CN102991669B - Aircraft fluidic thrust vector control system - Google Patents
Aircraft fluidic thrust vector control system Download PDFInfo
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- CN102991669B CN102991669B CN201210536374.6A CN201210536374A CN102991669B CN 102991669 B CN102991669 B CN 102991669B CN 201210536374 A CN201210536374 A CN 201210536374A CN 102991669 B CN102991669 B CN 102991669B
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Abstract
The invention discloses an aircraft fluidic thrust vector control system. With the control system, 306-degree flying attitudes of the aircraft can be controlled; response time of the control system is shortened; control precision of the control system is increased; a structure of the control system is simplified; and the weight of the aircraft is reduced. The aircraft fluidic thrust vector control system comprises a fuel gas turbine engine, a main airflow channel, a secondary flow nozzle, a secondary flow channel assembly and a Coanda effect surface. A small part of the gas is introduced out from an engine compression chamber to be used as a secondary flow gas source of the vector thrust control system in the same direction, and is injected into the secondary flow channel by using a Coanda effect. A wall attachment effect is produced after the secondary flow in the same direction with the main airflow flows through the Coanda effect surface, and Coanda effect is further generated by guiding the main airflow along the wall attachment direction, so that a deflection torque is obtained. Precision control for pitching, being off-course and rolling of the aircraft can be realized by controlling the outflow direction and the flow rate of the secondary flow.
Description
Technical field
The present invention relates to a kind of aircraft jet thrust vector control system, belong to field of aerospace technology.
Background technology
In the design of traditional flight control system, people by control surface deflection produce the turning to aircraft as operating torque of asymmetric aerodynamic torque, climb, the flight attitude such as underriding, roll implements manipulation.This master mode must be aided with many complicated heavy hydraulic pressure or electric liquid drives steering wheel and other supporting relevant devices just can carry out, and the installation of rudder face has destroyed continuous smooth wing, there are a lot of gaps, thereby produce very large leak resistance, control surface deflection, also by increasing RCS (RCS) value of aircraft, is unfavorable for stealthy simultaneously.Afterwards, people install combustion gas rudder face after aircraft rear engine, produce flight attitude control side force, but exhaust residue easily stop up gas circuit by the direction that changes engine gas stream, necessary well-designed filtering installation, and the moment that combustion gas rudder face produces is less.Thrust vectoring control technology be just progressively applied to the 4th generation opportunity of combat and advanced ballistic missile on, current thrust vectoring control technology generally adopts mechanical means, as the adjustment sheet that engine nozzle swings, engine nozzle installs adjustable baffle plate or deflection expansion segment outward additional.Mechanical thrust vector spray, in bringing dramatic benefit, also makes propulsion system pay larger cost, increased cost, the quality etc. of system mechanics complexity, jet pipe.Reach into hundred cover parts and thousands of parts for the parts of thrust vectoring control as hinge, seal strip, hydraulic actuation system, deflection film, the maintenance to aircraft simultaneously, stealthy and fuselage trim is very unfavorable.
Along with ultra-compact, the high viability of following operational aircraft and designing requirement that can endurance air inlet system and exhaust system, traditional mechanical type thrust vector control system can not meet these requirements.These factors cause seeking the vectored thrust production method without external activity parts, have occurred the conformal vectored thrust technology based on jet current principle.Conformal Thrust Vectoring Technology refers to and is keeping or do not changing under the prerequisite of aerodynamic arrangement of overall aircraft stream line pattern (conformal) very much, the thrust component that engine thrust produces by the deflection of jet pipe or tail jet substitutes the controlsurface of former aircraft or strengthens the operating function of aircraft, the flight of aircraft is carried out to the technology of controlling in real time.Jet thrust vector control nozzle is different from mechanical conditioning type vector spray, it is by the interaction between air-flow, use Condar (Coanda) effect to control tiny bypass gas flow and change, and the change of bypass gas flow can cause than its much bigger mobile generation deflection vector.Coanda effect refers to fluid (current or air-flow) to be had and leaves original flow direction, change into along with the mobile tendency of body surface of protruding, in the time there is surface friction between the body surface that fluid and it are flow through, the flow velocity of fluid can slow down, as long as the curvature of body surface is not too large, according to the bernoulli principle in fluid mechanics, the slowing down of flow velocity can cause fluid to be attracted on body surface flowing.Coanda effect is applied to power-boosting wing flap and trailing edge circulation control technology the earliest, and for improving lift, it is the core technology of jet thrust vector control system.At present Coanda effect is applied to jet thrust vector and realizes the system of 360 ° of attitude controls of aircraft and do not see yet related application.
Summary of the invention
In view of this, the invention provides a kind of aircraft jet thrust vector control system, can realize 360 ° of flight attitude controls of aircraft, shorten control system response time, improve system control accuracy simultaneously, realize comprehensive control, simplified control system structure, alleviates aircraft weight.
Aircraft jet thrust vector control system comprises gas turbine engine, main air flow passage, Secondary Flow jet pipe, secondary stream passage assembly and Coanda effect face.
Wherein, main air flow passage is arranged on gas turbine engine shrink nozzle afterbody, coaxial with driving engine.
Secondary stream passage assembly is coaxial with main air flow passage, is fixed on the afterbody of main air flow passage by flange, and secondary stream passage assembly comprises inner and outer wall, and the cross section of inside and outside wall is rectangle; It between inside and outside wall, is secondary stream passage.Wherein, inwall, as the extension of main air flow passage, separates main air flow passage and secondary stream passage.On four angles of inwall, secondary stream passage baffle plate is set, secondary stream passage is divided into a upper and lower, left and right part, wherein, the secondary stream passage of above and below is wider than the secondary stream passage of left and right.The secondary stream passage of each direction becomes 2 Secondary Flow subchannels that size is identical by Secondary Flow subchannel barrier partitions respectively.
On gas turbine engine compression chamber, bleed ports is set, draws the in the same way Secondary Flow source of the gas of fraction gas as vectored thrust control system, described Secondary Flow source of the gas is no more than 5% of all gas in engine compresses chamber.At each Secondary Flow subchannel outer wall, gas injection port is set; In main air flow passage outside, 8 Secondary Flow jet pipes are installed, 8 Secondary Flow jet pipes are connected with 8 gas injection ports respectively; In main air flow passage arranged outside gas-distributing pipe road, gas-distributing pipe road connects gas injection port and 8 Secondary Flow jet pipes.
4 of the outer wall afterbodys at secondary stream passage assembly are installed respectively Coanda effect face.
On each Secondary Flow jet pipe, control cock is installed.
For alleviating the weight of jet thrust vector control system, can between gas turbine engine shrink nozzle and axial main air flow passage, leave the gap of 20 ~ 30cm.
For easy to process, main air flow passage can be designed to cuboid, in the upper and lower, left and right in main air flow passage outside, 4 along 2 Secondary Flow jet pipes are axially installed respectively.
For reaching good Coanda effect, the angle of shear scope in the present invention between Coanda effect face and the outer wall of secondary stream passage assembly is 5 ° ~ 10 °.
Control cock in the present invention can be proportional control valve, thereby can fine adjustment Secondary Flow air flow rate, improves the positioning precision that flight is controlled.
Beneficial effect:
(1) the present invention utilizes Coanda effect, drives the change of primary air direction, thereby aircraft is controlled in real time by the direction that changes Secondary Flow, the present invention is without handling mechanical part, and the overall aerodynamic arrangement of not change of flight device, installs simple, cost is low, and control process response time is little.
(2) the present invention leaves the gap of 20 ~ 30cm between transmitting set shrink nozzle and axial main air flow passage, effectively alleviates the weight of jet thrust vector control system.
(3) the Secondary Flow source of the gas that the present invention draws from engine compresses chamber is no more than 5% of all gas in engine compresses chamber, does not affect the axial thrust of driving engine.
(4) the present invention's proportion of installation control cock on Secondary Flow jet pipe, can fine adjustment Secondary Flow air flow rate, improves the positioning precision that flight is controlled.
Brief description of the drawings
Fig. 1 is aircraft jet thrust vector control system device block diagram.
Fig. 2 is aircraft jet thrust vector control system device three-dimensional side view.
Fig. 3 is aircraft jet thrust vector control system device back view.
Fig. 4 is aircraft jet thrust vector control system device right elevation.
Fig. 5 is aircraft jet thrust vector control system device birds-eye view.
Wherein, 1-driving engine, 2-bleed ports, 3-gas-distributing pipe road, 4-Secondary Flow jet pipe, 5-control cock, 6-flange, 7-gas injection port, 8-Secondary Flow subchannel baffle plate, 9-secondary stream passage, 10-Coanda effect face, 11-main air flow passage, 12-secondary stream passage baffle plate, 13-1 Secondary Flow subchannel, 14-2 Secondary Flow subchannel, 15-3 Secondary Flow subchannel, 16-4 Secondary Flow subchannel, 17-5 Secondary Flow subchannel, 18-6 Secondary Flow subchannel, 19-7 Secondary Flow subchannel, 20-8 Secondary Flow subchannel, the inwall of 21-secondary stream passage assembly, the outer wall of 22-secondary stream passage assembly.
Detailed description of the invention
Below in conjunction with the accompanying drawing embodiment that develops simultaneously, describe the present invention.
The invention provides a kind of aircraft jet thrust vector control system, comprise gas turbine engine 1, main air flow passage 11, Secondary Flow jet pipe 4, secondary stream passage assembly and Coanda effect face 10, as shown in Figure 1.
Wherein, main air flow passage 11 is arranged on driving engine 1 shrink nozzle afterbody, coaxial with driving engine 1, for easy to process, main air flow passage 11 can be set to cuboid.The shrink nozzle of driving engine 1 is discharged the axial primary air of high-pressure gas as control system, and primary air flows to jet thrust vector control system afterbody along axial main air flow passage 11, produces axial advance power, promotes aircraft and advances.Utilize the directionality of TC engine high-pressure injection air-flow, this jet-stream wind moves along injection direction in certain distance, can scattering, between transmitting set 1 shrink nozzle and axial main air flow passage 11, design the gap of 20 ~ 30cm, thereby alleviate the weight of jet thrust vector control system.
Secondary stream passage assembly is coaxial with main air flow passage 11, is fixed on the afterbody of main air flow passage 11 by flange 6, and secondary stream passage assembly comprises inwall 21 and outer wall 22, and the cross section of inside and outside wall is rectangle; It between inside and outside wall, is secondary stream passage 9, wherein, inwall 21 is as the extension of main air flow passage 11, main air flow passage 11 and secondary stream passage 9 are separated, on four angles of inwall, secondary stream passage baffle plate 12 is set, secondary stream passage 9 is divided into 4 of upper and lower, left and right part, as shown in Figure 2 and Figure 3.For ensureing that aircraft pitching power is greater than yaw forces, the secondary stream passage of above and below is wider than the secondary stream passage of left and right.The secondary stream passage of each direction is separated into 2 Secondary Flow subchannels that size is identical with Secondary Flow subchannel baffle plate 8 respectively, as shown in Figure 3.
On driving engine 1 compression chamber, bleed ports 2 is set, draw the in the same way Secondary Flow source of the gas of fraction gas as vectored thrust control system, in the upper and lower, left and right in main air flow passage 11 outsides, 4 along 2 Secondary Flow jet pipes 4 are axially installed respectively, on the outer wall of each secondary subflow passage, gas injection port 7 is set, Secondary Flow source of the gas flows into these 8 Secondary Flow jet pipes 4 by gas-distributing pipe road 3, and by corresponding gas injection port 7, Secondary Flow is injected in each Secondary Flow subchannel, Secondary Flow flows out in the same way by Secondary Flow subchannel and primary air.
4 of outer wall 22 afterbodys at secondary stream passage assembly are installed respectively Coanda effect face 10, and what Coanda effect face 10 can be for arc is tubaeform to what turn up, as shown in Figure 1 and Figure 2, Coanda effect face can for arc to the trapezoidal faces of turning up.Between the outer wall 22 of Coanda effect face 10 and secondary stream passage assembly, angle of shear scope is 5 ° ~ 10 °, as shown in Figure 4.Unobstructed between Coanda effect face 10 and primary air, with the attached wall effect of the rear generation of Coanda effect face 10 of flowing through of primary air Secondary Flow in the same way, i.e. Coanda effect, Secondary Flow and axially form shear layer between primary air, guiding primary air produces Coanda effect along attached wall direction, thereby obtains deflecting torque.4 Coanda effect faces can ensure to obtain upwards, downward pitching moment and yawing moment left, to the right.
For ensureing that driving engine has enough axial thrusts, the Secondary Flow source of the gas of drawing from driving engine 1 compression chamber is no more than 5% of all gas in engine compresses chamber.
Control cock 5 is installed on Secondary Flow jet pipe, by controlling the outflow orientation of switch control Secondary Flow of control cock 5, thereby realizes pitching, driftage, the rolling control to aircraft.Described control cock 5 can be proportional control valve, can fine adjustment Secondary Flow air flow rate, improve the positioning precision that flight is controlled.
In the time that aircraft craspedodrome does not need other attitude controls, the proportional control valve 5 of 8 Secondary Flow jet pipes 4 is all in closed condition; In the time that needs are realized pitch control subsystem, above or below the proportional control valve of two Secondary Flow subchannels open by same proportional control value, Secondary Flow produces Coanda effect by Coanda effect face, between Secondary Flow and primary air, form shear layer, and then guiding primary air produces Coanda effect, cause axial primary air to effect surface deflection, produce moment up or down; In the time that needs are realized driftage control, the proportional control valve of left or right-hand two Secondary Flow subchannels is opened by same proportional control value, Secondary Flow produces Coanda effect by Coanda effect face, and then guiding primary air produces Coanda effect, cause axial primary air to effect surface deflection, produce moment to the left or to the right; In the time that aircraft will be realized rolling control, the Secondary Flow jet pipe that top Secondary Flow subchannel is corresponding is only opened one, opens the Secondary Flow jet pipe of the below secondary subchannel that is skew symmetry direction with it simultaneously, thereby produces asymmetric moment, realizes rolling.The combination control of 4 Coanda effect faces and 8 Secondary Flow subchannels can realize 360 ° of comprehensive attitude controls of aircraft.
Jet thrust vector control system of the present invention, without handling mechanical part, has shortened control process response time.
In sum, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention.Within the spirit and principles in the present invention all, any amendment of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (6)
1. an aircraft jet thrust vector control system, is characterized in that comprising gas turbine engine (1), main air flow passage (11), Secondary Flow jet pipe (4), secondary stream passage assembly and Coanda effect face (10);
Wherein, main air flow passage (11) is arranged on gas turbine engine (1) shrink nozzle afterbody, coaxial with driving engine (1);
Secondary stream passage assembly is coaxial with main air flow passage (11), be fixed on the afterbody of main air flow passage (11) by flange (6), secondary stream passage assembly comprises inwall (21) and outer wall (22), and the cross section of inside and outside wall is rectangle; Between inside and outside wall, be secondary stream passage (9), wherein, inwall (21), as the extension of main air flow passage, separates main air flow passage and secondary stream passage; On four angles of inwall, secondary stream passage baffle plate (12) is set, secondary stream passage (9) is divided into 4 of upper and lower, left and right part, wherein, the secondary stream passage of above and below is wider than the secondary stream passage of left and right; The secondary stream passage of each direction uses respectively Secondary Flow subchannel baffle plate (8) to be separated into 2 Secondary Flow subchannels (13,14 that size is identical; 15,16; 17,18; 19,20);
On gas turbine engine (1) compression chamber, bleed ports (2) is set, draws the in the same way Secondary Flow source of the gas of fraction gas as vectored thrust control system, described Secondary Flow source of the gas is no more than 5% of all gas in engine compresses chamber; At each Secondary Flow subchannel (13,14,15,16,17,18,19,20) outer wall, gas injection port (7) is set; In main air flow passage (11) outside, 8 Secondary Flow jet pipes (4) are installed, 8 Secondary Flow jet pipes (4) are connected with 8 gas injection ports (7) respectively; In main air flow passage (11) arranged outside gas-distributing pipe road (3), gas-distributing pipe road (3) connect bleed ports (2) and 8 Secondary Flow jet pipes (4);
4 of outer wall (22) afterbodys at secondary stream passage assembly are installed respectively Coanda effect face (10);
In the upper control cock (5) of installing of each Secondary Flow jet pipe (4).
2. a kind of aircraft jet thrust vector control system as claimed in claim 1, is characterized in that, leaves the gap of 20～30cm between gas turbine engine (1) shrink nozzle and axial main air flow passage (11).
3. a kind of aircraft jet thrust vector control system as claimed in claim 1, is characterized in that, described main air flow passage (11) is cuboid.
4. a kind of aircraft jet thrust vector control system as claimed in claim 3, is characterized in that, in the upper and lower, left and right in main air flow passage (11) outside, 4 along 2 Secondary Flow jet pipes (4) are axially installed respectively.
5. a kind of aircraft jet thrust vector control system as claimed in claim 1, is characterized in that, the angle of shear scope between the outer wall (22) of described Coanda effect face (10) and secondary stream passage assembly is 5 °～10 °.
6. a kind of aircraft jet thrust vector control system as claimed in claim 1, is characterized in that, described control cock (5) is proportional control valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210536374.6A CN102991669B (en) | 2012-12-12 | 2012-12-12 | Aircraft fluidic thrust vector control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210536374.6A CN102991669B (en) | 2012-12-12 | 2012-12-12 | Aircraft fluidic thrust vector control system |
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| Publication Number | Publication Date |
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| CN102991669A CN102991669A (en) | 2013-03-27 |
| CN102991669B true CN102991669B (en) | 2014-12-03 |
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| CN201210536374.6A Expired - Fee Related CN102991669B (en) | 2012-12-12 | 2012-12-12 | Aircraft fluidic thrust vector control system |
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Families Citing this family (19)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103612751B (en) * | 2013-11-18 | 2015-12-09 | 岑溪市东正新泵业贸易有限公司 | Air amplification type aircraft propulsion device |
| CN103786863A (en) * | 2014-02-17 | 2014-05-14 | 李彦征 | Jet-propelled vertical-lift air bag aircraft |
| CN105329437A (en) * | 2014-08-04 | 2016-02-17 | 任军 | Vertical/horizontal flight fixed-nozzle fixed wing aircraft |
| CN105022042B (en) * | 2015-07-01 | 2018-01-26 | 西北工业大学 | A kind of the terminal grid and method of aero-engine gas extraction system RCS tests |
| KR20180061182A (en) | 2015-09-02 | 2018-06-07 | 제톱테라 잉크. | Ejector and airfoil structure |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| USD868627S1 (en) | 2018-04-27 | 2019-12-03 | Jetoptera, Inc. | Flying car |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN106347637B (en) * | 2016-09-29 | 2018-09-07 | 湖北航天技术研究院总体设计所 | The anti-thermally induced flow integrated apparatus of attitude control jet pipe under a kind of high Mach environment |
| CN107021235B (en) * | 2017-04-06 | 2019-11-08 | 王子墨 | A kind of low-to-medium altitude aircraft driving device, driving method and low-to-medium altitude aircraft |
| CN107084070B (en) * | 2017-06-01 | 2018-12-07 | 南京航空航天大学 | A kind of wedge shape controls cellular type fluid thrust vector spray |
| EP3645854A4 (en) | 2017-06-27 | 2021-03-24 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN112761815A (en) * | 2021-01-22 | 2021-05-07 | 中国航发沈阳发动机研究所 | Aero-engine vector spray pipe structure |
| CN113415412B (en) * | 2021-06-25 | 2022-10-25 | 中国人民解放军国防科技大学 | Wide-speed-range jet flow control aircraft |
| CN113294262A (en) * | 2021-07-08 | 2021-08-24 | 中国航空发动机研究院 | Vector spray pipe based on self-excitation sweep oscillation jet flow |
| CN113371178B (en) * | 2021-07-13 | 2023-04-07 | 上海交通大学 | Normal flow thrust vectoring nozzle control device based on oscillating jet flow and aircraft |
| CN113389654A (en) * | 2021-07-20 | 2021-09-14 | 中国航空发动机研究院 | Vector spray pipe based on self-excitation pulse oscillation jet flow |
| CN114993681B (en) * | 2022-05-12 | 2023-01-17 | 北京理工大学 | Method for detecting performance of jet type micro-attitude engine |
| CN117289712A (en) * | 2023-11-27 | 2023-12-26 | 中国航空研究院 | Virtual control surface jet flow control system and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0796196A4 (en) * | 1994-12-30 | 1998-04-01 | Grumman Aerospace Corp | Fluidic control thrust vectoring nozzle |
| US6195981B1 (en) * | 1998-07-22 | 2001-03-06 | General Electric Company | Vectoring nozzle control system |
| US6679048B1 (en) * | 2000-10-24 | 2004-01-20 | Lockheed Martin Corporation | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection |
| US8800259B2 (en) * | 2008-09-22 | 2014-08-12 | Rolls-Royce North American Technologies, Inc. | Thrust vector system |
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