CN112761823A - Expansion section lateral drainage thrust vector control spray pipe - Google Patents
Expansion section lateral drainage thrust vector control spray pipe Download PDFInfo
- Publication number
- CN112761823A CN112761823A CN202011509100.9A CN202011509100A CN112761823A CN 112761823 A CN112761823 A CN 112761823A CN 202011509100 A CN202011509100 A CN 202011509100A CN 112761823 A CN112761823 A CN 112761823A
- Authority
- CN
- China
- Prior art keywords
- drainage
- guide rod
- spray pipe
- nozzle
- drainage channel
- Prior art date
- 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.)
- Granted
Links
Images
Classifications
-
- 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
-
- 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
Abstract
The invention relates to a thrust vector control spray pipe for lateral drainage of an expansion section. The gas drainage hole is formed in the expansion section of the spray pipe body, the inside of the gas drainage hole is embedded in the drainage pipe, and a second guide rod through hole is formed in the drainage pipe and perpendicular to the second drainage channel. The expansion section of the spray pipe body is provided with a guide rod channel. The position of the flow guide rod is controlled to plug or open the flow guide channel, and when the fuel gas in the spray pipe is sprayed out from the flow guide channel, a reverse control moment is generated. A plurality of thrust vector control devices can be symmetrically arranged on the spray pipe, and each thrust vector control device can be opened and closed for multiple times; thrust vector control may be achieved when opening one or more of the drainage channels individually or asymmetrically. When a plurality of drainage channels are symmetrically opened, the lateral forces in all directions are mutually offset, lateral moment is not generated, and the axial thrust of the engine can be reduced.
Description
Technical Field
The invention belongs to the technical field of rocket engines, and particularly relates to a thrust vector control structure of a rocket engine nozzle.
Background
With the deep development of military and civil integration, rocket technology plays an increasingly important role in the field of meteorological detection, a meteorological detection rocket usually takes a solid rocket engine as a power device, a thrust vector control spray pipe of the rocket engine is an important component of an aircraft control system which adopts the rocket engine as the power device, and the thrust vector control spray pipe mainly completes three tasks: firstly, a certain lateral force is provided according to a preset program, so that the aircraft flies according to a preset track; secondly, providing a certain lateral force to correct the attitude when the attitude or the stability of the aircraft is disturbed; and thirdly, changing the flight orbit according to the instruction.
The thrust vector control technology of the rocket engine commonly used at present comprises a gas rudder technology, a swinging spray pipe technology and a secondary flow turbulent flow control technology. The gas rudder technology brings about larger total thrust loss of the engine, and the swinging spray pipe technology and the secondary flow technology bring about larger structural complexity. The application provides a thrust vector control spray pipe technology for lateral drainage of an expansion section, which can realize control of the thrust of a rocket engine and a scheme.
Disclosure of Invention
The invention aims to provide a thrust vector control structure of a rocket engine nozzle, wherein when the rocket engine works, fuel gas generated by propellant combustion is sprayed out of the nozzle to generate axial reaction thrust, and when a thrust vector control device starts to work, lateral thrust is generated to realize thrust vector control.
The rocket engine jet pipe is usually a Laval jet pipe, the thrust vector control jet pipe mainly comprises a jet pipe main body structure and a thrust vector control device, the jet pipe main body structure comprises a jet pipe body, a convergent section heat insulation layer, a back lining, a throat liner and an expansion section heat insulation layer, and the thrust vector control system mainly comprises a control system, a driving motor, a driving rod, a guide rod and a drainage tube.
The nozzle body is made of high-strength steel, one end of the nozzle body is provided with a flange connection interface connected with an engine combustion chamber, the nozzle convergence section is made of carbon fiber/phenolic aldehyde and high silica/phenolic aldehyde composite die pressing materials for heat insulation, the throat liner is made of C/C composite materials, the back lining is made of high silica/phenolic aldehyde materials, and the nozzle expansion section is made of carbon fiber/phenolic aldehyde and high silica/phenolic aldehyde composite die pressing materials for heat insulation. The heat-insulating rear end of the convergent section limits the front end face of the throat insert to prevent the throat insert from moving towards the inlet of the nozzle. The front end face of the expansion section limits the rear end face of the throat insert and prevents the throat insert from moving towards the outlet direction of the spray pipe.
The gas drainage hole has been designed on the spray tube body expansion section, and the inside drainage tube that has scarf jointed in gas drainage hole, the external diameter of drainage tube equals the internal diameter in gas drainage hole, and the drainage tube adopts refractory metals such as tungsten copper infiltration, molybdenum alloy to process the shaping, and the drainage tube bonds on gas drainage hole and with the gas drainage hole laminating sealed well. And a second guide rod through hole is vertically formed in the drainage tube and the second drainage channel. The expansion section of the spray pipe body is provided with a first guide rod through hole, and the first guide rod through hole and the second guide rod through hole are completely overlapped to form a guide rod channel together.
The guide rod channel is vertically intersected with the drainage channel, the drainage channel is composed of a first drainage channel, a second drainage channel and a third drainage channel, the first drainage channel, the second drainage channel and the third drainage channel are arranged on the expansion section in a heat insulation mode, the diameters of the first drainage channel, the second drainage channel and the third drainage channel are equal, and the drainage channel is perpendicular to the axis direction of the spray pipe. The diameter of the guide rod is smaller than the outer diameter of the drainage tube, and the thermal protection of the drainage tube to the spray pipe body is facilitated when fuel gas passes through the drainage channel. The diameter of the guide rod is larger than the inner diameter of the drainage tube, and the sealing performance of the drainage channel to the channel is improved when the drainage channel is in a closed state.
The guide rod is connected with the guide rod channel in a sliding fit mode, and the guide rod is made of refractory metals such as tungsten copper infiltration and molybdenum alloy. The diversion rod is rigidly connected with the driving rod, the movement of the driving rod is controlled by the control system and the driving motor, and the diversion rod is driven to axially move in the horizontal direction without rotating.
The nozzle body throat position has set up control system and driving motor's mount pad, has designed spacing step on the mount pad, and control system and driving motor can not lead to the fact the influence with nozzle body surface direct contact when installing at the mount pad, avoid nozzle body surface high temperature to control system and driving motor's performance.
The spray tube work initial stage water conservancy diversion pole removes to the right-hand member, and third drainage channel misplaces completely with first drainage channel, second drainage channel this moment, and the water conservancy diversion pole carries out the shutoff to third drainage channel, and the gas that flows in the spray tube this moment can't follow the blowout of drainage channel, consequently does not produce the lateral control power.
When the control system gives a lateral force control instruction, the control system and the driving motor drive the guide rod to move to the leftmost end, the third drainage channel is completely overlapped with the first drainage channel and the second drainage channel at the moment, the drainage channels are communicated, high-temperature and high-pressure fuel gas in the jet pipe is sprayed out from the drainage channels to generate a reaction lateral control moment, partial flow is sprayed out laterally to reduce the axial flow, and therefore the axial thrust of the jet pipe is reduced.
In order to realize the thrust vector control of more nimble spray tube, can set up N (2 ~ 24 for N) on the spray tube symmetry, a plurality of thrust vector controlling means promptly, every thrust vector controlling means all can open and shut many times, can obtain different control moment through controlling single or a plurality of guide rod.
The invention has the following characteristics:
1) the thrust vector control spray pipe is composed of a spray pipe main body structure and a thrust vector control system. The main structure of the nozzle consists of a nozzle body, a convergent section heat insulation, a throat liner, a back lining and an expansion section heat insulation. The thrust vector control system consists of a control system, a driving motor, a driving rod, a guide rod, a drainage tube and the like.
2) The drainage tube is perpendicular to the guide rod, the guide rod penetrates through the drainage tube, the diameter of the guide rod is smaller than the outer diameter of the drainage tube, and when fuel gas passes through the drainage channel, the thermal protection of the drainage tube on the spray pipe body is facilitated. The diameter of the guide rod is larger than the inner diameter of the drainage tube, and the sealing performance of the drainage channel to the channel is improved when the drainage channel is in a closed state.
3) The first guide rod through hole on the spray pipe body limits the position of the guide rod, so that the guide rod can only move along the direction of the through hole. The free end on the rightmost side of the guide rod is of a spherical structure, so that the situation that the guide rod and the first guide rod through hole are blocked and cannot move can be avoided. The guide rod vertically penetrates through the drainage tube, so that the guide rod can limit the position of the drainage tube and prevent the drainage tube from changing under the condition of gas scouring.
4) The drainage tube and the guide rod are made of refractory metals such as tungsten copper infiltrated and molybdenum alloy, and compared with non-metal materials, the drainage tube and the guide rod have better strength and rigidity, and can not deform and move in the working process, so that the good matching performance among related parts is ensured.
5) When control system and driving motor drive water conservancy diversion pole and move to the right-hand member, third drainage channel misplaces completely with first drainage channel, second drainage channel this moment, and the water conservancy diversion pole carries out the shutoff to third drainage channel, and the unable drainage channel blowout of following of gas that flows in the spray tube this moment, consequently does not produce the lateral control power.
6) When a control system gives a lateral force control instruction, the driving motor drives the guide rod to move to the leftmost end, the third drainage channel is overlapped with the first drainage channel and the second drainage channel at the moment, the drainage channels are communicated, high-temperature and high-pressure gas in the jet pipe is sprayed out from the drainage channels, a lateral control moment is generated, and thrust vector control is achieved.
7) The control system and the driving motor can drive the guide rod to reciprocate for multiple times, so that the flexibility of thrust vector control is improved.
8) Control system and driving motor install on the motor mount pad, have set up spacing step on the mount pad to realize that control system and driving motor and spray tube body surface are not direct contact, guaranteed that spray tube surface temperature rise can not cause the influence to control system and driving motor.
9) A plurality of thrust vector control units are arranged in the circumferential direction of the spray pipe in a symmetrical mode, and thrust vector control can be achieved when one or a plurality of drainage channels are opened independently or asymmetrically. When a plurality of drainage channels are symmetrically opened, lateral forces in all directions are mutually offset, lateral control moment is not generated on the aircraft, and the axial thrust of the engine can be reduced by the lateral ejection of the fuel gas flow.
Drawings
FIG. 1 shows a nozzle block diagram;
FIG. 2 is a view showing the internal structure of the nozzle (with the drainage holes closed);
FIG. 3 is a view of the nozzle body;
FIG. 4 is a view showing a drainage hole;
FIG. 5 is a view showing the structure of a guide bar;
FIG. 6 shows the structure of the inside of the nozzle (in the state where the drainage holes are opened).
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
The invention is described in further detail below with reference to the figures and examples.
The thrust vector control spray pipe mainly comprises a spray pipe main body structure and a thrust vector control system, wherein the spray pipe main body structure comprises a spray pipe body 1, a convergent section heat insulation 2, a back lining 3, a throat lining 4 and an expansion section heat insulation 5, and the thrust vector control system mainly comprises a control system, a driving motor 6, a driving rod 7, a guide rod 8 and a drainage pipe 9.
The nozzle body 1 is formed by processing high-strength stainless steel, one end of a fuel gas inlet of the nozzle body 1 is provided with a mechanical interface 1-1 connected with an engine combustion chamber, the interface provided by the scheme is a flange connection interface and can also be a connection interface such as a thread and a snap ring, a carbon fiber/phenolic aldehyde and high silica/phenolic aldehyde composite die pressing material is adopted for the heat insulation 2 of the convergence section, a high silica/phenolic aldehyde material is adopted for the back lining 3, a C/C composite material is adopted for the throat lining 4, a carbon fiber/phenolic aldehyde and high silica/phenolic aldehyde composite die pressing material is adopted for the heat insulation 5 of the expansion section, the heat insulation inner surface of the nozzle is contacted with fuel gas of a rocket engine, carbon-based materials are adopted for the inner layer materials, the scouring resistance of the nozzle can. In order to prevent the throat insert 4 from falling off under the impact of gas, the space position of the throat insert 4 is restrained by the heat insulation 2 of the convergent section and the heat insulation 5 of the divergent section.
The expansion section of the spray pipe body 1 is provided with gas drainage holes 1-3, a drainage pipe 9 is embedded in the gas drainage holes 1-3, the outer diameter of the drainage pipe 9 is equal to the inner diameter of the gas drainage holes 1-3, the drainage pipe 9 can be formed by processing refractory metals such as tungsten copper infiltrated and molybdenum alloy, and the drainage pipe 9 is adhered to the gas drainage holes 1-3 and well jointed and sealed with the gas drainage holes 1-3. A second guide rod through hole 9-2 is arranged on the drainage tube 9 and is vertical to the second drainage channel 9-1. The expansion section of the spray pipe body 1 is provided with first guide rod through holes 1-4, and the first guide rod through holes 1-4 and the second guide rod through holes 9-2 are completely overlapped to form a guide rod channel together. The guide rod channel is vertically intersected with the drainage channel, the drainage channel is composed of a first drainage channel 5-1, a second drainage channel 9-1 and a third drainage channel 8-1 on the expansion section heat insulation 5, the diameters of the first drainage channel 5-1, the second drainage channel 9-1 and the third drainage channel 8-1 are equal, and the drainage channel is perpendicular to the axis direction of the spray pipe. The diameter of the guide rod 8 is smaller than the outer diameter of the drainage tube 9, so that the thermal protection of the drainage tube 9 on the spray pipe body 1 is facilitated when the fuel gas passes through the drainage channel. The diameter of the guide rod 8 is larger than the inner diameter of the drainage tube 9, so that the sealing performance of the drainage channel is improved when the drainage channel is in a closed state.
The guide rod 8 is connected with the guide rod channel in a sliding fit mode, and the guide rod 8 can be made of refractory metals such as tungsten infiltrated copper and molybdenum alloy. The guide rod 8 is rigidly connected with the driving rod 7, the movement of the driving rod 7 is controlled by the control system and the driving motor 6, and the guide rod 8 is driven to axially move in the horizontal direction without rotating. The positions of the guide rods 8 are limited by the first guide rod through holes 1-4 on the spray pipe body, so that the guide rods 8 can only move along the direction of the through holes. The free end on the rightmost side of the guide rod 8 is of a spherical structure, so that the situation that the guide rod 8 and the first guide rod through holes 1-4 are blocked and cannot move can be avoided. The guide rod 8 vertically penetrates through the drainage tube 9, so that the guide rod 8 can limit the position of the drainage tube 9 and prevent the drainage tube 9 from changing under the condition of gas scouring.
The mounting seat 1-2 of the control system and the driving motor 9 is arranged at the throat part of the spray pipe body 1, the limiting step is designed on the mounting seat 1-2, the control system and the driving motor 6 cannot be in direct contact with the outer surface of the spray pipe body 1 when being mounted on the mounting seat 1-2, and the influence of the high temperature of the outer surface of the spray pipe body 1 on the performance of the control system and the driving motor 6 is avoided.
The guide rod 8 moves to the rightmost end in the initial working stage of the spray pipe, the third drainage channel 8-1, the first drainage channel 5-1 and the second drainage channel 9-1 are completely staggered, the guide rod 8 blocks the third drainage channel 8-1, and gas flowing in the spray pipe cannot be sprayed out of the drainage channels at the moment, so that lateral control force is not generated. When the control system gives a lateral force control instruction, the control system and the driving motor 6 drive the guide rod 8 to move to the leftmost end, at the moment, the third drainage channel 8-1 is completely overlapped with the first drainage channel 5-1 and the second drainage channel 9-1, the drainage channels are communicated, high-temperature and high-pressure fuel gas in the spray pipe is sprayed out from the drainage channels to generate a reaction lateral control moment, partial flow is sprayed out laterally to cause the reduction of axial flow, and therefore the axial thrust of the spray pipe is reduced.
In order to realize more flexible thrust vector control of the spray pipe, a plurality of thrust vector control devices can be symmetrically arranged on the spray pipe, each thrust vector control device can be opened and closed independently or in combination for a plurality of times, and different control moments can be obtained by controlling a single or a plurality of guide rods.
It will be understood by those skilled in the art that the foregoing is only a preferred embodiment of the present invention, and is not intended to limit the invention, and that any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (10)
1. A thrust vector control spray pipe for lateral drainage of an expansion section is composed of a spray pipe main body structure and a thrust vector control system, wherein the spray pipe main body structure is composed of a spray pipe body, a convergence section heat insulation layer, a back lining, a throat liner and an expansion section heat insulation layer; the expansion section of the spray pipe body is provided with a gas drainage hole, a drainage pipe is embedded in the gas drainage hole, the outer diameter of the drainage pipe is equal to the inner diameter of the gas drainage hole, and the drainage pipe is bonded on the gas drainage hole and well attached and sealed with the gas drainage hole; a second guide rod through hole is formed in the drainage tube and is perpendicular to the second drainage channel; a first guide rod through hole is formed in the expansion section of the spray pipe body, and the first guide rod through hole and the second guide rod through hole are completely overlapped to form a guide rod channel together; the guide rod channel is vertically intersected with the drainage channel; the drainage channel comprises first drainage channel, second drainage channel and the third drainage channel on the water conservancy diversion pole on the expansion section heat insulation, and first drainage channel, second drainage channel and third drainage channel diameter are equal, and drainage channel perpendicular to spray tube axis direction.
2. The divergent section side draft thrust vectoring nozzle of claim 1 wherein said deflector rod has a diameter less than the outer diameter of the draft tube; the diameter of the guide rod is larger than the inner diameter of the drainage tube.
3. The divergent section lateral flow guiding thrust vectoring nozzle of claim 1 or 2, wherein the nozzle body is provided at the throat with a mounting seat for the control system and the drive motor, the mounting seat being provided with a limit step, the control system and the drive motor being mounted on the mounting seat in a manner of non-direct contact with the outer surface of the nozzle body.
4. The divergent section side draft thrust vectoring nozzle of claim 3 wherein the third flow directing passage is completely offset from the first flow directing passage and the second flow directing passage when the diverter rod is positioned at the rightmost end.
5. The divergent section side draft thrust vectoring nozzle of claim 3 wherein the third flow directing passage completely overlaps the first flow directing passage and the second flow directing passage when the flow directing bar is at the far left end.
6. The lateral flow-guiding thrust vectoring nozzle of claim 3, wherein N thrust vectoring devices are symmetrically disposed on the nozzle, where N is 2 to 24, and each thrust vectoring device can be opened and closed independently or in combination.
7. The divergent section side draft thrust vectoring nozzle of claim 1 wherein said deflector rod is in sliding fit engagement with the deflector rod passage; the guide rod is rigidly connected with the driving rod; the motion of the driving rod is controlled by a control system and a driving motor, and the guide rod is driven to axially move in the horizontal direction without rotating.
8. The divergent section side draft thrust vectoring nozzle of claim 1, wherein said nozzle body fuel gas inlet end is provided with a mechanical interface for connection to an engine combustion chamber, said mechanical interface being a flange connection interface, a threaded connection interface, or a snap ring connection interface; the nozzle convergent section is made of carbon fiber/phenolic aldehyde and high silica/phenolic aldehyde composite die pressing materials for heat insulation, the throat liner is made of C/C composite materials, the backing is made of high silica/phenolic aldehyde materials, and the nozzle expansion section is made of carbon fiber/phenolic aldehyde and high silica/phenolic aldehyde composite die pressing materials for heat insulation.
9. The divergent section side draft thrust vectoring nozzle of claim 1 wherein the convergent section adiabatic rear end limits the throat insert front face; the front end surface of the expansion section limits the rear end surface of the throat insert.
10. The divergent section side draft thrust vectoring nozzle of claim 1 wherein said deflector rod is fabricated from a tungsten infiltrated copper or molybdenum alloy refractory metal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011509100.9A CN112761823B (en) | 2020-12-19 | 2020-12-19 | Expansion section lateral drainage thrust vector control spray pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011509100.9A CN112761823B (en) | 2020-12-19 | 2020-12-19 | Expansion section lateral drainage thrust vector control spray pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112761823A true CN112761823A (en) | 2021-05-07 |
| CN112761823B CN112761823B (en) | 2022-03-18 |
Family
ID=75694840
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011509100.9A Active CN112761823B (en) | 2020-12-19 | 2020-12-19 | Expansion section lateral drainage thrust vector control spray pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112761823B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113443119A (en) * | 2021-06-15 | 2021-09-28 | 中国科学院力学研究所 | Novel high-speed aircraft based on rocket range extension and control method thereof |
| CN116291968A (en) * | 2023-03-02 | 2023-06-23 | 哈尔滨工业大学 | Direction-changeable tail nozzle and installation method and use method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1434195A (en) * | 1972-08-01 | 1976-05-05 | Secr Defence | Rocket motor thrust vector control means |
| DE3138869C2 (en) * | 1981-09-30 | 1984-07-12 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | "Guided missile" |
| US4754927A (en) * | 1986-12-08 | 1988-07-05 | Colt Industries Inc. | Control vanes for thrust vector control nozzle |
| US5125596A (en) * | 1989-05-23 | 1992-06-30 | Cavalleri Robert J | Fluid shielded movable strut for missile and rocket thrust vector control |
| US6105364A (en) * | 1989-10-11 | 2000-08-22 | Rolls-Royce Plc | Vstovl engines |
| CN101939528A (en) * | 2007-08-08 | 2011-01-05 | 罗尔股份有限公司 | Variable area fan nozzle with bypass flow |
| CN210714882U (en) * | 2019-08-16 | 2020-06-09 | 重庆零壹空间科技集团有限公司 | Rocket engine jet pipe |
-
2020
- 2020-12-19 CN CN202011509100.9A patent/CN112761823B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1434195A (en) * | 1972-08-01 | 1976-05-05 | Secr Defence | Rocket motor thrust vector control means |
| DE3138869C2 (en) * | 1981-09-30 | 1984-07-12 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | "Guided missile" |
| US4754927A (en) * | 1986-12-08 | 1988-07-05 | Colt Industries Inc. | Control vanes for thrust vector control nozzle |
| US5125596A (en) * | 1989-05-23 | 1992-06-30 | Cavalleri Robert J | Fluid shielded movable strut for missile and rocket thrust vector control |
| US6105364A (en) * | 1989-10-11 | 2000-08-22 | Rolls-Royce Plc | Vstovl engines |
| CN101939528A (en) * | 2007-08-08 | 2011-01-05 | 罗尔股份有限公司 | Variable area fan nozzle with bypass flow |
| CN210714882U (en) * | 2019-08-16 | 2020-06-09 | 重庆零壹空间科技集团有限公司 | Rocket engine jet pipe |
Non-Patent Citations (1)
| Title |
|---|
| 宋亚飞等: "流体推力矢量技术", 《飞航导弹》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113443119A (en) * | 2021-06-15 | 2021-09-28 | 中国科学院力学研究所 | Novel high-speed aircraft based on rocket range extension and control method thereof |
| CN116291968A (en) * | 2023-03-02 | 2023-06-23 | 哈尔滨工业大学 | Direction-changeable tail nozzle and installation method and use method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112761823B (en) | 2022-03-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112761823B (en) | Expansion section lateral drainage thrust vector control spray pipe | |
| CA2855370C (en) | Concentric nozzles for enhanced mixing of fluids | |
| CN104712460B (en) | A kind of solid propellant rocket of thrust controllable | |
| EP2604837B1 (en) | System for directing air flow to a plurality of plena | |
| CA1316516C (en) | Aerofoil/hydrofoil | |
| CN104234870A (en) | Slotted coaxial pintle type injector thrust chamber | |
| US20150030446A1 (en) | Nacelle for an aircraft bypass turbojet engine | |
| CN103185354A (en) | Methods and systems for cooling a transition nozzle | |
| CN103206880A (en) | Multi-channel Cooling Plenum | |
| CN111365144B (en) | Flexible joint and solid rocket engine jet pipe adopting same | |
| CN110318878A (en) | Sky and space plane Active Cooling System based on Magnetohydrodynamic Power bypass | |
| EP1998035B1 (en) | Fluidic vectoring for exhaust nozzle | |
| JP7246470B2 (en) | Pumping unit for fuel cell systems for pumping and/or controlling gaseous media | |
| US7093617B2 (en) | Fluidic diverter valve with a non-spherical shuttle element | |
| CN112539116B (en) | Variable throat diameter and variable expansion ratio spray pipe structure | |
| CN211573653U (en) | Ejector structure of small turbojet engine | |
| CN102121552B (en) | High-temperature high-pressure spray pipe | |
| CN116753075A (en) | Air inlet channel and precooler integrated structure of wide-speed-range engine | |
| CN115450798A (en) | Long-time working solid rocket engine and long tail jet pipe thereof | |
| US9932845B2 (en) | Impingement cooled nozzle liner | |
| CN115653779A (en) | Multi-shaft pneumatic thrust vectoring nozzle and multi-shaft thrust adjusting method | |
| US5405103A (en) | Device for actuating a mechanical member, in particular for the force guidance of a missile, and missile equipped with said device | |
| US20050150207A1 (en) | Fluidic diverter valve with a variable valve-bore clearance | |
| CN109515757B (en) | Jet aircraft attitude control device | |
| US11339745B1 (en) | Dual flowpath exhaust for fuel cooling in a hypersonic propulsion system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |