Rocket pipeline air pressure automatic test device and method

Abstract

The invention provides a rocket pipeline air pressure automatic test device and method. The device comprises a driving air source, an air supply air source, an air booster pump, a filtering module, a pressure and speed regulating module and multiple parallel detection branches. The gas booster pump comprises a driving chamber and a booster chamber, and the filtering module and the pressure and speed regulating module are arranged on the first pipeline; the filtering module is used for filtering the driving gas source; the pressure and speed regulating module is used for regulating the pressure and flow velocity of the driving air source; the gas supply gas source is communicated with the pressurizing chamber of the gas pressurizing pump through a second pipeline; the multi-path parallel detection branch is communicated with the pressurizing chamber through the output main path; the multi-path parallel detection branch comprises a plurality of parallel branches; wherein the different branches are used for transmitting gas with pressure required by the test to different test pieces. The automation degree is improved, the test efficiency is improved, and pipelines of various specifications can be detected at the same time.

Description

Technical Field

[0001] This application relates to the field of testing equipment technology, and in particular to an automated testing device and method for rocket pipeline air pressure. Background Technology

[0002] The production and verification testing (hereinafter referred to as testing) of rockets (mainly liquid rockets) involves a large number of pressure-bearing connecting pipelines, hereinafter referred to as pipelines. These pressure-bearing pipelines, connecting joints, or welded joints must undergo gas pressure testing to assess their sealing performance and strength. The pipelines need to be filled with gas at a certain pressure. However, due to limitations imposed by different connection methods, specifications, and pressure requirements, batch testing is often not possible. Frequent manual switching between different pipelines is required, resulting in low automation levels and low efficiency in production testing and experimentation.

[0003] Traditional pneumatic testing equipment consists of a single-unit pneumatic pressure booster. This type of booster has only one pressure output end with a single interface, and can only adjust one pressure. For parameters that need to be tested, they can only be recorded manually. Personnel must participate manually throughout the process, which is cumbersome, complex, and time-consuming. For batch production or when there are many pipelines, it consumes a lot of personnel and is inefficient, which is not conducive to the company's flight-based production and launch requirements.

[0004] Therefore, there is an urgent need to provide an automated testing device and method for rocket pipeline air pressure to solve the problems of low automation, low testing efficiency, and inability to simultaneously test multiple specifications of pipelines. Summary of the Invention

[0005] The purpose of this application is to provide an automated testing device and method for rocket pipeline air pressure, which improves the degree of automation, increases testing efficiency, and allows for simultaneous testing of pipelines of various specifications.

[0006] To achieve the above objectives, as a first aspect of this application, this application provides an automated testing device for rocket pipeline gas pressure. The device includes: a driving gas source, a supply gas source, a gas booster pump, a filter module, a pressure regulating and speed controlling module, and multiple parallel detection branches. The gas booster pump includes a driving chamber and a pressurizing chamber, with a first piston and a second piston respectively disposed within the driving chamber and the pressurizing chamber, and the first piston and the second piston are connected by a connecting rod. The driving gas source is connected to the driving chamber of the gas booster pump via a first pipeline. The filter module and the pressure regulating and speed controlling module are disposed on the first pipeline. The filter module is used to filter the driving gas source. The pressure regulating and speed controlling module is used to adjust the pressure and flow rate of the driving gas source. The supply gas source is connected to the pressurizing chamber of the gas booster pump via a second pipeline. The multiple parallel detection branches are connected to the pressurizing chamber via an output main path. The multiple parallel detection branches include multiple parallel branches; wherein different branches are used to deliver gas at the required test pressure to different test specimens.

[0007] The rocket pipeline gas pressure automated test device described above includes a pressure regulating and speed regulating module comprising: a first electronically actuated pressure reducing valve and an electronically actuated throttle valve; the first electronically actuated pressure reducing valve and the electronically actuated throttle valve are connected within the first pipeline; the first electronically actuated pressure reducing valve is used to regulate the pressure of the gas input from the driving gas source into the first pipeline; and the electronically actuated throttle valve is used to regulate the flow rate of the gas input from the driving gas source into the first pipeline.

[0008] In the rocket pipeline gas pressure automated test device described above, the filter module is a first filter; the first filter is connected inside the first pipeline; the first filter is located between the driving gas source and the first electronically actuated pressure reducing valve.

[0009] The rocket pipeline air pressure automated test device described above includes a first solenoid valve installed on the first pipeline; one end of the first solenoid valve is connected to the electronic actuator throttle valve, and the other end is connected to the drive chamber.

[0010] As described above, in the automated test device for rocket pipeline air pressure, a second filter and a shut-off valve are provided on the second pipeline; one end of the second filter is connected to the gas supply source, and the other end is connected to the shut-off valve; the end of the shut-off valve away from the second filter is connected to the pressurization chamber; when the shut-off valve is opened, the gas from the gas supply source is delivered to the pressurization chamber.

[0011] As described above, the automated test device for rocket pipeline gas pressure includes a third filter, a first safety valve, a second solenoid valve, and a third solenoid valve on the main output line. The third filter is used to filter the gas pumped out by the gas booster pump. The first safety valve is used to prevent the pipeline pressure from exceeding the warning value. The second solenoid valve is a pressure supply switch. The third solenoid valve is a pressure relief port for the main output line.

[0012] The rocket pipeline gas pressure automated testing device described above includes a first pressure sensor installed on the first pipeline and a second pressure sensor installed on the output pipeline; the first pressure sensor is used to display the adjusted gas pressure; and the second pressure sensor is used to display the pressurized pipeline gas pressure.

[0013] The automated rocket pipeline gas pressure testing device described above includes a first branch, a second branch, a third branch, and a fourth branch in a multi-parallel detection system. The first branch is equipped with a second electronically actuated pressure reducing valve, a third pressure sensor, a fourth solenoid valve, and a fifth solenoid valve. The second electronically actuated pressure reducing valve is used to adjust the gas pressure to the required test pressure. The third pressure sensor is used to display the gas pressure in the pipeline after pressure reduction. The fourth solenoid valve opens to transmit gas to the test piece for gas pressure testing. The fifth solenoid valve is used to release pressure.

[0014] In the rocket pipeline gas pressure automated test device described above, the gas supply source is connected to nitrogen or compressed air.

[0015] As a second aspect of this application, this application provides an automated test method for rocket pipeline gas pressure, applied to the aforementioned automated test device for rocket pipeline gas pressure. The method includes: adjusting the pressure and flow rate of the gas output from the driving gas source to the required range through a pressure regulating and speed regulating module on the first pipeline, and delivering it to a gas booster pump; opening a shut-off valve to deliver the gas from the gas supply source to the gas booster pump; when the gas pressure is insufficient, starting the gas booster pump to boost the gas pressure in the booster chamber to the maximum pressure required for the test; adjusting the gas pressure to the required test pressure through a second electronically actuated pressure reducing valve on the branch; opening a fourth solenoid valve to deliver the gas to the test piece for gas pressure testing; after the test, the second electronically actuated pressure reducing valve is reset to zero, the fifth solenoid valve is opened first to release pressure, and then the fourth solenoid valve is opened to release all the pressure on the branch.

[0016] The beneficial effects achieved by this application are as follows:

[0017] (1) In pipeline testing, this application can accommodate multiple specifications, multiple connection methods and multiple pressure requirements, thereby improving testing efficiency.

[0018] (2) This application is equipped with a pressure sensor, an electronically actuated pressure reducing valve, and functions such as pressure data curve acquisition and digital pressure control. The device is easy to operate, can be used for batch testing, and improves test efficiency.

[0019] (3) This application is equipped with an automatic safety valve release device and a solenoid valve pressure relief port to improve safety. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can be obtained based on these drawings.

[0021] Figure 1 This is a schematic diagram of the structure of an automated rocket pipeline air pressure testing device according to an embodiment of this application.

[0022] Reference numerals: 1-Drive air source; 2-First pipeline; 3-Gas booster pump; 4-Supply air source; 5-Second pipeline; 6-Output main line; 7-Multi-channel parallel detection branch; 8-Second safety valve; 21-First filter; 22-First electronic actuator pressure reducing valve; 23-First pressure sensor; 24-Electronic actuator throttle valve; 25-First solenoid valve; 31-Drive chamber; 32-Pressure boosting chamber; 33-First piston; 34-Second piston; 35-Connecting rod; 51-Second filter; 52-Stop valve; 61-Third filter; 62-Second pressure sensor; 63-First safety valve; 64-Second solenoid valve; 65-Third solenoid valve; 71-Second electronic actuator pressure reducing valve; 72-Third pressure sensor; 73-Fourth solenoid valve; 74-Fourth pressure sensor; 75-Fifth solenoid valve. Detailed Implementation

[0023] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0024] Example 1

[0025] like Figure 1As shown, this application provides an automated testing device for rocket pipeline gas pressure. The device includes: a driving gas source 1, a supply gas source 4, a gas booster pump 3, a filter module, a pressure and speed regulation module, and a multi-parallel detection branch 7. The gas booster pump 3 includes a driving chamber 31 and a booster chamber 32. A first piston 33 and a second piston 34 are respectively installed in the driving chamber 31 and the booster chamber 32. The first piston 33 and the second piston 34 are connected by a connecting rod 35. The diameter of the driving chamber 31 is larger than the diameter of the booster chamber 32, and the volume of the driving chamber 31 is larger than the volume of the booster chamber 32. The driving chamber 31 and the booster chamber 32 are separated and not interconnected. The diameter of the first piston 33 is larger than that of the second piston 34. The diameter of the first piston 33 is such that it moves within the drive chamber 31, and the second piston 34 moves within the pressure chamber 32. The drive gas source 1 is connected to the drive chamber 31 of the gas booster pump 3 via the first pipeline 2. A filter module and a pressure regulating and speed regulating module are installed on the first pipeline 2. The filter module is used to filter the drive gas source 1. The pressure regulating and speed regulating module is used to regulate the pressure and flow rate of the drive gas source 1. The gas supply source 4 is connected to the pressure chamber 32 of the gas booster pump 3 via the second pipeline 5. The multi-parallel detection branch 7 is connected to the pressure chamber 32 via the output main pipeline 6. The multi-parallel detection branch 7 includes multiple parallel branches. Different branches are used to deliver the gas required for the test to different test pieces.

[0026] It needs to be explained that the working principle of the gas booster pump 3 is as follows: low-pressure gas acts on the large-area driving piston (i.e., the first piston 33), which pushes the small-area booster piston (i.e., the second piston 34) through the connecting rod 35, thus doing work on the gas input from the gas supply source 4 into the booster chamber 32, achieving "gas-driven gas" non-electric boosting. The driving gas source 1 is only connected to the driving chamber 31 (large piston side), and the gas is controlled by the reversing valve to enter the left or right end cavity of the driving chamber 31, driving the first piston 33 to reciprocate; while the gas to be boosted enters the booster chamber 32 (small piston side).

[0027] like Figure 1 As shown, the pressure regulating and speed regulating module includes: a first electronic actuator pressure reducing valve 22 and an electronic actuator throttle valve 24; the first electronic actuator pressure reducing valve 22 and the electronic actuator throttle valve 24 are connected in the first pipeline 2; the first electronic actuator pressure reducing valve 22 is used to regulate the pressure of the gas input into the first pipeline 2 by the driving gas source 1; the electronic actuator throttle valve 24 is used to regulate the flow rate of the gas input into the first pipeline 2 by the driving gas source 1.

[0028] like Figure 1As shown, the filter module is a first filter 21; the first filter 21 is connected in the first pipeline 2; the first filter 21 is located between the drive air source 1 and the first electronically actuated pressure reducing valve 22. The first filter 21 is used to filter out impurities in the drive air source 1, preventing dirt in the drive air source 1 from entering the drive chamber 31, thereby improving the reliability and service life of the device.

[0029] like Figure 1 As shown, a first solenoid valve 25 is installed on the first pipeline 2; one end of the first solenoid valve 25 is connected to the electronic actuator throttle valve 24, and the other end is connected to the drive chamber 31. The electronic actuator throttle valve 24 is responsible for fine speed regulation, and the first solenoid valve 25 is responsible for rapid on / off and safety isolation. The two are connected in series, which not only maintains the regulation accuracy, but also provides dual protection of electronic control and safety.

[0030] like Figure 1 As shown, a second filter 51 and a shut-off valve 52 are installed on the second pipeline 5. One end of the second filter 51 is connected to the gas supply source 4, and the other end is connected to the shut-off valve 52. The end of the shut-off valve 52 away from the second filter 51 is connected to the pressurization chamber 32. When the shut-off valve 52 is opened, the gas from the gas supply source 4 is delivered to the pressurization chamber 32. The second filter 51 is responsible for cleaning, and the shut-off valve 52 is responsible for isolation. The two are connected in series between the gas supply source 4 and the pressurization chamber 32, which not only protects the high-pressure moving parts (second piston 34), but also provides the prerequisites for safe operation, clean testing, and rapid maintenance.

[0031] like Figure 1 As shown, the main output line 6 is equipped with a third filter 61, a first safety valve 63, a second solenoid valve 64, and a third solenoid valve 65. The third filter 61 is used to filter the gas pumped out by the gas booster pump 3; the first safety valve 63 is used to prevent the pipeline pressure from exceeding the warning value; the second solenoid valve 64 is a pressure switch; and the third solenoid valve 65 is a pressure relief port for the main output line 6. The third filter 61 provides terminal cleaning function, the first safety valve 63 provides mechanical overpressure protection, the second solenoid valve 64 enables remote supply and stop, and the third solenoid valve 65 enables rapid pressure relief within seconds. These four components are integrated sequentially on the main output line 6, solving the problems of cleanliness, safety, controllability, and efficiency with a minimal number of components.

[0032] like Figure 1 As shown, a first pressure sensor 23 is installed on the first pipeline 2, and a second pressure sensor 62 is installed on the output pipeline; the first pressure sensor 23 is used to display the adjusted gas pressure; the second pressure sensor 62 is used to display the pressurized pipeline gas pressure.

[0033] like Figure 1As shown, the multi-channel parallel detection branch 7 includes a first branch, a second branch, a third branch, and a fourth branch; the first, second, third, and fourth branches have the same structure and are arranged in parallel. The first branch is equipped with a second electronically actuated pressure reducing valve 71, a third pressure sensor 72, a fourth solenoid valve 73, a fourth pressure sensor 74, and a fifth solenoid valve 75; the fourth solenoid valve 73 is connected to the second electronically actuated pressure reducing valve 71 via a pipeline, and the third pressure sensor 72 is connected to the pipeline between the fourth solenoid valve 73 and the second electronically actuated pressure reducing valve 71. The output end of the fourth solenoid valve 73 is connected to the first output branch, which is used to deliver gas at the required pressure to the test piece; the fourth pressure sensor 74 is installed on the first output branch to detect the gas pressure on the first output branch. The second electronically actuated pressure reducing valve 71 is used to adjust the gas pressure to the required test pressure; the third pressure sensor 72 is used to display the gas pressure in the pipeline after pressure reduction; the fourth solenoid valve 73 is opened to deliver gas to the test piece for gas pressure testing; and the fifth solenoid valve 75 is used to release pressure.

[0034] In a specific embodiment of the present invention, the gas supply source 4 is connected to nitrogen or compressed air. The type of gas input into the pressurization chamber 32 of the gas supply source 4 is selected according to the experimental requirements.

[0035] like Figure 1 As shown, a second safety valve 8 is installed on the pipeline at the input end of the multi-parallel detection branch 7. The second safety valve 8 is an automatic pressure relief device used to detect whether the pressure at the input end of the multi-parallel detection branch 7 exceeds a set threshold. If it exceeds the set threshold, the gas pressure is automatically released to ensure that the pressure at the input end of the multi-parallel detection branch 7 is within the set threshold range, thereby improving the safety of the device.

[0036] As a specific embodiment of the present invention, the working principle of the present invention is as follows: The system is connected to the driving gas source 1, which first passes through the G1 filter. The J1 electronic actuator pressure reducing valve adjusts the pressure of the driving gas source 1 to 0.8-1.0 MPa. The P1 pressure sensor displays the adjusted pressure. The electronic actuator throttle valve 24 can adjust the gas flow rate, increasing or decreasing the booster efficiency. The gas after speed adjustment reaches the DQ1 solenoid valve. After DQ1 is opened, the gas enters and can start the booster pump. The gas supply source 4 is connected to nitrogen or compressed air, which passes through the G2 filter and is then turned off by opening MJ1. Valve 52 outputs gas to the system pipeline. If the pressure is insufficient after balancing, DQ1 is activated to start the booster pump and boost the pressure to the maximum pressure required for the test (enveloping branches 1 to 4). Filter G3 filters the gas pumped out by the booster pump. Pressure sensor P2 displays the gas pressure in the pipeline after boosting. Safety valve A1 is used to prevent the pipeline pressure from exceeding the warning value (the warning value for this system is 55 MPa). Solenoid valve DQ2 is a pressure supply switch. Solenoid valve DQ3 is the main pipeline pressure relief port. Safety valve A2 is an automatic pressure relief device after solenoid valve DQ2, and has the same function as A1. In branch 1, the J2 electronic pressure reducing valve adjusts to the required test pressure, the P3 pressure sensor displays the reduced gas pressure in the pipeline, the DQ4 solenoid valve opens and transmits the pressure to the test piece for the gas pressure test, and the DQ4 valve closes. The equipment monitors and collects the data from the P4 pressure sensor. After the test, the J2 electronic pressure reducing valve returns to zero, the DQ5 solenoid valve is opened first to release pressure, and then the DQ4 solenoid valve is opened to release all the pressure in the branch. The same applies to branches 2 to 4.

[0037] Testing revealed that the automated device in this application operates smoothly and is easy to use. All testing instruments were calibrated or verified, and the results were all satisfactory. The safety relief device opens promptly when the working pressure is exceeded, the data acquisition system accurately collects pressure curves and automatically generates reports, the electronic pressure regulator is precise, and the timing alarm is reliable and effective. Both efficiency and safety meet the design requirements.

[0038] Experiments have shown that the functions of the automated rocket pipeline air pressure detection device of this application meet the design requirements and can be used in actual testing work.

[0039] Example 2

[0040] This application provides an automated testing method for rocket pipeline air pressure, applied to an automated testing device for rocket pipeline air pressure, the method comprising:

[0041] Step S1: The pressure and flow rate of the gas output from the driving gas source are adjusted to the required range by the pressure and speed regulating module on the first pipeline and then delivered to the gas booster pump.

[0042] Step S2: Open the shut-off valve to deliver the gas from the gas supply source to the gas booster pump.

[0043] Step S3: When the gas pressure is insufficient, start the gas booster pump to increase the gas pressure in the booster chamber to the maximum pressure required for the test.

[0044] Step S4: The gas pressure is adjusted to the required test pressure by the second electronically operated pressure reducing valve on the branch.

[0045] Step S5: Open the fourth solenoid valve to deliver gas to the test piece for a pneumatic test.

[0046] Step S6: After the test is completed, the second electronic actuator pressure reducing valve returns to zero, the fifth solenoid valve is opened first to release pressure, and then the fourth solenoid valve is opened to release all the pressure on the branch.

[0047] The beneficial effects achieved by this application are as follows:

[0048] (1) In pipeline testing, this application can accommodate multiple specifications, multiple connection methods and multiple pressure requirements, thereby improving testing efficiency.

[0049] (2) This application is equipped with a pressure sensor, an electronically actuated pressure reducing valve, and functions such as pressure data curve acquisition and digital pressure control. The device is easy to operate, can be used for batch testing, and improves test efficiency.

[0050] (3) This application is equipped with an automatic safety valve release device and a solenoid valve pressure relief port to improve safety.

[0051] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0052] In the description of this application, the word "for example" is used to mean "used as an example, illustration, or description." Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is provided to enable any person skilled in the art to make and use the invention. Details are set forth in the following description for purposes of explanation. It should be understood that those skilled in the art will recognize that the invention can be made without using these specific details. In other instances, well-known structures and processes will not be described in detail to avoid obscuring the description of the invention with unnecessary detail. Therefore, the invention is not intended to be limited to the embodiments shown, but is consistent with the broadest scope of the principles and features disclosed in this application.

[0053] The above description is merely an embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principle of the present invention should be included within the scope of the claims of the present invention.

Claims

1. An automated testing device for rocket pipeline air pressure, characterized in that, The device includes: a driving gas source, a supply gas source, a gas booster pump, a filter module, a pressure and speed regulation module, and multiple parallel detection branches; The gas booster pump includes a drive chamber and a booster chamber, and a first piston and a second piston are respectively disposed in the drive chamber and the booster chamber, and the first piston and the second piston are connected by a connecting rod; The driving gas source is connected to the driving chamber of the gas booster pump through a first pipeline; The filtration module and the pressure and speed regulating module are installed on the first pipeline; the filtration module is used to filter the driving air source; the pressure and speed regulating module is used to regulate the pressure and flow rate of the driving air source. The gas supply source is connected to the booster chamber of the gas booster pump via a second pipeline; The multi-parallel detection branch is connected to the pressurization chamber through the main output path; The multi-parallel detection branch includes multiple parallel branches; wherein different branches are used to deliver gas at the required test pressure to different test pieces.

2. The automated rocket pipeline air pressure testing device according to claim 1, characterized in that, The pressure regulating and speed regulating module includes: a first electronically actuated pressure reducing valve and an electronically actuated throttle valve; The first electronically actuated pressure reducing valve and the electronically actuated throttle valve are connected within the first pipeline; The first electronically actuated pressure reducing valve is used to regulate the pressure of the gas input from the driving gas source into the first pipeline; The electronic actuator throttle valve is used to regulate the flow rate of the gas input into the first pipeline from the driving gas source.

3. The automated rocket pipeline air pressure testing device according to claim 2, characterized in that, The filtering module is a first filter; The first filter is connected inside the first pipeline; The first filter is located between the driving air source and the first electronically actuated pressure reducing valve.

4. The automated rocket pipeline air pressure testing device according to claim 2, characterized in that, A first solenoid valve is installed on the first pipeline; One end of the first solenoid valve is connected to the throttle valve of the electronic actuator, and the other end is connected to the drive chamber.

5. The automated rocket pipeline air pressure testing device according to claim 1, characterized in that, A second filter and a shut-off valve are installed on the second pipeline; One end of the second filter is connected to the gas supply source, and the other end is connected to the shut-off valve; The end of the shut-off valve furthest from the second filter is connected to the pressurization chamber; When the shut-off valve is opened, the gas from the gas supply source is delivered to the pressurization chamber.

6. The automated rocket pipeline air pressure testing device according to claim 1, characterized in that, The main output line is equipped with a third filter, a first safety valve, a second solenoid valve, and a third solenoid valve; The third filter is used to filter the gas pumped out by the gas booster pump; The first safety valve is used to prevent the pipeline pressure from exceeding the warning value; The second solenoid valve is a pressure switch; The third solenoid valve is the pressure relief port for the main output line.

7. The automated rocket pipeline air pressure testing device according to claim 1, characterized in that, A first pressure sensor is installed on the first pipeline, and a second pressure sensor is installed on the output pipeline; The first pressure sensor is used to display the adjusted gas pressure; The second pressure sensor is used to display the pressure of the gas in the pipeline after pressurization.

8. The automated rocket pipeline air pressure testing device according to claim 1, characterized in that, The multi-path parallel detection branch includes a first branch, a second branch, a third branch, and a fourth branch; The first branch is equipped with a second electronically actuated pressure reducing valve, a third pressure sensor, a fourth solenoid valve, and a fifth solenoid valve; The second electronically operated pressure reducing valve is used to adjust the gas pressure to the pressure required for the test; The third pressure sensor is used to display the gas pressure in the pipeline after depressurization; The fourth solenoid valve is opened to deliver gas to the test piece for a gas pressure test. The fifth solenoid valve is used for pressure relief.

9. The automated rocket pipeline air pressure testing device according to claim 1, characterized in that, The gas supply source is connected to nitrogen or compressed air.

10. An automated testing method for rocket pipeline air pressure, characterized in that, The method, applied to the automated rocket pipeline air pressure testing device according to any one of claims 1-9, comprises: The pressure and flow rate of the gas output from the driving gas source are adjusted to the required range by the pressure and speed regulating module on the first pipeline and then delivered to the gas booster pump. Open the shut-off valve to deliver the gas from the gas supply source to the gas booster pump; When the gas pressure is insufficient, start the gas booster pump to increase the gas pressure in the booster chamber to the maximum pressure required for the test; The gas pressure is adjusted to the required test pressure by the second electronically activated pressure reducing valve on the branch. Open the fourth solenoid valve to deliver gas to the test piece for a pneumatic test; After the test, the second electronic pressure reducing valve was reset to zero, the fifth solenoid valve was opened first to release pressure, and then the fourth solenoid valve was opened to release all the pressure on the branch.

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