CN112780448A - Thrust adjusting mechanism of solid rocket engine - Google Patents
Thrust adjusting mechanism of solid rocket engine Download PDFInfo
- Publication number
- CN112780448A CN112780448A CN202110104852.5A CN202110104852A CN112780448A CN 112780448 A CN112780448 A CN 112780448A CN 202110104852 A CN202110104852 A CN 202110104852A CN 112780448 A CN112780448 A CN 112780448A
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- China
- Prior art keywords
- throat
- spray pipe
- rotating shaft
- driving motor
- engine
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
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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
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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
- F02K9/97—Rocket nozzles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a thrust adjusting mechanism of a solid rocket engine, which comprises a spray pipe shell, a spray pipe heat insulating layer, a driving motor, a support body, a throat insert, a throat plug, a composite rotating shaft and a transmission mechanism, wherein the spray pipe heat insulating layer is arranged on the spray pipe shell; the driving motor is arranged on the outer side of the equal straight section of the spray pipe shell and is connected with a throat plug inside the spray pipe shell through a composite rotating shaft arranged in the radial direction, and the throat plug is arranged on the axis of the engine through a support body; the inner wall of the spray pipe shell is provided with a spray pipe heat insulation layer; the throat liner is arranged on the inner side of the heat insulating layer of the spray pipe; the driving motor drives the composite rotating shaft to rotate, the transmission mechanism converts the rotation of the composite rotating shaft into axial movement of the throat bolt, the throat bolt moves towards the throat lining direction or away from the throat lining direction along the axis of the engine to change the throat area, and after the preset position is reached, the driving motor stops supplying power and is in a self-locking state. The invention can realize coaxial layout of the larynx bolt without influencing the charging design.
Description
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to a thrust adjusting mechanism of a solid rocket engine.
Background
The solid rocket engine has the advantages of simple structure, convenient maintenance, high reliability and simple and convenient operation, and is widely applied to missile power systems. But the controllability of the solid rocket engine is poorer compared with that of the liquid rocket engine. Therefore, the energy management technology of the solid rocket engine becomes a technical problem to be solved and broken through urgently in the industry, and is one of the important development directions of the solid rocket engine. The method realizes real-time effective control of the energy output of the engine in the working process of the solid rocket engine, realizes optimal distribution of the energy of the engine according to requirements, and has important significance for improving the energy utilization rate of the engine, increasing the range, and improving the maneuvering capability and the battlefield adaptability. The missile system is upgraded in a crossing manner.
Adjusting the laryngeal area through a laryngeal plug is currently one of the most studied and hottest gates. The throat plug type structure is generally divided into a coaxial type and a non-coaxial type. The non-coaxial engine has the combustion chamber axis vertical to the throat plug, so that the design is relatively easy, but the thrust direction is completely changed. And coaxial engine larynx bolt need go deep into from the head, and charge structure and seal structure are restricted, and larynx bolt length is overlength, and the thermal protection requirement is high, and the engine design degree of difficulty is great. Therefore, it becomes more critical to reduce the design difficulty of the whole device and reduce the influence on the engine structure without changing the thrust direction of the engine in a limited space.
Disclosure of Invention
In view of the above, the invention provides a thrust adjusting mechanism of a solid rocket engine, which can realize coaxial layout of throats without influencing charging design.
The technical scheme adopted by the invention is as follows:
a thrust adjusting mechanism of a solid rocket engine comprises a spray pipe shell, a spray pipe heat insulation layer, a driving motor, a support body, a throat liner, a throat plug, a composite rotating shaft and a transmission mechanism;
the driving motor is arranged on the outer side of the equal straight section of the spray pipe shell and is connected with a throat bolt in the spray pipe shell through a composite rotating shaft arranged in the radial direction, and the throat bolt is arranged on the axis of the engine through a support body; the inner wall of the spray pipe shell is provided with a spray pipe heat insulation layer; the throat liner is arranged on the inner side of the heat insulating layer of the spray pipe;
the driving motor drives the composite rotating shaft to rotate, the transmission mechanism converts the rotation of the composite rotating shaft into axial movement of the throat bolt, the throat bolt moves towards the throat lining direction or away from the throat lining direction along the axis of the engine to change the throat area, and after the preset position is reached, the driving motor stops supplying power and is in a self-locking state.
Furthermore, the composite rotating shaft consists of two sections, wherein the section connected with the driving motor is made of non-metallic materials, and the section connected with the transmission mechanism is made of refractory alloy.
Further, the matched part of the composite rotating shaft and the spray pipe shell adopts radial sealing.
Further, the support body is made of refractory alloy.
Further, the laryngeal plug is made of high-temperature refractory alloy.
Furthermore, the transmission mechanism comprises a gear and a rack, the gear is fixed on the composite rotating shaft, and the rack is fixed on the throat bolt.
Has the advantages that:
1. the invention adjusts the throat area of the engine by moving the throat bolt, further realizes real-time adjustment of the thrust of the engine, can realize stepless adjustment of the thrust in a section according to the required thrust range, can realize the correlation of engine energy management and missile missions, improves the maneuvering flexibility of the missile, and meets the multi-mission requirements. The outer side of the engine spray pipe is distributed, and the throat plug and the engine combustion chamber are coaxially distributed, so that the thrust direction of the engine is not influenced; through the mode of turning into larynx bolt axial removal with compound axis of rotation, avoid traditional coaxial-type larynx bolt to the restriction of engine powder charge design, both can realize larynx bolt coaxial layout and do not influence the powder charge design, but also reduced the larynx bolt design degree of difficulty.
2. The composite rotating shaft consists of two sections, and the section connected with the driving motor is made of a non-metal material, so that good heat insulation and sealing effects are ensured, and heat transfer of the rotating shaft close to the motor side is reduced; the section connected with the transmission mechanism is made of hard-to-fuse gold, so that the structural integrity of the rotating shaft is ensured, and the output torque is effectively transmitted to the laryngeal plug.
Drawings
FIG. 1 is a schematic structural view of the present invention;
the device comprises a nozzle shell 1, a nozzle heat-insulating layer 2, a driving motor 3, a support 4, a throat liner 5, a throat plug 6 and a composite rotating shaft 7.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a thrust adjusting mechanism of a solid rocket engine, which comprises a spray pipe shell 1, a spray pipe heat insulation layer 2, a driving motor 3, a support body 4, a throat liner 5, a throat bolt 6, a composite rotating shaft 7 and a transmission mechanism, wherein the spray pipe heat insulation layer 2 is arranged on the spray pipe shell.
The driving motor 3 is arranged on the outer side of the equal straight section of the spray pipe shell 1 and is connected with a throat bolt 6 inside the spray pipe shell 1 through a composite rotating shaft 7 which is radially arranged, and the matching part of the composite rotating shaft 7 and the spray pipe shell 1 adopts radial sealing. The throat plug 6 is arranged on the axis of the engine through the support body 4; the inner wall of the spray pipe shell 1 is provided with a spray pipe heat insulation layer 2, and the throat liner 5 is arranged on the inner side of the spray pipe heat insulation layer 2.
The driving motor 3 drives the composite rotating shaft 7 to rotate, the transmission mechanism converts the rotation of the composite rotating shaft 7 into axial motion of the throat bolt 6, the throat bolt 6 moves towards the throat lining 5 or away from the throat lining 5 along the axis of the engine to change the throat area, the working pressure of the combustion chamber is changed in real time, and the thrust of the engine is adjusted in real time. After reaching the predetermined position, the driving motor 3 stops supplying power and is in a self-locking state.
The side of the throat plug 6 facing the throat insert 5 is a head, and because a cavity formed between the tail of the throat plug 6 and the supporting body 4 is communicated with a combustion chamber in the moving process of the throat plug 6, the throat plug 6 can receive aerodynamic force pointing to the direction of the throat of the engine along the axial direction, the driving motor 3 has to have good self-locking performance.
The composite rotating shaft 7 consists of two sections, and the section connected with the driving motor 3 is made of a non-metal material, so that good heat insulation and sealing effects are ensured, and heat transfer of the rotating shaft close to the motor side is reduced; the section connected with the transmission mechanism is made of hard-to-fuse gold, so that the structural integrity of the rotating shaft is ensured, and the output torque is effectively transmitted to the laryngeal plug 6.
The supporting body 4 is used as an assembly cabin and a bearing conversion center of the core component of the whole driving mechanism and is made of refractory alloy. The larynx 6 adopts high-temperature refractory alloy to reduce the ablation of high-temperature high-pressure and high-flow-rate fuel gas to the larynx 6.
The transmission mechanism comprises a gear and a rack, the gear is fixed on the composite rotating shaft 7, and the rack is fixed on the throat bolt 6. The tooth-shaped structure meshed with the gear can also be directly processed on the throat bolt 6.
When the driving motor 3 receives the forward voltage signal, the driving motor 3 rotates forward, the driving motor 3 drives the composite rotating shaft 7 to rotate forward, the composite rotating shaft 7 rotates to drive the throat bolt 6 to move in the cavity of the supporting body 4 along the axis of the engine towards the direction of the throat liner 5, and after the preset position is reached, the driving motor 3 stops supplying power and is in a self-locking state. At the moment, the geometrical throat area formed by the throat plug 6 and the throat insert 5 is reduced due to the movement of the throat plug 6, the pressure of the engine combustion chamber is increased along with the reduction of the throat area, and the flow of the engine is increased, and the thrust is increased.
When the driving motor 3 receives a reverse voltage signal, the driving motor 3 rotates reversely, the driving motor 3 drives the composite rotating shaft 7 to rotate reversely, the composite rotating shaft 7 drives the throat bolt 6 to move in the cavity of the supporting body 4 along the axis of the engine to the direction far away from the throat liner 5, and after the preset position is reached, the driving motor 3 stops supplying power and is in a self-locking state. At this time, the geometrical throat area formed by the throat plug 6 and the throat insert 5 is increased by the movement of the throat plug 6, the combustion chamber pressure is decreased as the throat area is increased, and the engine flow rate is decreased and the thrust is decreased.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. A thrust adjusting mechanism of a solid rocket engine is characterized by comprising a spray pipe shell, a spray pipe heat insulation layer, a driving motor, a support body, a throat insert, a throat plug, a composite rotating shaft and a transmission mechanism;
the driving motor is arranged on the outer side of the equal straight section of the spray pipe shell and is connected with a throat bolt in the spray pipe shell through a composite rotating shaft arranged in the radial direction, and the throat bolt is arranged on the axis of the engine through a support body; the inner wall of the spray pipe shell is provided with a spray pipe heat insulation layer; the throat liner is arranged on the inner side of the heat insulating layer of the spray pipe;
the driving motor drives the composite rotating shaft to rotate, the transmission mechanism converts the rotation of the composite rotating shaft into axial movement of the throat bolt, the throat bolt moves towards the throat lining direction or away from the throat lining direction along the axis of the engine to change the throat area, and after the preset position is reached, the driving motor stops supplying power and is in a self-locking state.
2. The thrust adjustment mechanism for a solid rocket engine of claim 1 wherein said composite rotatable shaft is comprised of two sections, the section connected to said drive motor being a non-metallic material and the section connected to said drive mechanism being a refractory alloy.
3. The thrust adjustment mechanism for a solid rocket engine of claim 1 wherein radial seals are used where the composite rotary shaft engages the nozzle housing.
4. The thrust adjustment mechanism for a solid rocket engine of claim 1 wherein said support body is made of a refractory alloy.
5. The solid-rocket engine thrust adjustment mechanism of claim 1 wherein said throats are formed from a high temperature refractory alloy.
6. The thrust adjustment mechanism for a solid rocket engine of claim 1 wherein said gear mechanism comprises a gear and a rack, the gear being fixed to the composite rotatable shaft and the rack being fixed to the throats.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110104852.5A CN112780448A (en) | 2021-01-26 | 2021-01-26 | Thrust adjusting mechanism of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110104852.5A CN112780448A (en) | 2021-01-26 | 2021-01-26 | Thrust adjusting mechanism of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112780448A true CN112780448A (en) | 2021-05-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110104852.5A Pending CN112780448A (en) | 2021-01-26 | 2021-01-26 | Thrust adjusting mechanism of solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112780448A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113339157A (en) * | 2021-06-16 | 2021-09-03 | 西安交通大学 | Variable thrust's miniature solid rocket engine flexible nozzle system |
| CN115059559A (en) * | 2022-07-26 | 2022-09-16 | 哈尔滨工业大学 | Valve capable of accurately regulating thrust of solid rocket engine |
| CN115387934A (en) * | 2022-09-14 | 2022-11-25 | 北京中科宇航技术有限公司 | Solid rocket engine and throat adjusting device thereof |
| CN115711188A (en) * | 2022-11-21 | 2023-02-24 | 北京中科宇航技术有限公司 | Structure for improving sealing performance of bonding interface of integral die-pressing spray pipe |
| CN115726902A (en) * | 2022-11-21 | 2023-03-03 | 北京中科宇航技术有限公司 | Long-time working solid rocket engine and throat plug device thereof |
Citations (7)
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|---|---|---|---|---|
| US6986246B2 (en) * | 2002-05-21 | 2006-01-17 | Mitsubishi Heavy Industries, Ltd. | Side thruster valve and side thruster device |
| US20090211225A1 (en) * | 2007-01-29 | 2009-08-27 | Ghkn Engineering, Llc | Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles |
| US20160003195A1 (en) * | 2013-03-07 | 2016-01-07 | Herakles | Nozzle having a variable neck section for a spacecraft thruster provided with a mobile needle |
| CN105736179A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gas flow adjusting device of solid rocket ramjet |
| CN105736184A (en) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | Large thrust ratio, long-working micro-ablation throat insert and throat structure of expansion section |
| CN107503863A (en) * | 2017-09-06 | 2017-12-22 | 中国航空救生研究所 | A kind of nozzle thrust governor motion of solid propellant rocket |
| CN108087151A (en) * | 2016-11-22 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of electronic cone valve type Ducted rocket gas flow regulating device |
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2021
- 2021-01-26 CN CN202110104852.5A patent/CN112780448A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6986246B2 (en) * | 2002-05-21 | 2006-01-17 | Mitsubishi Heavy Industries, Ltd. | Side thruster valve and side thruster device |
| US20090211225A1 (en) * | 2007-01-29 | 2009-08-27 | Ghkn Engineering, Llc | Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles |
| US20160003195A1 (en) * | 2013-03-07 | 2016-01-07 | Herakles | Nozzle having a variable neck section for a spacecraft thruster provided with a mobile needle |
| CN105736184A (en) * | 2014-12-09 | 2016-07-06 | 上海新力动力设备研究所 | Large thrust ratio, long-working micro-ablation throat insert and throat structure of expansion section |
| CN105736179A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Gas flow adjusting device of solid rocket ramjet |
| CN108087151A (en) * | 2016-11-22 | 2018-05-29 | 江西洪都航空工业集团有限责任公司 | A kind of electronic cone valve type Ducted rocket gas flow regulating device |
| CN107503863A (en) * | 2017-09-06 | 2017-12-22 | 中国航空救生研究所 | A kind of nozzle thrust governor motion of solid propellant rocket |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113339157A (en) * | 2021-06-16 | 2021-09-03 | 西安交通大学 | Variable thrust's miniature solid rocket engine flexible nozzle system |
| CN115059559A (en) * | 2022-07-26 | 2022-09-16 | 哈尔滨工业大学 | Valve capable of accurately regulating thrust of solid rocket engine |
| CN115059559B (en) * | 2022-07-26 | 2024-05-24 | 哈尔滨工业大学 | Valve capable of accurately regulating and controlling thrust of solid rocket engine |
| CN115387934A (en) * | 2022-09-14 | 2022-11-25 | 北京中科宇航技术有限公司 | Solid rocket engine and throat adjusting device thereof |
| CN115387934B (en) * | 2022-09-14 | 2024-05-28 | 北京中科宇航技术有限公司 | Solid rocket engine and throat adjusting device thereof |
| CN115711188A (en) * | 2022-11-21 | 2023-02-24 | 北京中科宇航技术有限公司 | Structure for improving sealing performance of bonding interface of integral die-pressing spray pipe |
| CN115726902A (en) * | 2022-11-21 | 2023-03-03 | 北京中科宇航技术有限公司 | Long-time working solid rocket engine and throat plug device thereof |
| CN115726902B (en) * | 2022-11-21 | 2024-05-14 | 北京中科宇航技术有限公司 | Solid rocket engine working for long time and throat bolt device thereof |
| CN115711188B (en) * | 2022-11-21 | 2024-06-04 | 北京中科宇航技术有限公司 | Structure for improving sealing performance of bonding interface of integral molded spray pipe |
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Application publication date: 20210511 |
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