CN111532419A - Ring volume control unit for improving supersonic coanda jet flow adhesion pressure ratio - Google Patents
Ring volume control unit for improving supersonic coanda jet flow adhesion pressure ratio Download PDFInfo
- Publication number
- CN111532419A CN111532419A CN202010258942.5A CN202010258942A CN111532419A CN 111532419 A CN111532419 A CN 111532419A CN 202010258942 A CN202010258942 A CN 202010258942A CN 111532419 A CN111532419 A CN 111532419A
- Authority
- CN
- China
- Prior art keywords
- nozzle
- control unit
- jet
- circulation control
- wing
- 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.)
- Pending
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/04—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for blowing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
Abstract
The invention discloses a jet circulation control unit which is arranged at the tail edge of a wing and comprises a first high-pressure air cavity, a second high-pressure air cavity, a first nozzle, a second nozzle and a coanda profile, wherein the first nozzle is communicated with the first high-pressure air cavity and arranged towards the tail of the wing; a coanda profile is arranged between the first nozzle and the second nozzle, and a step structure is arranged between the first nozzle and/or the second nozzle and the coanda profile. By means of the step structure arrangement, a backflow zone is formed at the jet outlet of the nozzle, so that jet expansion is promoted. The shock wave caused by insufficient expansion interacts with the shear layer of the recirculation zone formed by the steps, the effect of insufficient expansion is reduced, separation caused by the shock wave is prevented, and attachment of the jet flow is promoted at a higher pressure ratio.
Description
Technical Field
The invention belongs to the field of jet circulation control of active flow control of an airplane, and particularly relates to a circulation control unit capable of improving the supersonic coanda jet adhesion pressure ratio.
Background
The jet circulation control technology enables compressed air to be ejected along the tangential line of the trailing edge of the control unit through the jet control system, the jet deflects under the action of the coanda effect to form a virtual control surface, the pitch and roll control capacity equivalent to that of the traditional flight control surface is obtained, and the aircraft has the longitudinal and transverse control capacity. The jet velocity of the jet seam outlet is controlled through the total pressure of the adjusting ring volume control unit chamber, the blowing momentum coefficient is changed, the jet intensity is changed, the jet flow direction and the control effect of the virtual control surface are adjusted, and the requirements of different attitude adjustment of the airplane on the control moment are met.
The design idea of the jet flow flight control system is to use an airflow jet control system to realize the flight control without movable parts. Various movable control surfaces on the airplane and related control subsystem components thereof are eliminated, the airplane can be used for next-generation airplanes, the movable control surfaces on the airplane are reduced, and the airplane control system has important effects on reducing weight, using and maintaining cost and mechanism complexity and improving stealth, maneuverability and agility of the airplane. As a key technology which is likely to bring revolutionary changes to the design of future airplanes, the jet control technology without control surface has become a hot spot of research of various military and strong countries.
In order to improve the circulation control efficiency at high subsonic velocity, the jet velocity must be increased, and supersonic coanda jet is adopted. The traditional circulation control unit adopts a contraction nozzle, high-pressure ratio jet flow rapidly expands at the downstream of a nozzle outlet to generate a series of shock waves, and the shock waves interact with external free flow and a coanda surface boundary layer. At higher pressure ratios, the jet is highly under-expanded and the jet separates completely from the coanda surface in the form of shock boundary layer interactions, limiting the application of this technique.
To limit the desorption of the jet due to insufficient expansion, a converging-diverging nozzle is used to spread the gas stream to ambient pressure, expanding the working pressure range over which the coanda jet attaches. However, the shrinkage-expansion nozzle with special profile requirements is processed in a closed and narrow jet flow seam channel (the minimum size is about 0.2mm), the processing difficulty is high, the processing precision cannot be guaranteed, and the consistency of the jet flow nozzle in the extension direction is difficult to guarantee.
Disclosure of Invention
The invention aims to provide a design of a circulation control unit for promoting supersonic coanda jet adhesion, aiming at the problem of shock wave separation caused by insufficient expansion of high-pressure ratio jet under the condition of high subsonic velocity free incoming flow. A backward step is introduced between the jet flow outlet of the nozzle and the coanda profile to form a backflow area, so that the jet flow expansion is promoted, and the shock wave strength caused by insufficient jet flow expansion is reduced; the shock wave interacts with the free shear layer of the reflux area, so that the separation caused by the interaction of the shock wave and the boundary layer of the coanda surface is prevented, and the attachment of the jet flow on the coanda profile under a high pressure ratio is promoted; the step also provides a low pressure region that diverts the jet to the wall surface, promoting adhesion.
The purpose of the invention is realized by the following technical scheme:
a jet circulation control unit is arranged at the tail edge of a wing and comprises a first high-pressure air cavity, a second high-pressure air cavity, a first nozzle, a second nozzle and a coanda profile, wherein the first nozzle is communicated with the first high-pressure air cavity and arranged towards the tail of the wing, the second nozzle is communicated with the second high-pressure air cavity and arranged towards the tail of the wing; a coanda profile is arranged between the first nozzle and the second nozzle, and a step structure is arranged between the first nozzle and/or the second nozzle and the coanda profile.
By means of the step structure arrangement, a backflow zone is formed at the jet outlet of the nozzle, so that jet expansion is promoted. That is, the shock wave caused by the insufficient expansion interacts with the shear layer of the recirculation zone formed by the step, thereby reducing the effect of the insufficient expansion, preventing the separation caused by the shock wave, and promoting the adhesion of the jet flow at a high pressure ratio.
According to a preferred embodiment, the step structure is a backward step, and the gap formed by the connection between the backward step and the coanda profile faces the tail direction of the wing.
According to a preferred embodiment the angle between the rearward step and the tangent of the coanda profile is β and the angle is between 60 ° and 120 °.
According to a preferred embodiment, the step height t of the step structure is set on the basis of the jet pressure ratio of the air flow emitted by the first nozzle and/or the second nozzle.
According to a preferred embodiment, the step height t of the step structure is set on the basis of the nozzle outflow height h of the first nozzle and/or the second nozzle and the standing chamber pressure ratio.
According to a preferred embodiment, the coanda profile is an arcuate structure and the radius of curvature of the coanda profile is R.
According to a preferred embodiment, the first and second nozzles are convergent nozzles or convergent-divergent nozzles.
According to a preferred embodiment, the first high pressure gas chamber and the second high pressure gas chamber are in communication with a high pressure gas generating apparatus.
An airfoil is provided with a jet circulation control unit with the structure.
The aircraft comprises a wing structure, wherein the wing structure is provided with jet circulation control units which are symmetrically arranged along the axis of an aircraft body and have the structure.
The main scheme and the further selection schemes can be freely combined to form a plurality of schemes which are all adopted and claimed by the invention; in the invention, the selection (each non-conflict selection) and other selections can be freely combined. The skilled person in the art can understand that there are many combinations, which are all the technical solutions to be protected by the present invention, according to the prior art and the common general knowledge after understanding the scheme of the present invention, and the technical solutions are not exhaustive herein.
The invention has the beneficial effects that: the invention discloses a jet circulation control unit, which promotes jet expansion and reduces shock wave intensity by introducing a backward step between a jet outlet of a nozzle and a coanda profile, and converts shock wave-boundary layer mutual interference into shock wave-free shear layer interaction, thereby preventing separation caused by the interaction between the shock wave and the boundary layer of the coanda profile and promoting the attachment of jet flow on the coanda profile under a higher pressure ratio.
Drawings
FIG. 1 is a schematic structural view of an airfoil of the present invention;
FIG. 2 is a schematic diagram of a configuration of a circulation control unit according to the present invention;
FIG. 3 is a schematic diagram of the parameters involved in the circulation control unit of the present invention;
FIG. 4 is a schematic flow diagram of a supersonic coanda jet of the present invention;
wherein 100-wing, 101-wing wall, 102-first high pressure air cavity, 103-second high pressure air cavity, 104-coanda profile, 105-first nozzle, 106-second nozzle, 107-backward step.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict.
It should be noted that, in order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are clearly and completely described below, and it is obvious that the described embodiments are some embodiments of the present invention, but not all embodiments.
Thus, the following detailed description of the embodiments of the present invention is not intended to limit the scope of the invention as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations and positional relationships that are conventionally used in the products of the present invention, and are used merely for convenience in describing the present invention and for simplicity in description, but do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not imply that the components are required to be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In addition, it should be noted that, in the present invention, if the specific structures, connection relationships, position relationships, power source relationships, and the like are not written in particular, the structures, connection relationships, position relationships, power source relationships, and the like related to the present invention can be known by those skilled in the art without creative work on the basis of the prior art.
Example 1:
referring to fig. 1 to 4, the present invention discloses a jet circulation control unit. The jet circulation control unit is arranged at the tail edge of the wing 100. The active flow control of the jet circulation is realized by the jet circulation control unit.
Preferably, the jet circulation control unit comprises a first high-pressure air chamber 102, a second high-pressure air chamber 103, a first nozzle 105, a second nozzle 106, and a coanda profile 104.
Preferably, the first high pressure air chamber 102 and the second high pressure air chamber 103 are in communication with a high pressure gas generating apparatus. The device is used for storing and outputting high-pressure gas.
Preferably, the first nozzle 105 is in communication with the first plenum 102, and the first nozzle 105 is disposed toward the aft portion of the wing 100. The second nozzle 106 is communicated with the second high-pressure air cavity 103, and the second nozzle 106 is arranged towards the tail of the wing 100. So that a high velocity ejection of the gas stream is achieved through the first nozzle 105 and/or the second nozzle 106.
Further, the first nozzle 105 and the second nozzle 106 may be a convergent nozzle or a convergent-divergent nozzle.
Preferably, a coanda profile 104 is provided between said first nozzle 105 and said second nozzle 106. And a step structure is arranged between the first nozzle 105 and/or the second nozzle 106 and the coanda profile 104.
By means of the step structure arrangement, a backflow zone is formed at the jet outlet of the nozzle, so that jet expansion is promoted. That is, the shock wave caused by the insufficient expansion interacts with the shear layer of the recirculation zone formed by the step, the effect of the insufficient expansion is mitigated, the separation caused by the shock wave is prevented, and the adhesion of the jet on the coanda profile is promoted at a higher pressure ratio.
Further, the step structure is a backward step 107. The gap formed by the connection between the rearward step 107 and the coanda profile 104 is located towards the aft direction of the wing 100.
Preferably, the step height t of the step structure may be set based on a jet pressure ratio of the air flow ejected from the first nozzle 105 and/or the second nozzle 106.
Preferably, the step height t of the step structure can also be set based on the nozzle outflow height h and the plenum pressure ratio of the first nozzle 105 and/or the second nozzle 106.
Preferably, the rearward step 107 is angled at an angle β to the tangent of the coanda profile 104, the angle being 60 ° to 120 °. The angle beta at the junction cannot be too large, otherwise the area formed by the junction is too small to function as a recirculation zone. The angle beta at the junction cannot be too small, otherwise jet oscillation occurs, which adversely affects the jet stability.
Preferably, the coanda profile 104 is an arcuate structure and the radius of curvature of the coanda profile 104 is R.
Preferably, the wall thickness of the wing wall in the circulation control unit is a, the outlet width of the first nozzle 105 and the second nozzle 106 is h, the height t of the backward step 107, the included angle beta between the backward step 107 and the tangential direction of the coanda profile 104 at the step, and the curvature radius R of the coanda profile. The design of the circulation control unit introducing the backward step has no influence on the proportional relation among the height h of the jet flow outlet of the nozzle, the curvature radius R of the coanda profile and the chord length c of the airfoil.
The backward step is introduced between the jet outlet of the nozzle and the coanda profile to promote jet expansion, reduce shock wave strength and convert shock wave-boundary layer mutual interference into shock wave-free shear layer interaction, so that separation caused by the interaction between the shock wave and the boundary layer of the coanda profile is prevented, and attachment of jet flow on the coanda profile under a high pressure ratio is promoted.
The design of the novel step type circulation control unit corresponding to the invention does not need to modify parameters such as the jet flow outlet height h of the traditional circulation control unit nozzle, the curvature radius R of the coanda profile and the like. Through the height and the included angle of the adjustment stair structure, the jet flow can be adjusted to keep the maximum pressure ratio critical value attached, the use of a contraction-expansion nozzle with the profile machining precision and the expansion direction machining precision which cannot be guaranteed can be avoided, and the backward stair structure is simple, easy to process and low in cost.
The invention also discloses an airfoil 100, and the airfoil 100 is provided with the jet circulation control unit with the structure. As shown in fig. 1, the airfoil 100 performs ejection of high-speed gas flow through a first nozzle 105 or a second nozzle 106, respectively, so as to change the surface pressure distribution of the airfoil 100, thereby generating an operating torque to realize control of the aircraft. Thereby avoiding the use of various traditional movable control surface structures and reducing the resistance of the wings.
The invention also discloses an airplane. The aircraft comprises a wing 100 structure, and the wing 100 structure is provided with a jet circulation control unit which is symmetrically arranged along the axis of the aircraft body and has the structure. The aircraft uses the wing 100 provided with the annular quantity control unit disclosed in the foregoing, so that the flight resistance is greatly reduced, the flight speed of the aircraft is improved, and aviation fuel is saved. In addition, as the wings of the airplane are not provided with various movable control surface structures, the radar scattering area is reduced, and the stealth effect of the airplane is further improved.
The foregoing basic embodiments of the invention and their various further alternatives can be freely combined to form multiple embodiments, all of which are contemplated and claimed herein. In the scheme of the invention, each selection example can be combined with any other basic example and selection example at will. Numerous combinations will be known to those skilled in the art.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A jet circulation control unit is characterized in that the jet circulation control unit is arranged at the tail edge of a wing,
the jet circulation control unit comprises a first high-pressure air cavity, a second high-pressure air cavity, a first nozzle, a second nozzle and a coanda profile,
the first nozzle is communicated with the first high-pressure air cavity, the first nozzle is arranged towards the tail of the wing, the second nozzle is communicated with the second high-pressure air cavity, and the second nozzle is arranged towards the tail of the wing;
a coanda profile is arranged between the first nozzle and the second nozzle, and a step structure is arranged between the first nozzle and/or the second nozzle and the coanda profile.
2. The unit of claim 1, wherein the step structure is a rearward step, and the gap formed by the connection between the rearward step and the coanda profile is oriented aft of the airfoil.
3. The jet circulation control unit of claim 2, wherein said rearward step includes an angle β with the tangent of the coanda profile, said angle being between 60 ° and 120 °.
4. The fluid circulation control unit of claim 1, wherein the step height t of the step structure is set based on a fluid pressure ratio of the air flow ejected from the first nozzle and/or the second nozzle.
5. A fluidic circuit volume control unit as claimed in claim 1, characterized in that the step height t of the step structure is set on the basis of the nozzle outflow height h of the first nozzle and/or the second nozzle and the standing chamber pressure ratio.
6. The jet circulation control unit of claim 1, wherein said coanda profile is arcuate in configuration and has a radius of curvature R.
7. The fluidic circuit volume control unit of claim 1, wherein the first nozzle and the second nozzle are convergent nozzles or convergent-divergent nozzles.
8. The jet circulation control unit of claim 1, wherein the first and second high pressure air chambers are in communication with a high pressure gas generating device.
9. An airfoil, characterized in that the airfoil is provided with a jet circulation control unit according to any one of claims 1 to 8.
10. An aircraft, characterized in that the aircraft comprises a wing structure, and the wing structure is provided with the jet circulation control unit as claimed in any one of claims 1 to 8, which is symmetrically arranged along the axis of the aircraft fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010258942.5A CN111532419A (en) | 2020-04-03 | 2020-04-03 | Ring volume control unit for improving supersonic coanda jet flow adhesion pressure ratio |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010258942.5A CN111532419A (en) | 2020-04-03 | 2020-04-03 | Ring volume control unit for improving supersonic coanda jet flow adhesion pressure ratio |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111532419A true CN111532419A (en) | 2020-08-14 |
Family
ID=71952306
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010258942.5A Pending CN111532419A (en) | 2020-04-03 | 2020-04-03 | Ring volume control unit for improving supersonic coanda jet flow adhesion pressure ratio |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111532419A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112295803A (en) * | 2020-09-25 | 2021-02-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet device with continuously adjustable nozzle height |
| CN112572773A (en) * | 2020-12-17 | 2021-03-30 | 中国人民解放军国防科技大学 | Wing lift increasing device and wing lift increasing method |
| CN113942651A (en) * | 2021-09-21 | 2022-01-18 | 西北工业大学 | Novel flight control device of SACCON type aircraft |
| CN114056551A (en) * | 2022-01-12 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual wing belly flap and wing body fusion airplane, constant air blowing method and variable-angle air blowing method |
| CN115195994A (en) * | 2022-07-14 | 2022-10-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow enhanced type combined control surface, aircraft and aircraft control method |
| CN115195996A (en) * | 2022-07-14 | 2022-10-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Airborne lightweight dual-channel circulation control unit |
| CN115489722A (en) * | 2022-11-07 | 2022-12-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Stepless switching control method and device for control surface of aircraft, aircraft and medium |
| CN116923688A (en) * | 2023-09-15 | 2023-10-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow circulation control device |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2939650A (en) * | 1957-02-07 | 1960-06-07 | Sebac Nouvelle Sa | Airplane wing with boundary layer control |
| GB869065A (en) * | 1957-02-07 | 1961-05-25 | Sebac Nouvelle Sa | Improvements in or relating to aircraft wings |
| US4664345A (en) * | 1983-11-24 | 1987-05-12 | Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschrankter Haftung | Method for stabilizing laminar separated boundary layers |
| US5133519A (en) * | 1989-04-21 | 1992-07-28 | Board Of Trustees Operating Michigan State University | Drag reduction method and surface |
| US7861977B1 (en) * | 2006-03-13 | 2011-01-04 | The United States Of America As Represented By The Secretary Of The Navy | Adaptive material actuators for Coanda effect circulation control slots |
| CN102167163A (en) * | 2011-03-25 | 2011-08-31 | 北京航空航天大学 | Synthetic jet circulation control method for increasing wing lifting force |
| CN104204541A (en) * | 2012-01-12 | 2014-12-10 | 依必安-派特圣乔根有限责任两合公司 | Axial or diagonal fan with trip edge on the rotor blade suction side |
| 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 |
-
2020
- 2020-04-03 CN CN202010258942.5A patent/CN111532419A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2939650A (en) * | 1957-02-07 | 1960-06-07 | Sebac Nouvelle Sa | Airplane wing with boundary layer control |
| GB869065A (en) * | 1957-02-07 | 1961-05-25 | Sebac Nouvelle Sa | Improvements in or relating to aircraft wings |
| US4664345A (en) * | 1983-11-24 | 1987-05-12 | Messerschmitt-Boelkow-Blohm Gesellschaft Mit Beschrankter Haftung | Method for stabilizing laminar separated boundary layers |
| US5133519A (en) * | 1989-04-21 | 1992-07-28 | Board Of Trustees Operating Michigan State University | Drag reduction method and surface |
| US7861977B1 (en) * | 2006-03-13 | 2011-01-04 | The United States Of America As Represented By The Secretary Of The Navy | Adaptive material actuators for Coanda effect circulation control slots |
| CN102167163A (en) * | 2011-03-25 | 2011-08-31 | 北京航空航天大学 | Synthetic jet circulation control method for increasing wing lifting force |
| CN104204541A (en) * | 2012-01-12 | 2014-12-10 | 依必安-派特圣乔根有限责任两合公司 | Axial or diagonal fan with trip edge on the rotor blade suction side |
| 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 |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112295803A (en) * | 2020-09-25 | 2021-02-02 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet device with continuously adjustable nozzle height |
| CN112295803B (en) * | 2020-09-25 | 2022-04-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet device with continuously adjustable nozzle height |
| CN112572773A (en) * | 2020-12-17 | 2021-03-30 | 中国人民解放军国防科技大学 | Wing lift increasing device and wing lift increasing method |
| CN113942651A (en) * | 2021-09-21 | 2022-01-18 | 西北工业大学 | Novel flight control device of SACCON type aircraft |
| CN114056551A (en) * | 2022-01-12 | 2022-02-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual wing belly flap and wing body fusion airplane, constant air blowing method and variable-angle air blowing method |
| CN114056551B (en) * | 2022-01-12 | 2022-04-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual wing belly flap and wing body fusion airplane, constant air blowing method and variable-angle air blowing method |
| CN115195994A (en) * | 2022-07-14 | 2022-10-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow enhanced type combined control surface, aircraft and aircraft control method |
| CN115195996A (en) * | 2022-07-14 | 2022-10-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Airborne lightweight dual-channel circulation control unit |
| CN115489722A (en) * | 2022-11-07 | 2022-12-20 | 中国空气动力研究与发展中心低速空气动力研究所 | Stepless switching control method and device for control surface of aircraft, aircraft and medium |
| CN116923688A (en) * | 2023-09-15 | 2023-10-24 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow circulation control device |
| CN116923688B (en) * | 2023-09-15 | 2023-12-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Jet flow circulation control device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111532419A (en) | Ring volume control unit for improving supersonic coanda jet flow adhesion pressure ratio | |
| CN108349585B (en) | Fluid propulsion system and thrust and lift generator for an aircraft | |
| US9180974B2 (en) | Aircraft with an integral aerodynamic configuration | |
| US4463772A (en) | Flush inlet for supersonic aircraft | |
| US8240125B2 (en) | Thrust vectoring system and method | |
| US2799989A (en) | Variable area jet nozzle | |
| US4343446A (en) | V/STOL Aircraft | |
| CN111470032B (en) | Pneumatic composite control tailless flying wing layout unmanned aerial vehicle and control method thereof | |
| CN104632411A (en) | Internal waverider-derived turbine base combined dynamic gas inlet adopting binary variable-geometry manner | |
| EP3112650B1 (en) | Inlet flow restrictor | |
| US8997454B2 (en) | Turbofan engine noise suppression using fan flow deflector | |
| US4387869A (en) | Mono-element combined supercritical high lift airfoil | |
| US20050258307A1 (en) | Jet engine nacelle for a supersonic aircraft | |
| Das et al. | Fluidic Thrust Vector Control of Aerospace Vehicles: State-of-the-Art Review and Future Prospects | |
| US4398687A (en) | Thrust deflector and force augmentor | |
| CN113443126A (en) | Full-flow control aircraft based on direct force control principle | |
| US20170197708A1 (en) | Nozzles for a reaction drive blade tip with turning vanes | |
| CN114087087B (en) | Multi-principle multi-mode pneumatic thrust vectoring nozzle and control method | |
| US4457480A (en) | Mono-element combined supercritical high lift airfoil | |
| EP1557356B1 (en) | Aircraft, particularly small aircraft, having a propulsion system including a plurality of pulse detonation engines (PDEs) | |
| CN108412635B (en) | Binary direct-injection oblique shock wave thrust vectoring nozzle | |
| US3414195A (en) | Sweeping jet wing aircraft with actuator strip flap and emergency vtol capability | |
| US20240052799A1 (en) | Jet vectoring apparatus | |
| CN214502251U (en) | Missile lateral jet flow control device with variable wedge-shaped wings | |
| Mace et al. | Fighter airframe/propulsion integration-A McDonnell Aircraft perspective |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200814 |