CN113602478B - Fluid control surface based on circulation control and vertical micro-jet flow - Google Patents
Fluid control surface based on circulation control and vertical micro-jet flow Download PDFInfo
- Publication number
- CN113602478B CN113602478B CN202110142145.5A CN202110142145A CN113602478B CN 113602478 B CN113602478 B CN 113602478B CN 202110142145 A CN202110142145 A CN 202110142145A CN 113602478 B CN113602478 B CN 113602478B
- Authority
- CN
- China
- Prior art keywords
- slot
- fluid chamber
- fluid
- control surface
- control
- 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a fluid control surface based on annular control and vertical micro jet flow, which is arranged at the rear edge of an aircraft wing (1), wherein the fluid control surface comprises four fluid chambers and a semicircular structure body (12) capable of rotating locally, the first fluid chamber (7) and the second fluid chamber (10), and the third fluid chamber (8) and the fourth fluid chamber (9) are distributed in an axisymmetric manner relative to the mean camber line of the control surface respectively; a first slot (4) is arranged in the tangential direction of the tail end of the first fluid chamber (7) and the semicircular structure body (12), and a second slot (11) is arranged in the tangential direction of the tail end of the second fluid chamber (10) and the semicircular structure body (12); the third slot (13) or the fourth slot (6) is opened by rotating the semicircular structure (12), the third slot (13) is arranged at the end of the third fluid chamber (8), and the fourth slot (6) is arranged at the end of the fourth fluid chamber (9).
Description
Technical Field
The invention relates to the field of aerodynamics, in particular to a fluid control surface based on circulation control and vertical micro-jet flow.
Background
Fixed wing aircraft typically employ movable control surfaces, such as ailerons, rudders, and the like, at the trailing edge of the wing to effect flow control of the wing surface, and thus achieve the desired control forces and control moments. Such conventional mechanical control surfaces require hydraulic actuators that add to the structural weight and complexity of the mechanism. In addition, such mechanical control systems have relatively long control times, and particularly when the control surface structure is heavy, the large inertial forces can further hinder its quick response capability.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a fluid control surface based on annular quantity control and vertical object plane micro jet flow.
In order to achieve the above-mentioned purpose, the present invention provides a fluid control surface based on annular control and vertical micro-jet, which is installed at the trailing edge of an aircraft wing, the fluid control surface includes four fluid chambers and a semi-circular structure body capable of rotating locally, wherein the first fluid chamber and the second fluid chamber are distributed axisymmetrically with respect to the mean camber line of the control surface, and the third fluid chamber and the fourth fluid chamber are distributed axisymmetrically with respect to the mean camber line of the control surface; a first slot is arranged in the tangential direction of the tail end of the first fluid chamber and the semicircular structure body, and a second slot is arranged in the tangential direction of the tail end of the second fluid chamber and the semicircular structure body; the third slot or the fourth slot is opened by rotating the semicircular structure, the third slot being provided at the end of the third fluid chamber and the fourth slot being provided at the end of the fourth fluid chamber.
As an improvement of the fluid control surface, the four fluid chambers are respectively provided with a valve close to the wing end.
As an improvement of the above-mentioned fluid control surface,
the valve of the first fluid chamber is used for being in an open state when the Mach number of the aircraft provided with the control surface is smaller than 0.5 in the incoming flow and lift force is required to be increased or low head moment is required to be generated, so that high-pressure gas is sprayed out through the first slot;
and the valve of the second fluid chamber is used for being in an open state when the Mach number of the aircraft provided with the control surface is smaller than 0.5 in the incoming flow and lift force is required to be reduced or head-up moment is required to be generated, so that high-pressure gas is sprayed out through the second slot.
As an improvement of the above-mentioned fluid control surface,
the valve of the third fluid chamber is used for being in an open state when the aircraft provided with the control surface flies at an incoming flow Mach number greater than 0.5 and needs to reduce lifting force or generate head-up moment, so that high-pressure gas pushes the semicircular structural body to rotate clockwise, the third slot is opened, and the high-pressure gas is sprayed out of the slot;
the valve of the fourth fluid chamber is used for being in an open state when the aircraft provided with the control surface flies at an incoming flow Mach number greater than 0.5 and needs to increase lifting force or generate low head moment, so that high-pressure gas pushes the semicircular structural body to rotate anticlockwise, the fourth slot is opened, and the high-pressure gas is sprayed out of the slot.
As an improvement of the fluid control surface, the third fluid chamber and the fourth fluid chamber are respectively provided with a small blocking block close to the semicircular structural body and used for limiting the local rotation of the semicircular structural body.
As an improvement of the fluid control surface, the radius of the semicircular structural body is more than 0.5 percent of the chord length of the aircraft wing and less than 1.5 percent of the chord length of the aircraft wing.
As an improvement to the above fluid control surfaces, the first and second slots each have a height greater than 0.0125% and less than 0.125% of the chord length of the aircraft wing.
As an improvement of the above fluid control surface, the width of each of the third and fourth slots is greater than 0.2% and less than 1.2% of the chord length of the aircraft wing.
Compared with the prior art, the invention has the advantages that:
1. compared with the traditional mechanical control surface, the fluid control surface based on the annular quantity control and the vertical micro jet flow has the advantages of higher response frequency, no need of a complex action device and reduced structural weight;
2. the fluid control surface based on the annular quantity control and the vertical micro jet flow can realize stronger control capability of the aircraft under the low-speed and high-speed flight conditions by switching and selecting in two different control modes of the annular quantity control and the micro jet flow in the system according to the flight speed of the aircraft, solves the problems of longer control time and larger structural weight of the traditional mechanical control surface, and has higher engineering practical value for improving the aerodynamic performance of the aircraft.
Drawings
FIG. 1 is a schematic illustration of a cross-section of a fluid control surface based on annular control and vertical micro-jets in accordance with the present invention;
FIG. 2 is a partial schematic view of the trailing edge of the control surface of the present invention during cyclic control;
FIG. 3 is a partial schematic view of the trailing edge of the control surface of the present invention with the vertical microjet third fluid chamber valve open;
FIG. 4 is a partial schematic view of the trailing edge of the control surface of the present invention with the valve of the vertical microjet fourth fluid chamber open.
Reference numerals
1. Aircraft wing 2, valve 3, block
4. A first slot 5, a rotation shaft 6, a fourth slot
7. First fluid chamber 8, third fluid chamber 9, fourth fluid chamber
10. Second fluid chamber 11, second slot 12, semicircular structure
13. Third slot
Detailed Description
The control surface realizes flow control on the surface of the wing by utilizing the annular quantity control of the coanda effect and two blowing modes of vertical micro jet flow, and generates required control force and control moment.
The invention discloses a fluid control surface based on annular quantity control and vertical micro jet flow, which can obviously improve the problem of longer response time of a conventional mechanical control surface by utilizing the inherent quick response characteristic of fluid. The annular quantity based on the coanda effect is controlled under the low-speed inflow condition, and the vertical micro jet flow has stronger fluid control capability under the high-speed inflow condition, so that the invention can realize the control force and moment required by the aircraft under different flight speeds.
The technical scheme of the invention is described in detail below with reference to the accompanying drawings and examples.
Example 1
As shown in fig. 1, embodiment 1 of the present invention provides a fluid control surface based on annular control and vertical micro-jets. The fluid control rudder surface comprises four fluid chambers and a semicircular structural body 12 which can rotate locally, wherein the first fluid chamber 7 and the second fluid chamber 10 are distributed in an axisymmetric manner relative to the mean camber line of the rudder surface, and the third fluid chamber 8 and the fourth fluid chamber 9 are distributed in an axisymmetric manner relative to the mean camber line of the rudder surface; a first slot 4 is provided at the end of the first fluid chamber 7 in a direction tangential to the semi-circular structure 12, and a second slot 11 is provided at the end of the second fluid chamber 10 in a direction tangential to the semi-circular structure 12; the third slot 13 or the fourth slot 6 is opened by rotating the semicircular structure 12, said third slot 13 being arranged at the end of the third fluid chamber 8 and said fourth slot 6 being arranged at the end of the fourth fluid chamber 9.
1) The trailing edge of the aircraft wing 1 is a semicircular structural body 12 which can roll locally and is used as a control surface for realizing the coanda effect; the semicircular structure body 12 is provided with a rotating shaft 5;
2) The upper and lower surfaces of the trailing edge of the aircraft wing 1 each have a slot tangential to the semi-circular structure 12: the first slot 4 and the second slot 11 are used as jet outlets for realizing annular control;
3) By means of the partial rolling of the semicircular structure 12, slots perpendicular to the trailing edge of the aircraft wing 1 can be realized in the upper and lower surfaces: the opening and closing of the third slot 13 and the fourth slot 6 are used as the outlet of the vertical jet flow;
4) The control system contains four fluid chambers: the first fluid chamber 7, the second fluid chamber 10, the third fluid chamber 8 and the fourth fluid chamber 9 are respectively jet flow inlets of upper and lower surface circulation control and vertical jet flow, and each chamber is provided with a corresponding angle valve to realize opening and closing of corresponding jet flow; such as valve 2, is arranged in the first fluid chamber 7;
5) The upper and lower surface annular volume control chambers are a first fluid chamber 7 and a second fluid chamber 10;
6) The rear edges of the upper vertical micro jet flow chamber, the lower vertical micro jet flow chamber, namely the third fluid chamber 8 and the fourth fluid chamber 9 are respectively provided with a small-sized blocking block which is used as a limiter for the local rolling of the semicircular structural body 12, and the blocking block 3 is arranged in the third fluid chamber 8;
7) The partial rolling of the semicircular structure 12 is achieved by the fluid control force of the chamber jet.
As shown in fig. 2, when the aircraft with the fluid control surface of the present invention flies at an incoming flow mach number less than 0.5, the inlet of the first fluid chamber 7 is opened and high-pressure gas is ejected through the first slot 4 when the lift force needs to be increased or a low head moment is generated. Due to the coanda effect, the jet will cause the airfoil upper surface, and particularly the airfoil trailing edge, to increase in velocity and lower upper surface pressure, thereby increasing the total annular volume and lift.
When the Mach number of the aircraft with the fluid control surface is smaller than 0.5 in the incoming flow, the inlet of the second fluid chamber 10 is opened when the lift force needs to be reduced or the head-up moment is generated, and high-pressure gas is sprayed out through the second slot 11. Due to the coanda effect, the jet will cause the airfoil lower surface, and particularly the airfoil trailing edge, to increase in velocity and lower surface pressure, which in turn causes the total annular volume to decrease and the lift to decrease.
As shown in fig. 3, when the aircraft with the fluid control surface of the present invention flies at an incoming flow mach number greater than 0.5, the inlet of the third fluid chamber 8 is opened when the lift force needs to be reduced or a head-up moment is generated, the semicircular structural body 12 is pushed to rotate clockwise by the high-pressure gas, the third slot 13 is opened, and the high-pressure gas is ejected from the slot. Due to the blocking effect of the jet, the flow velocity of the airfoil upper surface, particularly the trailing edge, is reduced, the upper surface pressure is increased, and the lift is reduced.
As shown in fig. 4, when the aircraft with the fluid control surface of the present invention flies at an incoming flow mach number greater than 0.5, the inlet of the fourth fluid chamber 9 is opened, the semicircular structural body 12 is pushed to rotate counterclockwise by the high-pressure gas, the fourth slot 6 is opened, and the high-pressure gas is ejected from the slot when the lift force needs to be increased or a low head moment is generated. Due to the blocking effect of the jet, the flow velocity of the airfoil lower surface, in particular the trailing edge, decreases, the lower surface pressure increases and the lift increases.
The invention discloses a direct fluid control surface for replacing a conventional mechanical control surface, which realizes flow control on the surface of a wing under different incoming flow conditions by utilizing two blowing modes of annular control of a coanda effect and vertical micro jet flow, and generates required control force and control moment.
Finally, it should be noted that the above embodiments are only for illustrating the technical solution of the present invention and are not limiting. Although the present invention has been described in detail with reference to the embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the present invention, which is intended to be covered by the appended claims.
Claims (5)
1. A fluid control surface based on annular control and vertical micro-jet flow, which is arranged at the rear edge of an aircraft wing (1), and is characterized in that the fluid control surface comprises four fluid chambers and a semicircular structural body (12) capable of rotating locally, wherein the first fluid chamber (7) and the second fluid chamber (10) are axially symmetrically distributed about the mean camber line of the control surface, and the third fluid chamber (8) and the fourth fluid chamber (9) are axially symmetrically distributed about the mean camber line of the control surface; a first slot (4) is arranged in a direction of tangency of the end of the first fluid chamber (7) and the semicircular structure (12), and a second slot (11) is arranged in a direction of tangency of the end of the second fluid chamber (10) and the semicircular structure (12); a third slot (13) or a fourth slot (6) is opened by rotating a semicircular structure (12), the third slot (13) being arranged at the end of the third fluid chamber (8), the fourth slot (6) being arranged at the end of the fourth fluid chamber (9);
the four fluid chambers are respectively provided with a valve close to the wing end;
the valve of the first fluid chamber (7) is used for being in an open state when the Mach number of the aircraft provided with the control surface is smaller than 0.5 in the incoming flow and the lift force needs to be increased or low head moment is generated, so that high-pressure gas is sprayed out through the first slot (4);
the valve of the second fluid chamber (10) is used for being in an open state when the Mach number of the aircraft provided with the control surface is smaller than 0.5 in the incoming flow and lift force is required to be reduced or head-up moment is required to be generated, so that high-pressure gas is sprayed out through the second slot (11);
the valve of the third fluid chamber (8) is used for being in an open state when the Mach number of the aircraft provided with the control surface is larger than 0.5 in the coming flow, lift force is required to be reduced or head-up moment is required to be generated, so that high-pressure gas pushes the semicircular structural body (12) to rotate clockwise, the third slot (13) is opened, and the high-pressure gas is sprayed out of the slot;
the valve of the fourth fluid chamber (9) is used for being in an open state when the Mach number of the aircraft provided with the control surface flies in an incoming flow, the Mach number is larger than 0.5, the lift force is required to be increased or the low head moment is required to be generated, so that the high-pressure gas pushes the semicircular structural body (12) to rotate anticlockwise, the fourth slot (6) is opened, and the high-pressure gas is sprayed out of the slot.
2. The fluid control surface based on annular control and vertical microjet according to claim 1, wherein the third fluid chamber (8) and the fourth fluid chamber (9) are each provided with a small block close to the semicircular structure (12) for limiting the local rotation of the semicircular structure (12).
3. The ring control and vertical microjet based fluid control surface of claim 1, wherein the radius of the semicircular structures (12) is greater than 0.5% and less than 1.5% of the chord length of the aircraft wing.
4. The ring control and vertical microjet based fluid control surface of claim 1, wherein the first slot (4) and the second slot (11) each have a height greater than 0.0125% and less than 0.125% of the chord length of the aircraft wing.
5. The ring control and vertical microjet based fluid control surface according to claim 1, wherein the width of the third slot (13) and the fourth slot (6) are both greater than 0.2% and less than 1.2% of the chord length of the aircraft wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110142145.5A CN113602478B (en) | 2021-02-02 | 2021-02-02 | Fluid control surface based on circulation control and vertical micro-jet flow |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110142145.5A CN113602478B (en) | 2021-02-02 | 2021-02-02 | Fluid control surface based on circulation control and vertical micro-jet flow |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113602478A CN113602478A (en) | 2021-11-05 |
| CN113602478B true CN113602478B (en) | 2023-06-13 |
Family
ID=78303274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110142145.5A Active CN113602478B (en) | 2021-02-02 | 2021-02-02 | Fluid control surface based on circulation control and vertical micro-jet flow |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113602478B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115307861B (en) * | 2022-10-10 | 2023-01-03 | 中国空气动力研究与发展中心低速空气动力研究所 | Flight verification method and flight verification model for torque control performance of jet control surface |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
| CN108349585A (en) * | 2015-09-02 | 2018-07-31 | 杰托普特拉股份有限公司 | Fluid propellant system and thrust and lifting force generator for aircraft |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4474251A (en) * | 1980-12-12 | 1984-10-02 | Hydronautics, Incorporated | Enhancing liquid jet erosion |
| JP4128833B2 (en) * | 2002-09-17 | 2008-07-30 | 三菱マテリアル資源開発株式会社 | Method and system for treating contaminated water and organic exhaust gas |
| US7984879B2 (en) * | 2006-09-06 | 2011-07-26 | Bae Systems Plc | Flow control actuators |
| JP5160098B2 (en) * | 2007-02-01 | 2013-03-13 | 株式会社ベルシオン | Flying boat |
| CN103204238B (en) * | 2013-04-18 | 2015-06-24 | 包绍宸 | Jet rudder surface control system, aircraft using same, and method for controlling aircraft |
| AU2017315790A1 (en) * | 2016-08-25 | 2019-03-14 | Jetoptera, Inc. | Variable geometry thruster |
| CN206318014U (en) * | 2016-12-19 | 2017-07-11 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of trailing edge and the flying wing with it |
| JP6826068B2 (en) * | 2018-03-27 | 2021-02-03 | 株式会社Ｓｕｂａｒｕ | Flow control system, flow control method and aircraft |
| CN111846215B (en) * | 2020-04-30 | 2022-04-22 | 南京航空航天大学 | Tail-pushing type non-control-surface double-duct unmanned aerial vehicle |
-
2021
- 2021-02-02 CN CN202110142145.5A patent/CN113602478B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108349585A (en) * | 2015-09-02 | 2018-07-31 | 杰托普特拉股份有限公司 | Fluid propellant system and thrust and lifting force generator for aircraft |
| CN107176286A (en) * | 2017-05-16 | 2017-09-19 | 华南理工大学 | Folding fixed-wing vertical take-off and landing unmanned aerial vehicle based on double ducted fan dynamical systems |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113602478A (en) | 2021-11-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4459083A (en) | Shapes for rotating airfoils | |
| RU2631728C1 (en) | Combined aircraft equipped with moment compensation device and method for forming additional rotation moment for mentioned aircraft | |
| EP2004484B1 (en) | Aircraft with aerodynamic lift generating device | |
| US4412664A (en) | Family of airfoil shapes for rotating blades | |
| US11485472B2 (en) | Fluid systems that include a co-flow jet | |
| US9908617B2 (en) | Active flow control for transonic flight | |
| US5655737A (en) | Split rudder control system aerodynamically configured to facilitate closure | |
| CN102421666B (en) | For improving the system of aircraft controllability | |
| US4736913A (en) | Fluid flow control device | |
| CN113602478B (en) | Fluid control surface based on circulation control and vertical micro-jet flow | |
| US4387869A (en) | Mono-element combined supercritical high lift airfoil | |
| CN112228242B (en) | Mechanical-pneumatic combined thrust vectoring nozzle with short-distance/vertical take-off and landing functions | |
| US20070029403A1 (en) | Dual point active flow control system for controlling air vehicle attitude during transonic flight | |
| CN113443126A (en) | Full-flow control aircraft based on direct force control principle | |
| US4398687A (en) | Thrust deflector and force augmentor | |
| CN105752319A (en) | Fixed wing aircraft adopting full-DOF (degree of freedom) tail wing and operating method | |
| CN113044205A (en) | Variable wing leading edge camber | |
| US4457480A (en) | Mono-element combined supercritical high lift airfoil | |
| CN114919735A (en) | Active flow control rudder | |
| CN113619772B (en) | Jet-type second grade spout circulation control wing section in coordination | |
| US10967957B2 (en) | Methods and apparatus to extend a leading-edge vortex of a highly-swept aircraft wing | |
| CN114906316A (en) | Supersonic blowing circular quantity trailing edge device and aircraft | |
| CN114735202A (en) | Wing and method for improving control surface control efficiency through blowing | |
| CN114394224A (en) | Bulge high-lift device based on three-dimensional coanda effect and design method thereof | |
| WO2000001576A2 (en) | A device for generating an aerodynamic force by differentially accelerating the fluid in the two sides of a surface |
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 |