Disclosure of Invention
The embodiment of the application solves the technical problem that the wing of the airplane in the prior art cannot be adjusted in size and shape according to actual needs by providing the deformable wing and the airplane.
In a first aspect, an embodiment of the application provides a deformable wing, which comprises a skin and a deformation mechanism arranged in the skin, wherein the deformation mechanism comprises a guide rail, at least one pull rod and a plurality of shape memory alloy wires, one end of the pull rod is slidably arranged in the guide rail, the other end of the pull rod is connected with the skin, one end of the shape memory alloy wire is connected with the guide rail, and the shape memory alloy wires are configured to drive the guide rail to rotate when being electrified so as to enable the pull rod to move in the length direction of the pull rod.
With reference to the first aspect, in a possible implementation manner, the guide rail includes at least one rotating portion, and the rotating portion includes a first guide section, a second guide section and a third guide section that are sequentially connected, where the second guide section is bent at an obtuse angle with respect to the first guide section in a first direction, and the third guide section is bent at an acute angle with respect to the second guide section in the first direction.
With reference to the first aspect, in a possible implementation manner, the deformable wing includes two shape memory alloy wires respectively located at two sides of the rotating portion, wherein one shape memory alloy wire is connected with the first guiding section of the rotating portion, and the other shape memory alloy wire is connected with the second guiding section of the same rotating portion.
With reference to the first aspect, in one possible implementation manner, the deformation mechanism includes two pull rods, the guide rail includes two rotating parts coaxially arranged, the third guiding sections of the two rotating parts are connected, the two rotating parts are connected with the shape memory alloy wire and configured to rotate simultaneously under the drive of the shape memory alloy wire, and one ends of the two pull rods are respectively slidably arranged on the two rotating parts.
With reference to the first aspect, in one possible implementation manner, the pull rod includes a first connection section, a second connection section and a third connection section that are sequentially connected, the first connection section and the third connection section are arranged in parallel, a free end of the first connection section is slidably arranged in the rotating portion, and a free end of the third connection section is connected to the skin.
With reference to the first aspect, in one possible implementation manner, the skin includes a plurality of skin connecting sections arranged along the length direction of the wing, two adjacent skin connecting sections are connected in a sliding manner, and the pull rod is arranged along the length direction of the wing.
With reference to the first aspect, in one possible implementation manner, the pull rod is disposed along a width direction of the wing.
With reference to the first aspect, in a possible implementation manner, the deformation mechanism further includes a housing, the guide rail and the plurality of shape memory alloy wires are located in the housing, the guide rail is rotationally connected with the inner wall of the housing, and ends, away from the guide rail, of the plurality of shape memory alloy wires are connected with the inner wall of the housing.
With reference to the first aspect, in a possible implementation manner, the deformation mechanism further includes a sleeve, one end of the sleeve is connected to the housing, and the pull rod passes through the sleeve.
In a second aspect, embodiments of the present application provide an aircraft comprising at least one deformable wing as described in the first aspect or any one of the possible implementations of the first aspect.
The technical scheme provided by the embodiment of the application has at least the following technical effects:
The embodiment of the application provides a deformable wing, when the size or shape of the wing needs to be changed, a shape memory alloy wire is electrified to enable the shape memory alloy wire to generate heat and deform, the shape memory alloy wire drives a guide rail to rotate, a pull rod connected with the guide rail moves in the length direction of the pull rod, and further the skin is driven to move or deform, so that the wing can change the size and the shape according to the flight state of an aircraft, and the occupied area of the aircraft can be reduced by reducing the size of the wing when the aircraft is stopped.
Detailed Description
The following description of the embodiments of the present application will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In the description of the embodiments of the present application, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the embodiments of the present application and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application. The terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance. Furthermore, the terms "mounted," "connected," and "coupled" are used herein in a broad sense, and may be, for example, fixedly connected, detachably connected, or integrally connected, or may be directly connected, or may be indirectly connected via an intermediate medium, or may be in communication with the interior of two elements. The specific meaning of the above terms in the embodiments of the present application will be understood by those of ordinary skill in the art according to specific circumstances.
An embodiment of the present application provides a deformable wing, and please refer to fig. 1 to 7 together. The coordinate system of the embodiment of the application is shown in fig. 1 to 5, wherein the X direction is a direction perpendicular to the airframe and pointing to the left from the airframe, the Y direction is a direction from the aircraft nose to the aircraft tail, and the Z direction is the height direction of the aircraft.
The deformable wing provided by the embodiment of the application comprises a skin 1 and a deformation mechanism 2 arranged in the skin 1. Fig. 4 and 5 show a specific structure of the deforming mechanism 2, and the deforming mechanism 2 includes a guide rail 21, at least one tie rod 22, and a plurality of shape memory alloy wires 23.
One end of the pull rod 22 is slidably disposed in the guide rail 21. Specifically, one end of the pull rod 22 is provided with a sliding shaft 2211 extending into the guide rail 21, and the guide rail 21 drives the pull rod 22 to move through the sliding shaft 2211 when rotating. The other end of the pull rod 22 is connected to the skin 1. Specifically, the other end of the tie rod 22 may be directly connected to the skin 1, or may be indirectly connected to the skin 1 through a member such as a spar or rib. If the tie rod 22 is directly connected to the skin 1, a connection method such as welding or riveting may be adopted, and if the tie rod 22 is indirectly connected to the skin 1 through members such as spar members or ribs, a connection method such as welding, riveting or bolting may be adopted.
One end of the shape memory alloy wires 23a, 23b, 23c, 23d is connected to the guide rail 21, and is configured to drive the guide rail 21 to rotate when energized, so that the tie rod 22 moves in its own longitudinal direction. Specifically, the shape memory alloy wires 23a, 23b, 23c, 23d generate heat when energized, and the heating amount of the shape memory alloy wires 23a, 23b, 23c, 23d is precisely controlled by controlling the current applied to the shape memory alloy wires 23a, 23b, 23c, 23d according to the law of thermal-force coupling cyclic deformation, so that the shape memory alloy wires 23a, 23b, 23c, 23d reach the austenite phase ending temperature, and at this time, the shape memory alloy wires 23a, 23b, 23c, 23d are transformed into the pure austenite phase, and the overall length is shortened to the length when the pure austenite phase. The deformable wing has a plurality of shape memory alloy wires 23a, 23b, 23c, 23d, and the guide rail 21 is rotated in different directions by energizing different shape memory alloy wires 23a, 23b, 23c, 23d, so that the rod 22 slidably connected to the guide rail 21 is reciprocated in the longitudinal direction thereof.
Illustratively, the deformation mechanism 2 shown in fig. 4 and 5 has two pull rods 22, and when the guide rail 21 is driven by the shape memory alloy wire 23 to rotate, the two pull rods 22 are close to or far away from each other, and the two pull rods 22 simultaneously drive the skin 1, so that the wing changes in size and shape. Of course, the deformation mechanism 2 may also have only one pull rod 22, and when the guide rail 21 rotates under the drive of the shape memory alloy wire 23, one pull rod 22 drives the skin 1, so that the wing changes in size and shape.
The shape memory alloy wire 23 in the embodiment of the application can drive the guide rail 21 to rotate, and the pull rod 22 connected with the guide rail 21 moves in the length direction of the pull rod, so as to drive the skin 1 to move or deform, so that the wing can change the size and shape according to the flight state of the airplane. And, when the aircraft is shut down, the aircraft footprint can be reduced by reducing the wing size.
By way of example, fig. 6 provides a specific construction of the guide rail 21. The guide rail 21 includes at least one rotating portion 211, and the rotating portion 211 includes a first guide section 2111, a second guide section 2112, and a third guide section 2113, which are connected in sequence. Specifically, the second guide section 2112 is bent at an obtuse angle with respect to the first guide section 2111 in the first direction, and the third guide section 2113 is bent at an acute angle with respect to the second guide section 2112 in the first direction.
The above specific structure enables the rotating portion 211 to occupy less space during rotation, and enables the rotating portion 211 to rotate by a small angle to drive the pull rod 22 to generate a large displacement.
Specifically, the rotating portion 211 provided in the embodiment of the present application is an integral structure, that is, the first guiding section 2111 is integrally connected to the second guiding section 2112, and the second guiding section 2112 is integrally connected to the third guiding section 2113. The rotation portion 211 of the integral structure allows the end portion of the pull rod 22 to smoothly pass through the junction of the first guide section 2111 and the second guide section 2112 and the junction of the second guide section 2112 and the third guide section 2113.
When the deforming mechanism 2 includes two tie rods 22, the guide rail 21 includes two rotating portions 211 coaxially provided. The third guide sections 2113 of the two rotating portions 211 are connected, and the guide rail 21 is integrally Z-shaped. Both rotating portions 211 are connected to the shape memory alloy wires 23a, 23b, 23c, 23d, and both rotating portions 211 are configured to be rotated simultaneously by the shape memory alloy wires 23a, 23b, 23c, 23 d. The ends of the two tie rods 22 are slidably disposed in the two rotating portions 211, respectively. When the deforming mechanism 2 has only one tie rod 22, the guide rail 21 may include only one rotating portion 211.
The deformable wing provided by the embodiment of the application comprises two shape memory alloy wires 23a, 23b, 23c and 23d which are respectively positioned at two sides of the rotating part 211. One of the shape memory alloy wires 23a, 23c is connected to the first guide section 2111 of the rotating portion 211, and the other shape memory alloy wire 23b, 23d is connected to the second guide section 2112 of the same rotating portion 211. Taking the directions shown in fig. 4 and 5 as an example, the rotating portion 211 rotates counterclockwise when the shape memory alloy wires 23a, 23c connected to the first guide section 2111 of the rotating portion 211 are electrically heated, and the rotating portion 211 rotates clockwise when the shape memory alloy wires 23b, 23d connected to the second guide section 2112 of the rotating portion 211 are electrically heated.
When the guide rail 21 includes two rotating portions 211, the shape memory alloy wires 23a, 23b, 23c, 23d may be provided on both sides of each rotating portion 211, or the shape memory alloy wires 23a, 23b, 23c, 23d may be provided on only both sides of one of the rotating portions 211.
Fig. 4 and 5 show a case where the deforming mechanism 2 includes two tie rods 22, the guide rail 21 includes two rotating portions 211, and shape memory alloy wires 23a, 23b, 23c, 23d are provided on both sides of each rotating portion 211. When the two shape memory alloy wires 23a, 23c connected to the first guide section 2111 in fig. 4 are energized, the two shape memory alloy wires 23a, 23c shorten, driving the two rotating portions 211 to rotate counterclockwise, the left side tie rod 22 moves rightward, the right side tie rod 22 moves leftward, and the two tie rods 22 move away from each other until the state shown in fig. 5 is reached. When the two shape alloy wires 23b, 23d connected to the second guide section 2112 in fig. 5 are energized, the two shape memory alloy wires 2323b, 23d shorten, driving the two rotating portions 211 to rotate clockwise, the left side pull rod 22 moves rightward, the right side pull rod 22 moves leftward, and the two pull rods 22 approach each other until the state shown in fig. 4 is reached.
Of course, the guide rail 21 is not limited to the specific structure shown in fig. 4 to 6, and other structures of the guide rail 21 may be adopted. For example, the guide rail 21 includes at least one rotating portion 211, the rotating portion 211 has a circular arc shape, and the rotating shaft 26 of the rotating portion 211 is located at an end of the circular arc shape.
Fig. 7 shows a specific structure of the pull rod 22, and the pull rod 22 includes a first connection section 221, a second connection section 222, and a third connection section 223 connected in sequence. The first connection section 221 is disposed in parallel with the third connection section 223. The free end of the first connecting section 221 is slidably disposed in the rotating portion 211, and the free end of the third connecting section 223 is connected to the skin 1. Specifically, the pull rod 22 is of an integral structure, that is, the first connecting section 221 is integrally connected with the second connecting section 222, and the second connecting section 222 is integrally connected with the third connecting section 223. Other connection methods may be used between the portions of the pull rod 22, such as welding the first connection section 221 to the second connection section 222, and welding the second connection section 222 to the third connection section 223.
When the deforming mechanism 2 includes two tie rods 22, the first connecting sections of the two tie rods 22 are parallel, and the displacement paths of the third connecting sections 223 of the two tie rods 22 coincide. When the two pull rods 22 are close to each other, the first connecting sections 221 of the two pull rods 22 do not interfere with each other, so that each pull rod 22 can have a larger displacement stroke, and the skin 1 can be driven to change in size and shape.
The pull rod 22 may have a structure other than that shown in fig. 7. For example, the pull rod 22 is a straight rod, and in order to avoid mutual interference of the two pull rods 22 during displacement, the two pull rods 22 are arranged in parallel, so that the displacement paths of the two pull rods 22 are not overlapped.
As shown in fig. 1 to 3, the skin 1 includes a plurality of skin 1 connecting sections disposed along the length direction of the wing, two adjacent skin 1 connecting sections are slidingly connected, and a pull rod 22 is disposed along the length direction of the wing. Illustratively, the wing middle skin 1 shown in fig. 1 and 2 comprises three skin connecting sections, namely the skin 1 comprises a first skin connecting section 11, a second skin connecting section 12 and a third skin connecting section 13, the first skin connecting section 11 is in sliding connection with the second skin connecting section 12, and the second skin connecting section 12 is in sliding connection with the third skin connecting section 13.
When the tie rods 22 of the deformation mechanism 2 pull the two skin connecting sections closer to each other, the length of the wing is reduced, and the wing is changed from the state shown in fig. 1 to the state shown in fig. 2. When the pull rod 22 of the deformation mechanism 2 pushes the connecting sections of the two skins 1 away from each other, the length of the wing is increased, and the wing is changed from the state shown in fig. 2 to the state shown in fig. 1.
In particular, the operation of the morphing mechanism 2 to change the wing length will be described with the specific configuration of the morphing mechanism 2 shown in fig. 4 and 5. When the length of the wing is required to be increased, two shape memory alloy wires 23a and 23c connected with the first guide section 2111 are electrified, the two shape memory alloy wires 23a and 23c are shortened, the guide rail 21 is driven to rotate anticlockwise, the two pull rods 22 are away from each other, and then the connecting sections of the two adjacent skins 1 are pushed to be away from each other, so that the length of the wing is increased. When the length of the wing is required to be reduced, two shape memory alloy wires 23b and 23d connected with the second guide section 2112 are electrified, the two shape memory alloy wires 23b and 23d are shortened, the guide rail 21 is driven to rotate clockwise, the two pull rods 22 are close to each other, and then the adjacent two skin connecting sections are pulled to be close to each other, so that the length of the wing is reduced.
By way of example, a specific structure for achieving a sliding connection between the first skin connection section 11 and the second skin connection section 12 is provided in fig. 3. The first skin connecting section 11 is provided in a double-layer structure at a position close to the second skin connecting section 12, and the second skin connecting section 12 is partially interposed between the double-layer structures. When the pull rod 22 moves in the length direction of the pull rod 22, the pull rod 22 drives the first skin connecting section 11 and the second skin connecting section 12 to move, the length of the double-layer structure of the second skin connecting section 12 inserted into the first skin connecting section 11 is changed, and the whole length of the wing is changed.
The tie rod 22 may be disposed in the width direction of the wing. When the pull rod 22 moves in the length direction, the cross section shape of the wing is driven to change, and the lift force of the airplane is affected.
As shown in fig. 4 and 5, the deforming mechanism 2 in the embodiment of the present application further includes a housing 24, the guide rail 21 and the plurality of shape memory alloy wires 23a, 23b, 23c, 23d are located in the housing 24, and the guide rail 21 is rotatably connected to the inner wall of the housing 24, and the ends of the plurality of shape memory alloy wires 23a, 23b, 23c, 23d, which are remote from the guide rail 21, are connected to the inner wall of the housing 24. Specifically, the shape memory alloy wires 23a, 23b, 23c, 23d are connected to the inner wall of the housing 24 by welding, riveting, or the like, and the guide rail 21 is connected to the inner wall of the housing 24 through the rotation shaft 26.
The housing 24 protects the guide rail 21 and the plurality of shape memory alloy wires 23a, 23b, 23c, 23d inside thereof. When the deformation mechanism 2 is installed in the wing, only the case 24 is fixed, and the installation positions for the guide rail 21 and the shape memory alloy wires 23a, 23b, 23c, 23d are not required.
With continued reference to fig. 4 and 5, the deformation mechanism 2 further includes a sleeve 25, one end of the sleeve 25 being connected to the housing 24. The pull rod 22 passes through the sleeve 25. The sleeve 25 protects the portion of the pull rod 22 that is located outside the housing 24. Further, in the sleeve 25 shown in fig. 4 and 5, rollers are provided inside, and the rollers contact the pull rod 22, thereby supporting and guiding the pull rod 22.
The embodiment of the application also provides an aircraft, which comprises at least one deformable wing. The aircraft can adjust the size and shape of the wing according to the flying speed, the flying height and the flying load in the flying process, so that the aircraft has better control performance.
In this specification, each embodiment is described in a progressive manner, and the same or similar parts of each embodiment are referred to each other, and each embodiment is mainly described as a difference from other embodiments.
The foregoing embodiments are only for illustrating the technical solution of the present application, but not for limiting the same, and although the present application has been described in detail with reference to the foregoing embodiments, it will be understood by those skilled in the art that modifications may be made to the technical solution described in the foregoing embodiments, or equivalents may be substituted for some or all of the technical features thereof, without departing from the spirit of the corresponding technical solution from the scope of the technical solution of the present application.