CN109184955B - Nested structure of double-combustion-chamber gas generator - Google Patents
Nested structure of double-combustion-chamber gas generator Download PDFInfo
- Publication number
- CN109184955B CN109184955B CN201811086241.7A CN201811086241A CN109184955B CN 109184955 B CN109184955 B CN 109184955B CN 201811086241 A CN201811086241 A CN 201811086241A CN 109184955 B CN109184955 B CN 109184955B
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- combustion chamber
- end socket
- rail
- sealing
- attitude
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/343—Joints, connections, seals therefor
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- 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)
- Portable Nailing Machines And Staplers (AREA)
Abstract
The invention relates to a nested structure of a double-combustion-chamber gas generator for a solid attitude and orbit control engine, which mainly comprises an end socket, an end socket inner heat insulation layer, an end socket outer heat insulation layer, a sealing ring and a positioning pin, wherein the nested structure mainly selects two large-diameter combustion chambers and one small-diameter combustion chambers, the end socket inner contour structure is connected with the small-diameter combustion chambers, and the end socket inner contour structure is fixed in the large-diameter combustion chambers through an outer contour structure. The gas generator nested structure can solve the problem of mass center drift of a small-sized double-combustion-chamber solid engine. The connection mode of the end socket, the attitude control combustion chamber and the rail control combustion chamber can be selected from but not limited to threaded connection, claw connection, pin connection, clamping key connection and the like. The invention relies on mature structure calculation to realize compact structure of the small-sized double-combustion-chamber gas generator, simple control of the interface and the reference, small mass center drift, contribution to overall control and design cost saving.
Description
Technical Field
The invention relates to a nested structure, in particular to a nested structure of a double-combustion-chamber gas generator for a small solid attitude control engine.
Background
The attitude and orbit control engine is used as a key part of the execution part of the direct force control of the missile, and directly influences the maneuvering capability and the control precision of the missile. The solid attitude and orbit control engine has the characteristics of simple structure, safety, reliability, easiness in storage, no maintenance and the like, and is suitable for weapons with higher requirements on safety, such as air bases, sea bases and the like.
The attitude and orbit control engine is generally composed of an attitude control system and an orbit control system, wherein the attitude control engine is arranged at the tail part of the power system to control the attitude, namely the control of a pitching channel, a yawing channel and a rolling channel, so that the detector can quickly and stably aim at a target; the rail control engine is arranged on a mass center plane and provides high transverse acceleration for the power system, so that the power system has transverse quick maneuvering flight capability.
Because the attitude control system and the rail control system work in a relatively independent mode, an independent attitude control combustion chamber and an independent rail control combustion chamber are mostly adopted in the design of the existing attitude and rail control engine. Although the structure is simple, the overall system size is large, the connection structure between the two is also needed to be considered, the connection interface is complex, the benchmark is not easy to control, and the weight and the design cost of the additional engine are increased.
Disclosure of Invention
The invention aims to provide a nested structure of a double-combustion-chamber gas generator, which solves the problem that the mass center of the attitude and orbit control engine seriously drifts in the working process. The gas generator mainly changes the structural form of a combustion chamber, and utilizes a nested structure to realize the compactness of the overall system and reduce the weight.
The technical scheme adopted by the invention is as follows: a
A nested configuration of a dual combustion chamber gas generator, comprising: the sealing head, an inner heat insulation layer of the sealing head, an outer heat insulation layer of the sealing head, a sealing ring and a positioning pin;
the end enclosure is used for connecting the attitude control combustion chamber and the rail control combustion chamber and embedding the attitude control combustion chamber into the rail control combustion chamber;
the end socket is bonded with the inner heat insulation layer of the end socket and the outer heat insulation layer of the end socket;
the sealing ring is used for sealing high-temperature fuel gas generated by the operation of the attitude control combustion chamber and the rail control combustion chamber;
the positioning pin is used for fixing the relative position of the seal head and the rail-controlled combustion chamber;
processing an internal thread and a sealing surface on the inner side of the end socket, processing an external thread on the outer side of the attitude control combustion chamber, processing a sealing groove at the root of the thread to place a corresponding attitude control sealing ring, and sealing the attitude control combustion chamber by the attitude control sealing ring after the attitude control combustion chamber and the attitude control combustion chamber are screwed down by the thread;
a clamping jaw bulge structure is arranged on the outer side of the end socket, and a sealing groove is machined below the clamping jaw bulge structure to place an orbit control sealing ring;
the end face of the rail-controlled combustion chamber is provided with corresponding jaw grooves and sealing faces, after the end socket and the attitude-controlled combustion chamber are assembled, the jaw bulge structures of the end socket are aligned with the jaw grooves of the rail-controlled combustion chamber, the end socket and the attitude-controlled combustion chamber are pressed tightly through a tool until the rail-controlled sealing rings are completely pressed into the corresponding sealing grooves, the end socket is rotated under the condition that the position of the rail-controlled combustion chamber is unchanged, until the positioning holes in the jaw bulge structures are superposed with the positioning holes in the rail-controlled combustion chamber, the positioning pins are placed into the rail-controlled combustion chamber to position the jaw bulge structures, and the end socket jaw bulge structures are prevented.
Compared with the prior art, the invention has the following remarkable advantages:
the invention enables the attitude control combustion chamber to be nested in the rail control combustion chamber, and the size of the gas generator is mainly determined by the appearance structure of the rail control combustion chamber. The structure can effectively reduce the length of the attitude and orbit control engine, so that the structure is more compact, and the space of the engine is saved. The rail-controlled combustion chamber is connected with the end socket through the clamping claws, so that the structure is simpler, and the overall reference control of the attitude and rail control engine is more facilitated. The embedded structure of the double-combustion-chamber gas generator can effectively avoid the mass center of the overall structure from drifting in the process, and is more beneficial to the overall control of the attitude and orbit control engine.
Drawings
FIG. 1 is a schematic view of a gasifier according to an embodiment of the present invention;
fig. 2 is a schematic view of a claw structure according to an embodiment of the present invention.
Detailed Description
Fig. 1 is a schematic view of a gas generator according to an embodiment of the present invention, in which 1 is a head with a jaw structure, 2 is an inner heat insulating layer of the head, 3 is an outer heat insulating layer of the head, 4 is a posture control seal ring, 5 is a posture control combustion chamber, 6 is a rail control combustion chamber, 7 is a rail control seal ring, and 8 is a positioning pin. Firstly, an inner heat insulation layer 2 of the end socket is used for isolating the influence of high-temperature gas generated by the operation of the attitude control combustion chamber on the end socket; the outer heat insulation layer 3 of the end socket is used for isolating the influence of high-temperature gas generated by the operation of the rail-controlled combustion chamber on the end socket; the end socket 1 with the clamping claw structure is bonded with an inner heat insulation layer 2 of the end socket and an outer heat insulation layer 3 of the end socket, and then the end socket is connected with an attitude control combustion chamber 5, the connection mode can be a threaded connection mode, and the end socket and the attitude control combustion chamber are sealed through an attitude control sealing ring 4.
Secondly, the seal head 1 with the clamping jaw structure is connected with the rail-controlled combustion chamber 6, the clamping jaw connection mode can be selected, and the seal head and the rail-controlled combustion chamber are sealed through a rail-controlled seal ring 7.
And finally, maintaining the position of the rail-controlled combustion chamber 6 unchanged, rotating the end socket 1 with the jaw structure until the positioning holes of the end socket and the rail-controlled combustion chamber coincide, and fixing the relative position of the end socket 1 with the jaw structure and the rail-controlled combustion chamber through the positioning pin 8. So far, the installation of the nested structure double-combustion-chamber gas generator is completed, the attitude control combustion chamber 5 and the rail control combustion chamber 6 are independently ignited to start working, and the working time length, the working pressure and the ignition sequence of the two combustion chambers can be determined according to the overall requirements.
Fig. 2 is a schematic diagram of a jaw structure, and the schematic diagrams (a) and (b) are structures of six jaws, and the nesting structure in the invention is not limited to the structure. According to the design requirements of the attitude and orbit control engine, different structural forms, processing materials and geometric parameters can be selected to adapt to different working pressures.
Claims (1)
1. A nested configuration of a dual combustion chamber gas generator, comprising: the sealing head, an inner heat insulation layer of the sealing head, an outer heat insulation layer of the sealing head, a sealing ring and a positioning pin;
the end enclosure is used for connecting the attitude control combustion chamber and the rail control combustion chamber and embedding the attitude control combustion chamber into the rail control combustion chamber;
the end socket is bonded with the inner heat insulation layer of the end socket and the outer heat insulation layer of the end socket;
the sealing ring is used for sealing high-temperature fuel gas generated by the operation of the attitude control combustion chamber and the rail control combustion chamber;
the positioning pin is used for fixing the relative position of the seal head and the rail-controlled combustion chamber;
processing an internal thread and a sealing surface on the inner side of the end socket, processing an external thread on the outer side of the attitude control combustion chamber, processing a sealing groove at the root of the thread to place a corresponding attitude control sealing ring, and sealing the attitude control combustion chamber by the attitude control sealing ring after the attitude control combustion chamber and the attitude control combustion chamber are screwed down by the thread;
a clamping jaw bulge structure is arranged on the outer side of the end socket, and a sealing groove is machined below the clamping jaw bulge structure to place an orbit control sealing ring;
the end face of the rail-controlled combustion chamber is provided with corresponding jaw grooves and sealing faces, after the end socket and the attitude-controlled combustion chamber are assembled, the jaw bulge structures of the end socket are aligned with the jaw grooves of the rail-controlled combustion chamber, the end socket and the attitude-controlled combustion chamber are pressed tightly through a tool until the rail-controlled sealing rings are completely pressed into the corresponding sealing grooves, the end socket is rotated under the condition that the position of the rail-controlled combustion chamber is unchanged, until the positioning holes in the jaw bulge structures are superposed with the positioning holes in the rail-controlled combustion chamber, the positioning pins are placed into the rail-controlled combustion chamber to position the jaw bulge structures, and the end socket jaw bulge structures are prevented.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811086241.7A CN109184955B (en) | 2018-09-18 | 2018-09-18 | Nested structure of double-combustion-chamber gas generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811086241.7A CN109184955B (en) | 2018-09-18 | 2018-09-18 | Nested structure of double-combustion-chamber gas generator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109184955A CN109184955A (en) | 2019-01-11 |
| CN109184955B true CN109184955B (en) | 2020-06-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811086241.7A Active CN109184955B (en) | 2018-09-18 | 2018-09-18 | Nested structure of double-combustion-chamber gas generator |
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| CN (1) | CN109184955B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115523058A (en) * | 2022-09-30 | 2022-12-27 | 北京航空航天大学 | Buckle formula solid-liquid rocket engine catalysis bed heat insulation structure |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203925780U (en) * | 2014-07-02 | 2014-11-05 | 中国航天科工集团第六研究院四十一所 | A kind of check ring joint structure of solid propellant rocket |
| RU2581516C1 (en) * | 2015-03-11 | 2016-04-20 | Публичное акционерное общество Научно-производственное объединение "Искра" | Method of forming inner thermal protective coating of rocket engine housing |
| CN106194502B (en) * | 2016-07-15 | 2018-03-02 | 北京航空航天大学 | A kind of solid-liquid Attitude rocket engine |
| CN206140787U (en) * | 2016-11-03 | 2017-05-03 | 湖北航天化学技术研究所 | Reverse nested double combustion chamber structure engine heat insulation layer forming device of single casing |
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2018
- 2018-09-18 CN CN201811086241.7A patent/CN109184955B/en active Active
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| CN109184955A (en) | 2019-01-11 |
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