CN112228250B - Liquid attitude control engine integrated block - Google Patents
Liquid attitude control engine integrated block Download PDFInfo
- Publication number
- CN112228250B CN112228250B CN202010947359.5A CN202010947359A CN112228250B CN 112228250 B CN112228250 B CN 112228250B CN 202010947359 A CN202010947359 A CN 202010947359A CN 112228250 B CN112228250 B CN 112228250B
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- China
- Prior art keywords
- installation end
- installation
- end faces
- integrated block
- propellant
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- 239000007788 liquid Substances 0.000 title claims abstract description 17
- 238000009434 installation Methods 0.000 claims abstract description 66
- 239000003380 propellant Substances 0.000 claims description 38
- 230000003014 reinforcing effect Effects 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 238000000034 method Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000013598 vector Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
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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
- F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
- F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
- F02K9/766—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with liquid propellant
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
-
- 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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Valve Device For Special Equipments (AREA)
Abstract
The invention discloses a liquid attitude control engine integrated block, which comprises an integrated block and an outwards extending installation connection structure; the integrated block is of an integrated structure, four sides of four quadrants of the integrated block I, II, III, IV are electromagnetic valve installation end faces, the electromagnetic valves are connected with the electromagnetic valve installation end faces through screws, an installation connection structure extends outwards between adjacent quadrants of the four quadrants of the integrated block I, II, III, IV, the inside of the installation connection structure extends outwards to form a cavity structure, the outer side face of the installation connection structure is an installation end face, the installation end face comprises a central installation end face and two side installation end faces, the central installation end face is a bearing support installation end face, the two side installation end faces are thrust chamber installation end faces, functions of the integrated block structure are optimized and improved, the problem of complex installation of the original structure is solved, production cost is reduced, production efficiency is improved, the overall structure layout is reasonable and concise, the attitude control unit is convenient and quick to assemble, and mechanical property and reliability of products are improved.
Description
Technical Field
The invention relates to the technical field of liquid attitude control power systems, in particular to a liquid attitude control engine integrated block.
Background
In the working process of aircrafts such as rockets, missiles, satellites and the like, the attitude of the aircrafts needs to be controlled and adjusted rapidly and accurately through attitude control engines, and usually, a plurality of attitude control engines are arranged on one aircrafts to provide thrust vectors so as to realize the attitudes such as pitching, yawing, rolling, rotating around a centroid and the like. In the liquid attitude control power system, a propellant management system controls the extrusion of the propellant, and the propellant is conveyed to an engine after flowing through a main pipeline. When the engine is in a working state, the electromagnetic valve is opened, propellant enters the thrust chamber to perform chemical combustion reaction, and generated high-temperature fuel gas is accelerated by the spray pipe and then sprayed out to form thrust, so that the work is completed. When the engine is not in working state, the electromagnetic valve is closed, the propellant flow passage is blocked, and the engine is shut down.
Typically, a plurality of attitude control power systems are arranged on an aircraft, and are activated in time according to the flight process to complete attitude control. And a plurality of engines are often arranged in a gesture control power system, the thrust and the duration of the engines are preset, and single or multiple combined state works are performed according to the actual working condition requirement of the flight process, so that the thrust required by gesture adjustment is formed. The supercharging system and the propellant management system work cooperatively to convey the propellant to the engine according to the specified flow and pressure. As shown in fig. 1-2, the conventional four-position control engine unit mainly comprises 1 integrated block, 4 electromagnetic valves, 4 thrust chambers, 1 bearing support and 8 switching pieces, wherein the 4 electromagnetic valves are fixed on four sides of the integrated block through fasteners, 2 switching pieces are distributed on two sides of each electromagnetic valve, one side of each switching piece is fixedly connected with the integrated block through the fasteners, and the other side of each switching piece is simultaneously fixedly connected with the bearing support and the thrust chamber mounting lugs through the fasteners. The inner side mounting hole position of the adapter is positioned in size through the integrated block hole position, the outer side hole position of the adapter is positioned in size through the mounting position of the bearing support, and the integrated block and the bearing support can be normally connected into a whole through the middle adapter. When the thrust chamber is installed, after the propellant inlet of the thrust chamber is in pressure connection and sealing with the propellant outlet of the electromagnetic valve, the installation hole positions of the support lugs of the thrust chamber, the installation hole positions of the bearing support and the installation hole positions on the outer side of the adapter are aligned at the same time, and then the thrust chamber can be fastened and installed by using the fastener. Therefore, the dimensional tolerance control and the machining process control accuracy of each single unit are required to be particularly high.
Because of the manufacturing variability of each single unit and the welding deformation of the thrust chamber mounting lugs, the problem that the deviation exists between the mounting hole position of the thrust chamber and the mounting hole position of the bearing bracket and the mounting hole position of the adapter can occur during actual mounting, thereby leading to the failure of successful assembly of the four-attitude control engine unit. Therefore, the production cost and the assembly time of the product are increased, and the reliability and the aesthetic degree of the product are reduced.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a liquid attitude control engine integrated block. The positioning and mounting modes of the original adapter, the bearing support and the thrust chamber mounting support lug are changed, and the problem that deviation exists between the thrust chamber mounting hole site and the bearing support and between the adapter mounting hole site in the original mounting mode is solved. The functional design of the integrated block structure is optimized and improved to solve the problem of complex installation of the original structure, reduce the cost, improve the production efficiency, simplify the structure and improve the mechanical property and the reliability.
The technical scheme adopted by the invention is that the liquid attitude control engine integrated block comprises an integrated block and an outwards extending installation connecting structure; the integrated block is of an integrated structure, four sides of four quadrants of the integrated block I, II, III, IV are electromagnetic valve installation end faces, four electromagnetic valves are connected with the electromagnetic valve installation end faces through screws, an outwards extending installation connection structure is arranged between adjacent quadrants of the integrated block I, II, III, IV, the inside of the outwards extending installation connection structure is of a cavity structure, the outer sides of the outwards extending installation connection structure are installation end faces, the installation end faces comprise a central installation end face and two side installation end faces, the central installation end faces are force bearing support installation end faces, a force bearing support of an installation unit is arranged, the two side installation end faces are thrust chamber installation end faces, a thrust chamber is installed through screws, propellant inlets are formed in the upper bottom face and the lower bottom face of the integrated block, the propellant inlets are connected with propellant dry pipelines, and the electromagnetic valve propellant inlets are communicated with four side propellant channels of the integrated block, and a solenoid valve propellant outlet is in pressure connection with the propellant inlets of the thrust chamber.
Further, the outward extending mounting connection structure symmetrically extends outwards from the side surface of the central body.
Further, the cavity structure is provided with a reinforcing rib, and the reinforcing rib is connected with the integrated block.
Further, smooth through holes and threaded through holes are formed in the central mounting end face and the two side mounting end faces and are used for screw connection and mounting.
Further, the outwards extending installation connection structure is an integrated polygonal symmetrical structure.
Further, the thrust chamber propellant inlet and the electromagnetic valve propellant outlet are radially sealed through an O-shaped rubber ring.
Further, the installation end faces of the electromagnetic valves are symmetrically and uniformly arranged.
The beneficial effects of the invention are as follows: the integrated block structure has the advantages that the function optimization and improvement design solves the problem of complex installation of the original structure, so that the production cost is reduced, the production efficiency is improved, the overall structure layout is more reasonable and concise, the attitude control unit assembly is more convenient and quick, and the mechanical property and the reliability of the product are improved. The novel integrated block, the electromagnetic valve, the thrust chamber and the connecting fastener jointly form the modularized liquid attitude control engine unit, and compared with the original structure, the novel attitude control engine unit has higher structural integrity, mechanical property and reliability, good maintainability, more convenient disassembly and assembly and more concise and attractive layout.
Drawings
Fig. 1 is an isometric view of an original four-position control unit.
Fig. 2 is a top view of the original four-gesture control unit.
Fig. 3 is an isometric view of an integrated circuit of the present invention.
Fig. 4 is an isometric view of a four-position control unit of the present invention.
The marks in the figure: the device comprises a 1-thrust bearing support, a 2-thrust chamber, a 3-adaptor, a 4-electromagnetic valve, a 5-integrated block, a 6-propellant inlet, a 7-electromagnetic valve installation end face, an 8-thrust chamber installation end face, a 9-thrust bearing support installation end face, a 10-propellant runner and 11-screws.
Detailed Description
The invention is further described with reference to the accompanying drawings 1-4, on the basis of the structural composition of the existing four-gesture control unit, the invention aims at the technical defects and problems of the existing four-gesture control unit, carries out integrated block structural improvement and functional innovation design, changes the independent and separate design structure of the original integrated block and the adapter, carries out integrated design on 8 adapters and the original integrated block, and replaces the structure and the function of the original adapter; the two-to-two positioning and mounting modes of the thrust chamber and the new integrated block and the bearing bracket and the new integrated block are realized.
The upper and lower bottom surfaces of the integrated block 5 are provided with propellant inlets 6 which are connected with propellant dry pipes. Four sides of the integrated block I, II, III, IV are symmetrically and uniformly distributed with electromagnetic valve installation end surfaces 7, four electromagnetic valves 4 are fixedly connected through screws 11, and an electromagnetic valve propellant inlet is communicated with a four-side propellant runner 10 of the integrated block.
The integrated block 5 is of an integral structure, the connecting structure is installed at the position, extending outwards, of the side face of the central body symmetrically between adjacent quadrants of the integrated block I, II, III, IV, of the 4 positions, extending outwards, of the connecting structure is of an integral polygonal symmetrical structure, the inside of the connecting structure is of a cavity design, reinforcing ribs are arranged in the cavity and connected with the central body of the integrated block, and structural strength is guaranteed; the outer side surface of the outwards extending installation connection structure is an installation end surface, wherein the installation end surface positioned in the middle is a unit bearing support installation end surface 9, the end surfaces positioned on two sides are thrust chamber installation end surfaces 8, and all the installation end surfaces are provided with smooth through holes and threaded through holes for screw connection installation. The thrust chamber 2 is fastened to the thrust chamber mounting end face 8 by screws 11, the thrust chamber propellant inlet is crimped with the solenoid valve propellant outlet and is radially sealed by an O-ring. The screw 11 is a socket head screw.
The four-attitude control liquid engine unit is composed of 1 integrated block 5, 4 electromagnetic valves 4 and 4 900N thrust chambers 2. The four thrust chambers 2 are symmetrically arranged, rated thrust is 900N, rated chamber pressure is 2.5MPa, and the envelope size phi 432 multiplied by 1121mm of the whole attitude control unit. The working principle of the double-component four-gesture control unit is as follows: the propellant management system controls the propellant to be extruded, flows through the trunk pipeline of the attitude control power system, flows in from the inlet of the integrated block 5 according to a certain proportion, flows through the cavity flow channel in the integrated block and then enters the electromagnetic valve 4. When the attitude control power system works, any one single electromagnetic valve 4 or two adjacent electromagnetic valves 4 can be opened according to the actual working condition, oxidant and fuel propellant in the integrated block 5 flow out through the flow passage outlet of the electromagnetic valve at the same time and enter the thrust chamber 2, the oxidant and the fuel react in the thrust chamber 2 in a chemical combustion mode, and generated high-temperature fuel gas is sprayed out after being accelerated by the spray pipe to form thrust required by the working condition, so that the attitude control and adjustment work is completed.
Claims (7)
1. The utility model provides a liquid attitude accuse engine integrated package which characterized in that: comprises an integrated block and an outwards extending installation connection structure; the integrated block is of an integrated structure, four sides of four quadrants of the integrated block I, II, III, IV are electromagnetic valve installation end faces, four electromagnetic valves are connected with the electromagnetic valve installation end faces through screws, an outwards extending installation connection structure is arranged between adjacent quadrants of the integrated block I, II, III, IV, the inside of the outwards extending installation connection structure is of a cavity structure, the outer sides of the outwards extending installation connection structure are installation end faces, the installation end faces comprise a central installation end face and two side installation end faces, the central installation end faces are force bearing support installation end faces, a force bearing support of an installation unit is arranged, the two side installation end faces are thrust chamber installation end faces, a thrust chamber is installed through screws, propellant inlets are formed in the upper bottom face and the lower bottom face of the integrated block, the propellant inlets are connected with propellant dry pipelines, and the electromagnetic valve propellant inlets are communicated with four side propellant channels of the integrated block, and a solenoid valve propellant outlet is in pressure connection with the propellant inlets of the thrust chamber.
2. The liquid-controlled engine manifold block of claim 1, wherein: the outward extending installation connection structure symmetrically extends outwards from the side surface of the central body.
3. The liquid-controlled engine manifold block of claim 1, wherein: the cavity structure is provided with a reinforcing rib, and the reinforcing rib is connected with the integrated block.
4. The liquid-controlled engine manifold block of claim 1, wherein: the central mounting end face and the two side mounting end faces are respectively provided with a smooth through hole and a threaded through hole for screw connection and mounting.
5. The liquid-controlled engine manifold block of claim 1, wherein: the outward extending installation connection structure is an integrated polygonal symmetrical structure.
6. The liquid-controlled engine manifold block of claim 1, wherein: the thrust chamber propellant inlet and the electromagnetic valve propellant outlet are radially sealed through an O-shaped rubber ring.
7. The liquid-controlled engine manifold block of claim 1, wherein: the electromagnetic valve installation end faces are symmetrically and uniformly arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010947359.5A CN112228250B (en) | 2020-09-10 | 2020-09-10 | Liquid attitude control engine integrated block |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010947359.5A CN112228250B (en) | 2020-09-10 | 2020-09-10 | Liquid attitude control engine integrated block |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112228250A CN112228250A (en) | 2021-01-15 |
| CN112228250B true CN112228250B (en) | 2023-06-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010947359.5A Active CN112228250B (en) | 2020-09-10 | 2020-09-10 | Liquid attitude control engine integrated block |
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| CN (1) | CN112228250B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113431707A (en) * | 2021-07-27 | 2021-09-24 | 北京宇航推进科技有限公司 | Single-component attitude control engine module and combination thereof |
| CN115339658B (en) * | 2022-08-15 | 2024-11-08 | 湖北航天技术研究院总体设计所 | Aircraft hydrodynamic system and liquid engine bracket assembly thereof |
| CN118242198B (en) * | 2024-04-09 | 2025-02-07 | 北京星河动力装备科技有限公司 | Rocket engines and launch vehicles |
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|---|---|---|---|---|
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| GB1439754A (en) * | 1972-09-29 | 1976-06-16 | Secr Defence | Hot gas thruster units |
| US4585191A (en) * | 1983-12-14 | 1986-04-29 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Propulsion apparatus and method using boil-off gas from a cryogenic liquid |
| US5279483A (en) * | 1990-12-21 | 1994-01-18 | Aerospatiale Societe Nationale Industrielle | Attitude control system for a three-axis stabilized satellite especially a remote sensing satellite |
| US5842665A (en) * | 1996-09-09 | 1998-12-01 | Hmx, Inc. | Launch vehicle with engine mounted on a rotor |
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| US9677504B2 (en) * | 2010-05-11 | 2017-06-13 | Orbital Atk, Inc. | Rockets, methods of rocket control and methods of rocket evaluation utilizing pressure compensation |
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2020
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| GB1439754A (en) * | 1972-09-29 | 1976-06-16 | Secr Defence | Hot gas thruster units |
| US4585191A (en) * | 1983-12-14 | 1986-04-29 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Propulsion apparatus and method using boil-off gas from a cryogenic liquid |
| US5279483A (en) * | 1990-12-21 | 1994-01-18 | Aerospatiale Societe Nationale Industrielle | Attitude control system for a three-axis stabilized satellite especially a remote sensing satellite |
| US5842665A (en) * | 1996-09-09 | 1998-12-01 | Hmx, Inc. | Launch vehicle with engine mounted on a rotor |
| CN106542082A (en) * | 2017-01-11 | 2017-03-29 | 中国科学院合肥物质科学研究院 | Module is received in a kind of exhibition of intelligent multiple-unit connection in series-parallel control |
| CN108895921A (en) * | 2018-07-03 | 2018-11-27 | 北京航空航天大学 | Hydrogen peroxide attitude control system for solid-liquid hybrid power carrier rocket |
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| CN109899566A (en) * | 2019-04-02 | 2019-06-18 | 沈阳航天新光集团有限公司 | A kind of pilot-operated type air-operated solenoid valve |
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| CN112228250A (en) | 2021-01-15 |
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