Variant missile wing based on ordered deformation superstructure

Abstract

The invention belongs to the technical field of missile wing structure design, and particularly relates to a morphing missile wing based on an ordered deformation superstructure, which comprises a wing rib, a wing spar and a skin, the wing ribs are provided with wing rib ordered deformation superstructures, so that the wing ribs can stretch and retract in the chordwise direction; the wing rib ordered deformation superstructure is formed by arraying a plurality of wing rib superstructure unit cells in the chord direction and the thickness direction of a variant missile wing, each wing rib superstructure unit cell comprises a double-V-shaped structural part, a star-shaped structural part and a single-V-shaped structural part, and the single-V-shaped structural part, the star-shaped structural part and the double-V-shaped structural part are sequentially arranged from thin to thick; the two sides of the star-shaped structural part are sequentially connected with the single-V-shaped structural part and the double-V-shaped structural part respectively, the two end points of the single-V-shaped structural part are connected with the two vertexes of one side of the star-shaped structural part respectively, the angular point of the waist of the double-V-shaped structural part and the angular point of the waist of the single-V-shaped structural part are connected together, and the opening directions of the double-V-shaped structural part and the single-V-shaped structural part are opposite. The wing rib and wing beam superstructure unit cell adopts a non-uniform cell wall design, so that the ordered deformation of the wing rib and wing beam ordered deformation superstructure is realized, and further the ordered deformation of the wing rib and the wing beam according to sequence and step by step is realized.

Description

Technical Field

[0001] The invention belongs to the technical field of missile wing structure design, and in particular is a variant missile wing based on an ordered deformation superstructure. Background Art

[0002] The complex flight environment places different demands on the flight performance of the aircraft. During the flight, the aircraft will experience changes from near the ground to high altitude, and the flight speed will also change from low speed to supersonic speed and hypersonic speed. Different flight phases have different requirements for lift-to-drag ratio and aerodynamic performance. For example, the long-distance cruise phase requires an increase in the wing area, while the accelerated flight phase requires a reduction in the wing area.

[0003] A variant wing is a deformable wing that changes the shape of the wing according to the needs of the aerodynamic shape to obtain good aerodynamic characteristics, thereby adapting to different flight environments and missions. The patent application with publication number CN116907287A, published on October 20, 2023, discloses a variant wing for an air-to-ship cruise missile and an air-to-ship cruise missile having the same. The variant wing includes a wing skeleton, a wing skin, and an auxiliary pull rope. The wing skeleton includes a short rod and a long rod. The middle parts of the two long rods are hinged to form a left wing main unit, and the middle parts of the other two long rods are hinged to form a right wing main unit. The left wing main unit and the right wing main unit are hinged and arranged on the air-to-ship cruise missile body; the wing skin is laid on the wing skeleton to provide lift; the auxiliary pull rope realizes the retraction and release of the wing skeleton, thereby changing the shape of the wing. However, the deformation of the chord-wise and span-wise directions of the variant missile wing is carried out synchronously, and only overall deformation can be achieved, but independent deformation in the span-wise and chord-wise directions cannot be achieved, and the deformation cannot be locally controlled, which limits the adaptability of the missile body to different flight missions. Summary of the invention

[0004] In view of the deficiencies in the prior art, the technical problem that the present invention intends to solve is to provide a variant missile wing based on an ordered deformation superstructure.

[0005] The present invention solves the technical problem by adopting the following technical solution: A variant missile wing based on an ordered deformation superstructure comprises a wing rib, a wing spar and a skin; the wing spar comprises a wing spar ordered deformation superstructure connector and a wing spar driver; a plurality of wing ribs are arranged in an array along a span direction, adjacent wing ribs are connected by the wing spar ordered deformation superstructure connector, and the wing spar driver is connected to each wing rib; The wing rib is provided with a wing rib orderly deformation superstructure, so that the wing rib can be expanded and contracted along the chord direction; the wing rib orderly deformation superstructure is formed by a plurality of wing rib superstructure cells arrayed in the chord direction and thickness direction of the variant missile wing, and the wing rib superstructure cell includes a double V-shaped structural member, a star-shaped structural member and a single V-shaped structural member, and the order of wall thickness from thin to thick is a single V-shaped structural member, a star-shaped structural member and a double V-shaped structural member; the two sides of the star-shaped structural member are respectively connected to the single V-shaped structural member and the double V-shaped structural member in sequence, the two end points of the single V-shaped structural member are respectively connected to the two vertices on one side of the star-shaped structural member, the corner points of the waist of the double V-shaped structural member are connected together, and the opening directions of the double V-shaped structural member and the single V-shaped structural member are opposite; the adjacent vertices of the star-shaped structural members of the two adjacent wing rib superstructure cells above and below are connected together, and the end points of the adjacent sides of the double V-shaped structural member are connected together; the adjacent two middle side end points of the double V-shaped structural members of the two adjacent wing rib superstructure cells on the left and right are connected together.

[0006] Further, the wing spar ordered deformation superstructure connecting member includes a wing spar ordered deformation superstructure and a wing spar connecting plate, and a wing spar ordered deformation superstructure is respectively provided on both sides of the wing spar connecting plate; the wing spar ordered deformation superstructure is formed by a plurality of wing spar superstructure unit cells arrayed along the thickness direction of the variant missile wing, the wing spar superstructure unit cell is formed by two wing spar superstructure unit cell structural members being bilaterally symmetrical, the wing spar superstructure unit cell structural members include eight-bar structural members, multi-triangular structural members and four-bar structural members, and the order of wall thickness from thin to thick is four-bar structural members, multi-triangular structural members and eight-bar structural members; The eight-bar structural member includes eight straight bars evenly arranged in two layers, and one ends of all the straight bars converge together to form the gathering end of the eight-bar structural member; the four-bar structural member is formed by four straight bars in a circular even array, and one ends of the four straight bars converge together to form the gathering end of the four-bar structural member; the multi-triangular structural member is formed by four isosceles triangle components in a circular even array, the vertices corresponding to one base angle of the four isosceles triangle components are connected together, the vertices corresponding to the top angles of the four isosceles triangle components are respectively connected to the four straight bars of the four-bar structural member, the four-bar structural member is connected to the gathering end of the eight-bar structural member, and the opening directions of the four-bar structural member and the eight-bar structural member are opposite; the other ends of the four straight bars of the inner layer of the eight-bar structural member of the two wing beam superstructure unit cell structural members are correspondingly connected together.

[0007] Furthermore, the interior of the star-shaped structural member is filled with a diamond-shaped structural member, and each vertex of the diamond-shaped structural member is connected to a corner point of a corresponding waist of the star-shaped structural member.

[0008] Furthermore, the double V-shaped structural member is formed symmetrically by two V-shaped structures, and a corner point is formed at the waist of the double V-shaped structural member.

[0009] Compared with the prior art, the present invention has the following beneficial effects: The variant wing of the present invention can flexibly switch deformation modes through single deformation of variable span and variable chord length, as well as combined deformation of the two, so as to adapt to different flight missions. The rib and spar superstructure unit cells adopt a non-uniform cell wall design to achieve orderly deformation of the rib and spar orderly deformation superstructure, and then achieve orderly deformation of the rib and spar in sequence and steps. It is also possible to achieve local orderly deformation by changing the wall thickness of the superstructure unit cells at different parts of the rib and spar orderly deformation superstructure, thereby enhancing the controllability of the deformation. The rib driver and spar driver composed of pneumatic muscles drive the spar and ribs to retract and retract, which is simpler in structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 It is a structural schematic diagram of the rib of the present invention; Figure 3 A schematic diagram of a rib ordered deformation superstructure of the present invention; Figure 4 It is a schematic structural diagram of a wing rib superstructure unit cell of the present invention; Figure 5 It is a schematic structural diagram of the spar ordered deformation superstructure connector of the present invention; Figure 6 It is a schematic diagram of the structure of a wing beam superstructure unit cell of the present invention; Figure 7 It is a deformation process diagram of the rib ordered deformation superstructure of the present invention; In the figure, 1-rib; 2-spar; 3-skin; 11-rib leading edge section; 12-chord-wise connecting hole; 13-span-wise connecting hole; 14-rib ordered deformation superstructure; 15-skin connecting member; 16-rib trailing edge section; 141-double V-shaped structural member; 142-star-shaped structural member; 143-single V-shaped structural member; 21-spar ordered deformation superstructure; 22-spar connecting plate; 211-eight-bar structural member; 212-multi-triangle structural member; 213-four-bar structural member. DETAILED DESCRIPTION

[0011] Specific embodiments are given below in conjunction with the accompanying drawings. The specific embodiments are only used to further introduce the technical solution of the present invention and are not intended to limit the protection scope of the present application.

[0012] The present invention provides a variant missile wing based on an ordered deformation superstructure (hereinafter referred to as a variant missile wing, see Figures 1 to 7), including ribs 1, spar 2 and skin 3; the spar 2 includes a spar ordered deformation superstructure connector and a spar driver; a plurality of ribs 1 are arranged in an array along the span direction, and the ribs 1 can be extended and retracted along the chord direction to realize the variable chord length of the variant wing; adjacent ribs 1 are connected by a plurality of spar ordered deformation superstructure connectors, a plurality of spar drivers are distributed on both sides of the ribs 1, and the spar drivers are connected to each rib 1, all the ribs 1 are connected in series, and the spar 2 is extended and retracted along the span direction through the spar driver, thereby realizing the variable span of the variant wing; the skin 3 is laid on the outside of all ribs 1 to form the aerodynamic shape of the variant wing.

[0013] like Figure 2 As shown, the rib 1 includes a rib leading edge section 11, a rib trailing edge section 16 and a rib leading and trailing edge connecting section; the rib leading and trailing edge connecting section includes a rib ordered deformation superstructure 14, a skin connector 15 and a rib driver, a plurality of skin connectors 15 are distributed on both sides of the rib ordered deformation superstructure 14 and are integrally formed therewith, each skin connector 15 is provided with a span-wise connecting hole 13 for connecting the spar driver; the rib leading edge section 11 and the rib trailing edge section 16 are both provided with chord-wise connecting holes 12, one end of the rib driver is fixedly connected to the chord-wise connecting hole 12 of the rib leading edge section 11, and the other end passes through the rib ordered deformation superstructure 14 and is fixedly connected to the chord-wise connecting hole 12 of the rib trailing edge section 16, for controlling the expansion and contraction of the rib ordered deformation superstructure 14 along the chord direction, thereby controlling the variable chord length of the variant wing.

[0014] like Figure 3 , 4As shown, the rib ordered deformation superstructure 14 is a honeycomb structure formed by a plurality of rib superstructure cells arranged in an array in the chord direction and thickness direction of the deformed missile wing. The rib superstructure cell includes a double V-shaped structural member 141, a star-shaped structural member 142 and a single V-shaped structural member 143; the interior of the star-shaped structural member 142 is filled with a diamond-shaped structural member, and each vertex of the diamond-shaped structural member is connected to the corner point of the corresponding waist of the star-shaped structural member 142; the double V-shaped structural member 141 is symmetrically formed by two V-shaped structures, and a corner point is formed at the waist of the double V-shaped structural member 141. The two sides of the star-shaped structural member 142 are respectively connected to the single V-shaped structural member 143 and the double V-shaped structural member 141 in sequence, so that the rib superstructure unit cell is a left-right symmetrical structure; the two end points of the single V-shaped structural member 143 are respectively connected to the two vertices on one side of the star-shaped structural member 142, the corner points of the waist of the double V-shaped structural member 141 are connected together with the corner points of the waist of the single V-shaped structural member 143, and the opening directions of the double V-shaped structural member 141 and the single V-shaped structural member 143 are opposite. The wing rib superstructure unit cell adopts a non-uniform wall thickness design, and the wall thickness is from thin to thick, which is a single V-shaped structural member 143, a star-shaped structural member 142 and a double V-shaped structural member 141, so that a strength difference is generated between different structural members, so that the wing rib superstructure unit cell can deform in an orderly manner; when the wing rib superstructure unit cell is subjected to an external load along the chord direction, the single V-shaped structural member 143 is bent and deformed first, and then the double V-shaped structural member 141 is bent and deformed, so as to realize the expansion and contraction of the wing rib superstructure unit cell along the chord direction, while the star-shaped structural member 142 does not bend and deform, and plays a role in supporting the wing rib superstructure unit cell. The adjacent vertices of the star-shaped structural member 142 of the two adjacent wing rib superstructure units on the upper and lower sides are connected together, and the end points of the adjacent sides of the double V-shaped structural member 141 are connected together; the adjacent middle two side end points of the double V-shaped structural member 141 of the two adjacent wing rib superstructure units on the left and right are connected together.

[0015] like Figure 5 , 6 As shown, the wing spar ordered deformation superstructure connector includes a wing spar ordered deformation superstructure 21 and a wing spar connecting plate 22; a wing spar ordered deformation superstructure is provided on both sides of the wing spar connecting plate 22, and the wing spar connecting plate 22 plays a role in supporting the wing spar ordered deformation superstructure connector.

[0016] The wing beam ordered deformation superstructure 21 is a honeycomb structure formed by a plurality of wing beam superstructure cells arranged in an array along the thickness direction of the deformed wing. The wing beam superstructure cell is formed by two wing beam superstructure cell structural members that are bilaterally symmetrical, and the wing beam superstructure cell structural members include an eight-bar structure member 211, a multi-triangle structure member 212, and a four-bar structure member 213; the eight-bar structure member 211 includes eight straight bars arranged in two layers, and the four straight bars in the inner layer and the outer layer are uniformly arranged in a circle, and one end of all the straight bars converge together to form the gathering end of the eight-bar structure member 211; the four-bar structure member 213 is formed by four straight bars arranged in a uniform circle, and one end of the four straight bars converge together to form the gathering end of the four-bar structure member 213. The multi-triangular structural member 212 is formed by four isosceles triangle members arranged uniformly in a circular pattern, the vertices corresponding to a base angle of the four isosceles triangle members are connected together, the vertices corresponding to the top angles of the four isosceles triangle members are respectively connected to the four straight rods of the four-rod structural member 213, the four-rod structural member 213 is connected to the gathering end of the eight-rod structural member 211, and the opening directions of the four-rod structural member 213 and the eight-rod structural member 211 are opposite; the other ends of the four straight rods of the inner layer of the eight-rod structural member 211 of the two wing beam superstructure unit cell structural members are connected together. The wing beam superstructure unit cell structural members also adopt a non-uniform wall thickness design, and the wall thicknesses are from thin to thick, namely, the four-bar structure 213, the multi-triangle structure 212, and the eight-bar structure 211, so that strength differences are generated between different structural members, and orderly deformation of the wing beam superstructure unit cell is achieved; when the wing beam superstructure unit cell is subjected to an external load along the span direction, the four-bar structure 213 is first bent and deformed, and then the eight-bar structure 211 is bent and deformed, so that the wing beam superstructure unit cell can be expanded and contracted along the span direction, while the multi-triangle structure 212 does not bend and deform, and plays a role in supporting the wing beam superstructure unit cell. The vertices of the adjacent isosceles triangle components of the two multi-triangle structures 212 on the same side of two adjacent wing beam superstructure units are connected together, and the two adjacent straight bars of the two eight-bar structures 211 are connected together.

[0017] The rib superstructure unit cell adopts a non-uniform wall thickness design, so that the rib ordered deformation superstructure 14 is orderly deformed in steps under the action of load. It is also possible to change the wall thickness of the single V-shaped structural member 143 of the rib superstructure unit cell at different parts of the rib ordered deformation superstructure 14 to achieve local orderly deformation of the rib ordered deformation superstructure 14, so as to achieve the controlled local orderly deformation of the variant wing. For example, if the wall thickness of the single V-shaped structural member 143 of the rib ordered deformation superstructure 14 decreases row by row from the leading edge to the trailing edge of the rib, and the wall thickness of the double V-shaped structural member 141 and the star-shaped structural member 142 of all the rib superstructure unit cells remains unchanged, when the rib ordered deformation superstructure 14 is subjected to an external load along the chord direction, the rib superstructure unit cells are bent and deformed row by row from the trailing edge to the leading edge. If the wall thickness of the single V-shaped structural member 143 in the middle row of the wing rib ordered deformation superstructure 14 is small, and the wall thickness of the single V-shaped structural member 143 in the two end rows is large, when the wing rib ordered deformation superstructure 14 is subjected to an external load along the chord direction, the wing rib superstructure unit cells in the middle row will bend and deform first, and then the two side rows will bend and deform. If the wall thickness of the single V-shaped structural member 143 in the middle row of the wing rib ordered deformation superstructure 14 is large, and the wall thickness of the single V-shaped structural member 143 in the two end rows is small, when the wing rib ordered deformation superstructure 14 is subjected to an external load along the chord direction, the wing rib superstructure unit cells in the two end rows will bend and deform first, and then the middle row will bend and deform. Similarly, the non-uniform wall thickness design of the spar superstructure unit cells can realize the orderly deformation of the spar ordered deformation superstructure 21.

[0018] In order to verify the ordered deformation characteristics of the superstructure, a finite element simulation is performed using the rib ordered deformation superstructure 14 as an example. The wall thickness of the single V-shaped structural member 143 of the rib ordered deformation superstructure 14 decreases row by row from the leading edge to the trailing edge of the rib, and the wall thickness of the double V-shaped structural member 141 and the star-shaped structural member 142 of all rib superstructure units remains unchanged. A chord-wise compression load is applied to them, as shown in FIG. Figure 7 As shown, the rib superstructure unit cell at the trailing edge of the rib first undergoes bending deformation, and the rib orderly deformation superstructure 14 as a whole deforms row by row from the trailing edge to the leading edge of the rib, and the deformation sequence follows the principle of weak first and strong later, that is, the rib superstructure unit cells with smaller thickness and weaker strength deform first; since the wall thickness of the double V-shaped structural parts 141 and the star-shaped structural parts 142 of all the rib superstructure unit cells remains unchanged, the double V-shaped structural parts 141 of all the rib superstructure unit cells deform simultaneously, and finally the orderly contraction of the overall structure is achieved, thereby proving the orderly deformation characteristics of the superstructure.

[0019] The working principle and workflow of the present invention are: The variant wing has three deformation modes: variable chord length, variable span length, and variable span length and chord length, which can meet the various requirements of the aerodynamic performance of the projectile in different flight phases.

[0020] When the chord length is changed, the length of the pneumatic muscle as the wing beam driver is kept unchanged, the pneumatic muscle as the wing rib driver is controlled to contract or extend, and the wing rib 1 is driven to contract or extend in an orderly manner along the chord direction, so as to realize the variable chord length of the variant wing. When the span is changed, the length of the pneumatic muscle as the wing rib driver is kept unchanged, the pneumatic muscle as the wing beam driver is controlled to contract or extend, and the wing beam 2 is driven to contract or extend in an orderly manner along the span direction, so as to realize the variable span of the variant wing. When the span and chord length are changed at the same time, the pneumatic muscles as the wing rib driver and the wing beam driver are contracted or extended at the same time, and the wing rib 1 and the wing beam 2 are driven to contract or extend in the chord direction and the span direction, so as to realize the combined deformation of the variant wing in the chord direction and the span direction. At the same time, the aspect ratio of the variant wing can be flexibly adjusted by controlling the expansion and contraction of the wing rib driver and the wing beam driver respectively.

[0021] Any matters not described in the present invention are applicable to the prior art.

Claims

1. A variant missile wing based on an ordered deformation superstructure, comprising ribs, spars and skins; characterized in that: The wing spar includes a wing spar ordered deformation superstructure connector and a wing spar driver; a plurality of wing ribs are arranged in an array along the span direction, adjacent wing ribs are connected by the wing spar ordered deformation superstructure connector, and the wing spar driver is connected to each wing rib; The wing rib is provided with a wing rib orderly deformation superstructure, so that the wing rib can be expanded and contracted along the chord direction; the wing rib orderly deformation superstructure is formed by a plurality of wing rib superstructure cells arrayed in the chord direction and thickness direction of the variant missile wing, and the wing rib superstructure cell includes a double V-shaped structural member, a star-shaped structural member and a single V-shaped structural member, and the order of wall thickness from thin to thick is a single V-shaped structural member, a star-shaped structural member and a double V-shaped structural member; the two sides of the star-shaped structural member are respectively connected to the single V-shaped structural member and the double V-shaped structural member in sequence, the two end points of the single V-shaped structural member are respectively connected to the two vertices on one side of the star-shaped structural member, the corner points of the waist of the double V-shaped structural member are connected together, and the opening directions of the double V-shaped structural member and the single V-shaped structural member are opposite; the adjacent vertices of the star-shaped structural members of the two adjacent wing rib superstructure cells above and below are connected together, and the end points of the adjacent sides of the double V-shaped structural member are connected together; the adjacent two middle side end points of the double V-shaped structural members of the two adjacent wing rib superstructure cells on the left and right are connected together.

2. The variant missile wing based on the ordered deformation superstructure according to claim 1 is characterized in that: The wing spar ordered deformation superstructure connecting member comprises a wing spar ordered deformation superstructure and a wing spar connecting plate, and a wing spar ordered deformation superstructure is respectively provided on both sides of the wing spar connecting plate; the wing spar ordered deformation superstructure is formed by a plurality of wing spar superstructure unit cells arranged in an array along the thickness direction of the variant missile wing, the wing spar superstructure unit cell is formed by two wing spar superstructure unit cell structural members being bilaterally symmetrical, the wing spar superstructure unit cell structural members comprise eight-bar structural members, multi-triangular structural members and four-bar structural members, and the order of wall thickness from thin to thick is four-bar structural members, multi-triangular structural members and eight-bar structural members; The eight-bar structural member includes eight straight bars evenly arranged in two layers, and one ends of all the straight bars converge together to form the gathering end of the eight-bar structural member; the four-bar structural member is formed by four straight bars in a circular even array, and one ends of the four straight bars converge together to form the gathering end of the four-bar structural member; the multi-triangular structural member is formed by four isosceles triangle components in a circular even array, the vertices corresponding to one base angle of the four isosceles triangle components are connected together, the vertices corresponding to the top angles of the four isosceles triangle components are respectively connected to the four straight bars of the four-bar structural member, the four-bar structural member is connected to the gathering end of the eight-bar structural member, and the opening directions of the four-bar structural member and the eight-bar structural member are opposite; the other ends of the four straight bars of the inner layer of the eight-bar structural member of the two wing beam superstructure unit cell structural members are correspondingly connected together.

3. The variant missile wing based on the ordered deformation superstructure according to claim 1 or 2, characterized in that: The interior of the star-shaped structural member is filled with a diamond-shaped structural member, and each vertex of the diamond-shaped structural member is connected with a corner point of a corresponding waist of the star-shaped structural member.

4. The variant missile wing based on the ordered deformation superstructure according to claim 3 is characterized in that: The double V-shaped structural member is symmetrically formed by two V-shaped structures, and a corner point is formed at the waist of the double V-shaped structural member.

Images