CN103158860A - Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material - Google Patents
Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material Download PDFInfo
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- CN103158860A CN103158860A CN2013100879156A CN201310087915A CN103158860A CN 103158860 A CN103158860 A CN 103158860A CN 2013100879156 A CN2013100879156 A CN 2013100879156A CN 201310087915 A CN201310087915 A CN 201310087915A CN 103158860 A CN103158860 A CN 103158860A
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Abstract
The invention discloses a variable trailing edge wing driven by combination of a shape memory alloy and a piezoelectric fibrous composite material, and relates to a variable trailing edge version wing driven by two different drivers. The problems that when an SMA (shape memory alloy) is used for driving, the response speed is slow, and when an MFC (fibrous composite material) is used for driving, the driving force driven is small are solved. The variable trailing edge wing comprises a skin, a fixing piece, a moving piece, at least one pair of shape memory alloy wires, at least one pair of elastic parts and at least one pair of piezoelectric fibrous composite materials, wherein the fixing piece is connected with the moving piece through the at least one pair of flexible assemblies, the at least one pair of shape memory alloy wires are arranged between the at least one pair of elastic parts, the at least one pair of shape memory alloy wires are respectively connected with the fixing piece and the moving piece, the moving piece can rotate through rolling the fixing piece, the skin is coated on the outer surfaces of the fixing piece and the moving piece, the moving piece comprises an upper plate, a lower plate and a connecting plate, and the upper plate, the lower plate and the connecting plate are connected into a whole and is of a ring-shaped structure. The variable trailing edge wing provided by the invention is used for manufacturing the wings on airplanes.
Description
Technical field
The present invention relates to the morphing of the variable trailing edge that two kinds of actuators of a kind of use drive, belong to the morphing aircraft field.
Background technology
Aircraft invention so far, the aeroperformance that how to improve aircraft is one of important content of studying of aircraft designer always.The wing of fixed wing machine is all outwards to stretch from fuselage according to fixing angle at present, enough firm, can not produce large movement or distortion during flight, although it has for these the pneumatic operation spares of front and rear edges wing flap that improve flight efficiency, but itself remains rigid surface, the feature of the mission requirements change wing when being difficult to according to flight, the pneumatic efficiency of aircraft wing can not get optimization.And the pinion of occurring in nature can carry out delicate adjustment according to the needs that fly at any time, reaches mirable high efficiency.Morphing take smart material and structure as the basis will be the effective ways that solve this problem of gap between conventional airplane wing and fine birds wing.It comprehensively is applied to aircraft wing with novel intelligent material, New Type of Actuator, exiter, sensor seamless ground, by using sensitive sensor and actuator, smooth and change constantly the shape of wing, changing flying condition is made response, thereby can make that aircraft optionally spirals aloft as bird, inverted flight and broadside.
Driver element is one of gordian technique of variant structure, and its effect is the instruction that execution information processing and control unit send.In intelligent variant structure, driver element and sensitive member generally are compounded in matrix inside, by information processing and control unit, according to the ambient parameter that recognizes, judgement by analysis, the driver element that material internal is imbedded in dependence is realized action, and then the characteristics such as the shape of change structure, stress, strain, makes variant structure realize the requirement of its environmental change.The actuator material of using at present mainly contains electromagnetism rheo-material, magnetostriction materials, electrostriction material, piezoelectric, shape-memory material, high molecular polymer etc.Marmem (SMA) and piezoelectric fibre composite material (MFC) are the intelligent drivers that generally adopts in research both at home and abroad.MFC has the advantages such as lightweight, efficient, easy manufacturing, the more important thing is can be applicable to curved-surface structure but compare with the other types actuator propulsive effort of MFC and moment or much smaller; The SMA propulsive effort is large, but fast not for the maneuvering flight response time of agility.
Summary of the invention
The objective of the invention is to drive for solving independent employing SMA the little problem of propulsive effort that speed of response is slow and drive with MFC, and then a kind of variable trailing edge wing that is driven by marmem and piezoelectric fibre composite material combination is provided.
the present invention solves the problems of the technologies described above the technical scheme of taking to be: a kind of variable trailing edge wing that is driven by marmem and piezoelectric fibre composite material combination of the present invention comprises covering, connecting element, movable part, at least one pair of shape-memory alloy wire, at least one pair of elastomeric element and at least one pair of piezoelectric fibre composite material, connecting element is connected with movable part by at least one pair of elastomeric element, be provided with at least one pair of shape-memory alloy wire between at least one pair of elastomeric element, the two ends of at least one pair of shape-memory alloy wire are connected with movable part with connecting element respectively, movable part can rotate around connecting element, covering is wrapped on the outside face of connecting element and movable part, movable part comprises upper plate, lower plate and connecting panel, upper plate, lower plate and connecting panel connect as one structure in the form of a ring, be bonded with at least one piezoelectric fibre composite material on the inside face of upper plate, be bonded with at least one piezoelectric fibre composite material on the inside face of lower plate, the piezoelectric fibre composite material that is bonded on the upper plate inside face arranges in pairs with the piezoelectric fibre composite material that is bonded on the lower plate inside face.
The invention has the beneficial effects as follows: the present invention proposes the scheme that the actuator of a kind of utilization marmem (SMA) and piezoelectric fibre composite material (MFC) combination drives trailing edge jointly, SMA is by connection fixture and movable part, elastomeric element connection fixture and movable part.When driving with SMA, can pull movable part to rotate around connecting element.MFC sticks on the inside face of movable part upper plate and lower plate, can drive movable part generation elastic deformation.Connecting element of the present invention is the fixing parts of a relative airframe, movable part be one as the parts of trailing edge, the present invention has utilized the large advantage of SMA propulsive effort (when imposing restriction, heavily stressed can reach 700Mpa), can drive the rotation of trailing edge generation wide-angle (corners of positive and negative 20 °), utilized simultaneously the advantage of MFC fast response time, but the fast driving trailing edge deforms.Compare with the morphing that existing independent utilization SMA or MFC drive, morphing can produce moderate finite deformation at the trailing edge place, has amplitude of deformation large (corners of positive and negative 20 °), the advantages such as fast response time (response time is less than 20 milliseconds).The present invention is simple in structure, and is reasonable in design, stable.
Description of drawings
Fig. 1 is main sectional structure intention of the present invention, and Fig. 2 is the main TV structure schematic diagram of connecting element of the present invention, and Fig. 3 is the main TV structure schematic diagram of movable part of the present invention, and Fig. 4 is the structural representation of joint.
The specific embodiment
the specific embodiment one: present embodiment is described in conjunction with Fig. 1, a kind of variable trailing edge wing that is driven by marmem and piezoelectric fibre composite material combination of present embodiment comprises covering 1, connecting element 2, movable part 7, at least one pair of shape-memory alloy wire 3, at least one pair of elastomeric element 5 and at least one pair of piezoelectric fibre composite material 8, connecting element 2 is connected with movable part 7 by at least one pair of elastomeric element 5, be provided with at least one pair of shape-memory alloy wire 3 between at least one pair of elastomeric element 5, are connected with movable part with connecting element 2 respectively and are connected in the two ends of at least one pair of shape-memory alloy wire 3, movable part 7 can rotate around connecting element 2, covering 1 is wrapped on the outside face of connecting element 2 and movable part 7, movable part 7 comprises upper plate 7-1, lower plate 7-2 and connecting panel 7-3, upper plate 7-1, lower plate 7-2 and connecting panel 7-3 connect as one structure in the form of a ring, be bonded with at least one piezoelectric fibre composite material 8 on the inside face of upper plate 7-1, be bonded with at least one piezoelectric fibre composite material 8 on the inside face of lower plate 7-2, the piezoelectric fibre composite material 8 that is bonded on upper plate 7-1 inside face arranges in pairs with the piezoelectric fibre composite material 8 that is bonded on lower plate 7-2 inside face.
The upper plate of the movable part of the structure in the form of a ring of present embodiment is connected the curve form of making one and being made into the target aerofoil profile with lower plate.To satisfy design and actual needs.
The specific embodiment two: in conjunction with Fig. 1 and 2, present embodiment is described, the described connecting element 2 of present embodiment comprises arc 2-1 and riser 2-2, and the front end of arc 2-1 is connected with a riser 2-2, consists of a through hole 2-4 between riser 2-2 and arc 2-1.So arrange, be convenient to captive joint with airframe.Other specific embodiment one is identical.
The specific embodiment three: present embodiment is described in conjunction with Fig. 1 and Fig. 2, the described connecting element 2 of present embodiment also comprises dull and stereotyped 2-3, be connected with a dull and stereotyped 2-3 on riser 2-2, the end of dull and stereotyped 2-3 has cylindrical boss 2-5, the middle part of connecting panel 7-3 has the concave surface 7-3-1 that the side with cylindrical boss 2-5 matches, and the side of cylindrical boss 2-5 abuts on the concave surface 7-3-1 of connecting panel 7-3.So arrange, reasonable in design, simple in structure, when SMA drives, can realize effectively that movable part 7 can rotate around connecting element 2, convenient and reliable.Other is identical with the specific embodiment two.
the specific embodiment four, in conjunction with Fig. 1～Fig. 3, present embodiment is described, the top of the rear end of the arc 2-1 of present embodiment is provided with the first shackle 2-1-1, the bottom of the rear end of arc 2-1 is provided with the second shackle 2-1-2, the upper end of connecting panel 7-3 has the 3rd shackle 7-3-2, the lower end of connecting panel 7-3 has the 4th shackle 7-3-3, the top of the rear end of arc 2-1 is connected with the upper plate 7-1 of movable part 7 with an elastomeric element 5 on the 3rd shackle 7-3-2 at the first shackle 2-1-1 by clasp joint, the bottom of the rear end of arc 2-1 is connected with the lower plate 7-2 of movable part 7 with another elastomeric element 5 on the 4th shackle 7-3-3 at the second shackle 2-1-2 by clasp joint.So arrange, connects easy reliably, easy to install, meet design requirement.Other is identical with the specific embodiment three.
The specific embodiment five: in conjunction with Fig. 1, present embodiment is described, described at least one pair of elastomeric element 5 of present embodiment is coil spring.So arrange, movable part is connected connection with connecting element reliably easy, and portable propelling spare can rotate around connecting element effectively simultaneously.Other and the specific embodiment one, two, three or four identical.
The specific embodiment six: present embodiment is described in conjunction with Fig. 1 and Fig. 4, the described wing of present embodiment also comprises four joints 4, be positioned on the riser 2-2 of dull and stereotyped 2-3 upper and lower sides a joint 4 is set respectively, the upper and lower side of connecting panel 7-3 respectively is provided with a joint 4, and each shape-memory alloy wire 3 removably connects with corresponding two joints 4.So arrange, take up room little, facilitate the connection of memory alloy wire.Other is identical with the specific embodiment three or four.
the specific embodiment seven: present embodiment is described in conjunction with Fig. 4, the described wing of present embodiment also comprises four bolts, each joint 4 is the cuboid joint, the middle part of the side of one of them thickness direction of each joint 4 has groove 4-1, the perforation direction of groove 4-1 and described one of them thickness direction are perpendicular, the middle part of the side of described one of them thickness direction has tapped bore 4-2, the perforation direction of the axis of tapped bore 4-2 and groove 4-2 is perpendicular, corresponding groove 4-1 is passed at the two ends of each memory alloy wire 3, be screwed into bolt at tapped bore 4-2 place and compress shape-memory alloy wire 3.So arrange, be convenient to the memory alloy wire Assembly ﹠Disassembly, connect reliably easy, when present embodiment is used, after first memory alloy wire being bolted, joint is welded on connecting element or movable part again, can realizes that SMA is connected the connection of movable part with connecting element, meet the design requirements and the actual needs.Other specific embodiment six is identical.
The specific embodiment eight: in conjunction with Fig. 1, present embodiment is described, the covering that the described covering 1 of present embodiment is made for elastomeric material.So arrange, plasticity is good, wrap up solidly, is convenient to the needs of exterior skin of the aerofoil profile of suitable different aircrafts, meets the design requirements and the actual needs.Other is identical with the specific embodiment one.
Claims (8)
1. one kind is made up by marmem and piezoelectric fibre composite material the variable trailing edge wing that drives, it is characterized in that: described wing comprises covering (1), connecting element (2), movable part (7), at least one pair of shape-memory alloy wire (3), at least one pair of elastomeric element (5) and at least one pair of piezoelectric fibre composite material (8), connecting element (2) is connected with movable part (7) by at least one pair of elastomeric element (5), be positioned at and be provided with at least one pair of shape-memory alloy wire (3) between at least one pair of elastomeric element (5), the two ends of at least one pair of shape-memory alloy wire (3) are connected 7 with connecting element (2) with movable part respectively) be connected, movable part (7) can rotate around connecting element (2), covering (1) is wrapped on the outside face of connecting element (2) and movable part (7), movable part (7) comprises upper plate (7-1), lower plate (7-2) and connecting panel (7-3), upper plate (7-1), lower plate (7-2) and connecting panel (7-3) connect as one structure in the form of a ring, be bonded with at least one piezoelectric fibre composite material (8) on the inside face of upper plate (7-1), be bonded with at least one piezoelectric fibre composite material (8) on the inside face of lower plate (7-2), the piezoelectric fibre composite material (8) that is bonded on upper plate (7-1) inside face arranges in pairs with the piezoelectric fibre composite material (8) that is bonded on lower plate (7-2) inside face.
2. a kind of variable trailing edge wing that is driven by the combination of marmem and piezoelectric fibre composite material according to claim 1, it is characterized in that: described connecting element (2) comprises arc (2-1) and riser (2-2), the front end of arc (2-1) is connected with a riser (2-2), consists of a through hole (2-4) between riser (2-2) and arc (2-1).
3. a kind of variable trailing edge wing that is driven by the combination of marmem and piezoelectric fibre composite material according to claim 2, it is characterized in that: described connecting element (2) also comprises flat board (2-3), be connected with a flat board (2-3) on riser (2-2), the end of dull and stereotyped (2-3) has cylindrical boss (2-5), the middle part of connecting panel (7-3) has the concave surface (7-3-1) that the side with cylindrical boss (2-5) matches, the side of cylindrical boss (2-5) abuts on the concave surface (7-3-1) of connecting panel (7-3).
4. according to claim 3 a kind of variable trailing edge wing that is driven by the combination of marmem and piezoelectric fibre composite material, it is characterized in that: the top of the rear end of arc (2-1) is provided with the first shackle (2-1-1), the bottom of the rear end of arc (2-1) is provided with the second shackle (2-1-2), the upper end of connecting panel (7-3) has the 3rd shackle (7-3-2), the lower end of connecting panel (7-3) has the 4th shackle (7-3-3), the top of the rear end of arc (2-1) is connected with the upper plate (7-1) of movable part (7) with an elastomeric element (5) on the 3rd shackle (7-3-2) at the first shackle (2-1-1) by clasp joint, the bottom of the rear end of arc (2-1) is connected with the lower plate (7-2) of movable part (7) with another elastomeric element (5) on the 4th shackle (7-3-3) at the second shackle (2-1-2) by clasp joint.
5. according to claim 1,2,3 or 4 described a kind of variable trailing edge wings that driven by the combination of marmem and piezoelectric fibre composite material, it is characterized in that: described at least one pair of elastomeric element (5) is coil spring.
6. according to claim 3 or 4 described a kind of variable trailing edge wings that driven by the combination of marmem and piezoelectric fibre composite material, it is characterized in that: described wing also comprises four joints (4), be positioned on the riser (2-2) of flat board (2-3) upper and lower sides a joint (4) is set respectively, the upper and lower side of connecting panel (7-3) respectively is provided with a joint (4), and each shape-memory alloy wire (3) is connected with corresponding two joints (4).
7. a kind of variable trailing edge wing that is driven by the combination of marmem and piezoelectric fibre composite material according to claim 6, it is characterized in that: described wing also comprises four bolts, each joint (4) is the cuboid joint, the middle part of the side of one of them thickness direction of each joint (4) has groove (4-1), the perforation direction of groove (4-1) and described one of them thickness direction are perpendicular, the middle part of the side of described one of them thickness direction has tapped bore (4-2), the perforation direction of the axis of tapped bore (4-2) and groove (4-2) is perpendicular, corresponding groove (4-1) is passed at the two ends of each memory alloy wire (3), locate to be screwed into bolt at tapped bore (4-2) and compress shape-memory alloy wire (3).
8. a kind of variable trailing edge wing that is driven by marmem and piezoelectric fibre composite material combination according to claim 1, is characterized in that: the covering that described covering (1) is made for elastomeric material.
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| CN108397333A (en) * | 2018-01-05 | 2018-08-14 | 浙江大学 | A kind of deformable blade mechanism of energy by ocean current generating set |
| CN108791811A (en) * | 2018-05-25 | 2018-11-13 | 中国航天空气动力技术研究院 | A kind of adaptive strain configuration wing of heat |
| CN108891577A (en) * | 2018-07-13 | 2018-11-27 | 北京工业大学 | A kind of rear variable camber wing driven with piezoelectric fibre composite material |
| CN109204779A (en) * | 2018-11-09 | 2019-01-15 | 中国电子科技集团公司第十四研究所 | A kind of self- recoverage wing cover system based on marmem |
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