Variable chord length and sweepback variant missile wing and aircraft

Abstract

The invention relates to the technical field of missile wing structure design, in particular to a variable chord length and sweepback variant missile wing which comprises a wing rib, a wing spar and a skin. The plurality of wing ribs are arrayed along the extension direction, and the adjacent wing ribs are connected through the spar; the wing rib comprises a wing rib front edge section, a wing rib rear edge section and a wing rib front and rear edge connecting section; the wing rib front and rear edge connecting section is formed by arraying a plurality of single crystal cell structures in three spatial directions, and each single crystal cell structure comprises a side plate, a center supporting plate and an arc-shaped rib; the two side plates are symmetrically arranged on the two sides of the center supporting plate, the center supporting plate and the two side plates are connected through a plurality of arc-shaped ribs which are evenly arrayed, the two arc-shaped ribs on the same side are symmetrical about the center supporting plate, the connecting sections of the front edge and the rear edge of the wing rib can stretch out and draw back in the chord length direction, and chord length changing of the variant missile wing is achieved. The spar comprises a first base plate, a second base plate, a first driven rod, a second driven rod, a third driven rod, a fourth driven rod, a driving rod and a fifth driven rod, and sweepback changing of the variant missile wing is achieved through deformation of the spar. According to the variant missile wing, the aerodynamic performance of the aircraft is improved, so that the aircraft can adapt to different flight environments and tasks.

Description

Technical Field

[0001] The invention belongs to the technical field of missile wing structure design, in particular to a variant missile wing with variable chord length and sweep and an aircraft. Background Art

[0002] The purpose of variant wings is to change the shape of the wings so that the aircraft can change the wing posture as needed when performing missions and storing, in order to obtain better aerodynamic performance and storage space. For example, when storing an aircraft, the wings need to be retracted to reduce the wing area, so that more aircraft can be stored in the same storage space and more aircraft can be carried in a single transport. Changing the chord length and sweep angle of the wing can change the wing area, and changing the sweep angle can also change the span of the wing, so that the aircraft can obtain better aerodynamic performance during flight. For example, increasing the chord length of the wing or reducing the sweep angle can increase the area of ​​the wing, so that the aircraft can obtain more lift and a longer flight distance during flight.

[0003] The patent application with publication date of June 29, 2018 and publication number of CN108225120A discloses a skin-frame structure wing, including a frame and skins on both sides, and a rib group is also arranged inside the frame, and the rib group includes a plurality of radial ribs, a plurality of annular ribs and a plurality of longitudinal ribs. However, the function of the wing is relatively single, and the wing cannot be deformed. During the flight, the aircraft cannot adjust the wing posture in time according to different flight environments, and the length and angle of the wing cannot be adjusted. It is also inconvenient to store and transport. 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 wing and an aircraft with variable chord length and sweep.

[0005] The present invention solves the technical problem by adopting the following technical solution: A variable chord length and swept variant missile wing, comprising a rib, a spar and a skin; a plurality of ribs are arranged in an array along a span direction, and adjacent ribs are connected by a spar; the ribs comprise a rib leading edge section, a rib trailing edge section and a rib leading and trailing edge connecting section; the rib leading and trailing edge connecting section is formed by a plurality of single cell structures arranged in three spatial directions, the single cell structure comprising a side plate, a central support plate and an arc-shaped rib; two side plates are symmetrically arranged on both sides of the central support plate, the central support plate and the two side plates are respectively connected by a plurality of arc-shaped ribs in a uniform array, the two arc-shaped ribs on the same side are symmetrical about the central support plate, and the arc-shaped ribs can be bent and deformed under the action of a load along the chord length direction, so that the single cell structure can be stretched and retracted along the chord length direction; The wing beam includes a first base plate, a second base plate and a multi-rod mechanism, and the multi-rod mechanism includes a first driven rod, a second driven rod, a third driven rod, a fourth driven rod, an active rod and a fifth driven rod; the upper end of the first driven rod is fixedly connected to an end of the first base plate close to the rear edge of the wing rib, the lower end of the first driven rod is rotatably connected to the middle part of the third driven rod, the upper end of the third driven rod is rotatably connected to the upper end of the active rod, the lower end of the third driven rod is rotatably connected to the upper end of the fourth driven rod, and the lower end of the fourth driven rod is rotatably connected to an end of the second base plate close to the rear edge of the wing rib; the lower end of the active rod is rotatably connected to an end of the second base plate close to the leading edge of the wing rib, the middle part of the active rod is rotatably connected to the lower end of the fifth driven rod, the upper end of the fifth driven rod is rotatably connected to the lower end of the second driven rod, the upper end of the second driven rod is slidably connected to the bottom of the first base plate, and the second driven rod and the first driven rod are always perpendicular to the first base plate and the second base plate.

[0006] Furthermore, adjacent single cell structures along the chord length direction share a side plate, adjacent arcuate ribs of adjacent single cell structures along the rib thickness direction are connected together, and adjacent arcuate ribs of adjacent single cell structures along the rib width direction are connected together.

[0007] Furthermore, the arc-shaped rib is formed by two 90-degree arc segments in opposite directions being tangentially connected.

[0008] Furthermore, the arc-shaped ribs are made of nylon, memory alloy or spring steel.

[0009] The present invention also provides an aircraft, characterized in that the aircraft comprises the above-mentioned variable chord length and swept variant wing.

[0010] Compared with the prior art, the present invention has the following beneficial effects: The single cell structure is a mechanical metamaterial structure. The arc-shaped ribs of the single cell structure have the characteristic of zero Poisson's ratio, so the overall deformation direction of the front and rear edge connection section of the wing rib can be limited, so that the front and rear edge connection section of the wing rib can only be stretched and retracted along the chord length direction, realizing the variable chord length of the variant wing. The front and rear edge connection section of the wing rib is composed of a single cell structure array, so the front and rear edge connection section of the wing rib is hollow as a whole, which reduces the overall mass of the wing and gives the aircraft better endurance.

[0011] The wing beam connecting adjacent wing ribs is actually a variable sweep mechanism. Compared with the traditional parallelogram linkage mechanism, the wing beam has more rod structures and higher strength, which ensures the stability of movement during the variable sweep process. The variable-variable wing can achieve spanwise contraction while achieving variable sweep, saving storage space for the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 It is a schematic diagram of the overall structure; Figure 2 This is a schematic diagram of the structure after removing the skin; Figure 3 is a schematic diagram of a single cell structure; Figure 4 It is a schematic diagram of the array of single cell structures along the chord length and rib thickness direction; Figure 5 It is a cross-sectional view of the overall structure along the upper and lower bisecting planes; Figure 6 is a schematic diagram of the structure of the wing spar; Figure 7 This is a schematic diagram of the distribution of wing ribs before variable sweep; Figure 8 This is a schematic diagram of the distribution of wing ribs after variable sweep; In the figure, 100-rib; 200-spar; 300-skin; 101 - side plate; 102 - central support plate; 103 - arc-shaped ribs; 201 - first base plate; 202 - first driven rod; 203 - second driven rod; 204 - third driven rod; 205 - fourth driven rod; 206 - active rod; 207 - second base plate; 208 - fifth driven rod. DETAILED DESCRIPTION

[0013] Specific embodiments are given below in conjunction with the accompanying drawings. The specific embodiments are only used to introduce the technical solutions of the present invention in detail and are not intended to limit the protection scope of the present application.

[0014] On the one hand, the present invention provides a variant missile wing with variable chord length and sweep (hereinafter referred to as the missile wing, see Figures 1 to 8 ), including ribs 100, spar 200 and skin 300; multiple ribs 100 are arranged in an array along the span direction, and the ribs 100 can be extended and retracted along the chord length direction to achieve variable chord length of the variant wing; the length and thickness of the ribs 100 change adaptively with the shape of the wing, that is, they change in a gradient from the wing root to the wing tip, while the width of the ribs 100 remains unchanged; adjacent ribs 100 are connected by spar 200, and the spar 200 can be bent to achieve variable sweep of the variant wing; the skin 300 is wrapped around the outside of all ribs 100, so that the surface of the variant wing is relatively smooth, ensuring the flight performance of the aircraft. The variant wing adopts an integral design, which can improve the overall strength of the aircraft.

[0015] The wing rib 100 includes a wing rib leading edge section, a wing rib trailing edge section and a wing rib leading and trailing edge connecting section; the wing rib leading edge section and the wing rib trailing edge section do not deform and play a role in supporting the wing rib; the wing rib leading and trailing edge connecting section is composed of a plurality of single cell structures arrayed along three directions of chord length, wing rib thickness and wing rib width, and each wing rib leading and trailing edge connecting section contains a different number of single cell structures, and the wing rib leading and trailing edge connecting section can be stretched and retracted along the chord length direction. The single cell structure is a bilaterally symmetrical structure, including side panels 101, a central support plate 102 and arc-shaped ribs 103; the two side panels 101 are symmetrically arranged on both sides of the central support plate 102, and the central support plate 102 and the two side panels 101 are respectively connected together by a plurality of arc-shaped ribs 103 in a uniform array, and the two arc-shaped ribs 103 on the same side are symmetrical about the central support plate 102; the arc-shaped ribs 103 are formed by two 90-degree arc segments in opposite directions being tangentially connected, and the arc-shaped ribs 103 can bend and deform under load, and when subjected to a load along the chord length direction, the single cell structure can expand and contract along the chord length direction, so that the connecting sections of the front and rear edges of the ribs can expand and contract along the chord length direction, thereby realizing a variable chord length of the variant wing. Adjacent single cell structures along the chord length direction share a side plate 101, adjacent arcuate ribs 103 of adjacent single cell structures along the rib thickness direction are connected together, and adjacent arcuate ribs 103 of adjacent single cell structures along the rib width direction are connected together.

[0016] The wing beam 200 includes a first base plate 201, a second base plate 207 and a multi-rod mechanism; the second base plate 207 is fixedly connected to the leading edge section of the wing rib near the wing root, the first base plate 201 is fixedly connected to the leading edge section of the wing rib near the wing tip, and the multi-rod mechanism is symmetrically arranged on both sides of the first base plate 201 and the second base plate 207; the multi-rod mechanism includes a first driven rod 202, a second driven rod 203, a third driven rod 204, a fourth driven rod 205, an active rod 206 and a fifth driven rod 208; the first driven rod 201 The upper end of the first driven rod 202 is fixedly connected to one end of the first base plate 201 near the rear edge of the wing rib, the lower end of the first driven rod 202 is rotatably connected to the middle part of the third driven rod 204, the upper end of the third driven rod 204 is rotatably connected to the upper end of the active rod 206, the lower end of the third driven rod 204 is rotatably connected to the upper end of the fourth driven rod 205, the lower end of the fourth driven rod 205 is rotatably connected to one end of the second base plate 207 near the rear edge of the wing rib; the lower end of the active rod 206 is rotatably connected to the middle part of the third driven rod 204 near the front edge of the wing rib The middle part of the active rod 206 is rotatably connected to the lower end of the fifth driven rod 208, the upper end of the fifth driven rod 208 is rotatably connected to the lower end of the second driven rod 203, the upper end of the second driven rod 203 is slidably connected to the bottom of the first substrate 201, and the second driven rod 203 and the first driven rod 202 are always perpendicular to the first substrate 201 and the second substrate 207; the initial position is that the first substrate 201 and the second substrate 207 completely overlap, when the sweep needs to be changed, the active rod 2 06 rotates clockwise around the second base plate 207, driving the third driven rod 204 to rotate clockwise around the rotation center with the active rod 206, the fourth driven rod 205 rotates clockwise around the second base plate 207, the fifth driven rod 208 rotates counterclockwise around the rotation center with the active rod 206, and the second driven rod 203 slides on the first base plate 201 toward the leading edge of the rib, so that the first base plate 201 translates toward the trailing edge of the rib relative to the second base plate 207, realizing the variable sweep function of the variant bomb wing. The movement of the active rod 206 toward the connection position of the fourth driven rod 205 and the second base plate 207 is a clockwise rotation, and the movement away from the connection position of the fourth driven rod 205 and the second base plate 207 is a counterclockwise rotation.

[0017] The arc-shaped ribs 103 are made of a flexible material with a certain rigidity, such as nylon, memory alloy, spring steel, etc., to ensure that the single cell structure can bend and deform under load and expand and contract along the chord length direction.

[0018] On the other hand, the present invention also provides an aircraft, which comprises the above-mentioned variable chord length and swept variant wing.

[0019] The working principle and workflow of the present invention are: When the chord length needs to be changed, the rib 100 is subjected to a load along the chord length direction, and all the arc-shaped ribs 103 of the single-cell structure of the connecting section of the front and rear edges of the rib are bent and deformed, so that the connecting section of the front and rear edges of the rib is elongated or shortened along the chord length direction, thereby lengthening or shortening the length of the rib 100, thereby realizing the variable chord length of the variant wing.

[0020] When the sweep is required to be changed, the active rod 206 rotates clockwise around the second base plate 207, driving the third driven rod 204 to rotate clockwise around the rotation center of the active rod 206, the driven rod 205 rotates clockwise around the second base plate 207, the fifth driven rod 208 rotates counterclockwise around the rotation center of the active rod 206, and the second driven rod 203 slides on the first base plate 201 toward the leading edge of the rib, so that the first base plate 201 translates toward the trailing edge of the rib relative to the second base plate 207, thereby realizing the variable sweep of the variant wing, see Figure 7 , 8 .

[0021] The variable chord length and variable sweep functions of the variant missile wing do not affect each other and are independent of each other. The variable chord length and variable sweep functions can also be achieved at the same time.

[0022] Any matters not described in the present invention are applicable to the prior art.

Claims

1. A variant missile wing with variable chord length and sweep, comprising ribs, spar and skin; a plurality of ribs are arranged in an array along the span direction, and adjacent ribs are connected by spar; characterized in that: The wing rib comprises a wing rib leading edge section, a wing rib trailing edge section and a wing rib leading and trailing edge connecting section; the wing rib leading and trailing edge connecting section is formed by a plurality of single cell structures arrayed in three directions in space, and the single cell structure comprises a side plate, a central support plate and an arc-shaped rib; two side plates are symmetrically arranged on both sides of the central support plate, and the central support plate and the two side plates are respectively connected by a plurality of arc-shaped ribs in a uniform array, and the two arc-shaped ribs on the same side are symmetrical about the central support plate, and the arc-shaped ribs can be bent and deformed under the action of a load in the chord length direction, so that the single cell structure can be stretched and retracted in the chord length direction; The wing beam includes a first base plate, a second base plate and a multi-rod mechanism, and the multi-rod mechanism includes a first driven rod, a second driven rod, a third driven rod, a fourth driven rod, an active rod and a fifth driven rod; the upper end of the first driven rod is fixedly connected to an end of the first base plate close to the rear edge of the wing rib, the lower end of the first driven rod is rotatably connected to the middle part of the third driven rod, the upper end of the third driven rod is rotatably connected to the upper end of the active rod, the lower end of the third driven rod is rotatably connected to the upper end of the fourth driven rod, and the lower end of the fourth driven rod is rotatably connected to an end of the second base plate close to the rear edge of the wing rib; the lower end of the active rod is rotatably connected to an end of the second base plate close to the leading edge of the wing rib, the middle part of the active rod is rotatably connected to the lower end of the fifth driven rod, the upper end of the fifth driven rod is rotatably connected to the lower end of the second driven rod, the upper end of the second driven rod is slidably connected to the bottom of the first base plate, and the second driven rod and the first driven rod are always perpendicular to the first base plate and the second base plate.

2. The variable chord length and swept variant wing according to claim 1, characterized in that: Adjacent single cell structures along the chord length direction share a side plate, adjacent arc-shaped ribs of adjacent single cell structures along the rib thickness direction are connected together, and adjacent arc-shaped ribs of adjacent single cell structures along the rib width direction are connected together.

3. The variable chord length and swept variant wing according to claim 1 or 2, characterized in that: The arc-shaped rib is formed by tangentially connecting two 90-degree arc segments in opposite directions.

4. The variable chord length and swept variant wing according to claim 3, characterized in that: The arc-shaped ribs are made of nylon, memory alloy or spring steel.

5. An aircraft, characterized in that: The aircraft comprises the variable chord length and swept variant wing according to claim 1.

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