Variant wing with variable chord length, camber and elongation and aircraft
By adopting a single-cell structure of variable chord length and variable curvature in the deformed wing and combining the design of the variable length drive unit, the problems of insufficient deformation complexity and accuracy of the wing in the prior art are solved, and efficient aerodynamic performance is achieved and improve flight efficiency.
Patent Information
- Application Number
- CN202411329385.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-24
- Publication Date
- 2024-12-27
- Estimated Expiration
- 2044-09-24
AI Technical Summary
Existing deformation wings are complex and difficult to maintain when achieving curvature and lengthening deformation, and are difficult to control accurately, affecting flight performance and efficiency.
Using a wing design that includes a variable chord length single cell structure and a variable curvature single cell structure, the wing expansion and bending are achieved through components such as X-shaped connecting rods, V-shaped connecting rods and wavy connecting rods, combined with variable length The drive unit achieves lengthening and changes, and uses flexible materials to improve stiffness and accuracy.
It realizes high-precision deformation of the wings, improves aerodynamic performance and flight efficiency, reduces wing quality, and enhances the endurance and flexibility of the aircraft.
Smart Images
Figure CN119190338A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of deformation wing structure design, in particular to a deformation wing and an aircraft with variable chord length, camber and span. Background Art
[0002] The purpose of the variant wing is to change the chord length, curvature and / or span of the wing so that the aircraft can change the shape of the wing and thus change the flight attitude according to the environment when performing a flight mission, so as to adapt to different flight environments and obtain better aerodynamic performance.
[0003] For example, during high-speed flight in the cruising phase, the drag can be reduced by reducing the wing area by changing the chord length, while during low-speed flight in the take-off and landing phases, lift can be provided by increasing the wing area. When performing specific tasks and facing emergencies during flight, the wing changes the lift distribution of the aircraft by changing the curvature, thereby improving the maneuverability of the aircraft. When the aircraft needs to fly at a lower speed and for a longer flight time, such as long-distance cruising or reconnaissance missions, the aircraft can increase the lift and lift-to-drag ratio by increasing the wingspan, thereby maintaining a high flight efficiency and extending the flight time. In situations where higher maneuverability and flexibility are required, such as take-off, landing, cruising, etc., the wind resistance is reduced by shortening the wingspan to improve the agility of the aircraft. In addition, variable span gives the aircraft better storage and transportation characteristics, making it more convenient for the aircraft to be stored and transported.
[0004] The invention patent application with publication date of March 26, 2019 and publication number of CN109515683A discloses a deformable wing with variable chord length and camber, including a leading edge section, a middle section and a trailing edge section of the wing, wherein a plurality of parallel arranged deformation units are distributed in the middle section of the wing, and the deformation unit comprises a parallelogram structure, and the wing can be changed in curvature and chord length by locking the lower triangle of the parallelogram structure to change the shape of the upper triangle and locking the upper triangle to change the shape of the lower triangle. The wing can achieve both bending and variable chord length functions through the parallelogram structure, and the deformation operation is complicated and not easy to maintain without deformation. Summary of the invention
[0005] In view of the deficiencies in the prior art, the technical problem to be solved by the present invention is to provide a variant wing and an aircraft with variable chord length, camber and span.
[0006] The present invention solves the technical problem by adopting the following technical solution:
[0007] A variant wing with variable chord length, camber and span, comprising a wing rib, a wing spar and a skin, wherein the wing rib can be extended, shortened and bent, and the wing spar can be extended and shortened; characterized in that the wing rib comprises a variable chord length single cell structure and a variable camber single cell structure, a plurality of variable chord length single cell structures are sequentially connected to form a wing rib body, the front and rear ends of the wing rib body are respectively connected to the variable camber single cell structures, and adjacent single cell structures share a substrate;
[0008] The variable chord length single cell structure includes a first connecting frame that limits the telescopic direction, and the first connecting frame includes an X-shaped connecting rod and a V-shaped connecting rod; two X-shaped connecting rods are connected side by side, and the middle parts of the two X-shaped connecting rods jointly form a quadrilateral frame, and the V-shaped connecting rod is located in the quadrilateral frame and its two ends are connected to the middle parts of the corresponding X-shaped connecting rods, so that the middle part of the first connecting frame forms a special-shaped structure;
[0009] The variable curvature single cell structure includes a second connecting frame for limiting the bending direction, and the second connecting frame includes a horizontal connecting rod, a wavy connecting rod and a reinforcing connecting rod; the two wavy connecting rods are symmetrically distributed on the upper and lower sides of the horizontal connecting rod, and each bending part of each wavy connecting rod is connected to the horizontal connecting rod through a reinforcing connecting rod, and the reinforcing connecting rod is inclined toward the free end of the variable curvature single cell structure.
[0010] Furthermore, the wing beam includes a first support plate, a second support plate and a variable length drive unit; the two second support plates are symmetrically distributed on both sides of the first support plate, and the middle part of at least one variable length drive unit is connected to the first support plate, and the two ends are connected to the corresponding second support plates;
[0011] The variable length driving unit includes a variable length driving member, a first connecting rod, a second connecting rod and a gear; one end of the two first connecting rods are rotatably connected to one end of one side of the first support plate through a connecting shaft, and the two connecting shafts are respectively provided with gears, and the two gears are meshed; the other ends of the two first connecting rods are respectively rotatably connected to one end of the corresponding second connecting rod, and the other ends of the two second connecting rods are respectively rotatably connected to one end of one side of the corresponding second support plate, and when the wing beam is in the original length state, a certain angle is formed between the connected first connecting rod and the second connecting rod; one end of the two variable length driving members are rotatably connected to the other end of one side of the first support plate, and the other ends of the two variable length driving members are respectively rotatably connected to the middle part of the corresponding first connecting rod.
[0012] Furthermore, the special-shaped structure in the middle of the first connecting frame has three collinear sharp corners, two of which are in the same direction, and the other is in the opposite direction.
[0013] Furthermore, the variable curvature single cell structure also includes a variable curvature driving component and a second substrate. The left and right sides of the two second substrates are respectively connected together by a second connecting frame. The two variable curvature driving components are located at the upper and lower parts of the two second substrates. The fixed end and telescopic end of the variable curvature driving component are respectively connected to the two second substrates.
[0014] Furthermore, the variable curvature single cell structure also includes a first connecting frame; the two first connecting frames are located on the upper and lower sides of the two second substrates, and the two sharp corners of the special-shaped structure with the same direction are close to the free end of the variable curvature single cell structure.
[0015] Furthermore, the variable string length single cell structure also includes a variable string length driver and a first substrate; at least two opposite sides of the two first substrates are connected together by a first connecting frame, and the fixed end and the telescopic end of the variable string length driver are respectively connected to the centers of the two first substrates.
[0016] An aircraft, characterized in that it comprises the above-mentioned variant wing with variable chord length, camber and span.
[0017] Compared with the prior art, the present invention has the following beneficial effects:
[0018] The variable chord length single cell structure and variable curvature single cell structure of the present invention are mechanical super structures. The special-shaped structure in the middle of the first connecting frame limits the deformation direction of the single cell structure, so that the variable chord length single cell structure and the variable curvature single cell structure have the special property of zero Poisson's ratio. At the same time, the second connecting frame of the variable curvature single cell structure provides a direction limit for the wing curvature change, improves the accuracy of the wing variable chord length and curvature, and also makes the variant wing have better aerodynamic performance. The first connecting frame and the second connecting frame are made of flexible materials with a certain rigidity, which improves the rigidity and deformation accuracy of the wing. The variable chord length single cell structure and the variable curvature single cell structure are both hollow structures, which makes the overall weight of the wing lighter and can increase the endurance of the aircraft. The wing has three deformation functions of variable chord length, curvature and span, so that the aircraft can change the shape of the wing when performing different flight missions to optimize the lift-to-drag ratio of the wing and improve flight performance and efficiency. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 It is a schematic diagram of the overall structure;
[0020] Figure 2 It is a schematic diagram of the structure of the wing rib;
[0021] Figure 3 Schematic diagram of the variable string length single cell structure;
[0022] Figure 4 is a structural schematic diagram of a first connecting frame;
[0023] Figure 5 Schematic diagram of the variable curvature single cell structure;
[0024] Figure 6 is a structural schematic diagram of a second connecting frame;
[0025] Figure 7 is a schematic diagram of the structure of the wing spar;
[0026] In the figure, 100-variable chord length single cell structure; 200-variable curvature single cell structure; 300-wing beam;
[0027] 101-first connecting frame; 102-variable chord length driving member; 103-first base plate; 201-second connecting frame; 202-variable curvature driving member; 203-second base plate; 301-first supporting plate; 302-second supporting plate; 303-variable extension driving member; 304-first connecting rod; 305-second connecting rod; 306-gear;
[0028] 101-1, X-shaped connecting rod; 101-2, V-shaped connecting rod; 201-1, horizontal connecting rod; 201-2, wave-shaped connecting rod; 201-3, reinforced connecting rod. DETAILED DESCRIPTION
[0029] 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.
[0030] In one aspect, the present invention provides a variant wing (hereinafter referred to as wing, see Figures 1 to 7 ), including a wing rib, a wing beam 300 and a skin; wherein the wing rib includes a variable chord length single cell structure 100 and a variable curvature single cell structure 200, a plurality of (two in this embodiment) variable chord length single cell structures 100 are sequentially connected to form a wing rib body, and the front and rear ends of the wing rib body are respectively sequentially connected to a plurality of variable curvature single cell structures 200, and adjacent single cell structures share a substrate. In this embodiment, the front end of the wing rib body is connected to a variable curvature single cell structure 200, and the rear end is connected to two variable curvature single cell structures 200. The variable chord length single cell structure 100 can extend and shorten along the length direction of the wing rib, so that the wing rib is extended and shortened to achieve variable chord length of the wing; the variable curvature single cell structure 200 can bend to achieve variable curvature of the wing.
[0031] The variable chord length single cell structure 100 includes a first connecting frame 101, a variable chord length driving member 102 and a first substrate 103; at least two opposite sides of the two first substrates 103 are connected together through the first connecting frame 101, the fixed end of the variable chord length driving member 102 is fixedly connected to the center of one of the first substrates 103, and the telescopic end is fixedly connected to the center of the other first substrate 103; the telescopic movement of the variable chord length driving member 102 drives the first connecting frame 101 to telescope, thereby realizing the variable chord length of the wing.
[0032] The first connecting frame 101 includes an X-shaped connecting rod 101-1 and a V-shaped connecting rod 101-2; the two X-shaped connecting rods 101-1 are connected side by side, and the middle parts of the two X-shaped connecting rods 101-1 together form a quadrilateral frame. The V-shaped connecting rod 101-2 is located in the quadrilateral frame and its two ends are fixedly connected to the middle parts of the corresponding X-shaped connecting rods 101-1, so that the middle part of the first connecting frame 101 forms a special-shaped structure with three sharp corners, and the three sharp corners are collinear, two of which are in the same direction, and the other sharp corner is in the opposite direction. The direction of the sharp corner of the special-shaped structure plays a dominant role in limiting the telescopic direction of the first connecting frame 101.
[0033] The variable curvature single cell structure 200 includes a second connecting frame 201, a variable curvature driving member 202 and a second substrate 203; the left and right sides of the two second substrates 203 are respectively connected together by the second connecting frame 201, and the two variable curvature driving members 202 are located at the upper and lower parts of the two second substrates 203, the fixed end of the variable curvature driving member 202 is fixedly connected to one of the second substrates 203, and the telescopic end of the variable curvature driving member 202 is fixedly connected to the other second substrate 203 (the end where the substrate is located is the free end of the variable curvature single cell structure); when the variable curvature driving member 202 on the upper side is extended and the variable curvature driving member 202 on the lower side is shortened, the variable curvature single cell structure 200 bends downward; when the variable curvature driving member 202 on the upper side is shortened and the variable curvature driving member 202 on the lower side is extended, the variable curvature single cell structure 200 bends upward; the second connecting frame 201 plays a leading role in limiting the bending direction of the variable curvature single cell structure 200.
[0034] The variable curvature single cell structure 200 also includes a first connecting frame 101; the two first connecting frames 101 are located on the upper and lower sides of the two second substrates 203, and the two sharp corners of the special-shaped structure of the first connecting frame 101 with the same direction are close to one side of the second substrate 203 connected to the telescopic end of the variable curvature driving member 202. The first connecting frame 101 is used to assist the bending deformation of the variable curvature single cell structure 200.
[0035] The second connecting frame 201 includes a horizontal connecting rod 201-1, a wavy connecting rod 201-2 and a reinforcing connecting rod 201-3; the two wavy connecting rods 201-2 are symmetrically distributed on the upper and lower sides of the horizontal connecting rod 201-1, and each bending part of the wavy connecting rod 201-2 is connected to the horizontal connecting rod 201-1 through a reinforcing connecting rod 201-3, and the reinforcing connecting rod 201-3 is inclined toward the second substrate 203 connected to the telescopic end of the variable curvature driving member 202, so that the second connecting frame 201 plays a leading role in limiting the bending direction of the variable curvature single cell structure 200.
[0036] The wing beam 300 includes a first support plate 301, a second support plate 302 and a variable length drive unit; the two second support plates 302 are symmetrically distributed on both sides of the first support plate 301, and the two second support plates 302 are fixedly connected to the corresponding wing ribs; the middle part of at least one variable length drive unit is connected to the first support plate 301, and the two ends are connected to the corresponding second support plates 302, and the variable length of the wing is achieved by the extension and contraction of the variable length drive unit. The variable length drive unit includes a variable length drive member 303, a first connecting rod 304, a second connecting rod 305 and a gear 306; one end of the two first connecting rods 304 is rotatably connected to one end of one side of the first support plate 301 through a connecting shaft, and the two connecting shafts are respectively provided with a gear 306, and the two gears 306 are meshed; the other ends of the two first connecting rods 304 are respectively rotatably connected to one end of the corresponding second connecting rod 305, and the other ends of the two second connecting rods 305 are respectively rotatably connected to one end of one side of the corresponding second support plate 302; when the wing beam 300 is at its original length, a certain angle is formed between the connected first connecting rod 304 and the second connecting rod 305, so as to facilitate the extension of the variable length drive unit. Contraction; one end of the two variable length driving members 303 is rotatably connected to the other end on one side of the first support plate 301, and the other ends of the two variable length driving members 303 are respectively rotatably connected to the middle part of the corresponding first connecting rod 304; the two variable length driving members 303 are extended at the same time to drive the two first connecting rods 304 to rotate around the first support plate 301, and then push the two second connecting rods 305 to rotate, so that the angle between the connected first connecting rods 304 and the second connecting rods 305 is increased, thereby realizing the extension of the variable length driving unit; conversely, the two variable length driving members 303 are contracted at the same time, so that the angle between the connected first connecting rods 304 and the second connecting rods 305 is reduced, thereby realizing the contraction of the variable length driving unit.
[0037] The two wing ribs are connected together by a wing spar, and the wing ribs and the wing spar are wrapped together by a skin. The wing adopts an integral design, which improves the overall strength of the wing and makes the wing profile smoother during the deformation process, thereby improving the aerodynamic performance.
[0038] The variable string length drive member 102, variable curvature drive member 202 and variable extension drive member 303 can be hydraulic rods, pneumatic rods or electric push rods. The first connecting frame 101 and the second connecting frame 201 are made of flexible materials with certain rigidity, such as nylon, spring steel, etc., to ensure the deformation function of the single cell structure.
[0039] On the other hand, the present invention also provides an aircraft, which comprises the above-mentioned variant wing with variable chord length, camber and span.
[0040] The working principle and workflow of the present invention are:
[0041] The variable chord length single cell structure 100 is driven to extend and shorten by the variable chord length driving member 102, so as to achieve the extension and shortening of the wing ribs and achieve the purpose of varying the chord length of the wing.
[0042] The curvature of the variable curvature single cell structure 200 is achieved through the variable curvature driving member 202. For a single variable curvature single cell structure 200, when the variable curvature driving member 202 on the upper side is extended and the variable curvature driving member 202 on the lower side is shortened, the variable curvature single cell structure 200 bends downward; when the variable curvature driving member 202 on the upper side is shortened and the variable curvature driving member 202 on the lower side is extended, the variable curvature single cell structure 200 bends upward; the curvature of the leading edge of the wing is achieved by the variable curvature of the variable curvature single cell structure 200 at the front end of the rib body, and the curvature of the trailing edge of the wing is achieved by the variable curvature of the variable curvature single cell structure 200 at the rear end of the rib body.
[0043] The two variable length driving members 303 extend simultaneously to drive the two first connecting rods 304 to rotate around the first support plate 301, thereby pushing the two second connecting rods 305 to rotate, so that the angle between the connected first connecting rods 304 and the second connecting rods 305 increases, thereby realizing the extension of the variable length driving unit, and then realizing the increase of the wing span; conversely, the two variable length driving members 303 contract simultaneously, so that the angle between the connected first connecting rods 304 and the second connecting rods 305 decreases, thereby realizing the contraction of the variable length driving unit, and then realizing the shortening of the wing span, thereby achieving the purpose of variable wing span.
[0044] The three deformation functions of the wing, namely, chord length, camber and span, do not affect each other and are independent of each other, thus realizing the deformation function of the composite wing.
[0045] Any matters not described in the present invention are applicable to the prior art.
Claims
1. A variant wing with variable chord length, camber and span, comprising ribs, spars and skins, wherein the ribs can be extended, shortened and bent, and the spars can be extended and shortened; characterized in that: The wing rib includes a variable chord length single cell structure and a variable curvature single cell structure. A plurality of variable chord length single cell structures are sequentially connected to form a wing rib body. The front and rear ends of the wing rib body are respectively connected to the variable curvature single cell structures. Adjacent single cell structures share a substrate. The variable chord length single cell structure includes a first connecting frame that limits the telescopic direction, and the first connecting frame includes an X-shaped connecting rod and a V-shaped connecting rod; two X-shaped connecting rods are connected side by side, and the middle parts of the two X-shaped connecting rods jointly form a quadrilateral frame, and the V-shaped connecting rod is located in the quadrilateral frame and its two ends are connected to the middle parts of the corresponding X-shaped connecting rods, so that the middle part of the first connecting frame forms a special-shaped structure; The variable curvature single cell structure includes a second connecting frame for limiting the bending direction, and the second connecting frame includes a horizontal connecting rod, a wavy connecting rod and a reinforcing connecting rod; the two wavy connecting rods are symmetrically distributed on the upper and lower sides of the horizontal connecting rod, and each bending part of each wavy connecting rod is connected to the horizontal connecting rod through a reinforcing connecting rod, and the reinforcing connecting rod is inclined toward the free end of the variable curvature single cell structure.
2. A variant wing with variable chord length, camber and span according to claim 1, characterized in that: The wing beam includes a first support plate, a second support plate and a variable length drive unit; the two second support plates are symmetrically distributed on both sides of the first support plate, and the middle part of at least one variable length drive unit is connected to the first support plate, and the two ends are connected to the corresponding second support plates; The variable length driving unit includes a variable length driving member, a first connecting rod, a second connecting rod and a gear; one end of the two first connecting rods are rotatably connected to one end of one side of the first support plate through a connecting shaft, and the two connecting shafts are respectively provided with gears, and the two gears are meshed; the other ends of the two first connecting rods are respectively rotatably connected to one end of the corresponding second connecting rods, and the other ends of the two second connecting rods are respectively rotatably connected to one end of one side of the corresponding second support plate, and when the wing beam is in the original length state, a certain angle is formed between the connected first connecting rod and the second connecting rod; one end of the two variable length driving members are rotatably connected to the other end of one side of the first support plate, and the other ends of the two variable length driving members are respectively rotatably connected to the middle part of the corresponding first connecting rod.
3. A variant wing with variable chord length, camber and span according to claim 1 or 2, characterized in that: The special-shaped structure in the middle of the first connecting frame has three collinear sharp corners, two of which are in the same direction, and the other is in the opposite direction.
4. A variant wing with variable chord length, camber and span according to claim 3, characterized in that: The variable curvature single cell structure also includes a variable curvature driving component and a second substrate. The left and right sides of the two second substrates are respectively connected together by a second connecting frame. The two variable curvature driving components are located at the upper and lower parts of the two second substrates. The fixed end and telescopic end of the variable curvature driving component are respectively connected to the two second substrates.
5. A variant wing with variable chord length, camber and span according to claim 3 or 4, characterized in that: The variable curvature single cell structure also includes a first connecting frame; the two first connecting frames are located on the upper and lower sides of the two second substrates, and the two sharp corners of the special-shaped structure with the same direction are close to the free end of the variable curvature single cell structure.
6. A variant wing with variable chord length, camber and span according to claim 1, characterized in that: The variable string length single cell structure also includes a variable string length driver and a first substrate; at least two opposite sides of the two first substrates are connected together by a first connecting frame, and the fixed end and the telescopic end of the variable string length driver are respectively connected to the centers of the two first substrates.
7. An aircraft, characterized in that: The aircraft comprises the variant wing with variable chord length, camber and span as claimed in claim 1.
Citation Information
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