[go: up one dir, main page]

CN110758715A - Deformable wing based on shape memory alloy driving - Google Patents

Deformable wing based on shape memory alloy driving Download PDF

Info

Publication number
CN110758715A
CN110758715A CN201911241621.8A CN201911241621A CN110758715A CN 110758715 A CN110758715 A CN 110758715A CN 201911241621 A CN201911241621 A CN 201911241621A CN 110758715 A CN110758715 A CN 110758715A
Authority
CN
China
Prior art keywords
shape memory
memory alloy
wing
airfoil
rigid box
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
Application number
CN201911241621.8A
Other languages
Chinese (zh)
Other versions
CN110758715B (en
Inventor
张威
张超
王文波
柳阳
刘新杰
刘兵飞
张博利
孙艳坤
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Civil Aviation University of China
Original Assignee
Civil Aviation University of China
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Civil Aviation University of China filed Critical Civil Aviation University of China
Priority to CN201911241621.8A priority Critical patent/CN110758715B/en
Publication of CN110758715A publication Critical patent/CN110758715A/en
Application granted granted Critical
Publication of CN110758715B publication Critical patent/CN110758715B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Air-Flow Control Members (AREA)

Abstract

一种基于形状记忆合金驱动的可变形机翼。其包括翼梁、翼肋、前墙、后墙、桁条、柔性蒙皮和驱动装置;驱动装置包括刚性箱体、滑块、转换机构、形状记忆合金丝、气弹簧、第一连杆、第二连杆、第三连杆、加热电阻丝和电隔离保护罩。本发明提供的基于形状记忆合金驱动的可变形机翼是通过对形状记忆合金丝温度的控制来实现对机翼形状的定量改变,使得机翼获得不同的升阻比。本可变形机翼的结构比较简单,同时通过形状记忆合金材料的引入,可以智能地改变翼型的形状,使得翼型获得更高的气动性能。

Figure 201911241621

A shape memory alloy-driven deformable wing. It includes wing spar, wing rib, front wall, rear wall, stringer, flexible skin and driving device; the driving device includes rigid box, slider, conversion mechanism, shape memory alloy wire, gas spring, first connecting rod, The second connecting rod, the third connecting rod, the heating resistance wire and the electrical isolation protective cover. The deformable airfoil driven by the shape memory alloy provided by the present invention realizes the quantitative change of the shape of the airfoil by controlling the temperature of the shape memory alloy wire, so that the airfoil obtains different lift-to-drag ratios. The structure of the deformable airfoil is relatively simple, and at the same time, the shape of the airfoil can be changed intelligently through the introduction of the shape memory alloy material, so that the airfoil can obtain higher aerodynamic performance.

Figure 201911241621

Description

一种基于形状记忆合金驱动的可变形机翼A shape memory alloy-driven deformable wing

技术领域technical field

本发明属于航空航天装备技术领域,特别是涉及一种基于形状记忆合金(SMA)驱动的可变形机翼。The invention belongs to the technical field of aerospace equipment, in particular to a shape memory alloy (SMA)-driven deformable wing.

背景技术Background technique

传统方法设计出的航空器机翼的翼型只能在某一固定的飞行状态下具有良好的气动性能,而无法在整个飞行过程中始终保持良好的气动性能。为了使翼型气动性能在各种飞行条件下达到最优,可变形翼型的设计应运而生,该设计能够在不同的飞行条件下改变翼型的形状,从而获得较优的气动性能。可变形翼型,既要容易的控制变形,也要具有很高的可控性和稳定性,对于当前的机翼设计制造技术具有很高的挑战性。但目前尚未发现基于形状记忆合金驱动的可变形机翼见诸报道。The airfoil of the aircraft wing designed by the traditional method can only have good aerodynamic performance in a certain fixed flight state, but cannot maintain good aerodynamic performance throughout the entire flight process. In order to optimize the aerodynamic performance of the airfoil under various flight conditions, the design of the deformable airfoil emerges as the times require, which can change the shape of the airfoil under different flight conditions to obtain better aerodynamic performance. Deformable airfoils need to be easy to control deformation, but also have high controllability and stability, which is very challenging for the current wing design and manufacturing technology. But so far no deformable wings driven by shape memory alloys have been reported.

发明内容SUMMARY OF THE INVENTION

为了解决上述问题,本发明的目的在于提供一种基于形状记忆合金驱动的可变形机翼。In order to solve the above problems, the purpose of the present invention is to provide a shape memory alloy-driven deformable airfoil.

为了达到上述目的,本发明提供的基于形状记忆合金驱动的可变形机翼包括:翼梁、翼肋、前墙、后墙、桁条、柔性蒙皮和驱动装置;其中,两个翼肋以垂直的方式对称且平行设置,每个翼肋的内侧面中部沿垂直方向设有一道凹槽;两条桁条上下平行设置,每条桁条的两端分别向外形成有一个能够插入在翼肋上凹槽内的凸台,因此桁条能够沿凹槽上下移动;翼梁、前墙和后墙均为长条形板,垂直设置,两端分别连接在两个翼肋上位于桁条一侧、翼肋的前部及后部的部位;柔性蒙皮覆盖在翼梁、前墙和后墙的上下端外部,并且内表面与两条桁条的外表面相连接;驱动装置包括刚性箱体、滑块、转换机构、形状记忆合金丝、气弹簧、第一连杆、第二连杆、第三连杆、加热电阻丝和电隔离保护罩;其中,刚性箱体为长方体形结构,设在两条桁条之间,一侧面固定在翼梁上靠近桁条的侧面上,并且刚性箱体的顶面、底面一侧部位分别形成有一个开孔;滑块设置在刚性箱体的内中部;形状记忆合金丝和气弹簧平行设置,两端分别固定在刚性箱体内远离开孔的内端面以及滑块的一侧面上;转换机构设置在刚性箱体内位于顶面、底面上开孔之间的部位,两端分别以可转动的方式设置在刚性箱体的两个侧面上;第一连杆的两端分别铰接在滑块的另一侧面以及转换机构的中部边缘;第二连杆和第三连杆的一端分别铰接在转换机构的两侧边缘部位,另一端分别贯穿刚性箱体的顶面、底面上的开孔后铰接在两条桁条上;加热电阻丝缠绕在形状记忆合金丝的表面,并且两端与机载电源相连;电隔离保护罩由柔性绝缘材料制成,包覆在加热电阻丝的外部。In order to achieve the above object, the deformable wing driven by shape memory alloy provided by the present invention includes: a spar, a wing rib, a front wall, a rear wall, a stringer, a flexible skin and a driving device; wherein, the two wing ribs are The vertical way is symmetrical and parallel, and the middle of the inner side of each rib is provided with a groove along the vertical direction; the two stringers are arranged in parallel up and down. A boss in the groove on the rib, so the stringer can move up and down along the groove; the spar, front wall and rear wall are all long strip plates, arranged vertically, and the two ends are respectively connected to the two ribs on the stringer One side, the front and rear parts of the rib; the flexible skin covers the outside of the upper and lower ends of the spar, front and rear walls, and the inner surface is connected to the outer surfaces of the two stringers; the drive device includes a rigid box body, slider, conversion mechanism, shape memory alloy wire, gas spring, first connecting rod, second connecting rod, third connecting rod, heating resistance wire and electrical isolation protective cover; wherein, the rigid box is a cuboid structure, It is set between two stringers, one side is fixed on the side of the wing spar close to the stringer, and an opening is formed on the top surface and the bottom side of the rigid box; the slider is arranged on the side of the rigid box. The inner middle part; the shape memory alloy wire and the gas spring are arranged in parallel, and the two ends are respectively fixed on the inner end surface of the rigid box away from the hole and one side of the slider; the conversion mechanism is arranged in the rigid box and is located between the openings on the top and bottom surfaces. The two ends are respectively arranged on the two sides of the rigid box in a rotatable manner; the two ends of the first link are hinged on the other side of the slider and the middle edge of the conversion mechanism respectively; the second link One end of the connecting rod and the third connecting rod are respectively hinged on the two side edges of the conversion mechanism, and the other end is hinged on the two stringers after passing through the openings on the top and bottom surfaces of the rigid box respectively; the heating resistance wire is wound around the shape memory The surface of the alloy wire, and the two ends are connected with the on-board power supply; the electrical isolation protective cover is made of flexible insulating material and wraps the outside of the heating resistance wire.

所述的第二连杆和第三连杆结构及尺寸相同。The second connecting rod and the third connecting rod have the same structure and size.

所述的加热电阻丝均匀缠绕在形状记忆合金丝的表面。The heating resistance wire is evenly wound on the surface of the shape memory alloy wire.

所述的形状记忆合金丝采用具有双程记忆效应的形状记忆合金材料制成。The shape memory alloy wire is made of a shape memory alloy material with two-way memory effect.

所述的柔性蒙皮包括设置在机翼上表面的柔性蒙皮和机翼下表面的柔性蒙皮。The flexible skin includes a flexible skin disposed on the upper surface of the wing and a flexible skin on the lower surface of the wing.

本发明提供的基于形状记忆合金驱动的可变形机翼是通过对形状记忆合金丝温度的控制来实现对机翼形状的定量改变,使得机翼获得不同的升阻比。本可变形机翼的结构比较简单,同时通过形状记忆合金材料的引入,可以智能地改变翼型的形状,使得翼型获得更高的气动性能。The deformable airfoil driven by the shape memory alloy provided by the present invention realizes the quantitative change of the shape of the airfoil by controlling the temperature of the shape memory alloy wire, so that the airfoil obtains different lift-to-drag ratios. The structure of the deformable airfoil is relatively simple, and at the same time, the shape of the airfoil can be changed intelligently through the introduction of the shape memory alloy material, so that the airfoil can obtain higher aerodynamic performance.

附图说明Description of drawings

图1为本发明提供的基于形状记忆合金驱动的可变形机翼结构示意图。FIG. 1 is a schematic structural diagram of a shape memory alloy-driven deformable airfoil provided by the present invention.

图2为本发明提供的基于形状记忆合金驱动的可变形机翼中驱动装置结构示意图。FIG. 2 is a schematic structural diagram of a driving device in a deformable wing driven by a shape memory alloy provided by the present invention.

图3为本发明提供的基于形状记忆合金驱动的可变形机翼中转换机构结构示意图。FIG. 3 is a schematic structural diagram of the conversion mechanism in the deformable wing driven by the shape memory alloy provided by the present invention.

图4为本发明提供的基于形状记忆合金驱动的可变形机翼中形状记忆合金丝、加热电阻丝和电隔离保护罩结构示意图。4 is a schematic structural diagram of the shape memory alloy wire, the heating resistance wire and the electrical isolation protective cover in the shape memory alloy driven deformable wing provided by the present invention.

具体实施方式Detailed ways

下面结合附图和具体实施例对本发明提供的基于形状记忆合金驱动的可变形机翼进行详细说明。The deformable airfoil driven by the shape memory alloy provided by the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

如图1—图4所示,本发明提供的基于形状记忆合金驱动的可变形机翼包括:翼梁1、翼肋2、前墙3、后墙4、桁条5、柔性蒙皮6和驱动装置7;其中,两个翼肋2以垂直的方式对称且平行设置,每个翼肋2的内侧面中部沿垂直方向设有一道凹槽10;两条桁条5上下平行设置,每条桁条5的两端分别向外形成有一个能够插入在翼肋2上凹槽10内的凸台9,因此桁条5能够沿凹槽10上下移动;翼梁1、前墙3和后墙4均为长条形板,垂直设置,两端分别连接在两个翼肋2上位于桁条5一侧、翼肋2的前部及后部的部位;柔性蒙皮6覆盖在翼梁1、前墙3和后墙4的上下端外部,并且内表面与两条桁条5的外表面相连接;驱动装置7包括刚性箱体8、滑块11、转换机构12、形状记忆合金丝13、气弹簧14、第一连杆15、第二连杆16、第三连杆17、加热电阻丝18和电隔离保护罩19;其中,刚性箱体8为长方体形结构,设在两条桁条5之间,一侧面固定在翼梁1上靠近桁条5的侧面上,并且刚性箱体8的顶面、底面一侧部位分别形成有一个开孔20;滑块11设置在刚性箱体8的内中部;形状记忆合金丝13和气弹簧14平行设置,两端分别固定在刚性箱体8内远离开孔20的内端面以及滑块11的一侧面上;转换机构12设置在刚性箱体8内位于顶面、底面上开孔20之间的部位,两端分别以可转动的方式设置在刚性箱体8的两个侧面上;第一连杆15的两端分别铰接在滑块11的另一侧面以及转换机构12的中部边缘;第二连杆16和第三连杆17的一端分别铰接在转换机构12的两侧边缘部位,另一端分别贯穿刚性箱体8的顶面、底面上的开孔20后铰接在两条桁条5上;加热电阻丝18缠绕在形状记忆合金丝13的表面,并且两端与机载电源相连;电隔离保护罩19由柔性绝缘材料制成,包覆在加热电阻丝18的外部。As shown in FIGS. 1 to 4 , the deformable wing driven by shape memory alloy provided by the present invention includes: spar 1, rib 2, front wall 3, rear wall 4, stringer 5, flexible skin 6 and Drive device 7; wherein, the two ribs 2 are symmetrically and parallel arranged in a vertical manner, and a groove 10 is arranged in the middle of the inner side of each rib 2 along the vertical direction; two stringers 5 are arranged in parallel up and down, each Both ends of the stringer 5 are respectively formed with a boss 9 that can be inserted into the groove 10 on the rib 2, so the stringer 5 can move up and down along the groove 10; the spar 1, the front wall 3 and the rear wall 4 are long strip-shaped plates, arranged vertically, and the two ends are respectively connected to the two rib 2 on one side of the stringer 5, the front part and the rear part of the rib 2; the flexible skin 6 covers the spar 1 , the upper and lower ends of the front wall 3 and the rear wall 4 are outside, and the inner surface is connected with the outer surfaces of the two stringers 5; the driving device 7 includes a rigid box 8, a slider 11, a conversion mechanism 12, a shape memory alloy wire 13, The gas spring 14, the first connecting rod 15, the second connecting rod 16, the third connecting rod 17, the heating resistance wire 18 and the electrical isolation protective cover 19; wherein, the rigid box 8 is a cuboid structure, which is arranged on two stringers 5, one side is fixed on the side of the spar 1 close to the stringer 5, and an opening 20 is formed on the top surface and the bottom side of the rigid box 8 respectively; the slider 11 is arranged on the rigid box 8 The shape memory alloy wire 13 and the gas spring 14 are arranged in parallel, and the two ends are respectively fixed on the inner end face of the rigid box 8 away from the hole 20 and one side of the slider 11; the conversion mechanism 12 is arranged on the rigid box 8. The inner part is located between the openings 20 on the top surface and the bottom surface, and the two ends are respectively arranged on the two sides of the rigid box 8 in a rotatable manner; The other side and the middle edge of the conversion mechanism 12; one end of the second connecting rod 16 and the third connecting rod 17 are hinged on the two side edges of the conversion mechanism 12 respectively, and the other ends respectively penetrate the top surface and the bottom surface of the rigid box 8 The opening 20 is hinged on the two stringers 5; the heating resistance wire 18 is wound on the surface of the shape memory alloy wire 13, and the two ends are connected to the on-board power supply; the electrical isolation protective cover 19 is made of flexible insulating material, covering Cover the outside of the heating resistance wire 18 .

所述的第二连杆16和第三连杆17结构及尺寸相同。The second connecting rod 16 and the third connecting rod 17 have the same structure and size.

所述的加热电阻丝18均匀缠绕在形状记忆合金丝13的表面。The heating resistance wire 18 is evenly wound on the surface of the shape memory alloy wire 13 .

所述的形状记忆合金丝13采用具有双程记忆效应的形状记忆合金材料制成。The shape memory alloy wire 13 is made of a shape memory alloy material with two-way memory effect.

所述的柔性蒙皮6包括设置在机翼上表面的柔性蒙皮和机翼下表面的柔性蒙皮。The flexible skin 6 includes a flexible skin disposed on the upper surface of the wing and a flexible skin on the lower surface of the wing.

现将本发明提供的基于形状记忆合金驱动的可变形机翼的工作原理阐述如下:The working principle of the shape memory alloy-driven deformable airfoil provided by the present invention is described as follows:

当需要改变机翼的形状时,首先通过机载电源给加热电阻丝18进行供电,由此对形状记忆合金丝13进行加热,以使形状记忆合金丝13产生形变,继而带动滑块11在刚性箱体8内左右移动,滑块11将通过第一连杆15带动转换机构12旋转,转换机构12再通过第二连杆16、第三连杆17带动两条桁条5沿凹槽10产生上下位移,最后由桁条5带动柔性蒙皮6产生变形,由此使得机翼的形状发生改变,因此能够基于不同的飞行条件实现机翼形状的定量改变,从而获得不同的升力。停止加热电阻丝18的加热时,在气弹簧14的作用下,通过滑块11、第一连杆15、第二连杆16和第三连杆17可使桁条5恢复初始位置。When the shape of the wing needs to be changed, the heating resistance wire 18 is first powered by the on-board power supply, thereby heating the shape memory alloy wire 13, so that the shape memory alloy wire 13 is deformed, and then the slider 11 is driven in the rigidity. The box body 8 moves left and right, the slider 11 will drive the conversion mechanism 12 to rotate through the first connecting rod 15, and the conversion mechanism 12 will drive the two beams 5 along the groove 10 through the second connecting rod 16 and the third connecting rod 17. Up and down displacement, and finally the flexible skin 6 is deformed by the stringer 5, which changes the shape of the wing, so the shape of the wing can be quantitatively changed based on different flight conditions, so as to obtain different lift. When the heating of the heating resistance wire 18 is stopped, under the action of the gas spring 14, the beam 5 can be restored to the initial position through the slider 11, the first link 15, the second link 16 and the third link 17.

Claims (5)

1.一种基于形状记忆合金驱动的可变形机翼,其特征在于:所述的基于形状记忆合金驱动的可变形机翼包括:翼梁(1)、翼肋(2)、前墙(3)、后墙(4)、桁条(5)、柔性蒙皮(6)和驱动装置(7);其中,两个翼肋(2)以垂直的方式对称且平行设置,每个翼肋(2)的内侧面中部沿垂直方向设有一道凹槽(10);两条桁条(5)上下平行设置,每条桁条(5)的两端分别向外形成有一个能够插入在翼肋(2)上凹槽(10)内的凸台(9),因此桁条(5)能够沿凹槽(10)上下移动;翼梁(1)、前墙(3)和后墙(4)均为长条形板,垂直设置,两端分别连接在两个翼肋(2)上位于桁条(5)一侧、翼肋(2)的前部及后部的部位;柔性蒙皮(6)覆盖在翼梁(1)、前墙(3)和后墙(4)的上下端外部,并且内表面与两条桁条(5)的外表面相连接;驱动装置(7)包括刚性箱体(8)、滑块(11)、转换机构(12)、形状记忆合金丝(13)、气弹簧(14)、第一连杆(15)、第二连杆(16)、第三连杆(17)、加热电阻丝(18)和电隔离保护罩(19);其中,刚性箱体(8)为长方体形结构,设在两条桁条(5)之间,一侧面固定在翼梁(1)上靠近桁条(5)的侧面上,并且刚性箱体(8)的顶面、底面一侧部位分别形成有一个开孔(20);滑块(11)设置在刚性箱体(8)的内中部;形状记忆合金丝(13)和气弹簧(14)平行设置,两端分别固定在刚性箱体(8)内远离开孔(20)的内端面以及滑块(11)的一侧面上;转换机构(12)设置在刚性箱体(8)内位于顶面、底面上开孔(20)之间的部位,两端分别以可转动的方式设置在刚性箱体(8)的两个侧面上;第一连杆(15)的两端分别铰接在滑块(11)的另一侧面以及转换机构(12)的中部边缘;第二连杆(16)和第三连杆(17)的一端分别铰接在转换机构(12)的两侧边缘部位,另一端分别贯穿刚性箱体(8)的顶面、底面上的开孔(20)后铰接在两条桁条(5)上;加热电阻丝(18)缠绕在形状记忆合金丝(13)的表面,并且两端与机载电源相连;电隔离保护罩(19)由柔性绝缘材料制成,包覆在加热电阻丝(18)的外部。1. A deformable airfoil driven by shape memory alloy, characterized in that: the deformable airfoil driven by shape memory alloy comprises: wing spar (1), wing rib (2), front wall (3) ), the rear wall (4), the stringer (5), the flexible skin (6) and the drive device (7); wherein, the two ribs (2) are arranged symmetrically and in parallel in a vertical manner, each rib ( 2) A groove (10) is arranged along the vertical direction in the middle of the inner side surface; two stringers (5) are arranged in parallel up and down, and two ends of each stringer (5) are respectively formed with a groove (10) that can be inserted into the rib. (2) Boss (9) in upper groove (10), so stringer (5) can move up and down along groove (10); spar (1), front wall (3) and rear wall (4) Both are long strip-shaped plates, arranged vertically, and the two ends are respectively connected to the two ribs (2) on one side of the stringer (5), the front part and the rear part of the rib (2); the flexible skin ( 6) Cover the outside of the upper and lower ends of the spar (1), the front wall (3) and the rear wall (4), and the inner surface is connected with the outer surfaces of the two stringers (5); the driving device (7) includes a rigid box Body (8), slider (11), conversion mechanism (12), shape memory alloy wire (13), gas spring (14), first link (15), second link (16), third link Rod (17), heating resistance wire (18) and electrical isolation protective cover (19); wherein, the rigid box (8) is a cuboid structure, arranged between two stringers (5), one side is fixed on the wing On the side of the beam (1) close to the stringer (5), an opening (20) is formed on the top surface and the bottom surface of the rigid box body (8) respectively; the slider (11) is arranged on the rigid box body (8); the shape memory alloy wire (13) and the gas spring (14) are arranged in parallel, and the two ends are respectively fixed on the inner end face of the rigid box (8) away from the hole (20) and the inner end face of the slider (11) On one side; the conversion mechanism (12) is arranged in the rigid box (8) at the position between the openings (20) on the top surface and the bottom surface, and the two ends are respectively rotatably arranged on the rigid box (8) The two sides of the first link (15) are hinged on the other side of the slider (11) and the middle edge of the conversion mechanism (12) respectively; the second link (16) and the third link One end of the (17) is hinged to the two side edges of the conversion mechanism (12) respectively, and the other end penetrates the openings (20) on the top and bottom surfaces of the rigid box (8) and is hinged to the two stringers (5). ); the heating resistance wire (18) is wound on the surface of the shape memory alloy wire (13), and both ends are connected to the on-board power supply; the electrical isolation protective cover (19) is made of flexible insulating material and is wrapped around the heating resistance wire (18) EXTERNAL. 2.根据权利要求1所述的基于形状记忆合金驱动的可变形机翼,其特征在于:所述的第二连杆(16)和第三连杆(17)结构及尺寸相同。2 . The shape memory alloy-driven deformable airfoil according to claim 1 , wherein the second link ( 16 ) and the third link ( 17 ) have the same structure and size. 3 . 3.根据权利要求1所述的基于形状记忆合金驱动的可变形机翼,其特征在于:所述的加热电阻丝(18)均匀缠绕在形状记忆合金丝(13)的表面。3. The shape memory alloy-driven deformable airfoil according to claim 1, wherein the heating resistance wire (18) is evenly wound on the surface of the shape memory alloy wire (13). 4.根据权利要求1所述的基于形状记忆合金驱动的可变形机翼,其特征在于:所述的形状记忆合金丝(13)采用具有双程记忆效应的形状记忆合金材料制成。4 . The shape memory alloy-driven deformable airfoil according to claim 1 , wherein the shape memory alloy wire ( 13 ) is made of a shape memory alloy material with two-way memory effect. 5 . 5.根据权利要求1所述的基于形状记忆合金驱动的可变形机翼,其特征在于:所述的柔性蒙皮(6)包括设置在机翼上表面的柔性蒙皮和机翼下表面的柔性蒙皮。5. The shape memory alloy-driven deformable wing according to claim 1, wherein the flexible skin (6) comprises a flexible skin arranged on the upper surface of the wing and a flexible skin on the lower surface of the wing skinning.
CN201911241621.8A 2019-12-06 2019-12-06 Deformable wing based on shape memory alloy drive Active CN110758715B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911241621.8A CN110758715B (en) 2019-12-06 2019-12-06 Deformable wing based on shape memory alloy drive

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911241621.8A CN110758715B (en) 2019-12-06 2019-12-06 Deformable wing based on shape memory alloy drive

Publications (2)

Publication Number Publication Date
CN110758715A true CN110758715A (en) 2020-02-07
CN110758715B CN110758715B (en) 2022-11-25

Family

ID=69341202

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911241621.8A Active CN110758715B (en) 2019-12-06 2019-12-06 Deformable wing based on shape memory alloy drive

Country Status (1)

Country Link
CN (1) CN110758715B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111717368A (en) * 2020-07-01 2020-09-29 电子科技大学 Flexible wing structure based on shape memory alloy and its manufacturing method
CN111924086A (en) * 2020-07-07 2020-11-13 北京机电工程研究所 A Deformable Mechanism Driven by Memory Alloy
CN112682334A (en) * 2020-12-11 2021-04-20 浙江工业大学 Reversible fan based on bistable-state blades and manufacturing method
CN113859516A (en) * 2021-10-22 2021-12-31 哈尔滨工业大学 Deformation wing parallel guide rail distributed type driving telescopic mechanism
CN115675833A (en) * 2022-12-29 2023-02-03 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 Polymorphic deformation wing based on active deformation skin
CN116331470A (en) * 2023-02-15 2023-06-27 西北工业大学 Wing deformation driving structure and aircraft

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6588709B1 (en) * 2002-03-20 2003-07-08 The Boeing Company Apparatus for variation of a wall skin
CN101367433A (en) * 2008-09-28 2009-02-18 哈尔滨工业大学 A Shape Memory Alloy Spring-Driven Profile Deformable Wing Structure
CN101503113A (en) * 2009-03-23 2009-08-12 哈尔滨工业大学 Shape memory spring driven hinder margin camber variable wing
US20100019096A1 (en) * 2008-07-23 2010-01-28 Alenia Aeronautica S.P.A. Actuator device based on a shape memory alloy, and a wing flap assembly fitted with such an actuator device
CN103158860A (en) * 2013-03-19 2013-06-19 哈尔滨工业大学 Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material
CN106005367A (en) * 2016-05-16 2016-10-12 中国航空工业集团公司西安飞机设计研究所 Flutter model with active flexible front edge
CN106516104A (en) * 2016-11-30 2017-03-22 哈尔滨工业大学 Device for reducing rotor wing vibration
CN107628228A (en) * 2017-08-28 2018-01-26 中国航空工业集团公司沈阳飞机设计研究所 A kind of leading edge of a wing continuously bent structure
CN109572995A (en) * 2018-11-19 2019-04-05 南京航空航天大学 The variable geometry type leading edge of a wing of two-way shape memory alloy and hydraulic composite drive

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6588709B1 (en) * 2002-03-20 2003-07-08 The Boeing Company Apparatus for variation of a wall skin
US20100019096A1 (en) * 2008-07-23 2010-01-28 Alenia Aeronautica S.P.A. Actuator device based on a shape memory alloy, and a wing flap assembly fitted with such an actuator device
CN101367433A (en) * 2008-09-28 2009-02-18 哈尔滨工业大学 A Shape Memory Alloy Spring-Driven Profile Deformable Wing Structure
CN101503113A (en) * 2009-03-23 2009-08-12 哈尔滨工业大学 Shape memory spring driven hinder margin camber variable wing
CN103158860A (en) * 2013-03-19 2013-06-19 哈尔滨工业大学 Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material
CN106005367A (en) * 2016-05-16 2016-10-12 中国航空工业集团公司西安飞机设计研究所 Flutter model with active flexible front edge
CN106516104A (en) * 2016-11-30 2017-03-22 哈尔滨工业大学 Device for reducing rotor wing vibration
CN107628228A (en) * 2017-08-28 2018-01-26 中国航空工业集团公司沈阳飞机设计研究所 A kind of leading edge of a wing continuously bent structure
CN109572995A (en) * 2018-11-19 2019-04-05 南京航空航天大学 The variable geometry type leading edge of a wing of two-way shape memory alloy and hydraulic composite drive

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111717368A (en) * 2020-07-01 2020-09-29 电子科技大学 Flexible wing structure based on shape memory alloy and its manufacturing method
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
CN111924086A (en) * 2020-07-07 2020-11-13 北京机电工程研究所 A Deformable Mechanism Driven by Memory Alloy
CN111924086B (en) * 2020-07-07 2021-12-10 北京机电工程研究所 A Deformable Mechanism Driven by Memory Alloy
CN112682334A (en) * 2020-12-11 2021-04-20 浙江工业大学 Reversible fan based on bistable-state blades and manufacturing method
CN113859516A (en) * 2021-10-22 2021-12-31 哈尔滨工业大学 Deformation wing parallel guide rail distributed type driving telescopic mechanism
CN115675833A (en) * 2022-12-29 2023-02-03 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 Polymorphic deformation wing based on active deformation skin
CN116331470A (en) * 2023-02-15 2023-06-27 西北工业大学 Wing deformation driving structure and aircraft

Also Published As

Publication number Publication date
CN110758715B (en) 2022-11-25

Similar Documents

Publication Publication Date Title
CN110758715A (en) Deformable wing based on shape memory alloy driving
CN107628229B (en) Truss type wing leading edge continuous variable camber structure
CN112550664B (en) A variable-camber wing structure driven by shape memory alloys
CN109572995B (en) Two-way shape memory alloy and hydraulic composite actuated variable airfoil leading edge of the wing
CN210258812U (en) Morphing wing based on active deformation negative Poisson ratio honeycomb structure
CN105905277B (en) A kind of aerodynamic configuration of aircraft using the rear edge support wing
CN111688911B (en) A deformable wing device based on a four-pointed star-shaped scissors mechanism and variable-length ribs
CN111284679B (en) A UAV Deformable Wing Structure Based on Negative Poisson's Ratio Units of Memory Alloy
CN103661929A (en) Plasma unmanned aerial vehicle
CN110588971B (en) Bird-like flying flapping-wing robot capable of automatically twisting wings
CN107472527B (en) Flapping wing driven to be retracted and extended by shape memory alloy
KR101902698B1 (en) Morphing wing
CN103171757B (en) A kind of self adaptation trailing edge actuating device using piezoelectric fibre composite material
CN102649477B (en) Flapping wing airplane
CN103523223B (en) Transverse course control system and transverse course control method for flying wing configuration
CN102107730B (en) Dynamic controller of hinge-free aircraft
CN207324086U (en) Model of an airplane split flap structure without additional friction
CN103407574B (en) Novel efficient notch airfoil shape of parafoil unmanned plane and optimum design method thereof
CN107187579A (en) A kind of flight force and moment control method suitable for many aerofoil aeroplane clothes office
CN112278238B (en) Wing and aircraft that can warp in succession
CN108945392B (en) A humpback whale-fin-like wing structure with a leading edge burl
CN113602476B (en) Continuous deformation structure and deformation method for trailing edge of wing
CN111470030A (en) Wing leading edge bending mechanism based on gear five-bar mechanism driving
CN208593490U (en) Rudder plane controlling mechanism and model plane
CN103224020B (en) A kind of aircraft wing

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
EE01 Entry into force of recordation of patent licensing contract

Application publication date: 20200207

Assignee: Tianjin Ruifengcheng Automation Technology Co.,Ltd.

Assignor: CIVIL AVIATION University OF CHINA

Contract record no.: X2024980002543

Denomination of invention: A Deformable Wing Driven by Shape Memory Alloy

Granted publication date: 20221125

License type: Common License

Record date: 20240305

EE01 Entry into force of recordation of patent licensing contract