CN110758715A - Deformable wing based on shape memory alloy driving - Google Patents
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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。
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.
Description
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:
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
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
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
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
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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 |
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