CN114458478A - Double-station test bed and test method for extrusion pump pressure type rocket engine - Google Patents
Double-station test bed and test method for extrusion pump pressure type rocket engine Download PDFInfo
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- CN114458478A CN114458478A CN202011562933.1A CN202011562933A CN114458478A CN 114458478 A CN114458478 A CN 114458478A CN 202011562933 A CN202011562933 A CN 202011562933A CN 114458478 A CN114458478 A CN 114458478A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
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Abstract
The invention relates to a double-station test bed and a test method for an extrusion pump pressure type rocket engine. The parallel running of the extrusion type test subsystem and the pumping pressure type test subsystem is realized in the same space, the utilization rate of test resources is improved, the efficiency of test organization is improved, the preparation process of the test is performed in parallel, and the risk of the test process is reduced. The high-pressure nitrogen for the test is directly prepared in a liquid nitrogen volatilization mode, the test gas is uniformly prepared and stored, the reduction of gas purity and the introduction of excess materials caused by secondary pollution and repeated pressure relief of a pipeline are reduced, the purity of the nitrogen for the test is improved, and the reliability of the test is ensured. The high-pressure high-purity nitrogen preparation and storage subsystem, the centralized gas supply and distribution subsystem and the fire fighting subsystem are reused, so that resources are saved.
Description
Technical Field
The invention relates to the field of ground thermal ignition tests of liquid rocket engines, in particular to a double-station test bed of an extrusion pump pressure type rocket engine and a test method.
Background
In order to meet the development requirement of the liquid rocket engine, the ground test of the liquid rocket engine is divided into an assembly extrusion test and a complete machine test, and the two tests are generally independently built according to the test content and the requirement.
From the composition of the test bed, the two sets of test systems are all composed of subsystems such as a high-pressure pure gas source supply subsystem, a pipeline pressurization subsystem, a thrust bearing and restraining device subsystem, a nitrogen fire-fighting subsystem, a monitoring facility subsystem, a measurement subsystem and a control subsystem. The system is divided from a test organization, and after two sets of test systems are independently constructed, resources cannot be uniformly allocated, the dominant equipment cannot be used mutually, and the flows cannot be parallel, so that the complex test mechanism, the low personnel efficiency and the reduction of the safety coefficient are caused.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a double-station test bed of an extrusion pump pressure type rocket engine and a test method.
In order to achieve the aim, the invention provides an extrusion pump pressure type rocket engine double-station test bed which comprises a high-purity nitrogen acquisition and storage subsystem, a centralized gas supply and distribution subsystem, an extrusion test subsystem, a pump pressure test subsystem and a fire fighting subsystem;
the high-pressure high-purity nitrogen preparation and storage subsystem stores and supplies high-pressure nitrogen;
the centralized gas supply and distribution subsystem reduces the high-pressure nitrogen to a set pressure and then provides the nitrogen to the extrusion test subsystem, the pumping pressure test subsystem and the fire fighting subsystem;
the extrusion test subsystem utilizes nitrogen to pressurize the fuel storage tank and the oxidant storage tank, so that the fuel and the oxidant are discharged to a combustion chamber for combustion;
the pumping pressure test subsystem utilizes nitrogen to pressurize the liquid oxygen storage tank and the kerosene storage tank to perform an engine ignition test;
the fire protection subsystem extinguishes fire by injecting nitrogen.
The engine test piece is fixed to the thrust frame through the adapter frame and is fixed to the force bearing base through the thrust frame to restrain the thrust generated by the engine during working; different adapter racks are adopted for carrying out the extrusion test and the pump pressure test.
Further, a propellant supply subsystem is used to meter oxidizer and fuel to the engine assembly.
And the real-time monitoring subsystem is used for acquiring video images of the extrusion test and the pump pressure test and monitoring.
Further, the high-pressure high-purity nitrogen preparation and storage subsystem comprises a low-temperature liquid nitrogen storage tank, a nitrogen evaporation device and a high-pressure nitrogen storage tank; the low-temperature liquid nitrogen storage tank is used for storing liquid nitrogen; the liquid nitrogen can be gasified by a nitrogen evaporation device and then conveyed to the high-pressure nitrogen, and the high-pressure nitrogen storage tank is used for storing and supplying the high-pressure nitrogen. Further, the nitrogen evaporation device comprises a liquid nitrogen pump and a vaporizer; the liquid nitrogen pump drives liquid nitrogen to be boosted to a set pressure in the closed cavity and sent to the vaporizer for high-pressure vaporization, and vaporized nitrogen is conveyed forwards to the high-pressure nitrogen storage tank.
Furthermore, the centralized gas supply and distribution subsystem directly supplies the pressure of high-pressure nitrogen to a gas distribution plate main gas collecting pipe from 30MPa, realizes extrusion test bed nitrogen pressurization supply and pumping pressure test bed nitrogen pressurization supply through PLC remote control, and regulates the pressure to be reduced to 4.5MPa through a high-pressure reducer to be supplied to a fire-fighting subsystem.
Furthermore, the extrusion test subsystem comprises an extrusion test oxidant pressurized nitrogen conveying pipeline, an extrusion test oxidant high-pressure container, an extrusion test oxidant supply branch, an extrusion test fuel pressurized conveying pipeline, an extrusion test fuel high-pressure container, an extrusion test fuel supply branch, an ignition system and an extrusion test acquisition module;
the oxidant is supplied to the front of the engine through the extrusion test oxidant supply branch; the fuel is supplied to the front of the engine through the extrusion test fuel supply branch; the nitrogen is injected into an extrusion test oxidant high-pressure container through an extrusion test oxidant pressurizing nitrogen conveying pipeline for pressurizing, the nitrogen is injected into an extrusion test fuel high-pressure container through an extrusion test fuel pressurizing conveying pipeline for pressurizing, an ignition system is started, an ignition source for ignition is formed in an engine combustion chamber, the oxidant is opened through a front valve of an extrusion test oxidant supply branch and an extrusion test fuel supply branch, so that the oxidant and the fuel enter the combustion chamber for continuous combustion, the engine starts to work, and an extrusion test acquisition module acquires engine data.
Further, the pumping pressure test subsystem comprises a pumping pressure test oxidant pressurizing and conveying pipeline, a pumping pressure test oxidant low-pressure container, a pumping pressure test oxidant supply branch, a pumping pressure test fuel pressurizing and conveying pipeline, a pumping pressure test fuel low-pressure container, a pumping pressure test fuel supply pipeline, a pumping pressure test auxiliary gas path supply system, a pumping pressure test kerosene vacuumizing system and a pumping pressure test acquisition module;
the oxidant is supplied to the front of the engine through the pump pressure test oxidant supply branch; fuel is supplied to the front of the engine through a pump pressure test fuel supply branch;
the pump pressure test auxiliary gas path supply system supplies the pressure of a high-pressure gas cylinder for engine test to an engine system, the pump pressure test kerosene vacuumizing system is started, a kerosene cavity of the engine is vacuumized, a pump front valve of a fuel supply pipeline is opened, and kerosene is filled into the engine under the vacuum condition;
nitrogen is injected into the pump pressure test oxidant low-pressure container for pressurization through the pump pressure test oxidant pressurization conveying pipeline, and nitrogen is injected into the pump pressure test fuel low-pressure container for pressurization through the pump pressure test fuel pressurization conveying pipeline; the engine starts to work, and the squeezing test acquisition module acquires engine data.
The invention also provides a method for testing by using the double-station test bed of the extrusion pump pressure type rocket engine, which comprises the following steps: the compression test and the pump pressure test were performed.
Further, the squeeze test includes: the oxidant is supplied to the front of the engine through the extrusion test oxidant supply branch; the fuel is supplied to the front of the engine through the extrusion test fuel supply branch; nitrogen is injected into an extrusion test oxidant high-pressure container through an extrusion test oxidant pressurizing nitrogen conveying pipeline for pressurizing, nitrogen is injected into an extrusion test fuel high-pressure container through an extrusion test fuel pressurizing conveying pipeline for pressurizing, an ignition system is started, an ignition source for ignition is formed in an engine combustion chamber, a pump front valve of an oxidant is opened through an extrusion test oxidant supply branch and an extrusion test fuel supply branch, so that the oxidant and fuel enter the combustion chamber for continuous combustion, the engine starts to work, and an extrusion test acquisition module acquires engine data; when the engine works to a designated time, closing the oxidant supply branch and the fuel supply branch of the extrusion test, discharging residual propellant in a cavity channel of the engine, releasing pressure of an oxidant high-pressure container and a fuel high-pressure container of the extrusion test, recovering the oxidant and the fuel, sealing and storing a subsystem of the extrusion test at positive pressure, dismantling the engine, and ending the test;
the pump pressure test comprises: the oxidant is supplied to the front of the engine through a pump pressure test oxidant supply branch; fuel is supplied to the front of the engine through a pump pressure test fuel supply branch; the pump pressure test auxiliary gas path supply system supplies the pressure of a high-pressure gas cylinder for engine test to an engine system, the pump pressure test kerosene vacuumizing system is started, a kerosene cavity of the engine is vacuumized, a pump front valve of a fuel supply pipeline is opened, and kerosene is filled into the engine under the vacuum condition; nitrogen is injected into the pump pressure test oxidant low-pressure container for pressurization through the pump pressure test oxidant pressurization conveying pipeline, and nitrogen is injected into the pump pressure test fuel low-pressure container for pressurization through the pump pressure test fuel pressurization conveying pipeline; the engine starts to work, and the extrusion test acquisition module acquires engine data; and when the engine works to a designated time, closing the oxidant supply branch and the pump pressure test fuel supply pipeline of the propellant supply system, discharging residual propellant in the cavity channel of the engine, recovering the oxidant and the fuel, sealing and storing the pump pressure test subsystem at positive pressure, dismantling the engine, and ending the test.
The technical scheme of the invention has the following beneficial technical effects:
(1) the parallel running of the extrusion type test subsystem and the pumping pressure type test subsystem is realized in the same space, the utilization rate of test resources is improved, the efficiency of test organization is improved, the preparation process of the test is performed in parallel, and the risk of the test process is reduced.
(2) The extrusion type and pumping pressure type test subsystems of the invention reuse the high-pressure high-purity nitrogen preparation and storage subsystem, the centralized gas supply and distribution subsystem and the fire-fighting subsystem, thereby saving resources.
(3) The method adopts a liquid nitrogen volatilization mode to directly prepare the high-pressure nitrogen for the test, and the test gas is uniformly prepared and stored, so that the reduction of gas purity and the introduction of redundant substances caused by secondary pollution and repeated pressure relief of a pipeline are reduced, the purity of the nitrogen for the test is improved, and the reliability of the test is ensured.
Drawings
FIG. 1 is a schematic diagram of a double-station test bed;
FIG. 2 is a schematic diagram of a monitoring and measurement control subsystem;
FIG. 3 is a schematic diagram of the high purity nitrogen gas acquisition and storage device;
FIG. 4 is a schematic diagram of the components of the centralized gas supply and distribution subsystem;
FIG. 5 is a schematic diagram of the compression and pump test subsystem composition.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings in conjunction with the following detailed description. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The extrusion type rocket engine test is used for engine high-pressure component verification tests, the working pressure is 10MPa, the pumping pressure type test bed is suitable for rocket engine complete machine tests, and the working pressure is 0.6 MPa. Through the composition characteristic planning to test system, the pressure boost supply system who all uses in the test system adopts online adjustable closed loop flow control mode to carry out the selectivity supply, the harmless fire extinguishing system to the test demand places the formula of arranging, synthesize the test run thrust magnitude, set up different thrust magnitude engines of switching frame conversion, realize the multiple working form engine of a thrust frame, optimize the inertia coefficient, it is three-dimensional to realize propellant supply system through space azimuth overall arrangement, the integration of two kinds of stations of extrusion and pumping pressure has been realized in a physical space, the common resource of multiplexing test, utilize the basis to establish otherwise, the space utilization of test system has been improved.
The double-station integrated test bed comprises a high-pressure high-purity nitrogen preparation and storage subsystem 1, a centralized gas supply and distribution subsystem 2, an extrusion test subsystem 3, a pump pressure test subsystem 4, a fire-fighting subsystem 5, a measurement and control subsystem 6, a real-time monitoring subsystem, a selective pressurization conveying system (supplying pressurization gas to an extrusion test bed or a pump pressure test through valve control), a propellant supply system (a propellant supply system of the extrusion test bed and a propellant supply system of the pump pressure test bed) and a thrust constraint installation system.
The high-pressure high-purity nitrogen preparation and storage subsystem 1, as shown in fig. 3, includes a low-temperature liquid nitrogen storage tank, a nitrogen evaporation device and a high-pressure nitrogen storage tank. The low-temperature liquid nitrogen storage tank is used for storing liquid nitrogen for preparing high-purity nitrogen, and the liquid nitrogen is filled into the low-temperature liquid nitrogen storage tank for storage through the precision filter 1 and the liquid nitrogen inlet valve 2. After filling, the liquid nitrogen inlet valve is closed to be isolated from the outside, so that secondary pollution possibly caused in the storage process is avoided. The low-temperature liquid nitrogen storage tank is provided with a safety valve for protecting the safety of the storage tank, the pressure gauge detects the pressure in the storage tank, the liquid nitrogen discharge valve 3 is arranged for discharging liquid nitrogen conveniently, and the liquid nitrogen outlet valve 4 is arranged for controlling the liquid nitrogen to enter the nitrogen evaporation device through a liquid nitrogen delivery pipeline.
The nitrogen evaporation device comprises a liquid nitrogen pump 5 and a vaporizer 6; the liquid nitrogen is conveyed to a liquid nitrogen pump 5 through a pipeline for liquid pressure boosting, the liquid nitrogen is driven by the liquid nitrogen pump 5 to be boosted to the use pressure of 20MPa in a closed cavity and sent to a vaporizer 6 for high-pressure vaporization, and the vaporized nitrogen is conveyed forwards to a high-pressure nitrogen storage tank. The vaporizer is used for pressurization in a self-pressurization mode, external gas is not introduced, and secondary pollution is avoided. The pipeline of the nitrogen evaporation device for outputting nitrogen is provided with a one-way valve 8 and a nitrogen relief valve 7. The one-way valve 8 prevents high-pressure nitrogen from returning to the evaporation device, and the nitrogen relief valve 7 discharges nitrogen to prevent overpressure.
The high-pressure nitrogen storage tank receives high-pressure nitrogen from a pipeline, is used for supplying air sources before use and during use, is closed, adopts positive pressure in both an operation state and a storage state, and can not allow external natural gas to enter the system. The number of the high-pressure nitrogen storage tanks is set as required, and can be 1, 2 or more, and each high-pressure nitrogen storage tank is respectively provided with a nitrogen inlet valve 9, a nitrogen outlet valve 10, a nitrogen discharge valve 11, a safety valve and a pressure gauge.
The high-pressure high-purity nitrogen preparation and storage subsystem 1 boosts and evaporates liquid nitrogen, stores the liquid nitrogen into a gas storage tank, and supplies the liquid nitrogen to two sets of test devices in a unified manner through a high-flux supply pipeline.
The centralized gas supply and distribution subsystem 2 is composed of a filter, a pressure reducer, a control valve and a sensor as shown in fig. 4, high-pressure gas is conveyed to an inlet of the gas distribution system, pressure distribution is carried out through the gas pressure reducer, the gas is conveyed to parts with different gas demands through the control valve and a pipeline, large-range variable-pressure adjustable flow supply is realized by controlling the parallel number of the gas pressure reducers, and the requirements of large-flow high-pressure gas supply in an extrusion test and small-flow low-pressure accurate supply in a complete machine pump pressure test are realized. As shown in figure 4, the nitrogen output with six pressures is provided, 2-1 supplies 4.5MPa of process nitrogen for blowing to a combustion chamber and an engine, 2-2 ways of supply nitrogen for fire control 4.5MPa, 2-3 ways of oxidizer storage tanks for pressurization 8MPa, 2-4 fuel storage tanks for pressurization 8MPa, 2-5 test bed other pneumatic valves for supply 5MPa, and 2-6 gas distribution table driving gas for 0.6 MPa. High pressure nitrogen was sent through the filter to the front of each sub-circuit. Firstly, a manual valve in front of 2-6 branches is opened, high-pressure air is sent to a pressure reducer through a filter, and after the high-pressure air is sent out through the pressure reducer with the pressure of 0.6MPa, the pneumatic valve of the air distribution plate obtains driving air and can act under the control of an electromagnetic valve. The working principle of 2-5 and 2-1 is the same. 2-3 way middle and high pressure nitrogen is sent to before pneumatic valve, pneumatic valve remote control opens the back, and before high pressure nitrogen sent to main pressure reducer, 2-6 way drive gas adjustment primary pressure reducing valve, control second grade pressure valve applyed pressure to main pressure reducer to make main pressure reducer adjust to 8 MPa's high pressure boost air supply send to export pneumatic valve, open export pneumatic valve after, supply high pressure boost gas to the test bed. 2-4 paths and 2-3 paths of working principle.
The propellant supply subsystem is composed of an independent storage tank, a separate filling pipeline, a separate supply pipeline, a flowmeter, a temperature and pressure sensor, a valve and the like according to the characteristics of a supply medium. According to the test characteristics, storage tanks are arranged side by side in the spatial layout, the pipeline system is synchronously arranged at the left and right intervals, and the parts entering the test bed adopt replaceable flexible connecting pieces for butt joint in the specific test purpose, so that the aims of synchronous preparation and discrete supply are fulfilled.
The thrust restraint installation subsystem consists of a bearing foundation, a thrust frame and a switching frame, wherein the thrust frame is configured according to the maximum test thrust, the installation positions of the butt joint component of the propellant supply system and the nitrogen fire fighting device are reserved upwards, the switching frame is connected downwards, an engine test piece is fixed on the thrust frame through the switching frame, the thrust generated during the operation of the engine is restrained, and the stable continuous test is realized. Two tests with different properties can be converted through the adapter rack, and the test run with the two properties is realized on one test bearing device.
The nitrogen fire-fighting subsystem consists of a pressure reducer, a control valve and a nitrogen distribution device, high-pressure nitrogen is throttled by the pressure reducer and then is sent to the nitrogen distribution device through the control valve, and when abnormal conditions occur in a test, the nitrogen fire-fighting subsystem is remotely and automatically opened to perform nitrogen fire-fighting and non-damage protection on engine products.
The real-time monitoring subsystem consists of a high-definition camera position, an adjustable cradle head and an image display and storage system, is used for remotely monitoring the engine test process in real time, records the engine thermal ignition working process, realizes man-machine isolation and is intrinsically safe.
The measurement and control subsystem is composed of a sensor, a conditioner, a switching cabinet, a digital acquisition and recording device, a communication device, an upper computer and the like, and realizes the dynamic display of the device state and the full-flow recording of parameters in the whole process of the engine test. The measurement and control system is provided with a bus type butt joint switching system through a transfer cabinet, the upper computer measures and controls the switching of the acquisition state through a database configuration test system, and the measurement and control of two sets of test devices are realized on one set of hardware system.
The selective pressurized feed is shared by both the extrusion test system 3 and the pump pressure test system 4.
The extrusion test system 3 and the pump pressure test system 4 work on the similar principle, but the working medium and the operating pressure of the two systems are different. The device comprises an extrusion test oxidant pressurization nitrogen conveying pipeline 3-1, an extrusion test oxidant high-pressure container 3-2, an extrusion test oxidant supply branch 3-3, an extrusion test fuel pressurization conveying pipeline 3-4, an extrusion test fuel high-pressure container 3-5, an extrusion test fuel supply branch 3-6 and an ignition system 3-7. The squeeze test oxidant container 3-2 and the squeeze test fuel container 3-5 are pressurized, respectively. The oxidant is supplied to the front of the engine through an oxidant supply branch 3-3 of the extrusion test; the fuel is supplied to the front of the engine through the extrusion test fuel supply branch; nitrogen is injected into an extrusion test oxidant high-pressure container through an extrusion test oxidant pressurizing nitrogen conveying pipeline 3-1 to be pressurized, nitrogen is injected into an extrusion test fuel high-pressure container 3-5 through an extrusion test fuel pressurizing conveying pipeline 3-4 to be pressurized, an ignition system is opened, an ignition source for ignition is formed in an engine combustion chamber, oxidant is opened through an extrusion test oxidant supply branch 3-3 and a front valve of an extrusion test fuel supply branch pump, so that the oxidant and fuel enter the combustion chamber to be continuously combusted, the engine starts to work, and an extrusion test acquisition module acquires engine data.
The pumping pressure test subsystem consists of a liquid oxygen LOX supply system, a kerosene RP-1 supply system and a gas path auxiliary part, wherein the LOX supply system and the RP-1 supply system have similar principles and are respectively provided with a pumping pressure test oxidant pressurizing and conveying pipeline 4-1, a pumping pressure test oxidant low-pressure container 4-2, a pumping pressure test oxidant supply branch 4-3, a pumping pressure test fuel pressurizing and conveying pipeline 4-4, a pumping pressure test fuel low-pressure container 4-5, a pumping pressure test fuel supply pipeline 4-6, a pumping pressure test auxiliary gas path supply system 4-7 and a pumping pressure test kerosene vacuumizing system 4-8 in the figure 5. The oxidant is supplied to the front of the engine through a pump pressure test oxidant supply branch 4-3; fuel is supplied to the front of the engine through a pump pressure test fuel supply branch; the pump pressure test auxiliary gas path supply system 4-7 supplies the pressure of a high-pressure gas cylinder for engine test to an engine system, the pump pressure test kerosene vacuumizing system 4-8 is started, a coal oil cavity of the engine is vacuumized, a fuel supply pipeline 4-6 pump front valve is opened, and kerosene is filled into the engine under the vacuum condition; nitrogen is injected into the pump pressure test oxidant low-pressure container 4-2 through the pump pressure test oxidant pressurizing and conveying pipeline 4-1 for pressurizing, and nitrogen is injected into the pump pressure test fuel low-pressure container 4-5 through the pump pressure test fuel pressurizing and conveying pipeline 4-4 for pressurizing; the engine starts to work, and the squeezing test acquisition module acquires engine data.
The method for testing by using the double-station test bed of the extrusion pump pressure type rocket engine comprises the following steps:
the extrusion test comprises: test oxidizing agent LN2O is filled into the high-pressure container 3-2 through a filling pipeline for storage, medium in the high-pressure container 3-2 is supplied to the front of the engine through a propellant supply pipeline 3-3, 2-3 paths of output pressure of a gas distribution plate pressurization supply system is set, the gas distribution plate is opened to send out a pneumatic valve, and the output pressure is conveyed to the front of the high-pressure container 3-2 through a nitrogen conveying pipeline 3-1;
test Fuel C2H4Filling the medium into a high-pressure container 3-5 through a filling pipeline for storage, setting 2-4 paths of output pressure of a pressurization supply system of a gas distribution plate before the medium in the high-pressure container 3-5 is supplied to an engine through a propellant supply pipeline 3-6, opening the gas distribution plate to send out a pneumatic valve, and conveying the output pressure to the front of the container 3-5 through 3-4;
measuring system start collecting parameters, opening oxidant high pressure container 3-2 pressurizing valve, starting pressurizing high pressure container 3-2, when increasing to the required starting pressure of mission, opening fuel high pressure container 3-5 pressurizing valve, starting pressurizing high pressure container 3-5, when increasing to the required starting pressure of mission, starting automatic program, engine under the control of automatic program firstly opening 3-7 ignition system, forming ignition source in engine combustion chamber, oxidant supply branch 3-3 and fuel supply branch 3-6 pump front valve are opened under the control of program, LN2O and C2H4Filling and injecting the materials into a combustion chamber before injection according to a specific sequence, atomizing the materials, injecting the materials into the combustion chamber, igniting the materials by an ignition source at the combustion chamber to form continuous combustion, starting the engine to work, acquiring various parameters and video data in the process in real time, monitoring the working state of the engine, closing the engine when the engine works to a specified time, closing propellant supply systems 3-3 and 3-6, discharging residual propellants in a cavity channel of the engine, releasing pressure of high-pressure containers 3-2 and 3-5, recovering residual propellants from an oxidant high-pressure container 3-2, an oxidant supply branch 3-3, a fuel high-pressure container 3-5 and a fuel supply branch 3-6, sealing and storing the oxidant high-pressure container 3-2 and the oxidant supply branch 3-3 under positive pressure, dismantling the engine, and finishing the test.
The pump pressure test comprises: liquid oxygen for the test is filled into a low-pressure container 4-2 through a filling pipeline for storage, the liquid oxygen in the low-pressure container 4-2 is supplied to the front of an engine through a propellant 4-3, 2-3 paths of output pressure of a gas distribution plate pressurization supply system is set, a gas distribution plate is opened to send out a pneumatic valve, and the output pressure is conveyed to the front of the container 4-2 through a filling pipeline 4-1;
the RP-1 for the test is filled into a low-pressure container 4-5 through a filling pipeline for storage, the RP-1 in the low-pressure container 4-5 is supplied to the front of an engine through a propellant supply 4-6, 2-4 paths of output pressure of a gas distribution plate pressurization supply system is set, a gas distribution plate is opened to send out a pneumatic valve, and the output pressure is conveyed to the front of the low-pressure container 4-5 through a fuel pressurization conveying pipeline 4-4;
the pump pressure test auxiliary gas path supply system 4-7 supplies the pressure of a high-pressure gas cylinder for engine test to the engine system through a pipeline, the pump pressure test kerosene vacuum pumping system 4-8 is started, the coal oil cavity of the engine is vacuumized, after the coal oil cavity is pumped to a required value of a task book, the front pump valve of the fuel supply pipeline 4-6 is opened, and the kerosene is filled into the engine under the vacuum condition;
the measuring system starts to collect parameters, opens a pressurizing valve of an oxidant pressurizing and conveying pipeline 4-1, starts to pressurize a liquid oxygen low-pressure container 4-2, when the pressure is increased to a starting pressure required by a task book, opens a pressurizing valve of an RP-1 fuel container 4-4, starts to pressurize an RP-1 fuel low-pressure container 4-5, when the pressure is increased to the starting pressure required by the task book, starts an automatic program, an engine starts to ignite under the control of the automatic program, collects various parameters and video data in the process in real time, monitors the working state of the engine, closes the engine when the engine works to a specified time, closes an oxidant supply branch 4-3 and a fuel supply pipeline 4-6 of a propellant supply system, discharges residual propellant in a cavity of the engine, and releases the pressure of the liquid oxygen low-pressure container 4-2 and the fuel low-pressure container 4-5, and (3) recovering residual propellants from the liquid oxygen low-pressure container 4-2, the oxidant supply branch 4-3, the fuel low-pressure container 4-5 and the fuel supply pipeline 4-6, sealing and storing the system at positive pressure, disassembling the engine and finishing the test.
In conclusion, the invention relates to a double-station test bed and a test method for an extrusion pump pressure type rocket engine. The parallel running of the extrusion type test subsystem and the pumping pressure type test subsystem is realized in the same space, the utilization rate of test resources is improved, the efficiency of test organization is improved, the preparation process of the test is performed in parallel, and the risk of the test process is reduced. The high-pressure nitrogen for the test is directly prepared in a liquid nitrogen volatilization mode, the test gas is uniformly prepared and stored, the reduction of gas purity and the introduction of excess materials caused by secondary pollution and repeated pressure relief of a pipeline are reduced, the purity of the nitrogen for the test is improved, and the reliability of the test is ensured. The high-pressure high-purity nitrogen preparation and storage subsystem, the centralized gas supply and distribution subsystem and the fire fighting subsystem are reused, so that resources are saved.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (10)
1. A double-station test bed for an extrusion pump pressure type rocket engine is characterized by comprising a high-purity nitrogen acquisition and storage subsystem, a centralized gas supply and distribution subsystem, an extrusion test subsystem, a pump pressure test subsystem and a fire fighting subsystem;
the high-pressure high-purity nitrogen preparation and storage subsystem stores and supplies high-pressure nitrogen;
the centralized gas supply and distribution subsystem reduces the high-pressure nitrogen to a set pressure and then provides the nitrogen to the extrusion test subsystem, the pumping pressure test subsystem and the fire fighting subsystem;
the extrusion test subsystem utilizes nitrogen to pressurize the fuel storage tank and the oxidant storage tank, so that the fuel and the oxidant are discharged to a combustion chamber for combustion;
the pumping pressure test subsystem is used for pressurizing the liquid oxygen storage tank and the kerosene storage tank by using nitrogen to perform an engine ignition test;
the fire protection subsystem extinguishes fire by injecting nitrogen.
2. The double-station test bed of the squeeze pump type rocket engine according to claim 1, further comprising a thrust restraint mounting subsystem, which comprises a force bearing foundation, a thrust frame and an adapter frame, wherein the engine test piece is fixed to the thrust frame through the adapter frame, is fixed to the force bearing foundation through the thrust frame, and restrains the thrust generated by the engine during operation; different adapter racks are adopted for carrying out the extrusion test and the pump pressure test.
3. A double-station test bed for a squeeze pump rocket engine according to claim 1 or 2 wherein the propellant supply subsystem is adapted to meter oxidizer and fuel to the engine assembly.
4. The double-station test bed for the extrusion pump-type rocket engine according to claim 1 or 2, further comprising a real-time monitoring subsystem for collecting and monitoring video images of the extrusion test and the pump pressure test.
5. The double-station test bed of the squeeze pump type rocket engine according to claim 1 or 2, wherein the high-pressure high-purity nitrogen preparation and storage subsystem comprises a low-temperature liquid nitrogen storage tank, a nitrogen evaporation device and a high-pressure nitrogen storage tank; the low-temperature liquid nitrogen storage tank is used for storing liquid nitrogen; the liquid nitrogen can be gasified by a nitrogen evaporation device and then conveyed to the high-pressure nitrogen, and the high-pressure nitrogen storage tank is used for storing and supplying the high-pressure nitrogen. Further, the nitrogen evaporation device comprises a liquid nitrogen pump and a vaporizer; the liquid nitrogen pump drives liquid nitrogen to be boosted to a set pressure in the closed cavity and sent to the vaporizer for high-pressure vaporization, and vaporized nitrogen is conveyed forwards to the high-pressure nitrogen storage tank.
6. The double-station test bed of the extrusion pump pressure type rocket engine according to claim 1 or 2, wherein the centralized gas supply and distribution subsystem directly supplies the pressure of high-pressure nitrogen to a main gas collecting pipe of a gas distribution plate from 30MPa, realizes the nitrogen pressurization supply of the extrusion test bed and the nitrogen pressurization supply of the pump pressure test bed through PLC remote control, and supplies the nitrogen to a fire fighting subsystem after being regulated and reduced in pressure to 4.5MPa through a high-pressure reducer.
7. The double-station test bed of the extrusion pump-type rocket engine according to claim 1 or 2, wherein the extrusion test subsystem comprises an extrusion test oxidant pressurized nitrogen conveying pipeline, an extrusion test oxidant high-pressure container, an extrusion test oxidant supply branch, an extrusion test fuel pressurized conveying pipeline, an extrusion test fuel high-pressure container, an extrusion test fuel supply branch, an ignition system and an extrusion test acquisition module;
the oxidant is supplied to the front of the engine through the extrusion test oxidant supply branch; the fuel is supplied to the front of the engine through the extrusion test fuel supply branch; the nitrogen is injected into an extrusion test oxidant high-pressure container through an extrusion test oxidant pressurizing nitrogen conveying pipeline for pressurizing, the nitrogen is injected into an extrusion test fuel high-pressure container through an extrusion test fuel pressurizing conveying pipeline for pressurizing, an ignition system is started, an ignition source for ignition is formed in an engine combustion chamber, the oxidant is opened through a front valve of an extrusion test oxidant supply branch and an extrusion test fuel supply branch, so that the oxidant and the fuel enter the combustion chamber for continuous combustion, the engine starts to work, and an extrusion test acquisition module acquires engine data.
8. The double-station test bed for the extrusion pump-pressed rocket engine according to claim 7, wherein the pump-press test subsystem comprises a pump-press test oxidant pressurizing and conveying pipeline, a pump-press test oxidant low-pressure container, a pump-press test oxidant supply branch, a pump-press test fuel pressurizing and conveying pipeline, a pump-press test fuel low-pressure container, a pump-press test fuel supply pipeline, a pump-press test auxiliary gas path supply system, a pump-press test kerosene vacuumizing system and a pump-press test acquisition module;
the oxidant is supplied to the front of the engine through a pump pressure test oxidant supply branch; fuel is supplied to the front of the engine through a pump pressure test fuel supply branch;
the pump pressure test auxiliary gas path supply system supplies the pressure of a high-pressure gas cylinder for engine test to an engine system, the pump pressure test kerosene vacuumizing system is started, a kerosene cavity of the engine is vacuumized, a pump front valve of a fuel supply pipeline is opened, and kerosene is filled into the engine under the vacuum condition;
nitrogen is injected into the pump pressure test oxidant low-pressure container for pressurization through the pump pressure test oxidant pressurization conveying pipeline, and nitrogen is injected into the pump pressure test fuel low-pressure container for pressurization through the pump pressure test fuel pressurization conveying pipeline; the engine starts to work, and the squeezing test acquisition module acquires engine data.
9. The method for testing by using the double-station test bed of the squeeze pump type rocket engine of claim 8, which comprises the following steps: the compression test and the pump pressure test were performed.
10. The method of conducting an assay of claim 9,
the extrusion test comprises: the oxidant is supplied to the front of the engine through the extrusion test oxidant supply branch; the fuel is supplied to the front of the engine through the extrusion test fuel supply branch; nitrogen is injected into an extrusion test oxidant high-pressure container through an extrusion test oxidant pressurizing nitrogen conveying pipeline for pressurizing, nitrogen is injected into an extrusion test fuel high-pressure container through an extrusion test fuel pressurizing conveying pipeline for pressurizing, an ignition system is started, an ignition source for ignition is formed in an engine combustion chamber, a pump front valve of an oxidant is opened through an extrusion test oxidant supply branch and an extrusion test fuel supply branch, so that the oxidant and fuel enter the combustion chamber for continuous combustion, the engine starts to work, and an extrusion test acquisition module acquires engine data; when the engine works to a designated time, closing the oxidant supply branch and the fuel supply branch of the extrusion test, discharging residual propellant in a cavity channel of the engine, releasing pressure of an oxidant high-pressure container and a fuel high-pressure container of the extrusion test, recovering the oxidant and the fuel, sealing and storing a subsystem of the extrusion test at positive pressure, dismantling the engine, and ending the test;
the pump pressure test comprises: the oxidant is supplied to the front of the engine through a pump pressure test oxidant supply branch; fuel is supplied to the front of the engine through a pump pressure test fuel supply branch; the pump pressure test auxiliary gas path supply system supplies the pressure of a high-pressure gas cylinder for engine test to an engine system, the pump pressure test kerosene vacuumizing system is started, a kerosene cavity of the engine is vacuumized, a pump front valve of a fuel supply pipeline is opened, and kerosene is filled into the engine under the vacuum condition; nitrogen is injected into the low-pressure container of the oxidant for the pump pressure test through the pressurizing delivery pipeline of the oxidant for the pump pressure test for pressurizing, and nitrogen is injected into the low-pressure container of the fuel for the pump pressure test for pressurizing through the pressurizing delivery pipeline of the fuel for the pump pressure test for pressurizing; the engine starts to work, and the extrusion test acquisition module acquires engine data; and when the engine works to a designated time, closing the oxidant supply branch and the pump pressure test fuel supply pipeline of the propellant supply system, discharging residual propellant in the cavity channel of the engine, recovering the oxidant and the fuel, sealing and storing the pump pressure test subsystem at positive pressure, dismantling the engine, and ending the test.
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