CN109606630A - A kind of intelligence wing composite material rear system - Google Patents
A kind of intelligence wing composite material rear system Download PDFInfo
- Publication number
- CN109606630A CN109606630A CN201811306119.6A CN201811306119A CN109606630A CN 109606630 A CN109606630 A CN 109606630A CN 201811306119 A CN201811306119 A CN 201811306119A CN 109606630 A CN109606630 A CN 109606630A
- Authority
- CN
- China
- Prior art keywords
- wing
- trailing edge
- composite material
- intelligence
- pneumatic muscle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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
- B64C3/50—Varying camber by leading or trailing edge flaps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention relates to a kind of intelligent wing composite material rear systems, characterized in that rear perception and control system are made of fiber-optic grating sensor (18) and drive software；Pneumatic muscle actuator both ends in rear driving mechanism are fixed on wing stabilization front-axle beam (11), on the back rest (9) respectively, limited post (7) is fixed on composite substrate (3), after cable wire (6) passes through the hole of limited post (7), both ends are connect with pneumatic muscle actuator (13) and rear edge strip (4) respectively；Control computer (15) is connect by electromagnetic proportional valve (21) with pneumatic muscle actuator (13), realizes the driving deformed to trailing edge formations.Realization of the invention can be improved the pneumatic efficiency of wing structure, reduces the noise that wing aerodynamic generates, changes the camber of wing according to the demand of state of flight, realize intelligent perception and control to wing.The engineering verification for being embodied as flexible variable camber trailing edge of the invention has established important practical basis.
Description
Technical field
The invention belongs to morphing aircraft structure or intelligent aircaft configuration technologies, are related to a kind of intelligent wing composite wood
Expect rear system.
Background technique
In recent years, as what green aeronautical technology proposed reducing the civil aircraft energy and wanting to Aircraft noise reduction
It asks and the fast development of material and structure technology, aircraft wing rear active face is gradually developed by traditional rigid structure
For with host wing seamless connection and it is deformable and carrying flexible structure, referred to as can be changed camber trailing edge formations.If this can
Variable camber trailing edge formations also have perception and control function, then are known as intelligent trailing edge formations, intelligent and variable camber rear knot
Structure or intelligent wing can be changed camber trailing edge formations.Variable camber rear realizes wing main plane to the nothing between rear aerofoil
Seam, continuous, smooth compliant, and can carry.
For unmanned plane, variable camber rear can be improved its cruising ability and reduce RCSRadar Crosssection
Radar cross section；For fighter plane, noise when variable camber rear can be improved its mobility, increase voyage, reduce landing
With reduction RCS；For large aircraft, variable camber rear can be improved its payload, increase voyage etc..It can be seen that
Variable camber trailing edge technique has important military significance and wide application prospect.
Guarantee U.S. army in next generation for this purpose, flexible adaptive wing technology is just classified as by the U.S. early in the last century 80's
One of the key technology that discipline maintains the leading position.NASA successively implements work transformation matrix wing MAWMission Adaptive
Wing, active flexible wing AFWActive Flexible Wing, Active Aeroelastic Wing AAWActive Aeroelastic
One systems such as Wing, intelligent wing SWSmart Wing, morphing aircraft structure MASMorphing Aircraft Structure
Column project has sufficiently demonstrated flexible adaptive wing and has promoted the importance and key on aircraft aerodynamic performance.
2008-2015, European Union start and complete " Smart High Lift Devices for the Next Generation
WingSADE " plan.It demonstrates SADE and plans the feasibility applied aboard.This plans to test in distressed structure technical aspect
Adaptive leading edge, the deformation trailing edge flap, active wingtip trailing edge formations technology of civil aircraft wing are demonstrate,proved.Some Domestic Research Center
Institute and colleges and universities, have carried out the principle and feasibility study of wing flexible structure, have done a large amount of ground-breaking work.But with state foreign minister
Than there are also no small distances.With the deep propulsion that China's civil aircraft scientific research and model work, develop advanced Aeronautical R&D skill
Art, further carrying out variable camber wing flexible trailing edge and intelligent wing flexible trailing edge research becomes very necessary work.
Summary of the invention
The purpose of the invention is to overcome traditional deviation formula trailing edge, the pneumatic efficiency and drop of wing are improved
Low aerodynamic noise proposes a kind of intelligent wing composite material rear system, realizes seamless, the smooth continuous modification of trailing edge
And carrying.
The technical solution of the invention is as follows:
A kind of intelligence wing composite material rear system, the rear system by trailing edge formations, rear driving mechanism and
Rear perception is formed with 3 part of control system；Trailing edge formations include composite substrate 3, large deformation covering 1, flexible honeycomb 2,
Wherein composite substrate 3 is mounted on the wing stabilization back rest 9；Rear driving mechanism includes pneumatic muscle actuator 13, steel
Rope 6 and gas source 22；Rear perception and control system are made of fiber-optic grating sensor 18 and drive software；In rear driving mechanism
Pneumatic muscle actuator both ends be fixed on wing stabilization front-axle beam 11 respectively, on the back rest 9, limited post 7 is fixed on compound
On material substrate 3, after cable wire 6 passes through the hole of limited post 7, both ends are connect with pneumatic muscle actuator 13 and rear edge strip 4 respectively,
Realize the installation to rear driving structure；Control computer 15 is connect by electromagnetic proportional valve 21 with pneumatic muscle actuator 13,
Realize the driving deformed to trailing edge formations.
Preferably, the rear system total arrangement be trailing edge formations be located at wing rear portion and wing stabilization 19 it is seamless
Connection；Trailing edge formations are the full-height honeycomb of belt substrate；Pneumatic muscle actuator 13 is located in stabilization 19, using cable wire
6 connection rear edge strips 4 are realized with the control cooperation of computer 15 to trailing edge formations by the position of each limited post 7 control cable wire 6
Driving；Fiber-optic grating sensor 18 is located in composite substrate 3, realizes that the deformation to rear perceives.
Preferably, composite substrate 3 is the composite laminated plate for being internally embedded fiber-optic grating sensor 18, flexible bee
Nest 2 is cementing on composite substrate 3, and large deformation covering 1 is cementing on flexible honeycomb 2.
Preferably, large deformation covering 1 uses spandex fibre and silicon rubber under conditions of normal temperature, by being molded；
Wherein spandex fibre and silicon rubber mass ratio are 1:2, volume ratio 1:2.5.
Preferably, flexible honeycomb 2 is used to support large deformation covering 1, while the aerodynamic loading on rear being passed on substrate,
Flexible honeycomb 2 generates tangential deformation in trailing edge formations and does not generate exhibition to deformation, or the exhibition generated is to deformation: tangential deformation <
0.01。
Preferably, the flexible honeycomb 2 is 4 side shape overstretching honeycombs.The trade mark is AC-NH, and flexible honeycomb 2 is provided with for limiting
The fluting of limited post 7 processed.
Preferably, composite substrate 1 is to be embedded with fiber-optic grating sensor 18 or surface mount in trailing edge formations to have light
18 composite laminated plate of fiber grating sensor.
Preferably, the gas that rear driving mechanism utilizes gas source 22 to export, driving pneumatic muscle actuator 13 shrink, drive
Cable wire 6 generates pulling force, realizes the driving function of rear driving mechanism.
The present invention has the advantage that and beneficial effect,
The present invention uses large deformation covering 1, flexible honeycomb 2, composite substrate 3, fiber-optic grating sensor 18, Suo Lian
It connects, the components such as pneumatic muscle actuator 13, after assembling, is fixed on wing rear spar 9, connect with 19 slotless design of wing stabilization
Connect, can smooth compliant deformation bear the external load of structure again, realize a kind of intelligence wing composite material rear knot
Structure.The intelligent wing composite material trailing edge formations that the present invention realizes, realize the function of flexible trailing edge structure: can be smooth soft
Property deformation can bear the external load of structure again, while realizing the intelligent functions of flexible trailing edge: being perceived by fiber grating
The deformation position of rear, and control signal is fed back into control computer 15, realize the driving to trailing edge formations.Reality of the invention
It now can be improved the pneumatic efficiency of wing structure, reduce the noise that wing aerodynamic generates, machine is changed according to the demand of state of flight
The camber of the wing realizes intelligent perception and control to wing.Engineering verification for flexible variable camber trailing edge is established
Important practical basis.
Detailed description of the invention
Fig. 1 is intelligent wing composite material trailing edge formations schematic diagram of the invention.
Fig. 2 is intelligent wing composite material trailing edge formations and control system schematic diagram of the invention.
Specific embodiment
It elaborates with reference to the accompanying drawing to the present invention:
1 intelligent wing composite material rear total arrangement
Intelligent wing composite material rear total arrangement be rear be located at wing rear portion and wing stabilization 19 it is seamless
Connection；Trailing edge formations are the full-height honeycomb of belt substrate；Driver is located in stabilization 19, connects rear using cable wire 6
The driving to rear is realized with the control cooperation of computer 15 by the position of each limited post 7 control cable wire 6 in end；Fiber grating position
In in composite substrate 3, realization perceives the deformation of rear.
2 trailing edge formations
Trailing edge formations are by large deformation covering 1, flexible honeycomb 2, composite substrate 3, limited post 7, clip 5, rear edge strip
4, angle section 8, the composition of the back rest 9, attachment screw nut composition.
Large deformation covering 1 is the key part of flexible trailing edge structure.For the large deformation requirement for adapting to flexible trailing edge, need to cover
Leatherware has 10% or more adaptability to changes.Large deformation covering 1 of the invention is using spandex fibre 30D and silicon rubber HT-802 normal
Under conditions of temperature, by being molded.Spandex fibre and silicon rubber mass ratio reach 1:2, and volume ratio reaches 1:2.5.Molding
1 adaptability to changes of composite material large deformation covering pass through testing inspection, reach 30% or so.Its modulus is 15MPa size.
Flexible honeycomb 2 is used to support large deformation covering 1, while the aerodynamic loading on rear being passed on substrate, due to rear
Edge requires biggish deformability, and common honeycomb is not able to satisfy the deformation requirements of rear.The present invention crosses drawing using 4 side shapes
Stretch honeycomb.The trade mark is AC-NH.Due to being fixed with limited post 7 on substrate for 6 posting of cable wire, it is therefore desirable to flexible honeycomb 2
Processing fluting is carried out, since flexible honeycomb 2 is difficult to the characteristics of processing, the present invention uses independent mold, dedicated for flexible bee
The processing of nest 2 is slotted.
Substrate uses carbon fiber epoxy composite T700/BA9916, and the design thickness of thickness in monolayer 0.15mm, substrate are
2.0mm.Substrate is fixed on the back rest 9 by angle section 8.There is 5 part of clip in the end of substrate, for cable wire 6 to be fixed on clip 5
It is interior.Cable wire 6 bears, transmits the load of pneumatic muscle actuator 13, so that flexible trailing edge realizes smooth continuous modification.Composite material
The middle position of substrate 3 is embedded with multiple fiber-optic grating sensors 18.
Limited post 7 is used to limit the position of cable wire 6, so that cable wire 6 controls add in honeycomb always when flexible trailing edge deforms
In work fluting.Rear edge strip 4 can be made into metal or composite structure, for maintaining the aerofoil profile of wing.Honeycomb and covering
Connection using be glued connection, flexible trailing edge in the back rest 9 connection be Hybrid connections, as needed depending on, some use screw
Connection, some use screw using connection, the connection of pulley assembly 14, pneumatic muscle actuator 13 and wing stabilization 19 is glued
Connection.
3 rear driving mechanisms
Rear drive part is fixed on the clip 5 of rear edge strip 4 by 6 one end of cable wire, and one end passes through 7 hole of limited post, with
The connection of pneumatic muscle actuator 13, pulley assembly 14, pneumatic muscle actuator 13, airflow pipeline 20, electromagnetic proportional valve 21, gas source
22 compositions.
Pneumatic muscle actuator 13 is the critical component that rear realizes driving.The working principle of pneumatic muscle actuator 13
Be, under the action of 22 pressure of external air source, pneumatic muscle actuator 13 generate contraction, the size of shrinkage and air pressure size and
Drive performance is related.The relationship of shrinkage deformation and driving load can be determined by test.This relationship is usually non-thread
Property.The air-flow of gas source 22 is by electromagnetic proportional valve 21 and airflow pipeline 20, into pneumatic muscle actuator 13, in pressure
Under effect, pneumatic muscle actuator 13 generates contraction, and cable wire 6 pulls clip 5 by limited post 7, drives composite substrate 3,
Realize deflecting down for variable camber flexible trailing edge.Same mode adds pneumatic muscle actuator 13 above by gas source 22
Pressure, can be achieved with upward deflecting for variable camber flexible trailing edge.To realize the driving function of variable camber flexible trailing edge.
The perception of 4 rears and control system
Rear perception and control section are by fiber-optic grating sensor 18, signal picker 24, fiber Bragg grating (FBG) demodulator 25, control
Computer 15 processed forms.
The deformation signal of variable camber rear is acquired by signal picker 24, is carried out by fiber Bragg grating (FBG) demodulator 25
Demodulation, demodulated signal are sent into control computer 15.By conversion, the deformation state of rear is shown on software interface.Further,
User is inputted by software interface, controls pneumatic muscle actuator 13, changes the air pressure of input, realizes the adjusting deformed to rear
Control.
According to drawing and standard production or the corresponding part of purchase and standard component, for variable camber flexible trailing edge of the present invention
Assembly.These parts include, on rear: composite substrate 3, angle section 8, limited post 7, rear edge strip 4, clip 5, soft
Property honeycomb 2, large deformation composite material skin.On stabilization 19: pulley assembly 14, front-axle beam 11, the back rest 9, stabilization cover
Skin 12, rib 10, for driving: pneumatic muscle actuator 13, cable wire 6, regulating valve, gas source 22.For deforming perception: light
Fiber grating sensor 18, optical fiber, fiber-optic signal (FBG) demodulator 25, deformation controller or computer.
When assembly, multiple fiber-optic grating sensors 18 are embedded in the tangential interposition of composite substrate 3 in advance at equal intervals first
It sets, is located at below the first laying topmost.It is drawn above panel the outlet of optical fiber.The optical fiber future of extraction and fiber-optic signal
(FBG) demodulator 25, control computer 15 connect.
Limited post 7 is installed on composite substrate 3, clip 5 and rear edge strip 4 are installed in 3 one end of composite substrate.
Angle section 8 is installed in 3 other end of composite substrate.Angle section 8 with composite substrate 3 is fixed on the back rest 9.
6 one end of cable wire is fixed in clip 5, the other end passes through 7 hole of limited post, is drawn out to outside.Optical fiber is drawn out to
Outside pays attention to protection.By being glued, the splicing of flexible honeycomb 2 is located on substrate, as in autoclave, curing molding.
Large deformation covering 1 and flexible honeycomb 2 are connected by being glued, in an oven curing molding.
In this way, the compound material flexible rear with the back rest 9 has just been assembled and has been completed.
Pulley assembly 14 is fixed on rib 10, cable wire 6 is passed through into pulley assembly 14, by 13 one end of pneumatic muscle actuator
It is fixed on front-axle beam 11, the other end is connect with cable wire 6,6 length of cable wire is adjusted, so that pneumatic muscle actuator 13 is straight.It completes
The assembly of front-axle beam 11, the back rest 9, rib 10 completes the assembly of covering on stabilization 19, so that large deformation covering 1 is located at 9 edge strip of the back rest
Between 12 lower surface of upper surface and stabilization covering, installed with the mode that screw connects.
The airflow pipeline 20 drawn from gas source 22 is connect with the input interface of pneumatic muscle actuator 13.By optical fiber and light
Optical fiber signaling (FBG) demodulator 25 connects, and fiber-optic signal (FBG) demodulator 25 is connect with control computer 15, by electromagnetic proportional valve 21 and control
Computer 15 connects.
In this way, having the intelligent wing composite material trailing edge formations of perception and control function just to assemble completion.
When operation,
In rear control platform or computer, it is capable of the deformation position of real-time display rear.Including deformation angle, gas
Dynamic muscle pressure size, strain value size corresponding to fiber grating.
When needing to adjust trailing edge angle, the control deformation angle of rear is directly inputted, electromagnetism is adjusted by software control
Proportioning valve 21, the deformation of intelligent wing composite material rear can reach defined angle, and error is at 0.5 degree or so.
Claims (8)
1. a kind of intelligence wing composite material rear system, characterized in that the rear system is driven by trailing edge formations, rear
Mechanism and rear perception are formed with 3 part of control system；Wherein trailing edge formations include composite substrate (3), large deformation covering
(1), flexible honeycomb (2), the composite substrate (3) are mounted on the wing stabilization back rest (9)；Rear driving mechanism includes
Pneumatic muscle actuator (13), cable wire (6) and gas source (22)；Rear perception and control system by fiber-optic grating sensor (18) and
Drive software composition；Pneumatic muscle actuator both ends in rear driving mechanism are fixed on wing stabilization front-axle beam respectively
(11), on the back rest (9), limited post (7) is fixed on composite substrate (3), after cable wire (6) passes through the hole of limited post (7), two
End is connect with pneumatic muscle actuator (13) and rear edge strip (4) respectively, realizes the installation to rear driving structure；Control calculates
Machine (15) is connect by electromagnetic proportional valve (21) with pneumatic muscle actuator (13), realizes the driving deformed to trailing edge formations.
2. intelligence wing composite material rear system according to claim 1, characterized in that the rear system is overall
Layout is that trailing edge formations are located at the rear portion of wing and wing stabilization (19) are seamlessly connected；Trailing edge formations are the full-height of belt substrate
Honeycomb；Pneumatic muscle actuator (13) is located in stabilization (19), rear edge strip (4) is connected using cable wire (6), by each limit
Position column (7) controls the position of cable wire (6), and the driving to trailing edge formations is realized with control computer (15) cooperation；Fiber grating passes
Sensor (18) is located in composite substrate (3), realizes that the deformation to rear perceives.
3. intelligence wing composite material rear system according to claim 1, characterized in that composite substrate (3)
For the composite laminated plate for being internally embedded fiber-optic grating sensor (18), flexible honeycomb (2) is cementing in composite substrate (3)
On, large deformation covering (1) is cementing on flexible honeycomb (2).
4. intelligence wing composite material rear system according to claim 1, characterized in that large deformation covering (1) is adopted
With spandex fibre and silicon rubber under conditions of normal temperature, by being molded；Wherein spandex fibre and silicon rubber mass ratio are
1:2, volume ratio 1:2.5.
5. intelligence wing composite material rear system according to claim 1, characterized in that flexible honeycomb (2) is used for
It supports large deformation covering (1), while the aerodynamic loading on rear being passed on substrate, flexible honeycomb (2) produces in trailing edge formations
Life is tangential to be deformed and does not generate exhibition to deformation, or the exhibition generated is to deformation: tangential to deform < 0.01.
6. intelligence wing composite material rear system according to claim 5, characterized in that the flexible honeycomb (2)
For 4 side shape overstretching honeycombs, trade mark AC-NH, flexible honeycomb (2) is equipped with the fluting for limiting limited post (7).
7. intelligence wing composite material rear system according to claim 1, characterized in that composite substrate (1)
It is to be embedded with fiber-optic grating sensor (18) or surface mount in trailing edge formations to have the composite material of fiber-optic grating sensor (18)
Laminate.
8. intelligence wing composite material rear system according to claim 1, characterized in that rear driving mechanism utilizes
The gas of gas source (22) output, driving pneumatic muscle actuator (13) are shunk, and band running wire (6) generates pulling force, realize that rear drives
The driving function of motivation structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306119.6A CN109606630B (en) | 2018-11-02 | 2018-11-02 | Intelligent wing composite material trailing edge system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306119.6A CN109606630B (en) | 2018-11-02 | 2018-11-02 | Intelligent wing composite material trailing edge system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109606630A true CN109606630A (en) | 2019-04-12 |
| CN109606630B CN109606630B (en) | 2021-03-26 |
Family
ID=66002627
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811306119.6A Active CN109606630B (en) | 2018-11-02 | 2018-11-02 | Intelligent wing composite material trailing edge system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109606630B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268092A (en) * | 2020-02-19 | 2020-06-12 | 南京航空航天大学 | Structure for improving torsional rigidity of trailing edge structure of flexible wing |
| CN111409816A (en) * | 2020-04-22 | 2020-07-14 | 中国飞机强度研究所 | Variable camber wing leading edge structure |
| CN111661312A (en) * | 2020-05-20 | 2020-09-15 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN113173243A (en) * | 2021-05-10 | 2021-07-27 | 北京航空航天大学 | Piezoelectric fishbone wing structure |
-
2018
- 2018-11-02 CN CN201811306119.6A patent/CN109606630B/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268092A (en) * | 2020-02-19 | 2020-06-12 | 南京航空航天大学 | Structure for improving torsional rigidity of trailing edge structure of flexible wing |
| CN111409816A (en) * | 2020-04-22 | 2020-07-14 | 中国飞机强度研究所 | Variable camber wing leading edge structure |
| CN111661312A (en) * | 2020-05-20 | 2020-09-15 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN111661312B (en) * | 2020-05-20 | 2022-03-29 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN113173243A (en) * | 2021-05-10 | 2021-07-27 | 北京航空航天大学 | Piezoelectric fishbone wing structure |
| CN113173243B (en) * | 2021-05-10 | 2023-02-28 | 北京航空航天大学 | Piezoelectric fishbone wing structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109606630B (en) | 2021-03-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109606630A (en) | A kind of intelligence wing composite material rear system | |
| Thill et al. | Composite corrugated structures for morphing wing skin applications | |
| CN103158860B (en) | Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material | |
| US10640221B2 (en) | Wing airfoil stiffening for solar powered aircraft | |
| US10654557B2 (en) | Morphing skin for an aircraft | |
| JP5598699B2 (en) | Mechanism for receiving fluid flow | |
| CN105636773B (en) | Cohesive and adjustable composite component | |
| US20090159755A1 (en) | Aircraft control device | |
| CN104736433A (en) | Natural laminar flow wingtip | |
| CN105980701A (en) | Means for alleviating strain on a wind turbine rotor blade | |
| CN105479450A (en) | Six-degree-of-freedom non-redundant drive automatic fuselage posture adjusting mechanism | |
| CN102963521B (en) | Central wing of horizontal tail of civil airplane | |
| CN105966600A (en) | Resistance rudder capable of continuously deforming | |
| EP2895389B1 (en) | Passive load alleviation for aerodynamic lift structures | |
| CN110654530A (en) | Variable camber wing structure with deformation feedback | |
| CN113120219B (en) | Control device, aircraft and control method of flexible wing | |
| CN108016602B (en) | Honeycomb wing and aircraft | |
| KR101333252B1 (en) | Flap Morphing Wing | |
| US20150240659A1 (en) | Airfoil or rotor blade having a continuous trailing edge flap | |
| US20180237145A1 (en) | Deicing Apparatuses Comprising at least one standoff | |
| CN113602476B (en) | Continuous deformation structure and deformation method for trailing edge of wing | |
| Di Matteo et al. | Design and analysis of a morphing flap structure for high lift wing | |
| CN208715466U (en) | Unmanned aerial vehicle (UAV) control device and unmanned plane based on flow field control | |
| Vos et al. | Post-buckled precompressed (PBP) piezoelectric actuators for UAV flight control | |
| CN108557054B (en) | Control method of control system suitable for high-aspect-ratio wing aircraft |
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 |