CN105346705A - Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof - Google Patents
Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof Download PDFInfo
- Publication number
- CN105346705A CN105346705A CN201510912300.1A CN201510912300A CN105346705A CN 105346705 A CN105346705 A CN 105346705A CN 201510912300 A CN201510912300 A CN 201510912300A CN 105346705 A CN105346705 A CN 105346705A
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- rigid plate
- aerofoil
- curvature
- 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
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
Abstract
The invention provides a self-adaptive wing with a variable wing surface curvature. The self-adaptive wing is connected with a control system of an aircraft where the self-adaptive wing is installed and comprises a metal wing framework arranged at the lower part and a support structure arranged on the framework, wherein an adjustable curved surface is arranged on an upper wing surface of the wing; an actuation device is arranged at the interior of the wing and is connected with the adjustable curved surface; the actuation device is connected with a control system of the wing. Through the wing structure replacing the conventional flaperon structure and a control manner of the aircraft thereof, the high-speed performance and the low-speed performance of the aircraft can be balanced; the rising force of the wing is adjusted by changing the curvature of the upper wing surface of the wing so as to adapt to various flight situations.
Description
Technical field
The present invention relates to aircraft wing design field, be specially the adaptive wing of aerofoil variable curvature and the control mode of aircraft thereof.
Background technology
Contemporary aircraft can operational applications in speed and altitude range widely, this needs the aerodynamic feature of aircraft wing lifting surface change and control.Conventional aircraft generally adopts conventional trailing edge flap, to meet lift demand when taking off and land.But it is not enough to aeroperformance under meticulousr adjusting and optimizing aircraft cruising condition and the aeroperformance of aircraft under other states (as landing of taking off).The sixties in last century, aircraft can be made in flight course once respectively to be thought to balance high low-speed performance ﹑ by pivot change wing setting degree with the variable swept back wing technology adapting to different flight state and to improve the best solution of short take-off and landing (STOL) ability, and develop the many types of aircrafts such as F-14, but because its wing structure is too complicated, by the restriction of material technology, wing structure weight is not well controlled, and is finally abandoned.
Current solution changes airfoil lift area and trailing edge sinuousness by regaining trailing edge flap on a small quantity, with realize fly part of cruising during reduce resistance.At present, the roll guidance aerofoil of conventional aircraft is generally part chord length aileron, and its advantage is that mechanism is simple, but it takies wing exhibition to space comparatively greatly, limits traditional lift-rising performance of aircraft.And in order to meet the stall feature request of aircraft, the wing of mounting portion chord length aileron needs larger wing twist angle, this can cause aircraft induced drag when cruising to become large, reduces the 1ift-drag ratio of aircraft.And the efficiency of deflection to aircraft roll guidance of part chord length aileron is relatively low, particularly when aileron movement angle is larger, its driving efficiency sharply declines.
Summary of the invention
The object of this invention is to provide a kind of can trimmed flight device high low-speed performance, substitute traditional wing structure of flaperon structure and the control mode of aircraft thereof, a kind of adaptive wing of aerofoil variable curvature regulates airfoil lift to adapt to the Novel aerofoil of various flight progress by changing wing top airfoil curvature.
To achieve the above object of the invention, the technical solution adopted in the present invention is:
A kind of adaptive wing of aerofoil variable curvature, it is connected with the control system of place aircraft, the metal machine wing skeleton ﹑ that it comprises bottom is arranged on the supporting construction on skeleton, the top airfoil of wing is provided with adjustable curved surface, adjustable curved surface is that arcwall face can produce deformation change curvature, wing inside is provided with acting device and is connected with adjustable curved surface, and the scalable motion of acting device changes the curvature of adjustable curved surface, and acting device is connected with the control system of wing.
Adjustable curved surface comprises rigid plate, elasticity covering in certain radian, rigid plate at least comprises two pieces, the front portion of front rigid plate is connected with wing nose, rear portion is pressed in a rear rigid plate front portion, the rigid plate rear end of rearmost is connected with rear airfoil end, elasticity covering is coated on above rigid plate, and its edge is connected with wing, and the acting device of wing inside is connected with rigid plate.
Further, sliding block joint above the tail end inner face of the front rigid plate of adjustable curved surface and the leading portion of rear rigid plate, when adjustable surface location is the highest still there is certain intersection in two adjacent rigid plate.
The diverse location of supporting construction being provided with multiple acting device is distributed in below adjustable curved surface, each acting device is all connected with control system, acting device comprises pressurized strut, pressurized strut comprises expansion link, and the rigid plate that expansion link upper end is provided with small-sized turning cylinder and adjustable curved surface is hinged.
Further, the end of expansion link and rigid plate is hinged.
Between adjacent rigid plate, lap position place is provided with sliding track lock buckle structure, forward-backward rigidity plate keeps being flexibly connected by sliding track lock buckle structure, when rigid plate is moved with acting device, being limited direction of slip and the distance of two adjacent rigid plate by sliding track lock buckle structure, making two rigid plate can not produce gap when adjusting.
Further, sliding track lock buckle structure comprises Xian Wei Qi ﹑ Gu and Dings Duan ﹑ slide shaft, and limiting device is arranged on rigid plate rear end, front, limiting device is provided with hole, slide shaft can through hole and sliding block joint with it, and fixed end is fixedly installed rigid plate front end in the wings, and it is connected with slide shaft.
Elasticity covering is integral type flexible covering, to ensure the smooth of upper surface of the airfoil, wing and the front junction of flexible covering are fixed type, namely flexible covering front end is connected directly between on wing, and rear junction adopts mechanical position limitation card structure guarantee flexible covering can shrink from wing interior La Shen ﹑.During work, acting device drives its institute to rigid plate front portion and a upper rigid plate rear portion associated movement, and then causes the change of top airfoil elasticity covering curvature and wing thickness.
Described control system is connected with the control system of aircraft, and it is provided with programmable PLC, control module, and PLC is connected with acting device by control module.
For when aircraft low-speed operations, aerofoil surface bent thickness becomes large; When aircraft accelerates flight, aerofoil surface curvature thickness reduces gradually, until high-speed flight state, to realize the constant of aircraft Gong Jiao ﹑ lift in larger speed variation.Meanwhile, can be poor by the differential generation lift changing aerofoil surface curvature thickness, produce rolling moment, while guarantee wing aerodynamic efficiency, realize aileron effect.
Before application, under needing repeatedly wind tunnel test to measure friction speed v ﹑ density of air ρ, the wing configuration of wing when each state and difference make wing configuration corresponding to moving cell elongation and lift size to this wing.Determine corresponding relation and parameter, and flight control can according to state of flight information realization Automatic adjusument wing curved surface in follow-up application to realize wing to be stored into control system inside.
Control mode with the aircraft of this wing:
1. aircraft before take-off, wing top-surface camber is bent to best wing configuration when taking off by control system, and namely the elongation quantitative change of acting device is large, makes airfoil lift coefficient Cl and area S become large.Strengthened gradually by throttle in runway, after aircraft arrives certain speed (relevant with take-off weight), aircraft, slightly larger than gravity suffered by aircraft, " is mentioned ", is made aircraft liftoff with the relatively low elevation angle by the lift that wing produces.Process of climbing medium velocity increases, and wing makes corresponding adjustment according to control system, ensures that lift is constant.
2. mush after predetermined altitude, upper surface of the airfoil degree of crook reduces, and becomes best wing configuration when cruising, makes aircraft keep level-flight attitude under optimum aerodynamic conditions.
3., when cruising, aircraft is when running into the situation that density of air ρ Gai Bian ﹑ flying speed v changes, and wing regulates the optimum wing configuration under aerofoil curvature to conditions present automatically according to the setting of control system, and then aircraft efficient stable is flown.
4. when aircraft needs to do horizontal adjustment, flight control system suitably increases or reduces the elongation of acting device of both sides wing symmetrical cell, both sides wing curvature increases respectively or reduces, and it is poor that left and right sides wing produces lift, and then realizes the crosswise joint to aircraft.
5. during landing, reduce with throttle Jian little ﹑ speed, wing top airfoil curvature increases wing thickness and increases, and wing changes into optimum regime during landing gradually.Before landing, wing, from main regulation, precisely controls descending speed, finally makes aircraft with low speed grease it in.
Its principle is, the acting device start that wing inner vertical is installed changes profile geometric shape and the thickness of wing, and then causes the change of wing top airfoil curvature (airfoil lift coefficient Cl) and wing top airfoil area (wing area S).From lift formula F=1/2 ρ v2SCl(lift=1/2 × current density × speed square × wing area × lift coefficient), the change of wing top airfoil curvature (airfoil lift coefficient Cl) and wing top airfoil area (wing area S) can cause the change of airfoil lift, finally realize airfoil lift adjustment in a big way, to make wing can the various state of flight of self adaptation.And the most external of wing installs flexible covering, during to ensure control apparatus start, airfoil outer surface is smooth.When aircraft low-speed operations, wing thickness becomes causes greatly wing top airfoil curvature and area to become large; When accelerating flight, wing top airfoil curvature and area reduce gradually, until high-speed flight state, to realize the Automatic adjusument of aircraft Gong Jiao ﹑ lift in larger speed variation.Meanwhile, by change both sides wing top airfoil curvature and area poor to different directions differential generation lift, produce rolling moment, while ensureing wing aerodynamic efficiency, realize aileron effect.This wing inside only retain controlled by flight control system make moving cell and related sensor, the geometric configuration of its start control break wing profile, when keeping excellent aerodynamic performance, realize the control to aircraft, the final flaperon structure replacing conventional aircraft.
Beneficial effect of the present invention is:
The adaptive wing of this aerofoil variable curvature has abandoned traditional Fu Yi ﹑ wing flap and slat completely, the drive mechanism of the flap wing ﹑ aileron of numerous complicated in traditional wing and little aerofoil are removed, by the geometric configuration of the control system control break wing profile of aircraft, and then realize the control to aircraft wing lift.Both meet the aerodynamic performance requirement to wing under different condition, under each state, keep again optimum pneumatic efficiency.It is compared with traditional wing, and the structure design of its adjustable curved surface is more rationally perfect, and control mode is more accurately careful, can significantly improve the pneumatic efficiency of aircraft, strengthen flight control effort, and actv. alleviates wing structure weight, increases mission payload.
Accompanying drawing explanation
Fig. 1 is the wing flap aileron structural representation in conventional aircraft;
Fig. 2 is patent Example cross section structure schematic diagram of the present invention;
Fig. 3 is that patent Example wing of the present invention is along wing exhibition to structural representation;
Fig. 4 is patent Example plan structure schematic diagram of the present invention;
Fig. 5 is patent Example latching system structural representation of the present invention;
Fig. 6 is basic functional principle constitution diagram of the present invention.
Detailed description of the invention
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.Embodiment described in following exemplary embodiment does not represent all embodiments consistent with the present invention.On the contrary, they only with as in appended claims describe in detail, the example of device that aspects more of the present invention are consistent.
A kind of adaptive wing of aerofoil variable curvature as shown in drawings, it is connected with the control system of place aircraft, the metal machine wing skeleton ﹑ that it comprises bottom is arranged on the supporting construction 1 on skeleton, the top airfoil of wing is provided with adjustable curved surface, adjustable curved surface is that arcwall face can produce deformation change curvature, wing inside is provided with acting device 2 and is connected with adjustable curved surface, and the scalable motion of acting device 2 changes the curvature of adjustable curved surface, and acting device 2 is connected with the control system of wing.
Adjustable curved surface comprises rigid plate 3, elasticity covering 4 in certain radian, rigid plate 3 at least comprises two pieces, this embodiment is for three pieces, the front portion of front rigid plate is connected with wing nose, and rear portion is pressed in a rear rigid plate front portion, and the rear portion of middle one piece of rigid plate is pressed in the rigid plate front portion of rearmost, the rigid plate rear end of rearmost is connected with rear airfoil end, elasticity covering 4 is coated on above rigid plate 3, and its edge is connected with wing, and the acting device 2 of wing inside is connected with rigid plate.
Further, sliding block joint above the tail end inner face of the front rigid plate of adjustable curved surface and the leading portion of rear rigid plate, when adjustable surface location is the highest still there is certain intersection in two adjacent rigid plate 3.
The diverse location of supporting construction 1 being provided with multiple acting device 2 is distributed in below adjustable curved surface, each acting device 2 is all connected with control system, acting device 2 comprises pressurized strut, pressurized strut comprises expansion link, and the rigid plate 3 that expansion link upper end is provided with small-sized turning cylinder and adjustable curved surface is hinged.
Further, the end of expansion link and rigid plate 3 is hinged.
Between adjacent rigid plate, lap position place is provided with sliding track lock buckle structure 5, forward-backward rigidity plate keeps being flexibly connected by sliding track lock buckle structure 5, when rigid plate 3 is moved with acting device 2, being limited direction of slip and the distance of two adjacent rigid plate by sliding track lock buckle structure 5, making two rigid plate can not produce gap when adjusting.
Further, sliding track lock buckle structure 5 comprises limiting device 6 ﹑ fixed end 7 ﹑ slide shaft 8, limiting device 6 is fixedly installed on rigid plate rear end, front, limiting device 6 is provided with hole, slide shaft 8 can through hole and sliding block joint with it, fixed end 7 is fixedly installed rigid plate front bottom end in the wings, and it is connected with slide shaft 8.
Elasticity covering 4 is integral type flexible covering, to ensure the smooth of upper surface of the airfoil, wing and the front junction of flexible covering are fixed type, namely flexible covering front end is connected directly between on wing, and rear junction adopts mechanical position limitation card structure guarantee flexible covering can shrink from wing interior La Shen ﹑.During work, acting device drives its institute to rigid plate front portion and a upper rigid plate rear portion associated movement, and then causes the change of top airfoil elasticity covering curvature and wing thickness.
Described control system is connected with the control system of aircraft, and it is provided with programmable PLC, control module, and PLC is connected with acting device by control module, control system can adopt prior art, so that data collection process can be realized, according to formulae discovery, and make control command.
For when aircraft low-speed operations, aerofoil surface bent thickness becomes large; When aircraft accelerates flight, aerofoil surface curvature thickness reduces gradually, until high-speed flight state, to realize the constant of aircraft Gong Jiao ﹑ lift in larger speed variation.Meanwhile, lift can be produced by differential (differential is exactly that aerofoil dynamic amplitude in two, left and right is different) changing aerofoil surface curvature thickness poor, produce rolling moment, while guarantee wing aerodynamic efficiency, realize aileron effect.
Before application, under needing repeatedly wind tunnel test to measure friction speed v ﹑ density of air ρ, the wing configuration of wing when each state and difference make wing configuration corresponding to moving cell elongation and lift size to this wing.Determine corresponding relation and parameter, and flight control can according to state of flight information realization Automatic adjusument wing curved surface in follow-up application to realize wing to be stored into control system inside.
Control mode with the aircraft of this wing:
1. aircraft before take-off, wing top-surface camber is bent to best wing configuration when taking off by control system, and namely the elongation quantitative change of acting device is large, makes airfoil lift coefficient Cl and area S become large.Strengthened gradually by throttle in runway, after aircraft arrives certain speed (relevant with take-off weight), aircraft, slightly larger than gravity suffered by aircraft, " is mentioned ", is made aircraft liftoff with the relatively low elevation angle by the lift that wing produces.Process of climbing medium velocity increases, and wing makes corresponding adjustment according to control system, ensures that lift is constant.
2. mush after predetermined altitude, upper surface of the airfoil degree of crook reduces, and becomes best wing configuration when cruising, makes aircraft keep level-flight attitude under optimum aerodynamic conditions.
3., when cruising, aircraft is when running into the situation that density of air ρ Gai Bian ﹑ flying speed v changes, and wing regulates the optimum wing configuration under aerofoil curvature to conditions present automatically according to the setting of control system, and then aircraft efficient stable is flown.
4. when aircraft needs to do horizontal adjustment, flight control system suitably increases or reduces the elongation of acting device of both sides wing symmetrical cell, both sides wing curvature increases respectively or reduces, and it is poor that left and right sides wing produces lift, and then realizes the crosswise joint to aircraft.
5. during landing, reduce with throttle Jian little ﹑ speed, wing top airfoil curvature increases wing thickness and increases, and wing changes into optimum regime during landing gradually.Before landing, wing, from main regulation, precisely controls descending speed, finally makes aircraft with low speed grease it in.
Its principle is, the acting device start that wing inner vertical is installed changes profile geometric shape and the thickness of wing, and then causes the change of wing top airfoil curvature (airfoil lift coefficient Cl) and wing top airfoil area (wing area S).From lift formula F=1/2 ρ v2SCl(lift=1/2 × current density × speed square × wing area × lift coefficient), the change of wing top airfoil curvature (airfoil lift coefficient Cl) and wing top airfoil area (wing area S) can cause the change of airfoil lift, finally realize airfoil lift adjustment in a big way, to make wing can the various state of flight of self adaptation.And the most external of wing installs flexible covering, during to ensure control apparatus start, airfoil outer surface is smooth.When aircraft low-speed operations, wing thickness becomes causes greatly wing top airfoil curvature and area to become large; When accelerating flight, wing top airfoil curvature and area reduce gradually, until high-speed flight state, to realize the Automatic adjusument of aircraft Gong Jiao ﹑ lift in larger speed variation.Meanwhile, by change both sides wing top airfoil curvature and area poor to different directions differential generation lift, produce rolling moment, while ensureing wing aerodynamic efficiency, realize aileron effect.This wing inside only retain controlled by flight control system make moving cell and related sensor, the geometric configuration of its start control break wing profile, when keeping excellent aerodynamic performance, realize the control to aircraft, the final flaperon structure replacing conventional aircraft.
Above-described embodiment of the present invention, does not form limiting the scope of the present invention.Any amendment done within the spirit and principles in the present invention, equivalent replacement and improvement etc., all should be included within protection scope of the present invention.
Claims (8)
1. the adaptive wing of an aerofoil variable curvature, it is connected with the control system of place aircraft, the metal machine wing skeleton ﹑ that it comprises bottom is arranged on skeleton upper support structure, it is characterized in that: the top airfoil of wing is provided with adjustable curved surface, adjustable curved surface is that arcwall face can produce deformation change curvature, wing inside is provided with acting device and is connected with adjustable curved surface, the scalable motion of acting device changes the curvature of adjustable curved surface, acting device is connected with the control system of wing, described adjustable curved surface comprises the rigid plate in certain radian, elasticity covering, rigid plate at least comprises two pieces, the front portion of front rigid plate is connected with wing nose, rear portion is pressed in a rear rigid plate front portion, the rigid plate rear end of rearmost is connected with rear airfoil end, elasticity covering is coated on above rigid plate, its edge is connected with wing, the acting device of wing inside is connected with rigid plate.
2. the adaptive wing of aerofoil variable curvature according to claim 1, it is characterized in that: sliding block joint above the tail end inner face of the front rigid plate of adjustable curved surface and the leading portion of rear rigid plate, when adjustable surface location is the highest, two adjacent rigid plate still exist certain intersection.
3. the adaptive wing of aerofoil variable curvature according to claim 1, it is characterized in that: the diverse location of supporting construction is provided with multiple acting device and is distributed in below adjustable curved surface, each acting device is all connected with control system, acting device comprises hydraulic actuator, hydraulic actuator comprises expansion link, and the rigid plate that expansion link upper end is provided with small-sized turning cylinder and adjustable curved surface is hinged.
4. the adaptive wing of aerofoil variable curvature according to claim 3, is characterized in that, the end of expansion link and rigid plate is hinged.
5. the adaptive wing of aerofoil variable curvature according to claim 1, it is characterized in that: between adjacent rigid plate, lap position place is provided with sliding track lock buckle structure, forward-backward rigidity plate keeps being flexibly connected by sliding track lock buckle structure, when rigid plate is moved with acting device, being limited direction of slip and the distance of two adjacent rigid plate by sliding track lock buckle structure, making two rigid plate can not produce gap when adjusting.
6. the adaptive wing of aerofoil variable curvature according to claim 5, it is characterized in that: sliding track lock buckle structure comprises Xian Wei Qi ﹑ Gu and Dings Duan ﹑ slide shaft, limiting device is arranged on rigid plate rear end, front, limiting device is provided with hole, slide shaft can through hole and sliding block joint with it, fixed end is fixedly installed rigid plate front end in the wings, and it is connected with slide shaft.
7. the adaptive wing of aerofoil variable curvature according to claim 1, it is characterized in that: elasticity covering is integral type flexible covering, to ensure the smooth of upper surface of the airfoil, wing and the front junction of flexible covering are fixed type, namely flexible covering front end is connected directly between on wing, and rear junction adopts mechanical position limitation card structure guarantee flexible covering can shrink from wing interior La Shen ﹑.
8. a control mode for the adaptive wing of aerofoil variable curvature, is characterized in that: for when aircraft low-speed operations, and aerofoil surface bent thickness becomes large; When aircraft accelerates flight, aerofoil surface curvature thickness reduces gradually, until high-speed flight state, to realize the constant of aircraft Gong Jiao ﹑ lift in larger speed variation, meanwhile, poor by the differential generation lift changing aerofoil surface curvature thickness, produce rolling moment, while guarantee wing aerodynamic efficiency, realize aileron effect, concrete operations flow process is as follows:
1. aircraft before take-off, wing top-surface camber is bent to best wing configuration when taking off by control system, namely the elongation quantitative change of acting device is large, airfoil lift coefficient Cl and area S is made to become large, in runway, throttle is strengthened gradually, after aircraft arrives certain speed (relevant with take-off weight), the lift that wing produces is slightly larger than gravity suffered by aircraft, aircraft " is mentioned ", make aircraft liftoff with the relatively low elevation angle, process of climbing medium velocity increases, and wing makes corresponding adjustment according to control system, ensures that lift is constant;
2. mush after predetermined altitude, upper surface of the airfoil degree of crook reduces, and becomes best wing configuration when cruising, makes aircraft keep level-flight attitude under optimum aerodynamic conditions;
3., when cruising, aircraft is when running into the situation that density of air ρ Gai Bian ﹑ flying speed v changes, and wing regulates the optimum wing configuration under aerofoil curvature to conditions present automatically according to the setting of control system, and then aircraft efficient stable is flown;
4. when aircraft needs to do horizontal adjustment, flight control system suitably increases or reduces the elongation of acting device of both sides wing symmetrical cell, both sides wing curvature increases respectively or reduces, and it is poor that left and right sides wing produces lift, and then realizes the crosswise joint to aircraft;
5., during landing, subtract little ﹑ speed with throttle and reduce, wing top airfoil curvature increases wing thickness and increases, and wing changes into optimum regime during landing gradually, and before landing, wing, from main regulation, precisely controls descending speed, finally makes aircraft with low speed grease it in.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510912300.1A CN105346705A (en) | 2015-12-11 | 2015-12-11 | Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510912300.1A CN105346705A (en) | 2015-12-11 | 2015-12-11 | Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105346705A true CN105346705A (en) | 2016-02-24 |
Family
ID=55322822
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510912300.1A Pending CN105346705A (en) | 2015-12-11 | 2015-12-11 | Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105346705A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110539876A (en) * | 2019-09-03 | 2019-12-06 | 中国航空工业集团公司西安飞机设计研究所 | Wing with variable wing profile and airplane |
| CN110682994A (en) * | 2019-07-29 | 2020-01-14 | 浙江海洋大学 | Ship easy-to-move device |
| CN111191326A (en) * | 2019-12-27 | 2020-05-22 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating hydraulic flow demand of flight control actuator by airplane |
| CN112340016A (en) * | 2020-11-23 | 2021-02-09 | 西湖大学 | Wing structure, wing structure and flapping wing type aircraft |
| CN112607015A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Reconfigurable modular self-adaptive variant aircraft |
| CN112644688A (en) * | 2020-12-31 | 2021-04-13 | 中国商用飞机有限责任公司 | Aircraft wing |
| CN114194375A (en) * | 2021-12-27 | 2022-03-18 | 成都市鸿侠科技有限责任公司 | Airplane flap slide rail with self-locking function and machining process thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR922899A (en) * | 1946-01-14 | 1947-06-20 | Device for varying the curvature of airfoils, stabilizers and auxiliary surfaces of aerial locomotion devices | |
| WO2003082671A1 (en) * | 2002-03-28 | 2003-10-09 | Richard Linsley-Hood | Aerofoil with variable camber |
| CN102066196A (en) * | 2008-02-12 | 2011-05-18 | 塔莱斯公司 | Method for actively deforming an aerodynamic profile |
| CN202147840U (en) * | 2011-05-27 | 2012-02-22 | 孙玉国 | Wing with adjustable radian |
| CN102673774A (en) * | 2012-05-18 | 2012-09-19 | 北京理工大学 | Deforming wing mechanism |
| CN104379445A (en) * | 2012-04-30 | 2015-02-25 | 空中客车营运有限公司 | Morphing aerofoil |
| CN205273838U (en) * | 2015-12-11 | 2016-06-01 | 刘文浩 | Adaptive wing of airfoil variable curvature |
-
2015
- 2015-12-11 CN CN201510912300.1A patent/CN105346705A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR922899A (en) * | 1946-01-14 | 1947-06-20 | Device for varying the curvature of airfoils, stabilizers and auxiliary surfaces of aerial locomotion devices | |
| WO2003082671A1 (en) * | 2002-03-28 | 2003-10-09 | Richard Linsley-Hood | Aerofoil with variable camber |
| CN102066196A (en) * | 2008-02-12 | 2011-05-18 | 塔莱斯公司 | Method for actively deforming an aerodynamic profile |
| CN202147840U (en) * | 2011-05-27 | 2012-02-22 | 孙玉国 | Wing with adjustable radian |
| CN104379445A (en) * | 2012-04-30 | 2015-02-25 | 空中客车营运有限公司 | Morphing aerofoil |
| CN102673774A (en) * | 2012-05-18 | 2012-09-19 | 北京理工大学 | Deforming wing mechanism |
| CN205273838U (en) * | 2015-12-11 | 2016-06-01 | 刘文浩 | Adaptive wing of airfoil variable curvature |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110682994A (en) * | 2019-07-29 | 2020-01-14 | 浙江海洋大学 | Ship easy-to-move device |
| CN110539876A (en) * | 2019-09-03 | 2019-12-06 | 中国航空工业集团公司西安飞机设计研究所 | Wing with variable wing profile and airplane |
| CN111191326A (en) * | 2019-12-27 | 2020-05-22 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating hydraulic flow demand of flight control actuator by airplane |
| CN112340016A (en) * | 2020-11-23 | 2021-02-09 | 西湖大学 | Wing structure, wing structure and flapping wing type aircraft |
| CN112607015A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Reconfigurable modular self-adaptive variant aircraft |
| CN112644688A (en) * | 2020-12-31 | 2021-04-13 | 中国商用飞机有限责任公司 | Aircraft wing |
| CN114194375A (en) * | 2021-12-27 | 2022-03-18 | 成都市鸿侠科技有限责任公司 | Airplane flap slide rail with self-locking function and machining process thereof |
| CN114194375B (en) * | 2021-12-27 | 2023-07-21 | 成都市鸿侠科技有限责任公司 | Airplane flap sliding rail with self-locking function and processing technology thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105346705A (en) | Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof | |
| US4146200A (en) | Auxiliary flaperon control for aircraft | |
| US5681014A (en) | Torsional twist airfoil control means | |
| JP6196795B2 (en) | Performance-enhanced winglet system and method | |
| US5407153A (en) | System for increasing airplane fuel mileage and airplane wing modification kit | |
| US8056865B2 (en) | Mechanism for changing the shape of a control surface | |
| US8651431B1 (en) | Aircraft with movable winglets and method of control | |
| CN102458988B (en) | There is the aircraft of the box-like wing structure of λ | |
| US9856012B2 (en) | Morphing wing for an aircraft | |
| Szodruch et al. | Variable wing camber for transport aircraft | |
| Monner et al. | Design aspects of the adaptive wing—the elastic trailing edge and the local spoiler bump | |
| EP2599719A1 (en) | Aircraft with an integral aerodynamic configuration | |
| US20160009391A1 (en) | Stable Low Aspect Ratio Flying Wing | |
| US11180252B2 (en) | Aircraft with variable-geometry rhombohedral wing structure | |
| US20160342160A1 (en) | Landing method and system for air vehicles | |
| US9856013B2 (en) | Deformable wing including a mobile upper surface | |
| US10196129B2 (en) | Aerofoil and wings for air vehicles | |
| US9873503B2 (en) | Tailplane with positive camber | |
| EP0100775A1 (en) | Wing leading edge slat | |
| CN103287570A (en) | Z-shaped folding wing mechanism | |
| CN108622369A (en) | Morphing aircraft wing structure | |
| US6824109B2 (en) | Lift adjusting device for aircraft | |
| CN110001923A (en) | Passively activated fluid thumbpiece | |
| US6905092B2 (en) | Laminar-flow airfoil | |
| Greff | The development and design integration of a variable camber wing for long/medium range aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160224 |
|
| RJ01 | Rejection of invention patent application after publication |