Gas generator test system and method for gas pressurized liquid rocket engine

Abstract

The present application relates to a kind of gas generator test system and method for gas self-pressurized liquid rocket engine, solve the technical problem that gas generator can hardly produce matching liquid attitude control rocket engine gas flow under different working conditions.The system includes propellant supply system, propellant weighing and metering system, gas generator, gas cooling system and gas discharge valve group, gas discharge valve group includes multiple sets of gas discharge solenoid valve, and the outlet of at least one set of gas discharge solenoid valve is provided with exhaust orifice plate.The method includes:1, gas generator builds pressure;2, gas generator and gas self-pressurized liquid rocket engine are matched with working condition, obtain the matching relationship of gas generator gas flow and pressurized propellant flow and the matching relationship of gas flow and gas self-pressurized liquid rocket engine;3, test system is depressurized, and test is ended.

Description

Technical Field

[0001] This invention relates to a gas generator testing system, and more specifically to a gas generator testing system and method for a gas self-pressurized liquid rocket engine. Background Technology

[0002] Traditional liquid attitude control rocket engines typically use a "high-pressure nitrogen cylinder + pressure reducer" as their pressurization module. Newer liquid attitude control rocket engines use a "differential tank + gas generator + pressure regulator" as their pressurization module, with the pressurized propellant stored in the pressurized propellant tank. During operation, the pressurized propellant undergoes catalytic decomposition and combustion within the gas generator, producing high-temperature, high-pressure gas. This high-temperature, high-pressure gas is then regulated by the pressure regulator and divided into two paths: one flows to the main propellant tank chamber to pressurize the main propellant tank, ensuring the supply of main propellant to the thrust chamber of the liquid attitude control rocket engine; the other flows to the pressurized propellant tank chamber to pressurize the pressurized propellant tank, ensuring the supply of pressurized propellant for continuous operation of the gas generator.

[0003] Liquid attitude control rocket engines employ thrust chambers with a wide range of thrust levels, from millinewtons to tens of kilonewtons. The propellant flow rate during operation varies from milligrams to tens of kilograms. To meet the main propellant supply requirements of liquid rocket engines, gas generators need to operate normally under different conditions to match the gas flow rate demands of the liquid attitude control rocket engine under varying operating conditions. Therefore, performance testing of the gas generators under different operating conditions is necessary to meet the performance requirements of gas-powered self-pressurized liquid rocket engines.

[0004] In traditional liquid-fueled rocket engine thrust chamber tests, the chamber pressure and mixture ratio are typically adjusted by regulating the propellant tank pressure. Key parameters to monitor include chamber pressure, mixture ratio, specific impulse, and throat temperature. In contrast, gas generator tests, in addition to parameters such as chamber pressure, mixture ratio, specific impulse, and throat temperature, also require monitoring the matching characteristics of gas generator flow rate with pressurized propellant flow rate under various operating conditions, as well as the matching characteristics of gas flow rate with the gas-powered self-pressurized liquid-fueled rocket engine under various operating conditions. Summary of the Invention

[0005] To address the technical problem that gas generators struggle to produce gas flow rates matching those of liquid attitude control rocket engines under different operating conditions, this invention proposes a test system and method for a gas generator used in a gas-self-pressurized liquid rocket engine.

[0006] The technical solution provided by this invention is as follows:

[0007] A test system for a gas generator for a gas-fueled self-pressurized liquid rocket engine is characterized by comprising a propellant supply system, a propellant weighing and metering system, a gas generator, a gas cooling system, and a gas exhaust valve assembly.

[0008] The propellant supply system includes a propellant tank, a propellant tank pressurization and venting valve installed on the propellant tank, a manual main supply valve, a pneumatic main supply valve, a flow meter, and a product valve arranged sequentially along the propellant output direction; the propellant tank is equipped with a tank pressure gauge for measuring the tank pressure P. t ;

[0009] The propellant weighing and metering system includes a weighing and metering device for the propellant storage tank and a data acquisition device, which is used to measure the weight of the propellant storage tank in real time during the gas generator test and then calculate the amount of propellant consumed during the test.

[0010] The gas generator is used to receive pressurized propellant from the propellant supply system and decompose and burn it. A purge valve is connected between the gas generator and the product valve. A generator pressure gauge is installed on the gas generator to measure the chamber pressure P of the gas generator. h ;

[0011] The gas generator outlet is connected to one end of the gas exhaust pipe, and the other end of the gas exhaust pipe is connected to the gas exhaust valve assembly. A gas exhaust pressure gauge is installed between the gas generator outlet and the gas exhaust pipe to measure the gas exhaust pressure P at the gas generator outlet. p ;

[0012] The gas discharge valve assembly includes multiple sets of gas discharge solenoid valves. At least one set of gas discharge solenoid valves has an exhaust orifice plate at its outlet. The orifice diameter of the exhaust orifice plate and the number of gas discharge solenoid valves are set according to the gas flow rate of the gas self-pressurizing liquid rocket engine under various operating conditions corresponding to the gas generator test. This is used to meet the gas flow rate under various operating conditions by adjusting the number of gas discharge solenoid valves and / or the orifice diameter of the exhaust orifice plate.

[0013] The gas cooling system is used to cool the gas exhaust pipe and gas exhaust valve assembly.

[0014] Furthermore, the gas cooling system includes a cooling water cooling assembly and a nitrogen cooling assembly;

[0015] The cooling water cooling assembly includes a cooling water tank located outside the gas exhaust pipe, containing cooling water for cooling the gas exhaust pipe; the gas exhaust pipe is arranged in a tube-and-tube configuration to increase the contact area with the cooling water and improve the cooling effect.

[0016] The nitrogen cooling assembly includes a liquid nitrogen supply assembly and a cooling valve connected to the liquid nitrogen supply assembly for cooling the gas exhaust valve assembly.

[0017] Furthermore, the gas exhaust pipe is arranged in a tubular configuration.

[0018] Furthermore, the nitrogen pressure range at the outlet of the cooling valve of the nitrogen cooling assembly is 1~5MPa.

[0019] Furthermore, it also includes a gas emergency discharge system, which includes a gas emergency discharge pipe and at least one high-temperature pneumatic valve connected in series.

[0020] Furthermore, there are multiple high-temperature pneumatic valves connected in series in the gas emergency exhaust pipe. The opening switches of two adjacent high-temperature pneumatic valves are connected in series, and the closing switches are connected in series. This allows one valve's pneumatic signal to control multiple high-temperature pneumatic valves, simplifying the test system and improving its reliability.

[0021] The gas emergency discharge system is used for emergency discharge in case of gas overpressure, which improves the safety of the test system. Two high-temperature pneumatic valves connected in series effectively prevent abnormal gas discharge caused by internal leakage of the high-temperature discharge valve.

[0022] Furthermore, the propellant supply system also includes a filter, which is disposed between the pneumatic main supply valve and the flow meter.

[0023] This invention also provides a test method for a gas generator for a gas-fueled self-pressurized liquid rocket engine, characterized in that, based on the above-mentioned test system for a gas generator for a gas-fueled self-pressurized liquid rocket engine, it includes the following steps:

[0024] S1, Gas generator pressure build-up

[0025] Adjust the propellant tank pressurization and venting valve to the preset propellant tank pressure P. t0 Open the purge valve and charge nitrogen gas at a pressure of P0 into the combustion chamber of the gas generator until the pressure inside the combustion chamber reaches P0, in order to simulate the actual working conditions of the gas generator.

[0026] Open the manual main supply valve, pneumatic main supply valve, and product valve. The pressurized propellant is charged into the gas generator and undergoes decomposition and combustion. The gas discharge pressure P... p It begins to rise until the gas discharge pressure P p With tank pressure P t When the difference is less than 0.1 MPa, the pressure buildup ends;

[0027] S2. The gas generator, after pressure buildup, is matched with the gas-powered self-pressurized liquid rocket engine under operating conditions.

[0028] S2.1 Switch the orifice diameter of multiple sets of gas emission solenoid valves and exhaust orifice plates to match the current operating conditions;

[0029] S2.2 Obtain the target tank pressure P of the propellant storage tank under the current operating conditions. t ', Calculate the current chamber pressure P of the gas generator. h With the target tank pressure P t The difference between ′;

[0030] If the target tank pressure P t The pressure P of the current gas generator is greater than the pressure of the chamber. h And the current tank pressure P t1 Subtract the current chamber pressure P of the gas generator h If the pressure is not greater than 0.6 MPa, the pressure in the propellant storage tank is adjusted to the target tank pressure P through the pressurization and venting valve. t ′;

[0031] If the target tank pressure P t The pressure P of the current gas generator is less than '. h First, close the product valve, then open the gas discharge valve assembly until the chamber pressure of the gas generator drops to meet the target storage tank pressure P. t The pressure P of the current gas generator is greater than the pressure of the chamber. h And the current tank pressure minus the current gas generator chamber pressure P h When the pressure is not greater than 0.6 MPa, close the gas discharge valve assembly, open the product valve, and then adjust the tank pressure to the target tank pressure P through the propellant tank pressurization and venting valve. t ′;

[0032] Start the test and record the target tank pressure P in real time. t Below, the propellant flow rate, propellant tank weight, and gas discharge pressure P at the gas generator outlet are... p The chamber pressure of the gas generator;

[0033] S2.3, Return to step S2.2 and adjust the target tank pressure P. t ′, until the matching relationship between the gas flow rate of the gas generator and the pressurized propellant flow rate and the matching relationship between the gas flow rate and the gas self-pressurized liquid rocket engine under the current operating conditions are obtained under the pressure of each target storage tank;

[0034] S2.4 Return to step S2.1 and switch the current operating condition by switching the orifice diameter of multiple sets of gas emission solenoid valves and exhaust orifice plates;

[0035] Until the matching relationship between the gas flow rate of the gas generator and the pressurized propellant flow rate, and the matching relationship between the gas flow rate and the gas self-pressurized liquid rocket engine are obtained under various operating conditions;

[0036] S3, Gas generator test system pressure relief

[0037] Close the product valve, open the gas discharge valve assembly and nitrogen cooling system, repeat the gas discharge procedure until the chamber pressure of the gas generator drops below 0.15MPa, then close the gas discharge valve assembly;

[0038] Open the purging valve, introduce nitrogen into the gas generator, and repeat the purging procedure until the chamber pressure of the gas generator drops to atmospheric pressure. Then, close the purging valve, gas discharge valve group, and cooling valve in sequence to end the test.

[0039] Furthermore, in step S3, the gas emission procedure and purging procedure are specifically as follows: the gas emission valve assembly is opened for 3 seconds and closed for 20 seconds.

[0040] The beneficial effects of this invention are:

[0041] 1. This invention provides a test system for a gas generator of a gas self-pressurized liquid rocket engine. By setting up a gas discharge solenoid valve group, different combinations of opening / closing of exhaust orifice plates of different specifications and gas discharge solenoid valves are achieved to simulate the matching characteristics of gas flow rate of gas generator with pressurized propellant flow rate, and the matching characteristics of gas flow rate with gas self-pressurized liquid attitude control rocket engine under various operating conditions, thereby realizing the performance evaluation of the gas generator.

[0042] 2. This invention uses cooling water and nitrogen blowing to cool the high-temperature and high-pressure gas and the gas emission solenoid valve assembly, which effectively improves the working conditions of the gas emission components and gas emission valves in the gas emission solenoid valve assembly and enhances the reliability of the test system.

[0043] 3. The present invention incorporates an emergency gas emission system in the gas emission system, which enables emergency emission of high-temperature gas under overpressure, thereby improving the safety of the test system.

[0044] 4. The present invention adopts a real-time weighing and metering method for pressurized propellant, which can obtain the matching characteristics between the gas flow rate of the gas generator and the flow rate of the pressurized propellant. Attached Figure Description

[0045] Figure 1 This is a schematic diagram of an embodiment of the gas generator test system for a gas-fueled self-pressurized liquid rocket engine according to the present invention;

[0046] Figure 2 This is a schematic diagram of a gas emergency emission system in an embodiment of the present invention.

[0047] The attached figures are labeled as follows:

[0048] 1-Propellant storage tank, 2-Propellant storage tank pressurization and venting valve, 3-Manual main supply valve, 4-Pneumatic main supply valve, 5-Filter, 6-Flow meter, 7-Product valve, 8-Propellant weighing and metering system, 9-Gas generator, 10-Gas emission pressure gauge, 11-Gas emission pipe, 12-Gas emission valve assembly, 13-Gas emission solenoid valve, 14-Exhaust orifice plate, 15-Purge valve, 16-Cooling water tank, 17-Cooling valve, 18-High temperature pneumatic valve. Detailed Implementation

[0049] See Figure 1 This embodiment provides a gas generator test system for a gas-powered self-pressurized liquid rocket engine. The system includes a propellant supply system, a propellant weighing and metering system 8, a gas generator 9, a gas cooling system, a gas emission system, and a gas emergency emission system.

[0050] The propellant supply system includes a propellant tank 1, a propellant tank pressurization and venting valve 2 installed on the propellant tank 1, a manual main supply valve 3, a pneumatic main supply valve 4, a filter 5, a flow meter 6, and a product valve 7 arranged sequentially along the propellant output direction; the product valve 7 can be a solenoid valve, opening or closing this solenoid valve can realize the supply or cut-off of propellant required for the gas generator 9 to operate; the propellant tank 1 is equipped with a tank pressure gauge for measuring the tank pressure P. t The propellant used in propellant storage tank 1 is generally hydrazine 70 or anhydrous hydrazine.

[0051] The propellant weighing and metering system 8 includes a weighing and metering device and a data acquisition device for the propellant storage tank, which is used to measure the weight of the propellant storage tank in real time during the gas generator test and then calculate the amount of propellant consumed during the test.

[0052] Gas generator 9 is used to receive pressurized propellant from the propellant supply system and decompose and burn it. A purge valve 15 is connected between gas generator 9 and product valve 7. A generator pressure gauge is installed on gas generator 9 to measure the chamber pressure P of gas generator 9. h .

[0053] The gas emission system includes a gas emission pipe 11 connected to the outlet of the gas generator 9 and a gas emission valve assembly 12 connected to the gas emission pipe 11; a gas emission pressure gauge 10 is installed between the outlet of the gas generator 9 and the gas emission pipe 11 to measure the gas emission pressure P at the outlet of the gas generator 9. p .

[0054] The gas discharge valve assembly 12 includes six sets of gas discharge solenoid valves 13. Three sets of gas discharge solenoid valves 13 have exhaust orifice plates 14 at their outlets. The orifice diameter of the exhaust orifice plates 14 and the number of gas discharge solenoid valves 13 are set according to the gas flow rate of the gas self-pressurizing liquid rocket engine under various operating conditions corresponding to the gas generator test. This is used to adjust the number of gas discharge solenoid valves 13 and the orifice diameter of the exhaust orifice plates 14 to meet the gas flow rate requirements under various operating conditions. In this embodiment, the three exhaust orifice plates 14 have different orifice diameters and, together with the gas discharge solenoid valves 13, form a first discharge unit, a second discharge unit, and a third discharge unit, respectively, to simulate gas flow rates of 0.08 g / s, 0.5 g / s, and 6 g / s. The other three sets of gas discharge solenoid valves 13 are simultaneously open to simulate a gas flow rate of 120 g / s. Different combinations of the open / closed states of the three discharge units and the three sets of gas discharge solenoid valves 13 can simulate the operating characteristics of the gas generator 9 under 24 different operating conditions of the gas self-pressurizing liquid rocket engine.

[0055] The gas cooling system includes a cooling water cooling assembly and a nitrogen cooling assembly. The cooling water cooling assembly includes a cooling water tank 16 located outside the gas exhaust pipe 11, with cooling water between the cooling water tank 16 and the gas exhaust pipe 11 for cooling the gas exhaust pipe 11. The gas exhaust pipe 11 is arranged in a tubular configuration to increase the contact area with the cooling water and improve the cooling effect. The nitrogen cooling assembly includes a liquid nitrogen supply assembly and a cooling valve 17 connected to the liquid nitrogen supply assembly for cooling the gas exhaust valve assembly 12. The nitrogen pressure range at the outlet of the cooling valve 17 of the nitrogen cooling assembly is 1~5MPa.

[0056] See Figure 2 The gas emergency discharge system includes a gas emergency discharge pipe and two high-temperature pneumatic valves 18 connected in series. The opening and closing switches of the two high-temperature pneumatic valves 18 are connected in series, which is used to realize the control of the two high-temperature pneumatic valves 18 by one valve pneumatic signal, which simplifies the test system and improves the reliability of the test system. The gas emergency discharge system is used for emergency discharge in the event of gas overpressure, which improves the safety of the test system. The two high-temperature pneumatic valves 18 connected in series effectively avoid abnormal gas discharge caused by internal leakage of the high-temperature pneumatic valves 18.

[0057] The test procedure for the gas generator test system for the above-mentioned gas-powered self-pressurized liquid rocket engine includes the following steps:

[0058] S1, Gas generator pressure build-up

[0059] Adjust the propellant tank pressurization and venting valve to the preset propellant tank pressure of 3.0MPa±0.05MPa; open the purge valve 15 to charge the combustion chamber of the gas generator 9 with 2.4MPa±0.05MPa nitrogen until the pressure in the combustion chamber of the gas generator 9 reaches 2.4MPa±0.05MPa, then close the purge valve 15 to simulate the actual working conditions of the gas generator 9 in this embodiment.

[0060] Open the manual main supply valve 3, the pneumatic main supply valve 4, and the product valve 7. The pressurized propellant is filled into the gas generator 9 and undergoes decomposition and combustion. The gas discharge pressure P... p It begins to rise until the gas discharge pressure P p With tank pressure P t When the difference is less than 0.1 MPa, the pressure build-up ends.

[0061] S2. The gas generator 9, after pressure buildup, is matched with the gas-powered self-pressurized liquid rocket engine under operating conditions.

[0062] S2.1 Switch the orifice diameters of multiple sets of gas emission solenoid valves 13 and exhaust orifice plates 14 to match the current operating conditions.

[0063] S2.2 Obtain the target tank pressure P of the propellant storage tank under the current operating conditions. t ', Calculate the current chamber pressure P of gas generator 9. h With the target tank pressure P t The difference between ′;

[0064] If the target tank pressure P t The pressure P of the current gas generator 9 is greater than the chamber pressure P. h And the current tank pressure P t1 Subtract the current chamber pressure P of gas generator 9 h If the pressure is not greater than 0.6 MPa, the pressure in the propellant storage tank is adjusted to the target tank pressure P through the pressurization and venting valve. t ′;

[0065] If the target tank pressure P t The chamber pressure P of the current gas generator 9 is less than '. h First, close product valve 7, then open gas discharge valve assembly 12 until the chamber pressure of gas generator 9 drops to meet the target storage tank pressure P. t The pressure P of the current gas generator 9 is greater than the chamber pressure P. h And the current tank pressure minus the current chamber pressure P of the gas generator 9 h When the pressure is not greater than 0.6 MPa, close the gas discharge valve group 12, and then adjust the tank pressure to the target tank pressure P through the propellant tank pressurization and venting valve. t ′;

[0066] Start the test and record the target tank pressure P in real time.t Below, the propellant flow rate, propellant tank weight, and gas discharge pressure P at the outlet of gas generator 9 are measured. p The chamber pressure of gas generator 9.

[0067] S2.3, Return to step S2.2 and adjust the target tank pressure P. t Until the pressure of each target storage tank is obtained, the matching relationship between the gas flow rate of the current operating condition gas generator 9 and the pressurized propellant flow rate, as well as the matching relationship between the gas flow rate and the gas self-pressurized liquid rocket engine, are obtained.

[0068] S2.4 Return to step S2.1 and switch the current operating condition by switching the orifice diameters of multiple sets of gas emission solenoid valves 13 and exhaust orifice plates 14;

[0069] Until the matching relationship between the gas flow rate of the gas generator 9 and the pressurized propellant flow rate, and the matching relationship between the gas flow rate and the gas self-pressurized liquid rocket engine are obtained under various operating conditions.

[0070] If the gas pressure becomes too high during the test, the emergency gas discharge system can be activated via the control panel to release the gas pressure in an emergency.

[0071] S3, Gas generator test system pressure relief

[0072] Close product valve 7, open gas discharge valve group 12 and nitrogen cooling system, repeat the gas discharge procedure, gas discharge valve group 12 is open for 3 seconds and closed for 20 seconds until the chamber pressure of gas generator 9 drops below 0.15MPa, then close gas discharge valve group 12.

[0073] Open the purge valve 15, introduce nitrogen into the gas generator 9 and repeat the purge procedure. Open the gas discharge valve group 12 for 3 seconds and close it for 20 seconds until the chamber pressure of the gas generator 9 drops to atmospheric pressure. Then close the purge valve 15, the gas discharge valve group 12 and the cooling valve 17 in sequence to end the test.

Claims

1. A gas generator test system for a gas pressurized liquid rocket engine, characterized by: The propellant supply system, the propellant weighing and metering system (8), the gas generator (9), the gas cooling system and the gas exhaust valve group (12); The propellant supply system comprises a propellant tank (1), a propellant tank pressure increasing and discharging valve (2) arranged on the propellant tank (1), a manual total supply valve (3), a pneumatic total supply valve (4), a flow meter (6) and a product valve (7) arranged in sequence along a propellant output direction; the propellant tank (1) is provided with a tank pressure gauge for measuring tank pressure P t ; The propellant weighing and metering system (8) comprises a weighing and metering device and a collecting device of the propellant tank (1), which are used for real-time metering of the weight of the propellant tank (1) in the test process and further calculating the consumption of the propellant in the test process; The gas generator (9) is used for receiving and decomposing the pressurized propellant provided by the propellant supply system, and a blow-off valve (15) is connected between the gas generator (9) and the product valve (7), and a generator pressure gauge is arranged on the gas generator (9) for measuring the chamber pressure P of the gas generator (9) h ; The gas generator (9) is connected with one end of the gas discharge pipe (11), the other end of the gas discharge pipe (11) is connected with the gas discharge valve group (12), and the gas discharge pressure gauge (10) is arranged between the gas generator (9) and the gas discharge pipe (11) to measure the gas discharge pressure P of the gas generator (9) outlet p ; The gas exhaust valve group (12) comprises a plurality of groups of gas exhaust electromagnetic valves (13), and the outlet of at least one group of gas exhaust electromagnetic valves (13) is provided with a gas exhaust orifice plate (14), which is used for meeting the gas flow of each working condition by adjusting the number of groups of gas exhaust electromagnetic valves (13) and / or the orifice diameter of the gas exhaust orifice plate (14). The gas cooling system is used for cooling the gas exhaust pipe (11) and the gas exhaust valve group (12).

2. The gas generator test system for the gas self-pressurized liquid rocket engine according to claim 1, characterized in that: The gas cooling system comprises a cooling water cooling assembly and a nitrogen cooling assembly; The cooling water cooling assembly comprises a cooling water tank (16) arranged outside the gas exhaust pipe (11), and the cooling water tank (16) contains cooling water, which is used for cooling the gas exhaust pipe (11); The nitrogen cooling assembly comprises a liquid nitrogen supply assembly and a cooling valve (17) connected to the liquid nitrogen supply assembly, which are used for cooling the gas exhaust valve group (12).

3. The gas generator test system for the gas self-pressurized liquid rocket engine according to claim 2, characterized in that: The gas exhaust pipe (11) is arranged in a tube bank.

4. The gas generator test system for the gas self-pressurized liquid rocket engine according to claim 3, characterized in that: The nitrogen cooling assembly is arranged in a tube bank.

5. The gas generator test system for the gas self-pressurized liquid rocket engine according to any one of claims 1-4, characterized in that: It further comprises a gas emergency exhaust system, which comprises a gas emergency exhaust pipe and at least one high-temperature pneumatic valve (18).

6. The gas generator test system for the gas self-pressurized liquid rocket engine according to claim 5, characterized in that: The high-temperature pneumatic valve (18) has a plurality of valves, which are arranged in series in the gas emergency exhaust pipe, and the opening switch and the closing switch of adjacent two high-temperature pneumatic valves (18) are connected in series, which are used for realizing that one valve pneumatic signal controls a plurality of high-temperature pneumatic valves (18).

7. The gas generator test system for the gas self-pressurized liquid rocket engine according to claim 6, characterized in that: The propellant supply system further comprises a filter (5), which is arranged between the pneumatic total supply valve (4) and the flowmeter (6).

8. A method for testing a gas generator for a gas pressurized liquid rocket engine, characterized in that, The gas generator test system for the gas self-pressurized liquid rocket engine based on claim 2 comprises the following steps: S1, building pressure of the gas generator Adjusting the boost vent valve (2) of the propellant tank to the preset tank pressure P t0 Opening the blow-off valve (15) to fill the combustion chamber of the gas generator (9) with nitrogen at a pressure P0, until the pressure in the combustion chamber of the gas generator (9) reaches P0, to simulate the actual working condition of the gas generator (9); Opening the manual total supply valve (3), the pneumatic total supply valve (4) and the product valve (7), the pressurized propellant is filled into the gas generator (9) and decomposes and burns, the gas discharge pressure P p Start to rise until the gas discharge pressure P p differs from the tank pressure P t by less than 0.1 MPa, the pressure building is ended; S2, matching the gas generator (9) with the gas self-pressurized liquid rocket engine after building pressure is completed S2.1 Switch the orifice diameters of multiple sets of gas emission solenoid valves (13) and exhaust orifice plates (14) to match the current operating conditions; S2.2, obtaining a target tank pressure P of the propellant tank (1) in the current operating condition t S2.3, calculating a difference between the chamber pressure P of the current gas generator (9) and the target tank pressure P h t ′​ If the target tank pressure P t ′ is greater than the current chamber pressure P h of the gas generator (9), and the current tank pressure P t1 is less than the current chamber pressure P h of the gas generator (9) minus 0.6 MPa, the tank pressure is regulated by the propellant tank pressurization vent valve (2) to the target tank pressure P t ′; If the target tank pressure P t ′ is less than the current chamber pressure P h of the gas generator (9), first close the product valve (7), open the gas discharge valve group (12) until the chamber pressure of the gas generator (9) drops to meet the target tank pressure P t ′ greater than the current chamber pressure P h of the gas generator (9), and the current tank pressure minus the current chamber pressure P h of the gas generator (9) is not greater than 0.6 MPa, close the gas discharge valve group (12), open the product valve (7), and then adjust the tank pressure to the target tank pressure P t ′ through the propellant tank pressurization vent valve (2). Start test, record target tank pressure P in real time t Next, propellant flow, propellant tank (1) weight, gas generator (9) outlet gas discharge pressure P p , gas generator (9) chamber pressure; S2.3, return to step S2.2, adjust the target tank pressure P t until the gas flow rate of the current operating gas generator (9) and the pressurizing propellant flow rate match each other and the gas flow rate and the gas self-pressurization liquid rocket engine match each other under each target tank pressure. S2.4 Return to step S2.1 and switch the current operating condition by switching the orifice diameter of multiple sets of gas emission solenoid valves (13) and exhaust orifice plate (14); Until the matching relationship between the gas flow rate of the gas generator (9) and the pressurized propellant flow rate and the matching relationship between the gas flow rate and the gas self-pressurized liquid rocket engine are obtained under various working conditions; S3, Gas generator test system pressure relief Close the product valve, open the gas discharge valve assembly (12) and the nitrogen cooling assembly, repeat the gas discharge procedure until the chamber pressure of the gas generator (9) drops below 0.15 MPa, and then close the gas discharge valve assembly (12). Open the purge valve (15), introduce nitrogen into the gas generator (9) and repeat the purge procedure until the chamber pressure of the gas generator (9) drops to atmospheric pressure. Then, close the purge valve (15), the gas discharge valve group (12) and the cooling valve (17) in sequence to end the test.

9. The test method for a gas generator for a gas-fueled self-pressurized liquid rocket engine according to claim 8, characterized in that: In step S3, the gas emission procedure and the purging procedure are as follows: the gas emission valve group (12) is opened for 3 seconds and closed for 20 seconds.

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