Pump-fed liquid rocket engine system cold-start test apparatus and method

Abstract

The application discloses a kind of pump pressure liquid rocket engine system cold state starting test device, to solve the problem that prior art cannot accurately obtain the starting parameter of rocket engine, resulting in the risk of engine starting failure. Specifically includes gas supply unit and water medium supply unit;Gas supply unit includes gas supply bottle group, drive path pressure reducer and buffer gas cylinder;The output end of gas supply bottle group is connected to the input end of buffer gas cylinder, and the gas pressure in gas supply bottle group is greater than the starting gas pressure of rocket engine;Drive path pressure reducer is installed on the pipeline between gas supply bottle group and buffer gas cylinder;The output end of buffer gas cylinder is connected to the starter of rocket engine;The pipeline between buffer gas cylinder and starter is provided with on-off valve and control valve in turn along the direction of airflow;Water medium supply unit includes water tank and extrusion gas assembly;Water tank is communicated with oxidant inlet pipe and fuel agent inlet pipe of rocket engine respectively, and isolation valve is arranged on the pipeline thereof;Extrusion gas assembly is communicated with water tank.

Description

TECHNICAL FIELD

[0001] The present application relates to a cold start test device and method, in particular to a pump pressure type liquid rocket engine system cold start test device and method. BACKGROUND

[0002] The start-up characteristics (start-up parameters, start-up timing, etc.) of the pump pressure type liquid rocket engine are the most critical link in the development process of the rocket engine, and excellent start-up characteristics are the basic guarantee for the successful start-up and operation of the engine. Unreasonable start-up parameters may cause poor start-up acceleration, slow start-up, even start-up failure, and may also cause excessive start-up overshoot, leading to engine product structure damage and further leading to engine start-up failure.

[0003] In the traditional engine development process, the start-up characteristics are generally first calculated by simulation, then cold test is carried out under tank pressure (without speed), the simulation model is corrected according to the cold test results, the start-up parameters and start-up timing of the engine are determined, and finally hot test is carried out for verification. This method has the following problems:

[0004] A large number of empirical coefficients are needed to correct the simulation in order to calculate more accurate results. However, for new engine development in the early stage of development, the number of tests is generally small, and the accumulation of empirical coefficients is lacking. Moreover, the cold test under tank pressure (without speed) cannot truly simulate the actual start-up state of the engine, and the results have a large deviation from the actual start-up state of the engine. Therefore, the empirical correction provided by the simulation model is very limited. Therefore, in the early stage of development of new engines, the simulation results and the cold test under tank pressure (without speed) can only determine the approximate trend range of the start-up parameters, and cannot accurately determine the start-up parameters. This not only has the risk of unreasonable start-up parameters leading to start-up failure, but also needs multiple tests to correct, explore and verify the start-up parameters, which undoubtedly increases the development cost of the engine. SUMMARY

[0005] The purpose of the present application is to provide a pump pressure type liquid rocket engine system cold start test device and method to solve the technical problem that the prior art cannot accurately obtain the start-up parameters of the rocket engine, resulting in the risk of engine start-up failure, and multiple tests to correct, explore and verify the start-up parameters will increase the development cost of the engine.

[0006] In order to achieve the above purpose, the present application provides a pump pressure type liquid rocket engine system cold start test device, which is characterized by comprising a gas supply unit and a water medium supply unit;

[0007] The gas supply unit comprises a gas supply bottle group, a drive path pressure reducer and a buffer gas bottle;

[0008] The output end of the gas supply bottle group is connected with the input end of the buffer gas bottle, and is used for providing driving gas for the rocket engine, and the gas pressure in the gas supply bottle group is greater than the starting gas pressure of the rocket engine;

[0009] The driving path pressure reducer is installed on the pipeline between the gas supply bottle group and the buffer gas bottle, and is used for reducing the driving gas pressure to the starting gas pressure;

[0010] The output end of the buffer gas bottle is used for connecting the starter of the rocket engine;

[0011] The pipeline between the buffer gas bottle and the starter is sequentially provided with a on-off valve and a control valve in the gas flow direction;

[0012] The water medium supply unit comprises a water tank and a squeeze gas assembly connected with the water tank;

[0013] The water tank is communicated with the oxidant inlet pipe and the fuel agent inlet pipe of the rocket engine respectively, and is provided with an isolation valve on the pipeline;

[0014] The squeeze gas assembly is communicated with the water tank, and is used for providing squeeze gas to the water tank, so that the water in the water tank flows to the rocket engine to simulate the real load of the rocket engine.

[0015] Further, the gas supply unit further comprises a driving path air release valve;

[0016] The driving path air release valve is installed on the pipeline between the buffer gas bottle and the on-off valve, and is used for reducing the pressure of the driving gas.

[0017] Further, the gas supply unit further comprises a first pressure sensor;

[0018] The first pressure sensor is installed on the pipeline between the buffer gas bottle and the on-off valve, and is used for measuring the pressure of the driving gas.

[0019] Further, the gas supply unit further comprises a driving path flow meter;

[0020] The driving path flow meter is installed on the pipeline between the driving path pressure reducer and the buffer gas bottle.

[0021] Further, a control unit is further included;

[0022] The driving path pressure reducer is provided with an electronic controller, and the electronic controller is used for controlling the driving path pressure reducer;

[0023] The gas supply bottle group, the on-off valve, the driving path air release valve, the electronic controller, the first pressure sensor and the driving path flow meter are connected with the control unit.

[0024] Further, the gas supply bottle group is a helium or nitrogen bottle group;

[0025] The starter is a starting turbine or a starting powder.

[0026] Further, the extrusion gas assembly comprises an extrusion gas tank, an extrusion path pressure reducer and an extrusion path pressure booster;

[0027] The extrusion gas tank is communicated with the water tank.

[0028] The extrusion path pressure reducer and the extrusion path pressure booster are sequentially arranged on the pipeline between the extrusion gas tank and the water tank in the airflow direction, and are used for adjusting the pressure of the extrusion gas.

[0029] Further, the extrusion gas assembly further comprises a gas release valve, a second pressure sensor and an extrusion path flow meter.

[0030] The gas release valve and the second pressure sensor are both mounted on the pipeline between the extrusion path pressure booster and the water tank.

[0031] The extrusion path flow meter is mounted on the pipeline between the extrusion gas tank and the extrusion path pressure reducer.

[0032] Further, the extrusion gas tank, the extrusion path pressure reducer, the extrusion path pressure booster, the gas release valve, the second pressure sensor and the extrusion path flow meter are all connected with a control unit.

[0033] The application also provides a pump pressure type liquid rocket engine system cold state starting test method.

[0034] Step 1, building the pump pressure type liquid rocket engine system cold state starting test device mentioned above;

[0035] Step 2, closing the gas supply unit, adjusting the extrusion gas assembly, so that the extrusion gas pressure of the extrusion gas assembly leading to the water tank reaches a first preset value; the first preset value is the liquid path inlet pressure of the rocket engine; step 3, opening the isolation valve between the water tank and the rocket engine, and the water tank simulates to provide a real load to the rocket engine;

[0036] Step 4, opening the gas supply bottle group, the driving path pressure reducer and the buffer gas bottle, adjusting the driving path pressure reducer until the driving gas pressure in the pipeline between the gas supply bottle group and the on-off valve reaches a second preset value; the second preset value is the gas path inlet pressure of the rocket engine;

[0037] Step 5, sequentially opening the on-off valve and the control valve, and starting the rocket engine;

[0038] Step 6, obtaining the starting parameters in the starting process of the rocket engine.

[0039] The application has the following beneficial effects:

[0040] 1. The pump pressure liquid rocket engine system cold state starting test device provided by the application can simulate the actual starting state of a rocket engine, determine more accurate starting parameters for the rocket engine starting, ensure the stable starting of the rocket engine, effectively reduce the number of hot test runs, and greatly reduce the development cost and risk of the rocket engine.

[0041] 2. The buffer gas cylinder and the on-off valve are arranged between the drive line pressure reducer and the control valve, the on-off valve can be temporarily closed before the control valve is opened, and the drive gas with appropriate pressure is filled into the buffer gas cylinder, and then when the on-off valve and the control valve are opened, the problem that the drive gas cannot quickly reach the rocket engine due to long or winding pipelines is avoided.

[0042] 3. The drive line pressure relief valve is arranged on the pipeline between the buffer gas cylinder and the control valve, so that the pressure of the drive gas can be timely reduced, and the pressure of the drive gas is more accurate.

[0043] 4. The first pressure sensor is arranged on the pipeline between the output end of the buffer gas cylinder and the control valve, so that the pressure of the drive gas can be obtained in real time, the opening degree of the drive line pressure reducer is adjusted, and the input power of the starting turbine or the starting powder actuator is calculated.

[0044] 5. The helium / nitrogen cylinder group is used as the energy source to drive the turbine to work, the starting performance of the rocket engine under the real starting state is simulated, the obtained starting parameters of the rocket engine are more accurate, and strong support is provided for the first half-system hot test run of the rocket engine development to be successful.

[0045] 6. The gas supply cylinder group is arranged for the water tank, the gas supply cylinder group can provide extrusion gas for the water tank, the water tank provides a more real load for the rocket engine, and the accuracy of the finally obtained starting parameters is improved. DETAILED DESCRIPTION

[0046] Figure 1 is a structural schematic view of an embodiment of the pump pressure liquid rocket engine system cold state starting test device.

[0047] Reference numerals:

[0048] 1-gas supply unit, 11-gas supply cylinder group, 12-drive line pressure reducer, 13-buffer gas cylinder, 14-on-off valve, 15-control valve, 16-first pressure sensor, 17-drive line flowmeter, 18-electronic controller, 19-drive line pressure relief valve;

[0049] 2 - water medium supply unit, 21 - water tank, 22 - pressurized gas assembly, 221 - pressurized gas tank, 222 - pressurized line pressure reducer, 223 - pressurized line pressure booster, 224 - gas release valve, 225 - second pressure sensor, 226 - pressurized line flow meter, 23 - isolation valve;

[0050] 3 - rocket engine, 31 - starter, 32 - oxidizer inlet pipe, 33 - fuel agent inlet pipe. DETAILED DESCRIPTION

[0051] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0052] A pump pressure type liquid rocket engine system cold state starting test device is used to obtain starting parameters of a rocket engine 3, such as Figure 1 As shown in the figure, the device comprises a gas supply unit 1 and a water medium supply unit 2 connected with the rocket engine 3 respectively, and further comprises a control unit connected with the gas supply unit 1 and the water medium supply unit 2 respectively.

[0053] The gas supply unit 1 is used for providing cold gas with a certain power to the starting turbine of the rocket engine, and the driving pressure and timing can be adjusted according to the test content, so as to achieve the purpose of truly simulating the test of the rocket engine. Specifically, the gas supply bottle group 11, the driving path pressure reducer 12, the buffer gas bottle 13, the driving path air release valve 19, the first pressure sensor 16, the on-off valve 14, the driving path flow meter 17 and the control valve 15 are included. The output end of the gas supply bottle group 11 is in communication with the starter 31 of the rocket engine 3, and is used for providing the driving gas for starting to the rocket engine 3, and is the driving source for starting the rocket engine 3. The gas pressure in the gas supply bottle group 11 is greater than the starting pressure of the rocket engine 3, so that the driving force can be avoided when the driving gas in the gas supply bottle group 11 is discharged to the rocket engine 3 in a long pipeline. The gas supply bottle group 11 is a helium or nitrogen bottle group. The starter 31 is a starting turbine or a forced starting gunpowder starter. The driving path pressure reducer 12, the driving path flow meter 17, the buffer gas bottle 13, the driving path air release valve 19, the first pressure sensor 16, the on-off valve 14 and the control valve 15 are sequentially arranged on the pipeline between the gas supply bottle group 11 and the starter 31 in the gas flow direction. When the gas supply bottle group 11 discharges gas, the driving power will decrease to form a "pit", and the buffer gas bottle 13 can compensate the instantaneous supply amount of the gas path to fill the "pit". The buffer gas bottle 13 can be connected with a safety valve for safety protection to prevent overpressure. The driving path pressure reducer 12 is used for reducing the pressure of the driving gas to the starting pressure. The driving path air release valve 19 is used for reducing the pressure of the driving gas. The first pressure sensor 16 is used for measuring the pressure of the driving gas, and is used for the calculation of the power input of the starting turbine efficiency. The driving path flow meter 17 is used for measuring the flow of the driving gas, and is used for the calculation of the power input of the starting turbine efficiency. The electronic controller 18 is arranged on the driving path pressure reducer 12, and is used for controlling the driving path pressure reducer 12. The gas supply bottle group 11, the on-off valve 14, the driving path air release valve 19, the electronic controller 18, the first pressure sensor 16 and the driving path flow meter 17 are connected with the control unit. Remote control is facilitated, and the personal safety of the operator is improved.

[0054] The water medium supply unit 2 is used for filling the flow path in the rocket engine, and specifically comprises a water tank 21 and a pressurized gas assembly 22 connected with the water tank 21; the pressurized gas assembly 22 comprises a pressurized gas storage tank 221, a pressurized path flow meter 226, a pressurized path pressure reducer 222, a pressurized path pressure booster 223, a gas release valve 224 and a second pressure sensor 225. The water tank 21 is in communication with an oxidant inlet pipe 32 and a fuel agent inlet pipe 33 of the rocket engine 3 through a two-way pipe, the two-way pipe comprises a main pipe in communication with the water tank 21 and two sub-pipes in communication with the oxidant inlet pipe 32 and the fuel agent inlet pipe 33 respectively; meanwhile, the two sub-pipes are both in communication with the main pipe, and an isolation valve 23 is arranged on the main pipe; one pressure sensor is arranged on each of the two sub-pipes, and the data measured by the pressure sensor on the sub-pipe in communication with the oxidant inlet pipe 32 can be used for calculating the lift of the oxidant pump, and the data measured by the pressure sensor on the sub-pipe in communication with the fuel agent inlet pipe 33 can be used for calculating the lift of the fuel pump.

[0055] The pressurized gas storage tank 221 is in communication with the water tank 21, and is used for providing pressurized gas to the water tank 21, so that the water in the water tank 21 flows to the rocket engine 3 to simulate the actual load of the rocket engine 3. The pressurized path flow meter 226, the pressurized path pressure reducer 222, the pressurized path pressure booster 223, the gas release valve 224 and the second pressure sensor 225 are sequentially arranged on the pipeline between the pressurized gas storage tank 221 and the water tank 21 along the gas path. The pressurized path pressure reducer 222 and the pressurized path pressure booster 223 are used for adjusting the pressure of the pressurized gas, so that the gas pressure reaches the experimental requirement, i.e. the second preset value. The pressurized gas storage tank 221, the pressurized path pressure reducer 222, the pressurized path pressure booster 223, the gas release valve 224, the second pressure sensor 225 and the pressurized path flow meter 226 are connected with the control unit.

[0056] Generally, the closed cycle engine adopts a starting turbine as a cold state starting driving assembly, the starting turbine is coaxially connected with the main turbine of the engine, and can be a starting turbine provided by the rocket engine, or a process starting turbine designed for the test; the open cycle engine can adopt a powder starter connected with the turbine of the engine as a cold state starting driving assembly, or a powder starter or a nozzle connected with the turbine of the engine and designed for the test as a cold state starting driving assembly.

[0057] The pump pressure type liquid rocket engine system cold state starting test device provided by the application is verified by engine test, and the engine is started stably, the starting parameters are reasonably set, and the development cost and risk of the newly developed engine are greatly reduced.

[0058] The experimental principle of the application is as follows:

[0059] The gas supply unit is reasonably arranged to ensure that a stable forced driving gas source is supplied to the rocket engine, the water medium supply unit fills the liquid path pipeline and pump cavity of the rocket engine, the gas supply unit, the water medium supply unit and the corresponding function valves of the rocket engine product itself are opened and closed in turn according to the set predetermined program, the turbine pump is driven to rotate to a certain rotating speed, the starting characteristic related parameters of the rocket engine are monitored through the flow, pressure and rotating speed sensors, and the characteristics, performance, coordination and reliability of the engine turbine pump, generator, valve and pipeline of the rocket engine in the starting stage are analyzed and judged. The subsequent development work of the rocket engine is adjusted, corrected or improved according to the cold starting test results, and the first half-system hot test of the rocket engine is provided with reference.

[0060] The specific experimental steps are as follows:

[0061] Step 1, build the above pump pressure type liquid rocket engine system cold starting test device;

[0062] Step 2, close the gas supply unit 1, adjust the extrusion road pressure reducer 222, the extrusion road pressure increasing valve 223 and the air release valve 224 in the extrusion gas assembly 22, so that the extrusion gas pressure of the extrusion gas assembly 22 to the water tank 21 reaches the first preset value; the first preset value is the liquid path inlet pressure of the rocket engine 3;

[0063] Step 3, open the isolation valve 23 between the water tank 21 and the rocket engine 3, and the water tank 21 simulates to provide a real load to the rocket engine 3;

[0064] Step 4, open the gas supply bottle group 11, the driving road pressure reducer 12 and the buffer gas bottle 13, adjust the driving road pressure reducer 12 and the driving road air release valve 19 until the driving gas pressure in the pipeline between the gas supply bottle group 11 and the on-off valve 14 reaches the second preset value; the second preset value is the gas path inlet pressure of the rocket engine 3;

[0065] Step 5, open the on-off valve 14 and the control valve 15 in turn, and start the rocket engine 3;

[0066] Step 6, obtain the starting parameters in the starting process of the rocket engine 3 for analysis and research and development.

[0067] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto, any change or replacement within the technical range disclosed by the present application should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A cold start test device for a pump-type liquid rocket engine system, characterized by: It comprises a gas supply unit (1), a water medium supply unit (2) and a control unit; The gas supply unit (1) comprises a gas supply cylinder group (11), a driving path pressure reducer (12), a buffer gas cylinder (13), a first pressure sensor (16), a driving path flow meter (17), and a driving path air release valve (19); The output end of the gas supply bottle group (11) is connected to the input end of the buffer gas bottle (13) for providing driving gas to the rocket engine (3), and the gas pressure in the gas supply bottle group (11) is greater than the starting gas pressure of the rocket engine (3); The driving circuit pressure reducer (12) is installed on the pipeline between the gas supply cylinder group (11) and the buffer gas cylinder (13) and is used to reduce the driving gas pressure to the starting gas pressure; The output end of the buffer gas bottle (13) is used to connect to the starter (31) of the rocket engine (3); An on-off valve (14) and a control valve (15) are sequentially provided on the pipeline between the buffer gas cylinder (13) and the starter (31) along the air flow direction; The first pressure sensor (16) is installed on the pipeline between the buffer gas bottle (13) and the on-off valve (14) and is used to measure the pressure of the driving gas; The driving path flow meter (17) is installed on the pipeline between the driving path pressure reducer (12) and the buffer gas cylinder (13); The driving circuit air release valve (19) is installed on the pipeline between the buffer gas bottle (13) and the on-off valve (14) to reduce the pressure of the driving gas; The water medium supply unit (2) comprises a water tank (21) and an extrusion gas assembly (22) connected to the water tank (21); The water tank (21) is respectively connected to the oxidizer inlet pipe (32) and the fuel inlet pipe (33) of the rocket engine (3), and an isolation valve (23) is provided on the pipeline; The extrusion gas assembly (22) is in communication with the water tank (21) and is used to provide extrusion gas into the water tank (21), so that the water in the water tank (21) flows toward the rocket engine (3) to simulate the real load of the rocket engine (3); The driving path pressure reducer (12) is provided with an electronic controller (18), and the electronic controller (18) is used to control the driving path pressure reducer (12); The gas supply cylinder assembly (11), the on-off valve (14), the driving path air release valve (19), the electronic controller (18), the first pressure sensor (16), and the driving path flow meter (17) are all connected to the control unit.

2. The cold start test device for a pump-type liquid rocket engine system according to claim 1, characterized in that: The gas supply cylinder group (11) is a helium or nitrogen cylinder group; The starter (31) is a starting turbine or a gunpowder starter.

3. The cold start test device for a pump-type liquid rocket engine system according to claim 2, characterized in that: The extrusion gas assembly (22) includes an extrusion gas storage tank (221), an extrusion path pressure reducer (222), and an extrusion path pressure boosting valve (223); The extruded gas storage tank (221) is in communication with the water tank (21); The extrusion path pressure reducer (222) and the extrusion path pressure boosting valve (223) are sequentially arranged on the pipeline between the extrusion gas storage tank (221) and the water tank (21) along the air flow direction, and are used to adjust the pressure of the extrusion gas.

4. The cold start test device for a pump-type liquid rocket engine system according to claim 3, characterized in that: The extrusion gas assembly (22) further includes an air release valve (224), a second pressure sensor (225), and an extrusion path flow meter (226); The air release valve (224) and the second pressure sensor (225) are both installed on the pipeline between the extrusion line pressure boosting valve (223) and the water tank (21); The extrusion path flow meter (226) is installed on the pipeline between the extrusion gas storage tank (221) and the extrusion path pressure reducer (222).

5. The cold start test device for a pump-type liquid rocket engine system according to claim 4, characterized in that: The extrusion gas storage tank (221), the extrusion path pressure reducer (222), the extrusion path pressure boosting valve (223), the air release valve (224), the second pressure sensor (225), and the extrusion path flow meter (226) are all connected to the control unit.

6. A cold start test method for a pump-type liquid rocket engine system, characterized in that: The following steps are involved: Step 1: construct a cold start test device for a pump-type liquid rocket engine system according to any one of claims 1 to 5; Step 2: closing the gas supply unit (1) and adjusting the extruded gas assembly (22) so that the pressure of the extruded gas from the extruded gas assembly (22) to the water tank (21) reaches a first preset value; the first preset value is the pressure of the liquid path inlet of the rocket engine (3); Step 3: Open the isolation valve (23) between the water tank (21) and the rocket engine (3), so that the water tank (21) simulates providing a real load to the rocket engine (3); Step 4: Open the gas supply cylinder group (11), the drive circuit pressure reducer (12), and the buffer gas cylinder (13), and adjust the drive circuit pressure reducer (12) until the drive gas pressure in the pipeline between the gas supply cylinder group (11) and the on-off valve (14) reaches a second preset value; the second preset value is the gas circuit inlet pressure of the rocket engine (3); Step 5: Open the on-off valve (14) and the control valve (15) in sequence to start the rocket engine (3); Step 6: Obtain the starting parameters of the rocket engine (3) during the starting process.

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