CN113339157A - Variable thrust's miniature solid rocket engine flexible nozzle system - Google Patents
Variable thrust's miniature solid rocket engine flexible nozzle system Download PDFInfo
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- CN113339157A CN113339157A CN202110668823.1A CN202110668823A CN113339157A CN 113339157 A CN113339157 A CN 113339157A CN 202110668823 A CN202110668823 A CN 202110668823A CN 113339157 A CN113339157 A CN 113339157A
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- Prior art keywords
- flexible
- rocket engine
- solid rocket
- flexible nozzle
- throat
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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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
- F02K9/974—Nozzle- linings; Ablative coatings
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
Abstract
The invention discloses a flexible nozzle system of a variable-thrust miniature solid rocket engine, and belongs to the technical field of aerospace power propulsion devices. The flexible jet nozzle comprises a displacement acquisition module, a control module, a flexible jet nozzle and a plurality of servo mechanisms arranged in the circumferential direction of the flexible jet nozzle; the two ends of the flexible jet throat are respectively and fixedly connected with the contraction section and the expansion section of the jet pipe, the servo mechanism comprises a servo motor, a transmission rod and a transmission piece, the servo motor is connected with the transmission rod, the transmission rod is connected with the transmission piece, and the transmission piece is attached to the outer wall of the flexible jet throat; the displacement acquisition module is used for acquiring displacement data of the diameter change of the flexible jet, the displacement acquisition module and the servo motor are respectively connected with the control module, and the control module is connected to the upper computer. The invention has simple and reliable structure, is suitable for the micro solid rocket engine, and greatly improves the response speed of thrust change. Meanwhile, the input and output signals are fed back in real time through the displacement acquisition module and the control module, and the control precision of the thrust is improved.
Description
Technical Field
The invention belongs to the technical field of aerospace power propulsion devices, and particularly relates to a micro solid rocket engine flexible nozzle system with variable thrust.
Background
Miniaturization and miniaturization are an important direction in the development of modern spacecraft and weaponry. The system is required to have the characteristics of quick response, high precision and high reliability in the aerospace field and equipment weapons, and the characteristics are directly related to the micro solid rocket engine system, so that higher requirements are provided for the solid rocket engine system.
The micro solid rocket engine is often used for weapon equipment propulsion systems, spacecraft attitude adjustment systems and the like due to the characteristics of high reliability, long preservation time, short preparation time and the like. But the combustion controllability is poor, the thrust of the conventional solid rocket engine is closely related to the grain, and the thrust cannot be adjusted and changed in real time in the combustion propulsion process. In the flight process of weapon equipment, thrust changes such as low-speed cruising and acceleration sudden-prevention are often needed, the spacecraft needs to accurately control the thrust of the engine to realize accurate attitude adjustment, and the conventional miniature solid rocket engine cannot meet the requirement.
At present, the thrust control of a solid rocket engine is mainly divided into engine grain design and throat plug type variable thrust design; the design of the engine grain mainly realizes thrust change in different combustion stages by pouring different combustion sections or propellants in different stages, but cannot realize thrust change under real-time flight conditions; the throat-plug type variable thrust design has long response time, serious ablation and complex device, and is not suitable for a micro solid rocket engine.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a flexible nozzle system of a variable-thrust micro solid rocket engine, which has a reliable structure and high response speed and can realize accurate control on thrust variation of the rocket engine.
The invention is realized by the following technical scheme:
the invention discloses a variable thrust flexible nozzle system of a miniature solid rocket engine, which comprises a displacement acquisition module, a control module, a flexible nozzle and a plurality of servo mechanisms arranged in the circumferential direction of the flexible nozzle;
the two ends of the flexible jet throat are respectively and fixedly connected with the contraction section and the expansion section of the jet pipe, the servo mechanism comprises a servo motor, a transmission rod and a transmission piece, the servo motor is connected with the transmission rod, the transmission rod is connected with the transmission piece, and the transmission piece is attached to the outer wall of the flexible jet throat; the displacement acquisition module is used for acquiring displacement data of the diameter change of the flexible jet, the displacement acquisition module and the servo motor are respectively connected with the control module, and the control module is connected to the upper computer.
Preferably, the flexible throat nozzle comprises a flexible substrate layer, a heat insulation layer and an ablative coating in sequence from outside to inside.
Further preferably, the flexible substrate layer is a flexible high-temperature-resistant material layer, the heat insulation layer is a low-thermal conductivity material layer, and the ablation coating is a high-temperature-resistant ablation material coating.
Preferably, the displacement acquisition module comprises a data processor and a plurality of displacement sensors connected with the data processor, and the displacement sensors are arranged on the outer wall of the flexible jet nozzle between the transmission pieces.
Further preferably, the number of displacement sensors is equal to the number of drive straps.
Preferably, the drive strap is arcuate.
Further preferably, the arc is equal to the outer wall of the flexible throat.
Preferably, the number of servomechanisms is ≧ 4.
Preferably, the servo mechanisms are uniformly distributed on the outer side of the flexible throat nozzle in the circumferential direction.
Preferably, the transmission rod and the transmission piece are made of high-strength and high-temperature-resistant materials.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention discloses a variable thrust micro solid rocket engine flexible nozzle system, wherein a flexible nozzle is arranged between a nozzle contraction section and a nozzle expansion section, and the diameter of the flexible nozzle is controlled by a plurality of servo mechanisms arranged on the periphery of the flexible nozzle. The servo motor of the servo mechanism drives the transmission piece to move through the transmission rod to extrude the outer wall of the flexible jet throat, and the structure is simple and reliable, and is suitable for a miniature solid rocket engine; the diameter change is controlled by directly transmitting the pressure to the flexible jet throat, so that the response speed of thrust change is greatly improved. Meanwhile, the input and output signals are fed back in real time through the displacement acquisition module and the control module, and the control precision of the thrust is improved.
Furthermore, the flexible jet nozzle sequentially comprises a flexible substrate layer, a heat insulation layer and an ablation coating from outside to inside, the Young modulus of the flexible substrate layer is low, and the elastic deformation process of the jet nozzle with variable diameter can be well realized; the heat insulation layer is used for absorbing the heat of high-temperature jet flow of the throat and preventing the flexible substrate layer from being failed due to overhigh temperature. The ablative coating acts to directly contact the jet, isolating other portions of the jet from contact with the jet, and reducing heat transfer from the jet to the jet by burning itself.
Furthermore, the flexible substrate layer is made of flexible high-temperature-resistant materials, such as high-temperature-resistant rubber, expanded graphite and the like, and has the advantages that the flexible materials are easy to deform under the action of the transmission mechanism, and meanwhile, the transmission precision is high, and the failure condition cannot occur at the higher temperature of the engine jet throat. The heat insulating layer is made of low-heat-conductivity materials, such as high-silica glass fiber, asbestos and the like, and has the advantages that the high-temperature materials of the spray pipe and the flexible high-temperature-resistant materials can be separated, and heat transfer is reduced. The ablation coating adopts high-temperature-resistant ablation coating, such as a silicon carbide coating and a C/C composite material coating, and has the advantage that the ablation coating dissipates external heat energy by using a certain mass of material, so that the heat transfer from the outside to the body of the object is reduced.
Further, a plurality of displacement sensors of the displacement acquisition module are arranged on the outer wall of the flexible throat spray between the transmission pieces, so that displacement data can be acquired at multiple points, feedback is more accurate, and meanwhile work of the transmission pieces is not affected.
Furthermore, the number of the displacement sensors is equal to that of the transmission pieces, so that the displacement change of the action position of each transmission piece can be accurately monitored, and the control accuracy is improved.
Further, the driving strap is arc-shaped, the radian is equal to the outer wall of the flexible throat sprayer, the outer wall of the flexible throat sprayer can be better attached, and acting force is uniform.
Furthermore, the number of the servo mechanisms is more than or equal to 4, the servo mechanisms are circumferentially and uniformly distributed on the outer side of the flexible jet throat, the number of the servo mechanisms can be reasonably selected according to the size of the jet throat of the engine, and the diameter of the flexible jet throat can be more uniformly and accurately adjusted.
Drawings
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is a schematic top cross-sectional view of the present invention;
fig. 3 is a schematic diagram of the working principle of the present invention.
In the figure: 100-servo mechanism, 110-servo motor, 121-transmission rod, 122-transmission piece, 200-flexible jet nozzle, 210-flexible substrate layer, 220-thermal insulation layer, 230-ablation coating, 300-displacement acquisition module, 310-displacement sensor, 320-data processor and 400-control module.
Detailed Description
The present invention will now be described in further detail with reference to the accompanying drawings, which are included to illustrate and not to limit the invention:
the invention relates to a flexible nozzle system of a variable thrust micro solid rocket engine, which comprises a displacement acquisition module 300, a control module 400, a flexible nozzle 200 and a plurality of servo mechanisms 100 arranged in the circumferential direction of the flexible nozzle 200;
the two ends of the flexible jet throat 200 are respectively and fixedly connected with the contraction section and the expansion section of the jet pipe, the servo mechanism 100 comprises a servo motor 110, a transmission rod 121 and a transmission piece 122, the servo motor 110 is connected with the transmission rod 121, the transmission rod 121 is connected with the transmission piece 122, and the transmission piece 122 is attached to the outer wall of the flexible jet throat 200; the displacement acquisition module 300 is used for acquiring displacement data of the diameter change of the flexible jet nozzle 200, the displacement acquisition module 300 and the servo motor 110 are respectively connected with the control module 400, and the control module is connected to an upper computer.
In a preferred embodiment of the present invention, the flexible throat 200 comprises, in order from the outside to the inside, a flexible substrate layer 210, a thermal barrier layer 220, and an ablative coating 230. Preferably, flexible base layer 210 is a flexible expanded graphite layer, thermal barrier layer 220 is a high silica glass fiber layer, and ablative coating 230 is a silicon carbide coating.
In a preferred embodiment of the present invention, the displacement acquisition module 300 comprises a data processor 320 and a plurality of displacement sensors 310 connected to the data processor 320, wherein the plurality of displacement sensors 310 are disposed on the outer wall of the flexible throat 200 between the driving straps 122. Preferably, the number of displacement sensors 310 is equal to the number of drive straps 122.
In a preferred embodiment of the present invention, the driver blade 122 is arcuate in shape with an arc equal to the outer wall of the flexible throat 200.
In a preferred embodiment of the present invention, the number of servo mechanisms 100 is greater than or equal to 4, and the servo mechanisms are circumferentially and uniformly distributed outside the flexible throat 200.
The variable thrust micro solid rocket engine flexible nozzle system of the present invention is further illustrated in an embodiment as follows:
as shown in fig. 1, the present embodiment includes a servo mechanism 100, a flexible throat nozzle 200, a displacement acquisition module 300, and a control module 400; the servo mechanism 100 includes a servo motor 110 and a transmission device; the transmission device comprises a transmission rod 121 and a transmission sheet 122; the flexible jet 200 comprises a flexible substrate layer 210, a thermal barrier layer 220, and an ablative coating 230; the displacement acquisition module 300 comprises a displacement sensor 310 and a data processor 320; the servo motors 110 are fixedly connected with the engine jet pipe, and 8 servo motors are evenly arranged along the circumferential direction of the engine jet pipe; the transmission rod 121 is connected with the servo motor 110, the direction points to the center of the section circle of the flexible throat 200, 8 transmission rods are evenly arranged along the circumferential direction of the engine throat, and the length of the transmission rod 121 can be controlled by the servo motor 110; the transmission piece 122 is fixedly connected with the transmission rod 121 and the outer wall of the flexible substrate layer 210, the shape of the transmission piece is attached to the outer wall of the flexible substrate layer 210, and 8 transmission pieces are evenly arranged along the circumferential direction of the engine throat spray; the displacement sensors 310 are fixedly connected with the flexible substrate layer 210, distributed among the transmission pieces 122 and evenly distributed in 8 along the circumferential direction of the engine throat; the data processor 320 is fixedly connected with the servo motor 110, is arranged outside the servo motor 110 and is provided with 1 data processor; the control module 400 is fixedly connected with the servo motor 110 and the engine spray pipe, is arranged at the lower part of the servo motor 110, is averagely arranged by 8 along the circumferential direction of the engine spray throat and synchronizes data with the displacement acquisition module 300; the servo mechanism 100 receives a set thrust change control signal sent by the control module 400 to control the diameter change of the flexible throat 200, the displacement acquisition module 300 acquires and feeds back the displacement data of the flexible throat 200 and synchronously outputs the feedback signal to the control module 400, so that the accurate control of the diameter change of the throat of the rocket engine is achieved, and the purpose of controlling the thrust change of the rocket engine is achieved.
As shown in FIG. 2, the flexible throat 200 is fixedly connected to the contraction and expansion section of the nozzle, the flexible substrate layer 210 is made of flexible expanded graphite material, the thermal insulation layer 220 is made of high silica glass fiber, and the ablative coating 230 is made of silicon carbide coating. The displacement sensors 310 are fixedly connected with the flexible substrate layer 210, are distributed among the transmission plates, and are evenly distributed in the circumferential direction of the engine throat, so that the deformation of the flexible throat is monitored in real time; the data processor 320 is fixedly connected with the servo motor, is arranged outside the servo motor, and is totally 1, so as to receive the displacement sensor signal, process the displacement sensor signal and output the processed displacement sensor signal to the control module 400.
As shown in fig. 3, the control module 400 writes a control output signal before the engine works, or receives a signal sent from the ground during the engine works, and inputs a control signal to the servo motor 110 to perform real-time thrust control. The servo motor 110 is feedback-regulated by the signal of the synchronous displacement acquisition module 300, so that high-precision thrust control is realized.
The above description is only a part of the embodiments of the present invention, and although some terms are used in the present invention, the possibility of using other terms is not excluded. These terms are used merely for convenience in describing and explaining the nature of the invention and are to be construed as any additional limitation which is not in accordance with the spirit of the invention. The foregoing is merely an illustration of the present invention for the purpose of providing an easy understanding and is not intended to limit the present invention to the particular embodiments disclosed herein, and any technical extensions or innovations made herein are protected by the present invention.
Claims (10)
1. A variable thrust micro solid rocket engine flexible nozzle system is characterized by comprising a displacement acquisition module (300), a control module (400), a flexible nozzle (200) and a plurality of servo mechanisms (100) arranged in the circumferential direction of the flexible nozzle (200);
two ends of the flexible jet throat (200) are respectively and fixedly connected with the nozzle contraction section and the nozzle expansion section, the servo mechanism (100) comprises a servo motor (110), a transmission rod (121) and a transmission sheet (122), the servo motor (110) is connected with the transmission rod (121), the transmission rod (121) is connected with the transmission sheet (122), and the transmission sheet (122) is attached to the outer wall of the flexible jet throat (200); the displacement acquisition module (300) is used for acquiring displacement data of diameter change of the flexible jet nozzle (200), the displacement acquisition module (300) and the servo motor (110) are respectively connected with the control module (400), and the control module is connected to an upper computer.
2. The variable thrust micro solid rocket engine flexible nozzle system according to claim 1 wherein the flexible nozzle throat (200) comprises, in order from outside to inside, a flexible substrate layer (210), a thermal insulation layer (220), and an ablative coating (230).
3. The variable thrust micro solid rocket engine flexible nozzle system according to claim 2 wherein the flexible substrate layer (210) is a flexible high temperature resistant material layer, the thermal insulation layer (220) is a low thermal conductivity material layer, and the ablative coating (230) is a high temperature ablative material coating.
4. The flexible nozzle system of a variable thrust micro solid rocket engine according to claim 1, wherein the displacement acquisition module (300) comprises a data processor (320) and a plurality of displacement sensors (310) connected to the data processor (320), the plurality of displacement sensors (310) being disposed on the outer wall of the flexible nozzle (200) between the straps (122).
5. The variable thrust micro solid rocket engine flexible nozzle system according to claim 4 wherein the number of displacement sensors (310) is equal to the number of flights (122).
6. The variable thrust micro solid rocket engine flexible nozzle system according to claim 1 wherein the flight (122) is arcuate.
7. The variable thrust micro solid rocket engine flexible nozzle system according to claim 6 wherein the arc is equal to the outer wall of the flexible nozzle throat (200).
8. The variable thrust micro solid rocket engine flexible nozzle system according to claim 1, wherein the number of servomechanisms (100) is greater than or equal to 4.
9. The variable thrust micro solid rocket engine flexible nozzle system according to claim 1, wherein the servomechanisms (100) are circumferentially and evenly distributed outside the flexible nozzle throat (200).
10. The variable thrust micro solid rocket engine flexible nozzle system according to claim 1, wherein the driving rod (121) and the driving strap (122) are made of high strength and high temperature resistant material.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110668823.1A CN113339157B (en) | 2021-06-16 | 2021-06-16 | Variable thrust's miniature solid rocket engine flexible nozzle system |
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| CN202110668823.1A CN113339157B (en) | 2021-06-16 | 2021-06-16 | Variable thrust's miniature solid rocket engine flexible nozzle system |
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| CN113339157A true CN113339157A (en) | 2021-09-03 |
| CN113339157B CN113339157B (en) | 2022-07-12 |
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| WO2018004803A1 (en) * | 2016-06-27 | 2018-01-04 | Aerojet Rocketdyne, Inc. | Temperature compensating nozzle |
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| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN112253337A (en) * | 2020-10-20 | 2021-01-22 | 北京航空航天大学 | Flexible spray pipe based on fluid-solid coupling |
| CN112539116A (en) * | 2020-11-12 | 2021-03-23 | 西安长峰机电研究所 | Variable throat diameter and variable expansion ratio spray pipe structure |
| CN112780448A (en) * | 2021-01-26 | 2021-05-11 | 北京灵动飞天动力科技有限公司 | Thrust adjusting mechanism of solid rocket engine |
| US20210147099A1 (en) * | 2017-06-08 | 2021-05-20 | Avio S.P.A. | Attitude control and thrust boosting system and method for space launchers |
| CN213360272U (en) * | 2020-10-10 | 2021-06-04 | 江西洪都航空工业集团有限责任公司 | Pneumatic type spray pipe throat diameter adjusting device |
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2021
- 2021-06-16 CN CN202110668823.1A patent/CN113339157B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB941620A (en) * | 1960-11-23 | 1963-11-13 | Thiokol Chemical Corp | Steering device for rocket powered vehicles |
| JP2004324607A (en) * | 2003-04-28 | 2004-11-18 | Ihi Aerospace Co Ltd | Gas distributing device |
| CN104454241A (en) * | 2014-11-27 | 2015-03-25 | 江西洪都航空工业集团有限责任公司 | Engine jet pipe with throat diameter adjustable |
| WO2018004803A1 (en) * | 2016-06-27 | 2018-01-04 | Aerojet Rocketdyne, Inc. | Temperature compensating nozzle |
| US20210147099A1 (en) * | 2017-06-08 | 2021-05-20 | Avio S.P.A. | Attitude control and thrust boosting system and method for space launchers |
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| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
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| CN112253337A (en) * | 2020-10-20 | 2021-01-22 | 北京航空航天大学 | Flexible spray pipe based on fluid-solid coupling |
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