CN101693467A - Self-adapting morphing trailing edge based on SMA - Google Patents
Self-adapting morphing trailing edge based on SMA Download PDFInfo
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- CN101693467A CN101693467A CN200910145195A CN200910145195A CN101693467A CN 101693467 A CN101693467 A CN 101693467A CN 200910145195 A CN200910145195 A CN 200910145195A CN 200910145195 A CN200910145195 A CN 200910145195A CN 101693467 A CN101693467 A CN 101693467A
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Abstract
The invention relates to a self-adapting morphing trailing edge based on SMA, belonging to a self-adapting morphing wing which combines intellectual materials and structures. The wing is divided into 2-5 trailing edge segments, the adjacent trailing edge segments are connected by joints (5, 6 and 7) arranged at wing ribs, a deflection driving mechanism is arranged between the adjacent trailing edge segments, and the deflection of the entire trailing edge is realized by accumulative effects of the trailing edge segments. The self-adapting morphing wing is characterized in that the deflection driving mechanism comprises an upper SMA wire (10), a lower SMA wire (11) and a current excitation unit (15) which are respectively connected with the adjacent trailing edge segments. The self-adapting morphing trailing edge has the advantages of simple structure and easy control and achieves the goal of quick, stable and accurate pre-deformation of the trailing edge.
Description
Technical field
Self-adapting morphing trailing edge based on SMA of the present invention belongs to the self-adapting morphing structure that a kind of smart material and structure combines.
Background technology
The proposition of " Variable Geometry Wing " notion can be traced back to last century.As far back as 1916, the existing people of Britain proposed the patent application of " Variable Geometry Wing---can change the wing of geometric configuration ", the history in existing more than 90 year so far.Aeronautical technology development existing more than 100 year so far, the Flight Vehicle Design technology is constantly progressive.Retractable landing gear, wing flap, variable-sweep wing etc.In fact can be regarded as the starting stage of " intelligent deformation aircraft " development.
1979, U.S. NASA and Boeing were signed a contract, development flexible composite " adaptive wing ", and varied appearance obtains maximum pneumatic benefit continuously, and makes a flight test in 1987.1985～1992 years, NASA cooperated with Rockwell, carried out " initiatively elastic wing (AFW) " plan, and 1996 expand to later " AAW (AAW) " plan.Meanwhile, mechanisms such as the NASA of beforehand research office of U.S. Department of Defense, air force unite and carry out " the intelligent wing (Smart Wing) " study program, have showed the application potential of intellectual materials such as marmem.
The wing distressed structure has experienced the change procedure from the surface to essence.At first be " adjustment wing shapes ".More existing aircrafts possess the ability of adjusting wing shapes, as F-14 " panda " fighter plane of the U.S., and the latent sound of V-22 " osprey " tiltrotor and F-117 fighter plane etc.The wing of these aircrafts is rigid construction, so-called " adjustment wing shapes " in fact be exactly with certain a part of mobile certain angle of wing or till, with real " Variable Geometry Wing " notion be not the same thing.Next is " AAW (AAW) ".NASA and Air Force Research Laboratory authenticating AAW.Its notion is also different with Variable Geometry Wing, and it is similar with " wing warping " control system of Lai Te brother exploitation, be to adopt traditional control surface such as aileron and droope snoot to be distorted, to improve the maneuverability of the military jet airplane of High Performance from the pneumatic lightweight " flexible wing " of inducing.
The variation of above-mentioned two kinds of wings is not substantial variation.Real Variable Geometry Wing notion is that integrated application with novel intelligent material, actuator, exiter, sensor seamless is in a kind of new design concept of aircraft.Variable Geometry Wing is by using sensitive sensor and actuator, and is smooth and change memorized shape constantly, and changing flying condition is made response, thus make fly the functional image bird equally random aloft spiral, inclining flies and broadside.That is to say that Variable Geometry Wing can fundamentally improve cruising and ability to sprint of aircraft.
2003, U.S. Department of Defense Plan Bureau (DARPA) in advance formally started " morphing aircraft structure (MAS) " project.This project all keeps best performance by changing the aerodynamic configuration of aircraft awing when making aircraft in the execution different task, at different flight envelope.The MAS development effort of DARPA has utilized over nearly 10 years technological advance and the achievement in research in advanced material and control technology field, the profile of wing is changed completely, it is said that these up-to-date technologys even have can make the long-pending potential ability that expands to more than 300% of aerofoil surface.The development emphasis of DARPA present stage development effort is: the low velocity of sound and Variable Geometry Wing technology transonic speed, and three kinds of organization plans have been proposed, it is respectively " folded wing " scheme that Lockheed Martin Corporation proposes, " slip covering " scheme that air technology company of a new generation proposes, " compression wing " scheme that Raytheon Co. proposes.
In addition, domestic a lot of scholars have also carried out a large amount of basic research to the morphing structure, the variant Flight Vehicle Structure vibration Characteristics of carrying out as aircaft configuration intensity research institute of Northwestern Polytechnical University; BJ University of Aeronautics ﹠ Astronautics's aerospace institute Flight Vehicle Design and applied mechanics system have carried out analytical calculation and Deformation control to the distortion of SMA composite laminated plate and piezoelectric layer plywood adaptive structure; Fluid mechanics research institute has carried out detailed research at the rule of self adaptation aerofoil profile rudder face offset angle under the different Mach number and the angle of attack, the aerodynamic configuration of adaptive wing optimization etc.
Aspect the morphing structure design, 2007, doctor Xie Jiang of aeronautical engineering institute of Northwestern Polytechnical University is " machine science and technology " work literary composition " controlled motion of the flexible rib of adaptive wing is learned rule research ", designed a kind of adaptive wing basic element of character---flex-wing rib structure, analyzed the key parameter of pattern layout, derive the kinematics rule that single input drives down flexible rib distortion, and verified the correctness of flexible rib controlled motion rule by software emulation and model experiment.This flexibility rib by some independently rigid element interconnect by the rotating shaft and the hinge of sliding and form, and each rib can independent drive.Flexible rib relies on the yaw motion of inside unit and learns the wing profile alteration of form that rule realizes expection with certain movement.The rib unit is made of one " inner panel " and two " outside plate ", and all there are 4 connecting bores each unit, and wherein two holes, the outside are used for installing the hinge of sliding, and inboard two holes are used for installing rotating shaft.But because this structure interconnects by the rotating shaft and the hinge of sliding, structure is comparatively complicated, and deflection angle is subjected to certain limitation.Simultaneously, this structure does not have the corresponding driving unit, can't realize automatic guidance, and the deflection precision is relatively poor.
Summary of the invention
The objective of the invention is, develop a kind of simple in structure, self-adapting morphing trailing edge structure of being easy to control.Realize the trailing edge structure fast, stable, reach the purpose of predeformation accurately.
A kind of morphing trailing edge of the present invention based on SMA, be divided into 2-5 trailing edge section, adjacent trailing edge section links to each other by the joint that is installed on the rib position, deflection driven mechanism is installed between the adjacent trailing edge section, the deflection of trailing edge single-piece realizes by above-mentioned trailing edge section cumulative effect, it is characterized in that: above-mentioned joint is the radial type joint; Above-mentioned deflection driven mechanism is by the last SMA silk that connects adjacent trailing edge section respectively, SMA silk and current excitation unit are formed down; On be set forth in stringer, following stringer be installed between trailing edge section two ribs, describedly go up the last stringer that the SMA silk connects adjacent trailing edge section, following SMA silk connects the following stringer of adjacent trailing edge section.
With respect to the trailing edge structure of traditional Mechanical Driven bulk deformation, the structure of sectional type has realized the continuous modification of trailing edge structure, and replaces the complicated mechanical drive system that the weight of trailing edge distressed structure is alleviated greatly by the SMA drive system.This beneficial effect of the invention is to have simplified the trailing edge structure significantly, increased propulsive effort, improved distortion efficient, and verified the reasonableness that the SMA smart material and structure is used for the self-adapting morphing structure, can realize the continuous wing distortion of seamless no hinge, improve the pneumatic gentle bullet characteristic of aircraft.
Description of drawings
Fig. 1 is a variant trailing edge Overall Structure Design illustraton of model.
Fig. 2 is the driving rough schematic view in joint one.
Fig. 3 is that rib yaw displacement amount is simplified pattern.
Fig. 4 is a trailing edge structural experiment functional block diagram.
Fig. 5 is a trailing edge structure adaptive control experimental principle block diagram.
Label title among the figure: 1. the unit one, and 2. the unit two, and 3. the unit three, and 4. the unit four, 5. the joint one, and 6. the joint two, and 7. the joint three, 8. rib one, and 9. rib two, 10. goes up the SMA silk, 11. following SMA silk, stringer on 12., 13. times stringers, 14. wing box section, 15. current excitation unit, 16. bolted connection artis, 17.HG6333 the type DC regulated power supply, 18.SMA drive system, 19. trailing edge structures, 20. heating or cooling, the distortion of 21. drive configurations, 22. controlled objects, 23. sensor, 24. amplification filtering circuit, 25.DSP processing unit, 26. control circuit, 27. data acquisitions, 28. signal conditioning, 29.A/D conversion, 30. output PWM, 31. output control signals.
The specific embodiment
Aircraft self-adapting morphing trailing edge structure based on SMA of the present invention, be based on certain unmanned vehicle trailing edge aerofoil profile, with this aerofoil profile carrying observed data is according to the design-calculated structure mode, comprises trailing edge structure of being made up of epoxy resin board rib, the long purlin of aluminum alloy, rigid body crossbeam and the drive system of being made up of marmem (SMA).Structure drive scheme of the present invention as shown in Figure 1, the deflection of trailing edge structure realizes by a plurality of joints chain type cumulative effect.Wherein, joint one is formed with unit two in unit one; Joint two is formed with unit three in unit two; Joint three is formed with unit four in unit three.Drive system is made up of the SMA silk of parallel connection, be fixed on (the inner epoxy resin that embeds is done the insulation processing) on the stringer between two ribs, consider the flying condition of the true aerofoil profile of simulation, the wing structure horizontal positioned, overcoming amoeboid movement under self structure gravity and the certain actual load state, so the drive system of structure need be exported bigger propulsive effort.Drive system of the present invention adopts the parallel mode of arranging of 10 SMA to strengthen each joint and drives dynamics.With alive form heating SMA, make SMA undergo phase transition (generation memory effect) shrinkage distortion, drive joint deflect on axle, the continuous yaw motion of joint one, two, the three synthetic rib of last deflect stack separately, the yaw motion of rib one, two is done the motion that swings up and down of certain angle by the restraint strap motivation wing trailing edge structure of stringer.
Fig. 2 is the driving rough schematic view in joint one.
As previously mentioned, the yaw motion in each joint of trailing edge structure of the present invention is to be driven by SMA mounted thereto to realize, we select for use 0.5mm memory-type Ti-Ni alloy silk (nickel content 50.1at%) as the driver element in this distressed structure in this drive system, through actual measurement as can be known, adopt the electric current of 3.0A that SMA is heated, can realize complete phase transformation (generation memory effect) shrinkage distortion of SMA, and the recovery strain of SMA is about 4.7%.Because of the type of drive in each joint is consistent, design the placement scheme of SMA for example with a joint.
In Fig. 2, unit two does not deflect with respect to unit one, and promptly joint one is in balance position, keeps motionless.Finish the driving deflection in this joint by the differential type type of drive of forming by SMA1 and SMA2, known joint one SMA length ad (a ' d ') between normal temperature lower unit one and the unit two when balance position is 150mm (according to a concrete experimental model dimensional measurement gained), the recovery strain value of SMA
Be 4.7%, according to
The deflection that formula is calculated SMA1 is 7.05mm, and promptly the SMA1 length bd after the distortion is 142.95mm.The shrinkage distortion of SMA1 drives joint o deflection around the shaft α
1The angle is with actual measured value ad, bd, oc, cd substitution actan (ad-cd)/oc-actan (bd-cd)/oc=α
1Formula, get final product the deflect angle [alpha] in this joint
1=3.2619 °.In like manner, the account form of upper deflecting angle is consistent with said method.According to designing requirement, make the deflection angle in joint one, two, three identical, i.e. α
1=α
2=α
3=3.2619 °, can by
It is 180.2731mm that formula calculates joint two SMA length between unit two and the unit three when balance position, and joint three SMA length of unit three and unit four when balance position is 170.1000mm.
Fig. 3 is that rib yaw displacement amount is simplified pattern.
The yaw displacement amount of trailing edge structure can measure by the side-play amount of rib, and four unit constitute the rib of a long l, between the rotating shaft apart from l
oEquate.Unit two is made as α with respect to the deflect angle of unit one
1, unit three is made as α with respect to the deflect angle of unit two
2, unit four is made as α with respect to the deflect angle of unit three
2, same upper deflecting angle is made as respectively and is α '
1, α '
2, α '
3The yaw displacement h of rib then
3Can pass through h
3=l
0(sin α
1+ sin (α
1+ α
2)+sin (α
1+ α
2+ α
3))+l
0(sin α '
1+ sin (α '
1+ α '
2)+sin (α '
1+ α '
2+ α '
3)) the formula gained.With reference to certain unmanned plane aerofoil profile data, design-calculated rib total length l=600mm of the present invention is made of the long l in every unit four unit, three joints
o=150mm, wherein unit one is fixed with crossbeam, and other three unit are free to rotate.When angle of inclination were θ about the rib, three unit of deflection constituted an equicrural triangle BOB ' (amount of offset displacement up and down of design trailing edge structure is identical).The deflect angle in known each joint is all α mutually in the deflection angle in joint one calculates
1=α
2=α
3=3.2619 °, according to triangle corresponding relation formula (sin α
1+ sin (α
1+ α
2)+sin (α
1+ α
2+ α
3))/(cos α
1+ cos (α
1+ α
2)+cos (α
1+ α
2+ α
3))=tan θ/2 calculates ribs deflection angle θ=13.0477 ° up and down, again by formula h
3=l
0(sin α
1+ sin (α
1+ α
2)+sin (α
1+ α
2+ α
3))+l
0(sin α '
1+ sin (α '
1+ α '
2)+sin (α '
1+ α '
2+ α '
3)) can obtain rib yaw displacement amount h up and down
3=129.6889mm.
Fig. 4 is a trailing edge structural experiment functional block diagram.
In Fig. 4, trailing edge structure mode horizontal positioned and single-ended fixing is carried out exercise test overcoming under the structure self gravitation state.Adopt HG6333 type DC regulated power supply to pass to the electric current of 3A, finish the phase change transition of SMA, make its driving machine wing structure motion to SMA.In the structural variant process, can realize continuous modification.
Fig. 5 is a trailing edge structure adaptive control experimental principle block diagram
With design-calculated trailing edge structure as controll plant, utilize angular-motion transducer that trailing edge structure deflection angle is monitored, and extraction related angle displacement signal, through modulate circuit signal being carried out amplification filtering handles, arrive DSPF2812 chip event manager module output pwm signal as incoming signal, again through control circuit output control signal corresponding, closely control the yaw motion of trailing edge structure, formed the control loop of a closed loop, by corresponding control algorithm, can reach the purpose of adaptive control morphing deflection.
Claims (2)
1. self-adapting morphing trailing edge based on SMA, be divided into 2-5 trailing edge section, adjacent trailing edge section links to each other by the joint (5,6,7) that is installed on the rib position, between the adjacent trailing edge section deflection driven mechanism is installed also, the deflection of trailing edge single-piece realizes by above-mentioned trailing edge section cumulative effect, it is characterized in that:
Above-mentioned joint is the radial type joint;
Above-mentioned deflection driven mechanism is by the last SMA silk (10) that connects adjacent trailing edge section respectively, SMA silk (11) and current excitation unit (15) are formed down.
2. the self-adapting morphing trailing edge based on SMA according to claim 1, it is characterized in that: on be set forth in stringer (12), following stringer (13) be installed between trailing edge section two ribs, the described last stringer (12) that SMA silk (10) connects adjacent trailing edge section, the following stringer (13) of the adjacent trailing edge section of following SMA silk (11) connection gone up.
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| CN113602476B (en) * | 2021-08-16 | 2023-08-25 | 江西洪都航空工业集团有限责任公司 | Continuous deformation structure and deformation method for trailing edge of wing |
| CN114295012B (en) * | 2021-12-20 | 2023-11-03 | 北京机电工程研究所 | Rotary sweepback missile wing |
| CN114291287A (en) * | 2022-01-13 | 2022-04-08 | 北京机电工程研究所 | Design method of wing surface with continuously variable trailing edge |
| CN114275142B (en) * | 2022-01-13 | 2023-08-25 | 北京机电工程研究所 | Continuous variable trailing edge camber airfoil |
| CN114275142A (en) * | 2022-01-13 | 2022-04-05 | 北京机电工程研究所 | Wing surface with continuously variable trailing edge camber |
| CN115452308A (en) * | 2022-11-09 | 2022-12-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Deflection angle adjustable structure for measuring control surface manipulation efficiency in wind tunnel |
| CN115452308B (en) * | 2022-11-09 | 2023-03-14 | 中国空气动力研究与发展中心高速空气动力研究所 | Deflection angle adjustable structure for measuring control surface manipulation efficiency in wind tunnel |
| CN115649415A (en) * | 2022-12-29 | 2023-01-31 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Distributed shape memory alloy driven active deformation skin structure |
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