Vacuum resource device for load test in space station cabin and use method of vacuum resource device

Abstract

The invention discloses a vacuum resource device for a load test in a space station cabin and a use method of the vacuum resource device. The device is characterized by comprising an exhaust assembly, a bulkhead, a manual main valve, a vacuum gauge, an electric main valve, a load branch and a main pipeline, the exhaust assembly is used for exhausting and heating; the downstream of the cabin wall is connected with the exhaust assembly, and the upstream is connected with the manual main valve for realizing sealing in the sealed cabin; the downstream of the manual main valve is connected with the cabin wall, and the upstream of the manual main valve is connected with the electric main valve and used for achieving manual communication and isolation of the inner space vacuum environment and the outer space vacuum environment of the sealed cabin; the vacuum gauge is used for measuring the vacuum degree of a load test vacuum resource, is connected with the main pipeline and is positioned between the manual main valve and the electric main valve; the electric main valve is used for automatically controlling the on-off of the main pipeline, the downstream is connected with the manual main valve, and the upstream is connected with the main pipeline; the load branch is used for providing vacuum resources for a load test and is connected with the main pipeline. The reliability index is improved, and vacuum resources can be provided for multiple load tests at the same time.

Description

Technical Field

[0001] The present invention relates to the field of manned spaceflight, and particularly to a vacuum resource device for in-cabin payload tests of a space station and a method for using the same. Background Art

[0002] The space vacuum resource provides ideal conditions for carrying out various high-precision space tests. In the field of manned spaceflight, the demand for vacuum resources in in-cabin payload tests of the space station is increasing.

[0003] Searching for prior arts close to the invention, there is only 1 item particularly relevant to the present technology, which is "Review of the Vacuum Support System Scheme for Space Station Payloads" by authors such as Bu Junjun (Spacecraft Environment Engineering, Vol. 28, No. 6, December 2011), which discusses the 3-way electric valve series structure of two main-path electric valves in series and a single electric valve in the branch path on the International Space Station, leading the vacuum resource outside the sealed cabin to the payload workstations with demands inside the sealed cabin, and proposing the idea of a similar 3-way electric valve series vacuum support system scheme that can be adopted in China. However, the reliability of the 3-way electric valve series still cannot meet the current requirements for realizing space vacuum resources.

[0004] Therefore, there is an urgent need in this field for a method for realizing vacuum resources with high reliability, high safety, and long life, to improve the reliability of the existing technology in realizing vacuum resources and enhance the system's fault isolation and redundancy capabilities. Summary of the Invention

[0005] To solve the above problems, the present invention provides a vacuum resource device for in-cabin payload tests of a space station and a method for using the same.

[0006] The specific technical solution of the present invention is as follows:

[0007] A vacuum resource device for in-cabin payload tests of a space station includes an exhaust assembly, a cabin wall, a manual master valve, a vacuum gauge, an electric master valve, a payload branch, and a main-path pipeline;

[0008] The exhaust assembly is used for exhausting and heating;

[0009] The downstream of the cabin wall is connected to the exhaust assembly, and the upstream is connected to the manual master valve, for achieving sealing inside the sealed cabin;

[0010] The manual master valve, with its downstream connected to the cabin wall and its upstream connected to the electric master valve, is used for achieving manual connection and isolation between the sealed cabin and the outer space vacuum environment;

[0011] The vacuum gauge is used for measuring the vacuum degree achieved by the vacuum resource device for in-cabin payload tests of the space station, is connected to the main-path pipeline, and is located between the manual master valve and the electric master valve;

[0012] The electric main valve is used to automatically control the on / off of the main pipeline, connected to the manual main valve downstream and to the main pipeline upstream;

[0013] The load branch is used to provide vacuum resources for the load test and is connected to the main pipeline.

[0014] Furthermore, the manual main valve is directly installed on the bulkhead, set to the closed state during launch to ensure the safety of the sealed cabin; set to the normally open state after entering orbit.

[0015] Furthermore, the electric main valve is a parallel structure of two valves.

[0016] Furthermore, the load branch includes a branch manual valve, a branch electric valve, a load, and a branch pipeline; the branch manual valve, the branch electric valve, and the load are connected in series through the branch pipeline in sequence;

[0017] The branch electric valve is an electric valve;

[0018] The branch manual valve is a manual valve, normally open when the space station is in the unmanned state, and the vacuum resources are controlled by two series-connected valves, namely the electric main valve and the branch electric valve.

[0019] Furthermore, the branch electric valve and the electric main valve are electric valves with different principles to ensure reliable system closure.

[0020] Furthermore, the number of load branches is one or more than one.

[0021] Furthermore, the exhaust assembly has a temperature control function to prevent ice formation and blockage at the exhaust port due to the temperature drop caused by gas expansion during the exhaust process.

[0022] Furthermore, the inner diameters of the main pipeline and the branch pipeline are different to ensure efficient system operation without wasting resources;

[0023] The main pipeline is for the load demand when all loads work simultaneously; the branch pipeline is for the load demand of a single branch load.

[0024] The present invention also provides a method for using the vacuum resources of the above-mentioned vacuum resource device for in-cabin load tests of the space station, characterized in that when the space station is in the manned state, it includes the following steps:

[0025] Step 1: Before the load conducts the vacuum resource test for the first time, open the manual main valve; keep the manual main valve in the normally open state, and there is no need to open it again before subsequent loads conduct the vacuum resource test;

[0026] Step 2: Open the electric main valve; when the space station is in the manned state, the electric main valve remains in the open state after being opened, and there is no need to open it again before subsequent loads conduct the vacuum resource test;

[0027] Step 3: Open the branch manual valve;

[0028] Step 4: Open the branch electric valve;

[0029] Step 5: The payload conducts a vacuum resource test, or exhausts waste gas after the payload test is completed;

[0030] Step 6: After the payload test is completed, close the branch electric valve;

[0031] Step 7: Close the branch manual valve.

[0032] Furthermore, when the space station is in an unmanned state, its steps include:

[0033] Step 1: Check and ensure that the main electric valve is in the closed state and the branch manual valve is in the open state;

[0034] Step 2: Before the payload conducts a vacuum resource test, open the main electric valve;

[0035] Step 3: Open the branch electric valve;

[0036] Step 4: The payload conducts a vacuum resource test, or exhausts waste gas after the payload test is completed;

[0037] Step 5: After the payload test is completed, close the branch electric valve;

[0038] Step 6: Close the main electric valve.

[0039] Compared with the prior art, the beneficial effects achieved by the present invention are as follows:

[0040] The present invention designs a structure in which the main electric valve is in parallel and then in series with the branch electric valve, and the main electric valve and the branch electric valve are electric valves with different principles; the series-parallel structure of 4 manual and electric valves. Compared with the prior art, the reliability index is increased by 0.04 (the reliability index of a single electric valve is considered as 0.998, and the reliability index of a single manual valve is considered as 1).

[0041] The present invention separately sets a branch for each payload, and each branch is provided with 1 branch manual valve and 1 branch electric valve. The vacuum resource realization device for payload tests in the space station cabin can provide vacuum resources for multiple payload tests simultaneously. Description of the Drawings

[0042] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings without creative efforts.

[0043] Figure 1 This is the composition diagram of a vacuum resource device for in - cabin payload tests in a space station according to the present invention;

[0044] Explanation of reference numerals:

[0045] 1 is the exhaust assembly; 2 is the cabin wall; 3 is the manual master valve; 4 is the vacuum gauge; 5 is the electric master valve; 6 is the branch manual valve; 7 is the branch electric valve; 8 is the payload; 9 is the main pipeline; 10 is the branch pipeline; 11 is inside the sealed cabin. Detailed implementation manners

[0046] The following uses specific examples to illustrate the implementation manners of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention.

[0047] It should be noted that the diagrams provided in the following embodiments only illustrate the basic concept of the present invention in a schematic manner. Therefore, only the components related to the present invention are shown in the diagrams, rather than being drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and ratio of each component in actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0048] The following further elaborates on the present invention in combination with the attached Figure 1 for a more detailed description:

[0049] Figure 1 This is the composition diagram of a vacuum resource device for in - cabin payload tests in a space station according to the present invention. As Figure 1 shown, the vacuum resource device for in - cabin payload tests in the space station of the present invention includes an exhaust assembly 1, a cabin wall 2, a manual master valve 3, a vacuum gauge 4, an electric master valve 5, a payload branch, and a main pipeline 9;

[0050] The exhaust assembly 1 is used for exhausting and heating. Preferably, the exhaust assembly 1 has a temperature control function to avoid ice blocking at the exhaust port due to the temperature drop caused by gas expansion during the exhaust process. In this embodiment, the temperature control range of the exhaust assembly 1 is 5 - 50 °C.

[0051] The downstream of the cabin wall 2 is connected to the exhaust assembly 1, and the upstream is connected to the manual master valve 3, which is used to seal the inside of the sealed cabin 11.

[0052] The manual master valve 3 is connected to the bulkhead 2 downstream and to the electric master valve 5 upstream, and is used to manually connect and isolate the sealed cabin 11 from the outer space vacuum environment. In one embodiment, the manual master valve 3 is directly installed on the bulkhead 2 and is set to the closed state during launch. By utilizing the high reliability of the manual valve, the risk of leakage of the sealed cabin caused by vibration during launch is eliminated, ensuring the safety of the sealed cabin. After entering orbit, it is set to the normally open state to reduce the workload of personnel operation. When the upstream pipeline, equipment or load needs to be repaired or replaced, it is set to the closed state to isolate the sealed cabin from the outer space vacuum environment.

[0053] The vacuum gauge 4 is used to measure the vacuum degree achieved by the vacuum resource realization device for the load test in the space station cabin, is connected to the main pipeline 9, and is located between the manual master valve 3 and the electric master valve 5. The range and accuracy of the vacuum gauge 4 are selected according to the requirements of the load 8. In this embodiment, the vacuum degree level is lower than 0.1 Pa.

[0054] The electric master valve 5 is used to automatically control the on-off of the main pipeline 9, is connected to the manual master valve 3 downstream and to the main pipeline 9 upstream. Preferably, the electric master valve 5 is a double-valve parallel structure. When the space station is in the unmanned state, the electric master valve 5 can ensure reliable opening of the system.

[0055] The load branch is used to provide vacuum resources for the load test and is connected to the main pipeline 9. In one embodiment, the load branch includes a branch manual valve 6, a branch electric valve 7, a load 8 and a branch pipeline 10. The branch manual valve 6, the branch electric valve 7 and the load 8 are sequentially connected in series through the branch pipeline 10. The branch manual valve 6 is a manual valve and is in the normally open state when the space station is in the unmanned state. The vacuum resources are controlled by two series-connected valves, the electric master valve 5 and the branch electric valve 7, to ensure high reliability and high safety of the system. By utilizing the high reliability of the manual valve, the branch manual valve 6 can reliably isolate the faulty branch load 8 in the event of a load 8 failure. The branch electric valve 7 is an electric valve. When the space station is in the unmanned state, the branch electric valve 7 forms a series structure with the electric master valve 5. Preferably, the branch electric valve 7 and the electric master valve 5 are electric valves of different principles to ensure reliable closing of the system. In this embodiment, the electric master valve 5 is designed to be driven by a motor, and the branch electric valve 7 is designed to be a solenoid valve.

[0056] Preferably, the number of load branches is one or more; it can provide vacuum resources for multiple load 8 tests simultaneously; however, during exhaust gas emission, it is only used for single load 8 emission each time to avoid exhaust gas pollution of other loads 8.

[0057] When the upstream pipeline, equipment or load 8 needs to be repaired or replaced, it is set to the closed state to isolate the sealed cabin from the vacuum environment of outer space. The inner diameters of the main pipeline 9 and the branch pipeline 10 are different. The inner diameters of the main pipeline 9 and the branch pipeline 10 are different to ensure the efficient operation of the system and avoid wasting resources;

[0058] The main pipeline 9 is used for the load requirements when all loads 8 work simultaneously; the branch pipeline 10 is used for the working requirements of a single branch load, ensuring the efficient operation of the system and avoiding wasting resources. In this embodiment, the inner diameter of the main pipeline 9 is designed to be 40 mm, and the inner diameter of the branch pipeline 10 is designed to be 16 mm.

[0059] The usage method of the above-mentioned vacuum resource device for in-cabin load tests of the space station is as follows: When the space station is in the manned state, its steps include:

[0060] Step 1: Before the load 8 conducts the vacuum resource test for the first time, open the manual main valve 3; keep the manual main valve 3 in the long-open state, and there is no need to open it again before the subsequent load 8 conducts the vacuum resource test;

[0061] Step 2: Open the electric main valve 5; when the space station is in the manned state, the electric main valve 5 remains open after being opened, and there is no need to open it again before the subsequent load 8 conducts the vacuum resource test;

[0062] Step 3: Open the branch manual valve 6;

[0063] Step 4: Open the branch electric valve 7;

[0064] Step 5: The load 8 conducts the vacuum resource test, or discharges waste gas after the load 8 completes the test; when the load 8 conducts the vacuum resource test, one or more loads 8 conduct the vacuum resource test simultaneously; when the load 8 discharges waste gas after the test, only one load can discharge waste gas, and multiple loads 8 need to perform multiple operations to discharge waste gas.

[0065] Step 6: After the load 8 completes the test, close the branch electric valve 7;

[0066] Step 7: Close the branch manual valve 6.

[0067] The usage method of the above-mentioned vacuum resource device for in-cabin load tests of the space station is as follows: When the space station switches to the unmanned state, its steps include:

[0068] Step 1: Check and ensure that the electric main valve 5 is in the closed state and the branch manual valve 6 is in the open state;

[0069] Step 2: Before the load 8 conducts the vacuum resource test, open the electric main valve 5;

[0070] Step 3: Open the branch electric valve 7;

[0071] Step 4: The payload 8 conducts a vacuum resource test, or exhausts waste gas after the test of the payload 8 is completed; preferably, when the payload 8 conducts a vacuum resource test, one or more vacuum resource tests of the payload 8 are carried out simultaneously; when exhausting waste gas after the test of the payload 8 is completed, waste gas can only be exhausted for one payload at a time, and multiple operations must be carried out for multiple payloads 8 to exhaust waste gas;

[0072] Step 5: After the test of the payload 8 is completed, close the branch electric valve 7;

[0073] Step 6: Close the main electric valve 5.

[0074] Although the present invention has been disclosed above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A vacuum resource device for in-cabin payload tests of a space station, characterized in that It includes an exhaust assembly (1), a bulkhead (2), a manual main valve (3), a vacuum gauge (4), an electric main valve (5), a load branch, and a main pipeline (9); The exhaust assembly (1) is used for exhausting and heating; The downstream of the bulkhead (2) is connected to the exhaust assembly (1), and the upstream is connected to the manual main valve (3), which is used to seal the inside of the sealed cabin (11); The downstream of the manual main valve (3) is connected to the bulkhead (2), and the upstream is connected to the electric main valve (5), which is used to manually connect and isolate the inside of the sealed cabin (11) from the outer space vacuum environment; The vacuum gauge (4) is used to measure the vacuum degree reached by the vacuum resource realization device in the space station cabin, is connected to the main pipeline (9), and is located between the manual main valve (3) and the electric main valve (5); The electric main valve (5) is used to automatically control the on-off of the main pipeline (9), the downstream is connected to the manual main valve (3), and the upstream is connected to the main pipeline (9); The load branch is used to provide vacuum resources for the load test and is connected to the main pipeline (9).

2. The vacuum resource device for in - module payload tests of a space station according to claim 1, wherein, The manual main valve (3) is directly installed on the bulkhead (2), and is set to the closed state during launch to ensure the safety of the inside of the sealed cabin (11); it is set to the normally open state after entering the orbit.

3. A vacuum resource device for in-cabin load tests of a space station, as described in claim 1, wherein, The electric main valve (5) is a double-valve parallel structure.

4. The vacuum resource device for in - space - station cabin payload tests as claimed in claim 1, wherein, The load branch includes a branch manual valve (6), a branch electric valve (7), a load (8), and a branch pipeline (10); The branch manual valve (6), the branch electric valve (7), and the load (8) are sequentially connected in series through the branch pipeline (10); The branch electric valve (7) is an electric valve; The branch manual valve (6) is a manual valve, which is in the normally open state when the space station is in the unmanned state, and the vacuum resources are controlled by two series-connected valves, namely the electric main valve (5) and the branch electric valve (7).

5. The vacuum resource device for in-cabin payload tests of a space station according to claim 4, characterized in that, The branch electric valve (7) and the electric main valve (5) are electric valves with different principles to ensure the reliable closing of the system.

6. The vacuum resource device for in-cabin payload tests of a space station according to claim 1, wherein The load branch is one or more than one.

7. A vacuum resource device for in-cabin payload tests of a space station, as described in claim 1, wherein The exhaust assembly (1) has a temperature control function to prevent the exhaust port from freezing and blocking due to the temperature drop caused by the gas expansion during the exhaust process.

8. The vacuum resource device for in-cabin load tests of a space station according to claim 1, characterized in that, The inner diameters of the main pipeline (9) and the branch pipeline (10) are different to ensure the efficient operation of the system and avoid wasting resources; The main pipeline (9) is used for the load requirements when all loads (8) work simultaneously; The branch pipeline (10) is used for the load requirements of a single branch load to work.

9. The usage method of a vacuum resource device for in-cabin payload tests of a space station, as described in claim 1, is characterized in that When the space station is in the manned state, it includes the following steps: Step 1: Before the load (8) conducts the vacuum resource test for the first time, open the manual main valve (3); make the manual main valve (3) in the long-open state, and there is no need to open it again before the subsequent load (8) conducts the vacuum resource test; Step 2: Open the electric main valve (5); when the space station is in the manned state, the electric main valve (5) remains in the open state after being opened, and there is no need to open it again before the subsequent load (8) conducts the vacuum resource test; Step 3: Open the branch manual valve (6); Step 4: Open the branch electric valve (7); Step 5: The load (8) conducts the vacuum resource test, or discharges the waste gas after the load (8) test is completed; Step 6: After the load (8) test is completed, close the branch electric valve (7); Step 7: Close the branch manual valve (6).

10. The usage method according to claim 9, characterized in that, When the space station is converted to an unmanned state, the following steps are included: Step 1: Check and ensure that the main electric valve (5) is in the closed state and the branch manual valve (6) is in the open state; Step 2: Before the payload (8) conducts a vacuum resource test, open the main electric valve (5); Step 3: Open the branch electric valve (7); Step 4: The payload (8) conducts a vacuum resource test, or exhausts waste gas after the payload (8) test is completed; Step 5: After the payload (8) test is completed, close the branch electric valve (7); Step 6: Close the main electric valve (5).

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