CN115562320B - Variable thrust propulsion system and control method - Google Patents
Variable thrust propulsion system and control method Download PDFInfo
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- CN115562320B CN115562320B CN202211222300.5A CN202211222300A CN115562320B CN 115562320 B CN115562320 B CN 115562320B CN 202211222300 A CN202211222300 A CN 202211222300A CN 115562320 B CN115562320 B CN 115562320B
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- 238000000034 method Methods 0.000 title claims description 8
- 230000001105 regulatory effect Effects 0.000 claims abstract description 61
- 239000003380 propellant Substances 0.000 claims abstract description 48
- 238000005259 measurement Methods 0.000 claims abstract description 21
- 230000001276 controlling effect Effects 0.000 claims abstract description 13
- 238000006243 chemical reaction Methods 0.000 claims abstract description 12
- 230000007246 mechanism Effects 0.000 claims abstract description 5
- 239000007788 liquid Substances 0.000 claims description 53
- 239000012530 fluid Substances 0.000 claims description 7
- 238000010586 diagram Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Automation & Control Theory (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Feedback Control In General (AREA)
Abstract
The invention is applicable to the technical field of aircrafts, and provides a variable thrust propulsion system, which comprises: the device comprises a high-pressure gas channel, a gas channel filter and a control measurement system, wherein one end of the high-pressure gas channel is connected with an outlet of a high-pressure gas cylinder, and the other end of the high-pressure gas channel passes through the gas channel filter to be connected with an inlet of a pressure reducing valve. The proportion of the propellant flow of the track-controlled engine and the attitude-controlled engine can be adjusted by controlling the proportion three-way electric regulating valve, so that the flow of the propellant supplied to the engine is adjusted, the adjustment of the variable thrust of the engine is realized, and the weight and the complexity of a propulsion system can be greatly reduced; the control measurement system comprises a signal acquisition module, a data conversion module, a data processing module and a control module, the data processing module is used for calculating, data regulated by the proportional three-way electric regulating valve is generated, and the data are sent to an actuating mechanism of the proportional three-way electric regulating valve through the control module, so that the valve opening is regulated.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a variable thrust propulsion system and a control method.
Background
The aircraft is required to be subjected to continuous attitude adjustment and orbit adjustment during the on-orbit flight, the working thrust of the engine is different under different conditions and different adjustment demands, so that various engines with different thrust are required to be installed on the aircraft to meet the demands of different thrust, the flying demands of various different working conditions are realized, and the variable thrust propulsion system can realize few engines to meet the demands of different working conditions. Typically, the line is fixed, the engine flow resistance is also adjusted, the engine propellant flow is fixed at normal times, and the thrust is relatively fixed. Meanwhile, in the process of changing the track and adjusting the gesture, the gesture control engine and the track control engine usually work at different time, even if the gesture control engine and the track control engine work at the same time, the flow ratio of the gesture control propellant and the track control propellant is relatively fixed, the requirements on the working thrust of the engines are different under different environments and different requirements, and different thrust needs to be realized by a plurality of engines, or the working condition of each engine is independently adjusted, so that the variable thrust of a single engine is realized. Thus, the number of engines is increased, or the number of engines with variable thrust is increased, the weight of the system is increased, and the control is complicated.
Disclosure of Invention
The embodiment of the invention provides a variable thrust propulsion system, which aims to solve the problems in the background technology.
Embodiments of the present invention are thus implemented, a variable thrust propulsion system, comprising: the system comprises a high-pressure gas path channel, a gas path filter and a control measurement system; one end of the high-pressure gas channel is connected with an outlet of a high-pressure gas cylinder, the other end of the high-pressure gas channel passes through a gas channel filter and is connected with an inlet of a pressure reducing valve, an outlet of the pressure reducing valve is connected with one end of a low-pressure gas channel, the other end of the low-pressure gas channel is connected with an inlet of a storage tank body, the low-pressure gas channel is connected with a gas channel pressure sensor and a safety valve in parallel, an outlet of the storage tank body passes through a liquid channel filter and is connected with one end of a main liquid channel, the other end of the main liquid channel is connected with an inlet of a proportional three-way electric regulating valve, a first outlet of the proportional three-way electric regulating valve is connected with one end of a rail control liquid channel, the other end of the rail control liquid channel is connected with an inlet of a rail control engine, a second outlet of the proportional three-way electric regulating valve is connected with one end of a gesture control liquid channel, the other end of the attitude control liquid path channel is connected with an inlet of the attitude control engine, a temperature sensor is arranged on the proportional three-way electric regulating valve, a flow sensor is integrally arranged on the proportional three-way electric regulating valve, a control measurement system is respectively and electrically connected with the three-way electric regulating valve, the gas path pressure sensor and the liquid path pressure sensor, the flow sensor is arranged in the three-way electric regulating valve, the control measurement system is used for collecting gas pressure parameters of the gas path pressure sensor, temperature parameters of the temperature sensor, liquid parameters of the liquid path pressure sensor, flow parameters of the flow sensor and aperture proportional parameters of the proportional three-way electric regulating valve, and the control measurement system is used for controlling the opening proportional parameters of the proportional three-way electric regulating valve according to the pressure parameters, the temperature parameters, flow parameters, and the opening proportion parameter controls the thrust of the engine.
Further, the storage tank body comprises a storage tank air cavity and a storage tank liquid cavity, the low-pressure air passage is communicated with the storage tank air cavity, and the main liquid passage is communicated with the storage tank liquid cavity.
Further, the gas circuit pressure sensor is used for measuring the outlet air pressure of the pressure reducing valve, and the safety valve is used for guaranteeing the safety of the low-pressure gas circuit.
Further, the attitude control liquid path channel is used for conveying propellant to the attitude control engine.
Further, the rail control liquid path channel is used for conveying propellant to the rail control engine.
Further, the control measurement system comprises a signal acquisition module, a data conversion module, a data processing module and a control module;
The signal acquisition module is used for acquiring parameters of the pressure parameter, the temperature parameter, the flow and the opening proportion parameter in the system;
The data conversion module is used for converting the collected pressure parameter, the temperature parameter, the flow parameter and the opening proportion parameter into target data which can be identified by the data processing module;
the data processing module is used for calculating according to the target data by adopting a preset algorithm to generate control data for adjusting the three-way electric regulating valve of the comparative example;
the control module is used for sending the control data to an actuating mechanism of the proportional three-way electric regulating valve.
A control method of a variable thrust propulsion system applied to the variable thrust system of any one of claims 1 to 7, the control method comprising the steps of:
s1, firstly fitting out the corresponding relation between different opening degrees of the three-way electric regulating valve and different propellant flows, and recording the corresponding relation in the control measuring system;
S2, controlling a proportional three-way electric regulating valve to be adjusted to be suitable for the flow rate of the propellant under the rated working conditions of the track control engine and the attitude control engine by utilizing the control measuring system according to the flow rate of the propellant under the rated working conditions of the track control engine and the attitude control engine, so that the track control engine and the attitude control engine can work under the rated working conditions;
S3, when the track control engine needs to work under variable working conditions, determining first propellant flow of the track control engine according to the use condition of the track control engine, and controlling the opening proportion of a proportion three-way electric regulating valve by utilizing the control measuring system according to the first propellant flow and the corresponding relation to regulate the propellant flow of a track control liquid path channel so as to meet the requirement of the track control engine on variable thrust;
And S4, when the attitude control engine needs to work under a variable working condition, determining second propellant flow of the attitude control engine according to the working condition of the attitude control engine, and controlling the opening proportion of the proportional three-way electric regulating valve by utilizing the control measuring system according to the second propellant flow and the corresponding relation to regulate the propellant flow of the attitude control liquid path channel so as to meet the variable thrust requirement of the attitude control engine.
The invention has the beneficial effects that the flow rate proportion of the propellant of the track control engine and the attitude control engine can be regulated by controlling the proportion three-way electric regulating valve, so as to regulate the flow rate of the propellant of the supply engine, thereby realizing the regulation of the variable thrust of the engine and greatly reducing the weight and complexity of a propulsion system; the control measurement system comprises a signal acquisition module, a data conversion module, a data processing module and a control module, the data processing module is used for calculating, data regulated by the proportional three-way electric regulating valve is generated, and the data are sent to an actuating mechanism of the proportional three-way electric regulating valve through the control module, so that the valve opening is regulated.
Drawings
FIG. 1 is a schematic diagram of an overall structure of a variable thrust propulsion system according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a control measurement system of a variable thrust propulsion system according to an embodiment of the present invention.
1. A high pressure gas cylinder; 2. an air path filter; 3. a pressure reducing valve; 4. a gas circuit pressure sensor; 5. a safety valve; 6. a storage tank body; 61. a tank air cavity; 62. a reservoir fluid chamber; 7. a liquid path filter; 8. a hydraulic pressure sensor; 9. a proportional three-way electric regulating valve; 10. a rail-controlled engine; 11. a gesture control engine; 12. controlling a measurement system; 121. a signal acquisition module; 122. a data conversion module; 123. a data processing module; 124. a control module; 13. a high pressure gas path channel; 14. a low pressure gas path channel; 15. a main fluid path channel; 16. a rail-controlled fluid path channel; 17. and a liquid path channel is controlled by the gesture.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
Example 1
According to fig. 1, a variable thrust propulsion system comprises: a high pressure gas path channel 13, a gas path filter 2 and a control measurement system 12; one end of the high-pressure gas passage 13 is connected with an outlet of the high-pressure gas cylinder 1, the other end of the high-pressure gas passage 13 passes through the gas passage filter 2 to be connected with an inlet of the pressure reducing valve 3, the outlet of the pressure reducing valve 3 is connected with one end of the low-pressure gas passage 14, the other end of the low-pressure gas passage 14 is connected with an inlet of the storage tank body 6, the low-pressure gas passage 14 is connected with the gas passage pressure sensor 4 and the safety valve 5 in parallel, the outlet of the storage tank body 6 passes through the liquid passage filter 7 to be connected with one end of the main liquid passage 15, the other end of the main liquid passage 15 is connected with an inlet of the proportional three-way electric regulating valve 9, the main liquid passage 15 is connected with the liquid passage pressure sensor 8 in parallel, a first outlet of the proportional three-way electric regulating valve 9 is connected with one end of the rail control liquid passage 16, the other end of the rail control liquid passage 16 is connected with an inlet of the rail control engine 10, the second outlet of the proportional three-way electric regulating valve 9 is connected with one end of a gesture control liquid channel 17, the other end of the gesture control liquid channel 17 is connected with the inlet of the gesture control engine 11, a temperature sensor is arranged on the proportional three-way electric regulating valve 9, the proportional three-way electric regulating valve 9 is integrally provided with a flow sensor, the control measuring system 12 is respectively and electrically connected with the three-way electric regulating valve 9, the gas circuit pressure sensor 4 and the liquid circuit pressure sensor 8, the flow sensor is arranged in the three-way electric regulating valve 9, the control measuring system 12 is used for collecting gas pressure parameters of the gas circuit pressure sensor 4, temperature parameters of the temperature sensor, parameters of liquid of the liquid circuit pressure sensor 8, flow parameters of the flow sensor and aperture ratio parameters of the control three-way electric regulating valve 9, and the control measuring system is used for controlling the flow parameters according to the pressure parameters, the temperature parameter, the flow parameter, and the opening ratio parameter control the thrust of the engine.
The proportion three-way valve is controlled, so that the flow proportion of the propellant of the track control engine 10 and the gesture control engine 11 can be adjusted, and the flow of the propellant of the engine is further adjusted, thereby realizing the adjustment of the variable thrust of the engine and greatly reducing the weight and complexity of a propulsion system.
The tank body 6 includes a tank air chamber 61 and a tank liquid chamber 62, the low-pressure air passage 14 communicates with the tank air chamber 61, and the main liquid passage 15 communicates with the tank liquid chamber 62.
The tank body 6 is composed of the tank air cavity 61 and the tank liquid cavity 62, so that liquid and gas can be stored conveniently, and enough pressure and flow are provided for the attitude control engine 11 and the orbit control engine 10.
The gas circuit pressure sensor 4 is used for measuring the outlet air pressure of the pressure reducing valve 3, and the safety valve 5 is used for guaranteeing the safety of the low-pressure gas circuit.
The gas path pressure sensor 4 is arranged on the measurement pressure reducing valve 3, so that the outlet pressure of the gas path pressure sensor can be conveniently detected.
The attitude control liquid path channel 17 is used for delivering propellant to the attitude control engine 11.
The propellant is used for conveying the propellant to the attitude control engine 11 through the attitude control liquid path channel 17, so that the propellant split by the proportional three-way electric regulating valve 9 is conveniently conveyed to the attitude control engine 11.
The rail passage 16 is used to deliver a propellant to the rail engine 10.
Propellant can be delivered to the rail engine 10 through the rail control liquid passage 16, so that the propellant split by the proportional three-way electric regulating valve 9 can be conveniently delivered into the rail control engine 10.
Example two
The control measurement system 12 includes a signal acquisition module 121, a data conversion module 122, a data processing module 123, and a control module 124; the signal acquisition module 121 is configured to acquire the pressure parameter, the temperature parameter, the flow parameter, and the opening ratio parameter in the system; the data conversion module 122 is configured to convert the collected pressure parameter, the temperature parameter, the flow parameter, and the opening ratio parameter into target data that can be identified by the data processing module 123; the data processing module 123 is configured to calculate, according to the target data, by using a preset algorithm, and generate a control number for adjusting the three-way electric control valve 9 according to the target data; the control module 124 is configured to send the control data to an actuator of the proportional three-way electric control valve 9.
The control measurement system 12 comprises a signal acquisition module 121, a data conversion module 122, a data processing module 123 and a control module 124, and the opening degree of the proportional three-way electric regulating valve 9 is conveniently regulated through the connection action relation among the signal acquisition module 121, the data conversion module 122, the data processing module 123 and the control module 124.
The control and measurement system is a control center of the system and comprises a signal acquisition module, a data conversion module, a data processing module, a control module and the like, wherein the signal acquisition module comprises pressure acquisition, temperature acquisition, flow acquisition and the like. The data processing module is used for calculating the data, the control module is used for sending the data to the actuating mechanism of the proportional three-way electric regulating valve, and the control module is used for adjusting the opening degree of the valve.
Example III
1-2, A control method of a variable thrust propulsion system, applied to a variable thrust system according to any one of claims 1 to 7, comprising the steps of:
S1, firstly fitting out the corresponding relation between different opening degrees of the three-way electric regulating valve 9 and different propellant flows, and recording the corresponding relation in the control measuring system 12;
s2, according to the ratio of the flow of the propellant used under the rated working conditions between the rail control engine 10 and the attitude control engine 11, the control measuring system 12 is utilized to control the ratio three-way electric regulating valve 9 to be adjusted to be matched with the ratio of the flow of the propellant under the rated working conditions of the rail control engine 10 and the attitude control engine 11, so that the rail control engine 10 and the attitude control engine 11 can work under the rated working conditions;
s3, when the track control engine 10 needs to work under variable working conditions, determining first propellant flow of the track control engine according to the use condition of the track control engine 10, and controlling the opening proportion of the proportion three-way electric regulating valve 9 by utilizing the control measuring system 12 according to the first propellant flow and the corresponding relation to regulate the propellant flow of the track control liquid channel 16 so as to meet the variable thrust requirement of the track control engine 10;
And S4, when the attitude control engine 11 needs to work under variable working conditions, determining second propellant flow of the attitude control engine according to the working conditions of the attitude control engine 11, and controlling the opening proportion of the proportional three-way electric regulating valve 9 by utilizing the control measuring system 12 according to the second propellant flow and the corresponding relation to regulate the propellant flow of the attitude control liquid path channel 17 so as to meet the requirement of the attitude control engine 11 for changing thrust.
Specifically, a set of data corresponding to different propellant flows at different openings is fitted first and recorded into a control and measurement system. And adjusting the proportional three-way electric regulating valve to proper proportional distribution according to normal use conditions of the track control engine and the attitude control engine, so that the track control engine and the attitude control engine can work under rated conditions. When the track control engine needs to work under a variable working condition, the proportional three-way electric regulating valve is regulated to a proper opening degree according to the use working condition and fitted data, so that the requirement of the track control engine on variable thrust is met; when the attitude control engine needs to work under a variable working condition, the proportional three-way electric regulating valve is regulated to a proper opening degree according to the use working condition and the fitted data, so that the requirement of the attitude control engine on variable thrust is met.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (7)
1. A variable thrust propulsion system, comprising: a high-pressure gas path channel (13), a gas path filter (2) and a control measurement system (12); one end of the high-pressure air passage (13) is connected with an outlet of the high-pressure air cylinder (1), the other end of the high-pressure air passage (13) passes through the air passage filter (2) to be connected with an inlet of the pressure reducing valve (3), the outlet of the pressure reducing valve (3) is connected with one end of the low-pressure air passage (14), the other end of the low-pressure air passage (14) is connected with an inlet of the storage tank body (6), the low-pressure air passage (14) is connected with the air passage pressure sensor (4) and the safety valve (5) in parallel, the outlet of the storage tank body (6) passes through the air passage filter (7) to be connected with one end of the main liquid passage (15), the other end of the main liquid passage (15) is connected with an inlet of the proportional three-way electric regulating valve (9), the main liquid passage (15) is connected with the liquid passage pressure sensor (8) in parallel, a first outlet rail of the proportional three-way electric regulating valve (9) is connected with one end of the liquid passage (16), the other end of the rail-controlled liquid passage (16) is connected with an inlet of the engine (10), the other end of the proportional three-way electric regulating valve (9) is connected with the three-way electric regulating valve (17) and the other end of the three-way electric regulating valve (17) is connected with the three-way electric regulating valve (17), the control measurement system (12) is respectively and electrically connected with the three-way electric control valve (9), the gas circuit pressure sensor (4) and the liquid circuit pressure sensor (8), the three-way electric control valve (9) is internally provided with the flow sensor, the control measurement system (12) is used for collecting gas pressure parameters of the gas circuit pressure sensor (4), temperature parameters of the temperature sensor, parameters of liquid of the liquid circuit pressure sensor (8), flow parameters of the flow sensor and opening proportion parameters of the control three-way electric control valve (9), and the control measurement system is used for controlling thrust of an engine according to the pressure parameters, the temperature parameters, the flow parameters and the opening proportion parameters.
2. A variable thrust propulsion system according to claim 1, wherein the tank body (6) includes a tank air chamber (61) and a tank fluid chamber (62), the low pressure air passage (14) communicates with the tank air chamber (61), and the main fluid passage (15) communicates with the tank fluid chamber (62).
3. A variable thrust propulsion system according to claim 1, characterized in that the gas circuit pressure sensor (4) is arranged to measure the outlet gas pressure of the pressure reducing valve (3), and the safety valve (5) is arranged to secure the low pressure gas circuit.
4. A variable thrust propulsion system according to claim 1, characterized in that the attitude control liquid passage (17) is adapted to feed a propellant to the attitude control engine (11).
5. A variable thrust propulsion system according to claim 1, wherein the track-controlled fluid passage (16) is adapted to deliver propellant to the track-controlled engine (10).
6. A variable thrust propulsion system according to claim 1, wherein the control measurement system (12) comprises a signal acquisition module (121), a data conversion module (122), a data processing module (123) and a control module (124);
The signal acquisition module (121) is used for acquiring parameters according to the pressure parameter, the temperature parameter, the flow and the opening proportion parameter in the system;
the data conversion module (122) is used for converting the acquired pressure parameter, the acquired temperature parameter, the acquired flow parameter and the acquired opening proportion parameter into target data which can be identified by the data processing module (123);
The data processing module (123) is used for calculating according to the target data by adopting a preset algorithm to generate control data for adjusting the three-way electric regulating valve (9) of the comparison example;
The control module (124) is used for sending the control data to an actuating mechanism of the proportional three-way electric regulating valve (9).
7. A control method of a variable thrust propulsion system, characterized by being applied to the variable thrust system according to any one of claims 1 to 6, comprising the steps of:
s1, firstly fitting out the corresponding relations between different opening degrees of the three-way electric regulating valve (9) and different propellant flows, and recording the corresponding relations in the control measuring system (12);
S2, according to the ratio of the flow of the propellant used under the rated working conditions between the track control engine (10) and the attitude control engine (11), the control measuring system (12) is utilized to control the ratio three-way electric regulating valve (9) to be adjusted to be matched with the ratio of the flow of the propellant under the rated working conditions of the track control engine (10) and the attitude control engine (11), so that the track control engine (10) and the attitude control engine (11) can work under the rated working conditions;
S3, when the rail control engine (10) needs to work under variable working conditions, determining first propellant flow of the rail control engine according to the use condition of the rail control engine (10), and controlling the opening proportion of a proportion three-way electric regulating valve (9) by utilizing the control measuring system (12) according to the first propellant flow and the corresponding relation to regulate the propellant flow of a rail control liquid channel (16) so as to meet the variable thrust requirement of the rail control engine (10);
s4, when the attitude control engine (11) needs to work under variable working conditions, determining second propellant flow of the attitude control engine according to working conditions of the attitude control engine (11), and controlling the opening proportion of the proportional three-way electric regulating valve (9) by utilizing the control measuring system (12) according to the second propellant flow and the corresponding relation to regulate the propellant flow of the attitude control liquid path channel (17) so as to meet the requirement of variable thrust of the attitude control engine (11).
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| CN202211222300.5A CN115562320B (en) | 2022-10-08 | 2022-10-08 | Variable thrust propulsion system and control method |
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| CN202211222300.5A CN115562320B (en) | 2022-10-08 | 2022-10-08 | Variable thrust propulsion system and control method |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112594093A (en) * | 2020-12-04 | 2021-04-02 | 北京航空航天大学 | Control system of reciprocating displacement pump for solid-liquid rocket engine |
| CN112729852A (en) * | 2020-12-22 | 2021-04-30 | 西安精密机械研究所 | Three-component turbine power combustion subsystem combined test device and test method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB902055A (en) * | 1960-11-24 | 1962-07-25 | United Aircraft Corp | Rocket thrust control |
| KR101059796B1 (en) * | 2009-02-13 | 2011-08-26 | 한국과학기술원 | Rocket Propellant Flow Control |
| CN204405329U (en) * | 2014-11-01 | 2015-06-17 | 西安航天动力研究所 | Control system for variable thrust solid rocket motor test |
| CN112377330B (en) * | 2021-01-18 | 2021-04-13 | 北京星际荣耀空间科技股份有限公司 | Liquid rocket engine thrust adjustment method, device, equipment and storage medium |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112594093A (en) * | 2020-12-04 | 2021-04-02 | 北京航空航天大学 | Control system of reciprocating displacement pump for solid-liquid rocket engine |
| CN112729852A (en) * | 2020-12-22 | 2021-04-30 | 西安精密机械研究所 | Three-component turbine power combustion subsystem combined test device and test method |
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