CN101367433B - Shape memory alloy spring driven wing structure with deformable section plane - Google Patents
Shape memory alloy spring driven wing structure with deformable section plane Download PDFInfo
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- CN101367433B CN101367433B CN2008101372504A CN200810137250A CN101367433B CN 101367433 B CN101367433 B CN 101367433B CN 2008101372504 A CN2008101372504 A CN 2008101372504A CN 200810137250 A CN200810137250 A CN 200810137250A CN 101367433 B CN101367433 B CN 101367433B
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Abstract
The invention provides a wing structure with a deformable section, which is powered by a shape-memory alloy spring.. The wing structure comprises, a front edge and a back edge, a composite material skin, a bearing frame, a driving mechanism and a redundancy structure of a shape-memory alloy spring driving; the driving mechanism and the redundancy structure of a shape-memory alloy spring driving are arranged on the bearing frame; the redundancy structure of a shape-memory alloy spring driving comprises a shape-memory alloy spring, a nylon casing, a nylon adjusting nut, a SMA spring fixing screw cap, a SMA spring fixing stud and a nylon push rod; the shape-memory alloy spring is arranged in the nylon casing through the SMA spring fixing screw cap and the SMA spring fixing stud; the nylon casing is fixed on the bearing frame through the matching with the nylon nut; the nylon push rod is connected with the SMA spring fixing stud. The invention has the characteristics of light quantity, miniature, reasonable structure, easy operation and high reliability, and can realize the enough driving force and driving displacement in limited space, and the like.
Description
(1) technical field
The present invention relates to the aircraft wings structure technology, be specifically related to a kind of shape memory alloy spring driven wing cellule with deformable section plane.
(2) background technology
Since NASA carried out " the intelligent wing " plan in 1984 since, the correlative study of aircraft intelligent deformation structure was carried out widely by global research institution, organization and individual in succession.Developed into the extensive The deformation of aircraft from the notion of initial hinge-less bending.The distortion of aircraft mainly concentrates in the distortion of wing structure.Wing or missile wing structure are the major parts that aircraft such as aircraft or guided missile produce lift, and physical properties such as its shape, size, rigidity have very big influence for the aircraft in the motion of air-flow high speed.Some studies show that, on the aircraft wings structure the small raised or sunken aerodynamic force that all can cause in the redistribution of wing surface and cause the tremendous influence effect, this influence may be useful also may be deletrious.The researchist wishes always, is out of shape this wholesome effect effect that obtains by the wing structure that makes aircraft.Particularly the aerofoil profile of wing structure has crucial influence to lifting vehicle in the flight environment of vehicle that constantly changes, make aerofoil profile along with the variation of flight environment of vehicle is out of shape towards useful direction by driver element, will produce significance the flight efficiency of aircraft.General driver element is difficult to put to good use in the narrow space of wing structure, and these driver elements or distortion are not enough, or the propulsive effort deficiency, or the installing space deficiency.Use marmem (SMA) spring drive configuration just can in limited space, realize enough propulsive effort and drive displacement.
(3) summary of the invention
The object of the present invention is to provide and a kind ofly can in limited space, realize enough propulsive effort and drive displacement, shape memory alloy spring driven wing cellule with deformable section plane rational in infrastructure, simple to operate.
The object of the present invention is achieved like this: it comprises front and rear edge, composite material skin, bearing frame, the redundancy structure that driver train and shape memory alloy spring drive, the redundancy structure that driver train and shape memory alloy spring drive is installed on the bearing frame, the redundancy structure that shape memory alloy spring drives comprises shape memory alloy spring, nylon sleeve, the nylon setting nut, SMA spring hold-doun nut, SMA spring fixed bolt and nylon push rod, shape memory alloy spring is arranged in the nylon sleeve by SMA spring hold-doun nut and SMA spring fixed bolt respectively, nylon nut is by being fixed on the bearing frame with making nylon sleeve cooperating of nylon sleeve, and the nylon push rod connects SMA spring fixed bolt.
The present invention also has some technical characterictics like this:
1, described shape memory alloy spring, nylon sleeve, nylon setting nut, SMA spring hold-doun nut constitute the pulling force output mechanism in the driver train, shape memory alloy spring screws in from SMA spring hold-doun nut upper end, directly draws lead on SMA spring hold-doun nut surface;
2, described shape memory alloy spring, nylon sleeve, nylon setting nut, SMA spring fixed bolt and nylon push rod constitute the pressure output mechanism in the driver train, SMA spring fixed bolt passes the shape memory alloy spring setting, and the nylon push rod connects SMA spring fixed bolt and constitutes press-on pins;
3, described bearing frame is to be connected into trapezoidally by L shaped and U-shaped bar section of stainless steel, and three crossbeams are arranged, and lays respectively at sharp string, root string and the two neutrality line position, respectively has 10 on the crossbeam circular holes are installed, and size is less than contour of flange;
4, described front and rear edge and composite material skin constitute the load box, the composite material skin of load box outer surfac is made of composite material, middle additional strengthening is the steel channel-section rail, it is connected with composite material skin by glued membrane, three load crossbeams are realized being connected with leading edge and trailing edge by this buttress bracing struts, form leading edge box and trailing edge box;
5, described composite material skin comprises covering up and down, and be divided into two up and down, adopt the constraint condition of the solid Zhi Yiduan sliding support of an end respectively, covering is fixed on trailing edge box below, fix by backing plate, in the leading edge box by sliding support, when covering is subjected to loading, sliding support one end covering can be by sliding to both sides, covering and backing plate fix, the opposite side of backing plate contacts with roller, down roller by spring pressure taut envelope restriction covering perpendicular to the degree of freedom on the roller direction;
6, described driver train is connected with covering by the transition part, and the transition part comprises transition metal sheet and tie bolt, and the transition metal sheet is connected by glued membrane with covering, and tie bolt is fixed on the sheetmetal;
7, described shape memory alloy spring all adopts same specification and constitutes circuit series, and circuit series connects driving power, and connecting wire and covering between the driver element are fixed;
8, described covering down connects the pulling force output mechanism, last covering connects the pressure output mechanism, covering rear edge part and carrying structure directly glued joint, after leading edge portion and backing plate glued joint, backing plate is inserted in the carrying structure, last covering is not fixed with driver train, and the trailing edge of last covering directly is connected with bearing frame, and leading edge portion is connected the back and inserts in the bearing frame with backing plate.
The present invention controls the distortion of realization wing covering to the aim curve shape by being installed in the drive configuration element of some on the carrying structure of section deformable wings inside configuration by the location and the discrete point of these driver elements.The main driver element of drive configuration uses shape memory alloy spring, uses electro heat to drive.In addition, the covering constraint condition of shape memory alloy spring driving section deformable structure is different from the constraint condition of traditional wing structure covering, has used a kind of covering one end to retrain the constraint condition that an end can slide along wing in-plane fully in the section deformable structure.The present invention has lightweight, miniature, can realize enough propulsive effort and drive displacement in limited space, and is rational in infrastructure, simple to operate, characteristics such as reliability height.
Characteristics of the present invention have:
1, described composite material skin uses T700/ epoxy resin with (0/90/0/90/0) shop layer, forms through intermediate temperature setting;
2, described bearing frame is to be connected into trapezoidally by L shaped and U-shaped bar section of stainless steel, and three main crossbeams are arranged, and respectively has 10 on the crossbeam circular holes are installed, and undersized is in contour of flange, and it is the erecting stage of main carrying structure and driver element;
3, described nylon nut is by being fixed on the circular hole of carrying structure with making nylon sleeve cooperating of nylon sleeve, and regulates height;
4, described shape memory alloy spring uses the TiNi spring;
5, described nylon sleeve has outside thread, and it is the container of SMA spring and the effect with skin morph location;
6, described SMA spring hold-doun nut is the main transmitting element of spring output pulling force, uses the good copper material processing of electric conductivity, and the screw thread of nut matches with the middle footpath and the silk footpath of corresponding SMA spring;
7, described SMA spring fixed bolt is the main element of SMA spring thrust output, uses the good copper material processing of electric conductivity, and the screw thread of double-screw bolt matches with the middle footpath and the silk footpath of corresponding SMA spring;
8, described nylon push rod is that the driver element thrust output drives the upwards vital parts of distortion of covering.
(4) description of drawings
Fig. 1 is a carrying structure metal framework scheme drawing;
Fig. 2-Fig. 3 is the connection diagram of front and rear edge box and carrying structure;
Fig. 4 is that trailing edge covering connection mode and position concern scheme drawing;
Fig. 5 is that skins front edges connection mode and position concern scheme drawing;
Fig. 6 is the transition part scheme drawing between covering and driver train;
Fig. 7 is the overall form of the composition scheme drawing of section deformable missile wing;
Fig. 8-Fig. 9 is the driver train scheme drawing;
Figure 10-Figure 15 is a drive configuration vital parts scheme drawing;
Figure 16 is the connectivity scenario of series connected circuit.
(5) specific embodiment
The present invention is further illustrated below in conjunction with the drawings and specific embodiments:
In conjunction with the accompanying drawings, present embodiment comprises leading edge box 4, trailing edge box 2, composite material skin 1, bearing frame 10, the redundancy structure that driver train and shape memory alloy spring drive, the redundancy structure that driver train and shape memory alloy spring drive is installed on the bearing frame 10, the redundancy structure that shape memory alloy spring drives comprises shape memory alloy spring 14, nylon sleeve 15, nylon setting nut 16, SMA spring hold-doun nut 13, SMA spring fixed bolt and nylon push rod 17, shape memory alloy spring 14 is arranged in the nylon sleeve 15 by SMA spring hold-doun nut 13 and SMA spring fixed bolt respectively, nylon nut 16 is by being fixed on the bearing frame 10 with making nylon sleeve 15 cooperating of nylon sleeve 15, and nylon push rod 17 connects SMA spring fixed bolt.
In order to make the aircraft wings structure that distortion to predetermined curve can take place, utilize the displacement control of discrete point, the curve deformation of realization wing structure covering in the present embodiment by using the activation configuration of forming by the SMA spring.Summary of the invention mainly comprises following components:
1, carrying structure
The aerofoil profile deformable structure is except having the deformable function of section, and its another radical function is carrying.Its main carrying structure adopts shape (Fig. 1) framework to constitute main force's carrying structure, the driver train that drives skin morph also will be installed on main force's bearing frame, adopt three strings to crossbeam in whole wing structure inside, lay respectively at sharp string, root string and the two neutrality line position, have 10 on each crossbeam circular hole is installed, be used to install the driver element structure.
Bearing frame has certain bending, torsional stiffness, and when driver train took place to move to the covering applied load, its antagonistic force only can make carrying structure take place than small deformation.
Another main carrying structure is the load box that front and rear edge constitutes, and the covering of box outer surfac is made of composite material, and middle additional strengthening is the steel channel-section rail, and it is connected with composite material by glued membrane.Three load crossbeams realize be connected (Fig. 2-3) with leading edge with trailing edge by this buttress bracing struts.
2, stressed-skin construction
Covering uses the carbon fiber/epoxy resin composite material manufacturing, is shaped in particular mold.After the distortion of section shape generation appointment, for the covering that two ends are completely fixed, the strain that permissible range own will take place to surpass for it can cause composite material that damage even destruction are taken place.Consider the allowed band of composite material distortion, traditional covering that maintains static is divided into two up and down, and adopt an end to consolidate the constraint condition of Zhi Yiduan sliding support respectively, when covering is subjected to loading, sliding support one end covering can overcome the distortion and the contradiction of strain by the slip to both sides, is implemented between two restrained ends the equivalent deformation of " elongation " or " compression " on the covering macroscopic view.The fixed form of covering and position relation because covering 1 is fixed on trailing edge box 2 belows, for fear of the dislocation of covering 1 with trailing edge box 2 surfaces, are regulated the covering position by backing plate 3 as shown in Figure 4, make it surperficial with in one plane with the trailing edge box.
Covering 1 in leading edge box 4 by sliding support, in order to make covering 1 and leading edge box 4 surfaces in one plane need backing plate 5 to regulate the covering positions together equally, with the difference at trailing edge place be that backing plate 5 fixes with covering 1, can slide relative with leading edge box inside face, the opposite side of backing plate 5 contacts with roller 6.Perpendicular to the degree of freedom on the roller direction, its form of the composition and position relation are as shown in Figure 5 by spring pressure taut envelope restriction covering for down roller.
The outside face of covering and air draught direct contact make guided missile obtain the aerodynamic force of expecting awing by its aerodynamic configuration, and its appearance must be smooth smooth.Drive part and directly act on covering and makes covering that the distortion of expection take place, driver train can not destroy its surperficial planarization with being connected of covering, so must use the transition part to finish being connected of driving part and covering 1.As shown in Figure 6, transition metal sheet 7 is connected by glued membrane 9 with covering, and tie bolt 8 is fixed on the transition metal sheet 7.The overall form of the composition of the section deformable wings structure behind the integrated complete moving element as shown in Figure 7.
3, drive configuration
The core parts of drive configuration are shape memory alloy spring, and the SMA spring of selecting for use is silk footpath 1.5mm, and external diameter 9mm composition is the SMA spring of TiNi alloy, and the temperature of its metallographic examination is 65 ℃.Each part dimension of driver train all designs according to the installation dimension of SMA spring.Consider the particularity of marmem itself, it does not also have actv. welding means can realize firm the connection under the prerequisite that does not influence shape memory effect when being connected with other metals, so the main at present method of mechanical compaction of using realizes connecting.The character that has screw thread according to spring, designed a kind of fixed terminal, the SMA spring can screw in from the fixed terminal upper end, can guarantee at as far as possible little space internal fixation SMA spring, and fixed terminal uses the metallic copper manufacturing, can use soldering directly to draw lead on the surface, guarantee that circuit connects.
The SMA spring is installed in less space, and the consumption of SMA is less, if the material section of SMA is bigger, though the circuit resistance that is made of SMA will be very little, any short trouble all will make to drive and lose efficacy, and make power supply impaired.So other irrelevant metal partss of SMA and total need be isolated.This isolation is to adopt this insulating material with certain intensity of nylon by the isolation part that will make between SMA and other parts.In driver train the pulling force output mechanism in locating sleeve and jam nut adopt the nylon manufacturing.Locating sleeve and press-on pins adopt the nylon manufacturing in the pressure output mechanism, and the driver train that these micro parts are formed will be finished propulsive effort output and displacement accuracy control.Final project organization adopts the sleeve structure shown in Fig. 8-9, can reduce installation difficulty in the space up and down by utilizing crossbeam, and reduce radial dimension, makes the dense arrangement of the actuator of sharp string section become possibility.
The part that constitutes drive configuration has six kinds: SMA spring (Figure 10), nylon sleeve (Figure 11), nylon setting nut (Figure 12), SMA spring hold-doun nut (Figure 13), SMA spring fixed bolt (Figure 14) and nylon push rod (Figure 15).
4, circuit structure
Nylon sleeve in the drive configuration is the container of SMA spring, also is crucial setting element.By adjusting the setting height(from bottom) of nylon sleeve on carrying structure, determine the locating point of the distortion of covering up and down respectively.The adjustment of this height decides according to the key point data in the design process and copper spare thickness and covering thickness.
Because the distortion of whole each point of wing covering must could guarantee the continuity of shape synchronously, so the SMA spring that drives all adopts same specification and constitutes circuit series, to be applied to the electric current on each spring be identical to driving power like this, under identical environmental conditions, the temperature of SMA spring heating power is identical, and then cause that the situation that its phase transformation is out of shape is identical, reach synchronous purpose.
The number of driver element more (totally 30), when Series Wiring, need standard clean and tidy, the intersection that should as far as possible reduce lead increases reliability and is convenient to malfunction elimination, connects according to the order among Figure 16 when series connection, and connecting wire and covering between the driver element are fixed.Lead can not be interfered the location of moving of movable part and retaining element in welding process.
5, drive configuration and covering is connected
Covering all is a K/UP trend with following covering in the distortion of wing covering, and following covering needs tensile machine to provide pulling force to make the covering K/UP, and last covering needs pressure mechanism that the bending of bearing capacity guiding covering upwards is provided.According to the mounting condition of covering, following covering need glued joint the requirement of the validity and the skin-surface smooth and continuous that could guarantee pulling force with tensile machine.Each glueds joint part and glueds joint with the covering realization under the location of nylon sleeve, and the standard of installation is: brazed piece is after screwing in spring, and 15 springs penetrate simultaneously and are installed in corresponding sleeve pipe zero resistance on the carrying structure, otherwise additional resistance will influence the driving effect.
Following covering finished with being connected of driver element after, penetrate in the nylon sleeve of carrying structure after the SMA spring screwed in according to corresponding driver element, covering rear edge part and carrying structure are directly gluedd joint, after leading edge portion and backing plate glued joint, backing plate is inserted in the supporting construction in the carrying structure, finish down the installation of covering.
Last covering does not need to fix with driver train, pressure-driven mechanism mechanical adjustment be connected with electric power finish after, the trailing edge of last covering directly is connected with carrying structure, leading edge portion is connected the back and inserts supporting construction in the carrying structure with backing plate.
Claims (9)
1. shape memory alloy spring driven wing cellule with deformable section plane, it comprises front and rear edge, composite material skin, bearing frame, it is characterized in that it also comprises the redundancy structure that driver train and shape memory alloy spring drive, the redundancy structure that driver train and shape memory alloy spring drive is installed on the bearing frame, the redundancy structure that shape memory alloy spring drives comprises shape memory alloy spring, nylon sleeve, the nylon setting nut, SMA spring hold-doun nut, SMA spring fixed bolt and nylon push rod, shape memory alloy spring is arranged in the nylon sleeve by SMA spring hold-doun nut and SMA spring fixed bolt respectively, nylon nut is by being fixed on the bearing frame with making nylon sleeve cooperating of nylon sleeve, and the nylon push rod connects SMA spring fixed bolt.
2. shape memory alloy spring driven wing cellule with deformable section plane according to claim 1, it is characterized in that described shape memory alloy spring, nylon sleeve, nylon setting nut, SMA spring hold-doun nut constitute the pulling force output mechanism in the driver train, shape memory alloy spring screws in from SMA spring hold-doun nut upper end, directly draws lead on SMA spring hold-doun nut surface.
3. shape memory alloy spring driven wing cellule with deformable section plane according to claim 1, it is characterized in that described shape memory alloy spring, nylon sleeve, nylon setting nut, SMA spring fixed bolt and nylon push rod constitute the pressure output mechanism in the driver train, SMA spring fixed bolt passes the shape memory alloy spring setting, and the nylon push rod connects SMA spring fixed bolt and constitutes press-on pins.
4. shape memory alloy spring driven wing cellule with deformable section plane according to claim 1, it is characterized in that described bearing frame is to connect into trapezoidal by L shaped and U-shaped bar section of stainless steel, three crossbeams are arranged, lay respectively at sharp string, root string and the two neutrality line position, respectively have 10 on the crossbeam circular hole is installed, size is less than contour of flange.
5. shape memory alloy spring driven wing cellule with deformable section plane according to claim 1, it is characterized in that described front and rear edge and composite material skin constitute the load box, the composite material skin of load box outer surfac is made of composite material, middle additional strengthening is the steel channel-section rail, it is connected with composite material skin by glued membrane, three load crossbeams are realized being connected with leading edge and trailing edge by this buttress bracing struts, form leading edge box and trailing edge box.
6. root is dug the described shape memory alloy spring driven wing cellule with deformable section plane of claim 1, it is characterized in that described composite material skin comprises covering up and down, and be divided into two up and down, adopt the constraint condition of the solid Zhi Yiduan sliding support of an end respectively, covering is fixed on trailing edge box below, fix by backing plate, in the leading edge box by sliding support, when covering is subjected to loading, sliding support one end covering can be by sliding to both sides, covering and backing plate fix, and the opposite side of backing plate contacts with roller, down roller by spring pressure taut envelope restriction covering perpendicular to the degree of freedom on the roller direction.
7. shape memory alloy spring driven wing cellule with deformable section plane according to claim 1, it is characterized in that described driver train is connected with covering by the transition part, the transition part comprises transition metal sheet and tie bolt, the transition metal sheet is connected by glued membrane with covering, and tie bolt is fixed on the sheetmetal.
8. shape memory alloy spring driven wing cellule with deformable section plane according to claim 1, it is characterized in that described shape memory alloy spring all adopts same specification and constitutes circuit series, circuit series connects driving power, and connecting wire and covering between the driver element are fixed.
9. shape memory alloy spring driven wing cellule with deformable section plane according to claim 6, it is characterized in that described covering down connects the pulling force output mechanism, the described covering of going up connects the pressure output mechanism, following covering rear edge part and carrying structure directly glued joint, leading edge portion and backing plate insert backing plate in the carrying structure after glueing joint, and last covering is not fixed with driver train, the trailing edge of last covering directly is connected with bearing frame, and leading edge portion is connected the back and inserts in the bearing frame with backing plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101372504A CN101367433B (en) | 2008-09-28 | 2008-09-28 | Shape memory alloy spring driven wing structure with deformable section plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101372504A CN101367433B (en) | 2008-09-28 | 2008-09-28 | Shape memory alloy spring driven wing structure with deformable section plane |
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| CN101367433A CN101367433A (en) | 2009-02-18 |
| CN101367433B true CN101367433B (en) | 2010-08-04 |
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| GB201207525D0 (en) * | 2012-04-30 | 2012-06-13 | Airbus Operations Ltd | Morphing aerofoil |
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| US9981421B2 (en) * | 2014-07-16 | 2018-05-29 | The Boeing Company | Adaptive composite structure using shape memory alloys |
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| US10933974B2 (en) | 2019-04-29 | 2021-03-02 | Toyota Motor Engineering & Manufacturing North America, Inc. | Morphable body with shape memory material members |
| CN112278238B (en) * | 2019-07-26 | 2022-05-13 | 香港城市大学深圳研究院 | Wing and aircraft that can warp in succession |
| CN110422316A (en) * | 2019-09-04 | 2019-11-08 | 吉林大学 | A kind of deformable wing of unmanned plane and its deformation method |
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| CN110758715B (en) * | 2019-12-06 | 2022-11-25 | 中国民航大学 | Deformable wing based on shape memory alloy drive |
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| CN111717368B (en) * | 2020-07-01 | 2024-04-02 | 电子科技大学 | Flexible wing structure based on shape memory alloy and manufacturing method thereof |
| CN114291287B (en) * | 2022-01-13 | 2023-08-01 | 北京机电工程研究所 | Design method of continuous variable trailing edge airfoil |
| CN116395124B (en) * | 2023-06-07 | 2023-08-11 | 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 | Wing surface deformation mechanism based on shape memory alloy wire drive |
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2008
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