CN103158860B - 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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- CN103158860B CN103158860B CN201310087915.6A CN201310087915A CN103158860B CN 103158860 B CN103158860 B CN 103158860B CN 201310087915 A CN201310087915 A CN 201310087915A CN 103158860 B CN103158860 B CN 103158860B
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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 that a kind of use two kinds of actuators carry out the variable trailing edge driven, belong to morphing aircraft field.
Background technology
So far, the aeroperformance how improving aircraft is one of important content of studying of aircraft designer always in aircraft invention.The wing of current fixed wing machine is all outwards stretch from fuselage according to fixing angle, enough firm, large movement or distortion can not be produced during flight, although it has these pneumatic operation parts of front and rear edges wing flap for improving flight efficiency, but itself remains rigid surface, be difficult to the feature according to mission requirements change wing during flight, the pneumatic efficiency of aircraft wing can not get optimization.And the pinion of occurring in nature can need to carry out delicate adjustment according to what fly at any time, reach mirable high efficiency.The effective ways that morphing based on smart material and structure will be this problem of gap solved between conventional airplane wing and fine birds wing.It by novel intelligent material, New Type of Actuator, exiter, be comprehensively applied to aircraft wing sensor seamless, by applying sensitive sensor and actuator, smooth and change the shape of wing constantly, response is made to changing flying condition, thus aircraft can be made aloft optionally to carry out spiraling 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 are generally compounded in intrinsic silicon, by information processing and control unit, according to the ambient parameter recognized, judge by analysis, rely on the driver element imbedding material internal to realize action, and then the characteristic such as the shape of change structure, stress, strain, make variant structure realize the requirement of its environmental change.The actuator material of current application 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 generally adopted in research both at home and abroad.MFC has lightweight, efficient, the easy advantage such as manufacture, the more important thing is and can be applicable to curved-surface structure but compare with other types actuator, the propulsive effort of MFC and moment or much smaller; SMA propulsive effort is large, but fast not for the maneuvering flight response time of agility.
Summary of the invention
The object of the invention is to adopt separately SMA to carry out driving the problem that speed of response propulsive effort that is slow and that carry out driving with MFC is little for solving, and then provide a kind of and combine by marmem and piezoelectric fibre composite material the variable trailing edge wing driven.
The present invention solves the problems of the technologies described above the technical scheme taked to be: a kind of variable trailing edge wing 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 least one pair of elastomeric element, at least one pair of shape-memory alloy wire is provided with between at least one pair of elastomeric element, the two ends of at least one pair of shape-memory alloy wire are connected with connecting element and movable part 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, the inside face of upper plate is bonded with at least one piezoelectric fibre composite material, the inside face of lower plate is bonded with at least one piezoelectric fibre composite material, the piezoelectric fibre composite material be bonded on upper plate inside face is arranged in pairs with the piezoelectric fibre composite material be bonded on lower plate inside face.
The invention has the beneficial effects as follows: the present invention proposes a kind of actuator using marmem (SMA) and piezoelectric fibre composite material (MFC) to combine jointly to the scheme that trailing edge drives, SMA by connection fixture and movable part, elastomeric element connection fixture and movable part.When driving with SMA, movable part can be pulled to rotate around connecting element.MFC is pasted onto 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 parts that a relative airframe is fixed, movable part is the parts as trailing edge, present invention utilizes the large advantage of SMA propulsive effort (when imposing restriction, most heavily stressed can reach 700Mpa), the rotation of trailing edge generation wide-angle (corners of positive and negative 20 °) can be driven, make use of the advantage of MFC fast response time simultaneously, can deform by fast driving trailing edge.The morphing carrying out driving with existing independent utilization SMA or MFC is compared, morphing can produce moderate finite deformation at trailing edge place, there is amplitude of deformation large (corners of positive and negative 20 °), the advantages such as fast response time (response time is less than 20 milliseconds).Structure of the present invention is simple, reasonable in design, stable.
Accompanying drawing explanation
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.
Detailed description of the invention
Detailed description of the invention one: composition graphs 1 illustrates present embodiment, a kind of variable trailing edge wing 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 least one pair of elastomeric element 5, at least one pair of shape-memory alloy wire 3 is provided with 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 with connecting element 2 and movable part 7 respectively, 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 connects as one structure in the form of a ring, the inside face of upper plate 7-1 is bonded with at least one piezoelectric fibre composite material 8, the inside face of lower plate 7-2 is bonded with at least one piezoelectric fibre composite material 8, the piezoelectric fibre composite material 8 be bonded on upper plate 7-1 inside face is arranged in pairs with the piezoelectric fibre composite material 8 be 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 with lower plate makes one and the curve form being made into target aerofoil profile.With satisfied design and actual needs.
Detailed description of the invention two: present embodiment is described in conjunction with Fig. 1 and 2, connecting element 2 described in 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, forms a through hole 2-4 between riser 2-2 and arc 2-1.Setting like this, is convenient to be fixedly connected with airframe.Other detailed description of the invention one is identical.
Detailed description of the invention three: composition graphs 1 and Fig. 2 illustrate present embodiment, described in present embodiment, connecting element 2 also comprises dull and stereotyped 2-3, riser 2-2 is connected with a dull and stereotyped 2-3, 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 matched with the side of cylindrical boss 2-5, and the side of cylindrical boss 2-5 abuts on the concave surface 7-3-1 of connecting panel 7-3.Setting like this, reasonable in design, structure is simple, and when SMA drives, effectively can realize movable part 7 can rotate around connecting element 2, convenient and reliable.Other is identical with detailed description of the invention two.
Detailed description of the invention four, composition graphs 1 ~ Fig. 3 illustrates present embodiment, 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.Setting like this, connects reliably easy, easy to install, meets design requirement.Other is identical with detailed description of the invention three.
Detailed description of the invention five: composition graphs 1 illustrates present embodiment, described in present embodiment, at least one pair of elastomeric element 5 is coil spring.Setting like this, the connection of movable part and connecting element is reliably easy, and portable propelling part can rotate around connecting element effectively simultaneously.Other with detailed description of the invention one, two, three or four identical.
Detailed description of the invention six: composition graphs 1 and Fig. 4 illustrate present embodiment, wing described in present embodiment also comprises four joints 4, the riser 2-2 being positioned at dull and stereotyped 2-3 upper and lower sides arranges a joint 4 respectively, the upper and lower side of connecting panel 7-3 is respectively provided with a joint 4, and each shape-memory alloy wire 3 removably connects with corresponding two joints 4.Setting like this, takes up room little, facilitates the connection of memory alloy wire.Other is identical with detailed description of the invention three or four.
Detailed description of the invention seven: composition graphs 4 illustrates present embodiment, wing described in present embodiment also comprises four bolts, each joint 4 is cuboid joint, the middle part of the side of one of them thickness direction of each joint 4 has groove 4-1, through direction and one of them thickness direction described of groove 4-1 are perpendicular, the middle part of the side of one of them thickness direction described has tapped bore 4-2, the axis of tapped bore 4-2 and the through direction of groove 4-2 perpendicular, the two ends of each memory alloy wire 3 are through corresponding groove 4-1, bolt presses shape-memory alloy wire 3 is screwed at tapped bore 4-2 place.Setting like this, be convenient to memory alloy wire Assembly &Disassembly, connect reliably easy, when present embodiment uses, after first memory alloy wire being bolted, again by weld on connecting element or movable part, the connection of SMA and connecting element or movable part can be realized, meet the design requirements and the actual needs.Other detailed description of the invention six is identical.
Detailed description of the invention eight: composition graphs 1 illustrates present embodiment, the covering that described in present embodiment, covering 1 is made for elastomeric material.Setting like this, plasticity is good, wraps up solid, is convenient to the needs of the exterior skin of the aerofoil profile of applicable different aircraft, meets the design requirements and the actual needs.Other is identical with detailed description of the invention one.
Claims (7)
1. one kind is combined by marmem and piezoelectric fibre composite material the variable trailing edge wing driven, 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 least one pair of elastomeric element (5), be positioned between at least one pair of elastomeric element (5) and be provided with at least one pair of shape-memory alloy wire (3), the two ends of at least one pair of shape-memory alloy wire (3) are connected with connecting element (2) and movable part (7) respectively, 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, the inside face of upper plate (7-1) is bonded with at least one piezoelectric fibre composite material (8), the inside face of lower plate (7-2) is bonded with at least one piezoelectric fibre composite material (8), the piezoelectric fibre composite material (8) be bonded on upper plate (7-1) inside face is arranged in pairs with the piezoelectric fibre composite material (8) be bonded on lower plate (7-2) inside face,
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), forms a through hole (2-4) between riser (2-2) and arc (2-1).
2. a kind of variable trailing edge wing being combined driving by marmem and piezoelectric fibre composite material according to claim 1, it is characterized in that: described connecting element (2) also comprises flat board (2-3), riser (2-2) is connected with a flat board (2-3), 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) matched with the side of cylindrical boss (2-5), the side of cylindrical boss (2-5) abuts on the concave surface (7-3-1) of connecting panel (7-3).
3. a kind of variable trailing edge wing being combined driving by marmem and piezoelectric fibre composite material according to claim 2, 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.
4. a kind of variable trailing edge wing being combined driving by marmem and piezoelectric fibre composite material according to claim 1,2 or 3, is characterized in that: described at least one pair of elastomeric element (5) is coil spring.
5. a kind of variable trailing edge wing being combined driving by marmem and piezoelectric fibre composite material according to Claims 2 or 3, it is characterized in that: described wing also comprises four joints (4), the riser (2-2) being positioned at flat board (2-3) upper and lower sides arranges a joint (4) respectively, the upper and lower side of connecting panel (7-3) is respectively provided with a joint (4), and each shape-memory alloy wire (3) is connected with corresponding two joints (4).
6. a kind of variable trailing edge wing being combined driving by marmem and piezoelectric fibre composite material according to claim 5, it is characterized in that: described wing also comprises four bolts, each joint (4) is cuboid joint, the middle part of the side of one of them thickness direction of each joint (4) has groove (4-1), through direction and one of them thickness direction described of groove (4-1) are perpendicular, the middle part of the side of one of them thickness direction described has tapped bore (4-2), the axis of tapped bore (4-2) and the through direction of groove (4-2) perpendicular, the two ends of each memory alloy wire (3) are through corresponding groove (4-1), bolt presses shape-memory alloy wire (3) is screwed at tapped bore (4-2) place.
7. a kind of variable trailing edge wing being combined driving by marmem and piezoelectric fibre composite material according to claim 1, is characterized in that: the covering that described covering (1) is made for elastomeric material.
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| CN201310087915.6A CN103158860B (en) | 2013-03-19 | 2013-03-19 | Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material |
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| CN201310087915.6A CN103158860B (en) | 2013-03-19 | 2013-03-19 | Variable trailing edge wing driven by combination of shape memory alloy and piezoelectric fibrous composite material |
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| CN103158860A CN103158860A (en) | 2013-06-19 |
| CN103158860B true CN103158860B (en) | 2015-01-07 |
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