure pump 10 and the second filter 12.

[0028] The above is only the preferred embodiment of the present application, and does not limit the present application in any form. Although the present application has been disclosed as above, it is not intended to limit the present application. Any person skilled in the art can make some changes or modifications to the above disclosed technical content without departing from the scope of the present application, and any simple modification, equivalent replacement and improvement of the above embodiments within the scope of the present application are still within the protection scope of the present application.

Claims

1. An electrically propelled vacuum system, characterized in that, The vacuum chamber (1) is connected with the inlet of the vacuum pump (2), the outlet of the vacuum pump (2) is connected with the inlet of the gas storage tank (7) through a pipeline, the outlet of the gas storage tank (7) is connected with the inlet of the membrane pressure pump (10) through a pipeline, the outlet of the membrane pressure pump (10) is connected with the inlet of the gas cylinder (13) through a pipeline; The vacuum pump (2) is used for pumping out the gas in the vacuum chamber (1); The gas storage tank (7) is used for storing the gas pumped out from the vacuum chamber (1) by the vacuum pump (2); The membrane pressure pump (10) is used for compressing the gas in the gas storage tank (7); The gas cylinder (13) is used for storing the compressed gas by the membrane pressure pump (10).

2. An electric propulsion vacuum system according to claim 1, characterized in that The pipeline between the outlet of the vacuum pump (2) and the gas storage tank (7) is provided with the first filter (6).

3. An electric propulsion vacuum system according to claim 2, wherein, The pipeline between the vacuum pump (2) and the first filter (6) is provided with a branch pipeline, and the first vacuum ball valve (3) is installed on the branch pipeline.

4. An electric propulsion vacuum system according to claim 3, wherein, The pipeline between the branch pipeline and the first filter (6) is provided with the second vacuum ball valve (4) and the vacuum check valve (5) in sequence.

5. An electric propulsion vacuum system according to claim 1, wherein, The pipeline between the gas storage tank (7) and the membrane pressure pump (10) is provided with a branch pipeline, and the third vacuum ball valve (8) is installed on the branch pipeline.

6. An electric propulsion vacuum system according to claim 5, wherein, The branch pipeline and the membrane pressure pump (10) are provided with the first stop valve (9).

7. An electric propulsion vacuum system according to claim 1, wherein, The pipeline between the membrane pressure pump (10) and the gas cylinder (13) is provided with the second filter (12).

8. An electric propulsion vacuum system according to claim 7, wherein, The pipeline between the membrane pressure pump (10) and the second filter (12) is provided with the second stop valve (11).

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