Conformal structure suitable for large-wingspan flexible wing and design method

Abstract

The invention provides a conformal structure suitable for a large-wingspan flexible wing and a design method, and relates to the technical field of aircraft mechanical structure design. The unmanned aerial vehicle is provided with a fuselage and inflatable wings; fuselage fixing pieces are installed on the surface of the fuselage, at least one pulling point is arranged on the surface of each inflatable wing in the wingspan direction of the surface of the inflatable wing, at least one pulling point is located at the wingtip of the inflatable wing, wing fixing pieces are installed at the pulling points, and the wing fixing pieces are connected with the fuselage fixing pieces through traction pieces. According to the large-wingspan flexible inflatable wing, the wing can be prevented from generating large structural deformation in the lift force direction under the gravity and pneumatic action, and the engineering application problem that an existing large-wingspan flexible inflatable wing is large in deformation under the gravity and pneumatic load can be solved; the pulling point arrangement along the spanwise direction and the chordwise direction can be flexibly determined according to flight conditions; a certain dihedral angle or dihedral angle is pre-set for the inflatable wing by adjusting the length of the pull rope, so that the transverse stability of the aircraft is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft mechanical structure design, and in particular to a conformal structure suitable for a large-span flexible wing and a design method thereof. Background Art

[0002] The new concept of wing-boat integrated aerostat also usually adopts the combination of large-volume bladder and large-span inflatable wing to improve the load-bearing capacity and lift-to-drag ratio of the aerostat. However, the stiffness of the large-span flexible inflatable wing is extremely small, which is a typical large deformation nonlinear problem. It is very easy to deform under aerodynamic load, which will cause serious damage to the lift of the airship and may cause asymmetry of aerodynamic force on both sides of the wing, directly affecting the flight safety of the aircraft.

[0003] Inflatable wing is a typical flexible inflatable structure. A large number of internal constraints can ensure that it has a certain aerodynamic shape when it is inflated under superpressure. It is especially suitable for the lift components of low-speed aircraft, and has natural advantages such as large lift and light weight. It can be folded as needed when it is not inflated, and it only takes up a small space after folding, which is convenient for loading and transportation. When the inflatable wing is inflated during use, a wing with a similar load-bearing capacity to a rigid wing can be quickly obtained. It has many advantages such as high deployment reliability, reusability, and low cost. However, when the wingspan of the inflatable wing is large, air is usually used for inflation due to the limited relative thickness of the wing. At this time, under the action of gravity, the stiffness at the wing root is insufficient, and the wing root wrinkles, so that the wing bends downward. During the flight, since the aerodynamic lift is much greater than its own gravity, the wing root generates a large torque upward, causing the wing to wrinkle upward, and the lift is seriously reduced, which directly restricts the engineering application of large-scale inflatable wings.

[0004] In summary, there is an urgent need to design a conformal structure and design method suitable for large-span flexible wings that overcome the above-mentioned technical problems. Summary of the invention

[0005] The purpose of the present invention is to solve the problem that a large flexible inflatable wing is easily deformed under gravity and aerodynamic loads, and to propose a conformal structure and design method suitable for a large-span flexible wing.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is: a conformal structure suitable for a large-span flexible wing, comprising:

[0007] A drone having a fuselage and inflatable wings;

[0008] A fuselage fixing part is installed on the surface of the fuselage, at least one pulling point is arranged on the surface of the inflatable wing along its wingspan direction, and at least one pulling point is located at the wingtip of the inflatable wing, and wing fixing parts are installed at the pulling points, and the wing fixing parts are connected to the fuselage fixing parts through pulling parts.

[0009] The purpose of the present invention and the solution to its technical problems can be further achieved by adopting the following technical measures.

[0010] Optionally, the fuselage fixing member and the wing fixing member are both fixing patches, and the two are connected to the surfaces of the fuselage and the inflatable wing respectively by gluing or heat-sealing;

[0011] The wing fixing parts are each provided with a pull ring 1, the fuselage fixing parts are provided with a plurality of pull rings 2, and the two ends of the pulling part are respectively connected to the pull ring 1 and the pull ring 2.

[0012] Optionally, an adjustment mechanism is further provided between the fuselage fixing member and the pulling member.

[0013] Optionally, the adjustment mechanism includes the same internal threaded sleeve as the first threaded rod, the second threaded rod, and the first threaded rod and the second threaded rod, the ends of the first threaded rod and the second threaded rod facing away from each other are respectively integrally connected with a connecting ring and a hook, the threads on the first threaded rod and the second threaded rod are in opposite directions, and the threads at both ends of the internal threaded sleeve are in opposite directions;

[0014] One end of the pulling member is fixedly connected to the connecting ring, and the hook is connected to the second pull ring.

[0015] Optionally, the pulling member is a pull rope, and two ends of the pull rope are respectively connected to the pull ring 1 and the pull ring 2.

[0016] Optionally, the drawstring is detachably connected to the pull ring one and the pull ring two respectively by knotting or snapping.

[0017] Optionally, the wing fixing members are arranged in two rows along the chord direction of the inflatable wing, and the pull rings 2 are also arranged in two corresponding rows.

[0018] Optionally, the pull rope is a high-strength flexible pull rope with a circular cross-section.

[0019] Optionally, the fuselage fixing parts are symmetrically arranged on the upper and lower surfaces of the fuselage, and the wing fixing parts are symmetrically arranged on the upper and lower surfaces of the inflatable wing.

[0020] A design method for a conformal structure suitable for a flexible wing with a large wingspan, wherein the number of pull points to be set on the surface of the inflatable wing is determined according to the wingspan of the inflatable wing, the pull points on the inflatable wing can be set at one, two, three or more locations in the wingspan direction of the wing, wherein at least one pull point is located at the wingtip of the wing, and the pull points on the inflatable wing can also be set at one, two, three or more locations in the chord length direction of the wing;

[0021] A wing fixing is installed at each pulling point, and a fuselage fixing is installed on the surface of the fuselage;

[0022] Each wing fixing part is fixedly connected to the fuselage fixing part through a pulling part.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] 1. A conformal structure and design method suitable for a large-span flexible wing of the present invention, which can prevent the wing from undergoing large structural deformation in the lift direction under the action of gravity and aerodynamics by setting a plurality of distributed pulling points on the surface of the inflatable wing along the wingspan direction, installing wing fixings at the pulling points, setting fuselage fixings on the fuselage surface, and realizing the pulling connection between the pulling points at various locations of the wing and the fuselage through pulling pieces. The pulling point arrangement of the present invention can determine the distribution mode of the load according to the wingspan and flight speed, and the pulling point arrangement along the span direction and along the chord direction can be flexibly determined according to the flight conditions.

[0025] 2. The present invention provides a conformal structure and design method suitable for a large-span flexible wing. By setting an adjustment mechanism, the length of the pull rope can be adjusted to pre-adjust the inflatable wing to a certain upward or downward angle, thereby improving the lateral stability of the aircraft. The structure can be adjusted instantly according to the flight scenario and can adapt to different flight mission requirements.

[0026] 3. The pull wire of the present invention adopts a flexible pull wire with relatively high strength and a circular cross-section. It has the characteristics of small aerodynamic resistance and simple layout, and can reduce the additional resistance brought by the fixing device to the aircraft to the greatest extent; the pulling point position of the present invention is connected with the fuselage fixing parts and the wing fixing parts by knotting or snapping, and the number of pull wires can be adjusted at any time according to needs, and it also has the advantage of easy disassembly.

[0027] 4. The design method of the conformal structure of the large flexible inflatable wing of the present invention is a new idea for the coupling connection between the large wingspan inflatable wing and the aircraft fuselage. It can provide a simple, convenient and reliable implementation method for the engineering realization of the large wingspan inflatable wing, further explore the aerodynamic advantages of the inflatable wing, realize the combination of traditional aircraft and flexible wings, and promote the engineering application of this type of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of a top view of a conformal structure applicable to a large-span flexible wing provided by the present invention;

[0029] Figure 2 It is a side view structural schematic diagram of a conformal structure applicable to a large-span flexible wing provided by the present invention;

[0030] Figure 3 It is a partial enlarged schematic diagram of the fuselage of the conformal structure suitable for a large-span flexible wing provided by the present invention;

[0031] Figure 4 It is a partial enlarged schematic diagram of a wing of a conformal structure suitable for a large-span flexible wing provided by the present invention;

[0032] Description of reference numerals:

[0033] 1. Pull point 1;

[0034] 2. Pull point 2;

[0035] 3. Pull point three;

[0036] 4. Pull point four;

[0037] 5. Body;

[0038] 6. Adjustment mechanism; 61. First threaded rod; 62. Second threaded rod; 63. Internal threaded sleeve; 64. Connecting ring; 65. Hook;

[0039] 7. Pulling piece;

[0040] 8. Inflatable wings;

[0041] 9. Wing fixings; 91. Pull ring 1;

[0042] 10. Fuselage fixings; 101. Pull ring 2. DETAILED DESCRIPTION

[0043] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0044] like Figures 1 to 4 As shown, a conformal structure suitable for a large-span flexible wing comprises:

[0045] A drone having a fuselage 5 and an inflatable wing 8, wherein the large-wingspan flexible inflatable wing 8 is rigidly connected to the fuselage 5;

[0046] A fuselage fixing part 10 is installed on the surface of the fuselage 5, and at least one pulling point is arranged on the surface of the inflatable wing 8 along its wingspan direction, and at least one pulling point is located at the wingtip of the inflatable wing 8, and wing fixing parts 9 are installed at the pulling points, and the wing fixing parts 9 are connected to the fuselage fixing parts 10 through pulling parts 7.

[0047] In the present invention, the setting of the pulling point in the span direction of the inflatable wing 8 needs to be determined according to the span size of the inflatable wing. In order to ensure that the inflatable wing can maintain a good aerodynamic shape under gravity and aerodynamic load, it is necessary to perform segmented pulling and fixing according to the stiffness characteristics of the inflatable wing along the span direction. For example, for an inflatable wing 8 with a smaller wingspan, only the wingtip fixing method can be adopted, that is, only one pulling point is set at the wing tip. For an inflatable wing 8 with a larger wingspan, it needs to be divided into two, three or more sections for distributed fixing. That is, in addition to setting a pulling point at the wing tip, one or more pulling points can also be set on the wing, so that the inflatable wing 8 can be pulled and fixed in sections. For details, please refer to Figures 1 to 4 , taking the inflatable wing with a wingspan of 15m as an example, the flight speed of the aircraft is controlled below 30m / s; due to the overall flexibility of the inflatable wing 8, the inflatable wing 8 may also deform in the pitch direction, and two positions are selected along the span direction of the inflatable wing 8, namely 50% and 95%, and the pulling points are set at the positions of 50% and 95% of the wingspan respectively, and the position of 50% of the wingspan is attached Figure 1 The position of the middle pull point 1 and the pull point 2, the position of 95% of the wingspan is attached Figure 1 When the front and rear lift of the inflatable wing 8 is inconsistent along different positions, the inflatable wing 8 will twist forward and backward. By using more than two pulling points, the inflatable wing can be greatly restricted from twisting, such as Figure 1 As shown in the figure, two pulling points, namely pulling point three 3 and pulling point four 4, are respectively arranged at the leading edge and the trailing edge of the wing along the chord direction at the position of 95% of the wingspan, and two pulling points, namely pulling point one 1 and pulling point two 2, are arranged at the middle position of the wing, namely at the position of 50% of the wingspan, which are mainly located at the positions of 25-30% and 75-80% of the local chord direction, and all pulling points are symmetrically designed on the upper and lower surfaces of the wing.

[0048] Optionally, the fuselage fixing member 10 and the wing fixing member 9 are both fixing patches, which are connected to the surfaces of the fuselage 5 and the inflatable wing 8 respectively by gluing or heat-sealing to prevent the problem of excessive stress caused by local point fixing;

[0049] The wing fixing parts 9 are provided with a pull ring 1 91, the fuselage fixing parts 10 are provided with a plurality of pull rings 2 101, and the two ends of the pulling member 7 are respectively connected to the pull ring 1 91 and the pull ring 2 101. The two ends of the pulling member 7 are respectively connected to the pull ring 1 91 and the pull ring 2 101, and the pull ring 1 91 and the pull ring 2 101 are fixed on the fixing patch, which can prevent the pulling member 7 from damaging the skin of the drone and preventing the skin from being torn under strong pulling force.

[0050] Optionally, the pulling member 7 is a pull rope, and two ends of the pull rope are respectively connected to the pull ring 1 91 and the pull ring 2 101.

[0051] Optionally, the drawstring is detachably connected to the draw ring 1 91 and the draw ring 2 101 by knotting or buckling. The number of drawstrings can be adjusted at any time according to demand, and it has the advantage of convenient disassembly.

[0052] Optionally, the upper and lower surfaces of the fuselage 5 are symmetrically provided with the fuselage fixing parts 10, and the upper and lower surfaces of the inflatable wing 8 are symmetrically provided with the wing fixing parts 9. In order to make the inflatable wing 8 of the drone maintain better shape stability during flight, pull ropes are set on the upper and lower surfaces of the inflatable wing 8, and the inflatable wing 8 is fixed in two directions, the upper and lower surfaces. The upper surface is fixed mainly considering the characteristic that the flexible wing is easy to deflect downward under gravity or negative lift load, and two pull points are designed on the upper surface (i.e., the pull points set at 50% and 95% of the wingspan). The lower surface is fixed mainly considering the characteristic that the wing is easy to deflect upward under positive lift load, and two pull points are designed on the fixed section of the lower surface (i.e., at 50% and 95% of the wingspan). Regardless of the upper surface or the lower surface, the other end of the fixed pull rope is fixed to the upper and lower surfaces of the fuselage 5.

[0053] Optionally, the wing fixing members 9 are arranged in two rows along the chord direction of the inflatable wing 8, and the pull rings 101 are also arranged in two corresponding rows, as shown in the attached Figure 1 As shown in , pull point one 1 and pull point three 3 are one row, pull point two 2 and pull point four 4 are another row, that is, two rows, and two rows of pull points are also symmetrically arranged on the lower surface of each wing, and the pull points on the left and right wings are also symmetrically arranged.

[0054] In the embodiment of the present invention, the upper and lower surfaces of the inflatable wing 8 are both provided with a drawstring. When the drawstring is in a tensioned state, the upper and lower drawstrings of the wing simultaneously generate a pre-tightening force along the direction of the drawstring. When the inflated drone is flying in the air, the pressure on the lower surface of the inflatable wing 8 is greater than the pressure on the upper surface. Due to the low rigidity of the inflatable flexibility, the inflatable wing 8 will deform upward, and the inflatable wing 8 is prone to wrinkles or even bends, affecting the lift of the wing. At this time, the drawstring 7 on the lower surface of the inflatable wing 8 tends to be stretched, and the tension is significantly increased, generating a resisting force that prevents the inflatable wing 8 from moving upward, thereby maintaining the inflatable wing 8 in a relatively optimal aerodynamic shape state, ensuring the performance of the entire aircraft.

[0055] When the inflatable drone is in a hovering or parked state, the weight of the inflatable wing 8 itself will cause the wing to deform downward. At this time, the pull rope 7 on the upper surface of the inflatable wing tends to increase, thereby increasing the tension on the pull rope, generating an upward tension to prevent the inflatable wing from deforming downward, thereby ensuring the conformal requirements of the inflatable wing.

[0056] Optionally, the pull rope is a high-strength flexible pull rope with a circular cross section. Since the pull rope with a circular cross section is subjected to the same force from all directions, the pull rope with a circular cross section can be arranged relatively freely in space, but since the cross section of the wide rope is a rectangular, the long side has a large wind resistance. In order to reduce the influence of the pull rope on the resistance of the aircraft, the wide rope needs to ensure that the length direction of the rope cross section is parallel to the incoming flow when it is fixed, so as to minimize the influence of the pull rope on the resistance of the aircraft.

[0057] Optionally, an adjustment mechanism 6 is further provided between the fuselage fixing member 10 and the pulling member 7 .

[0058] Optionally, the adjustment mechanism 6 includes the same internal threaded sleeve 63 as the first threaded rod 61, the second threaded rod 62, and the first threaded rod 61 and the second threaded rod 62, the ends of the first threaded rod 61 and the second threaded rod 62 that are away from each other are respectively integrally connected with a connecting ring 64 and a hook 65, the threads on the first threaded rod 61 and the second threaded rod 62 are in opposite directions, and the threads at both ends of the internal threaded sleeve 63 are in opposite directions;

[0059] One end of the pulling member 7 is fixedly connected to the connecting ring 64 , and the hook 65 is connected to the second pull ring 101 .

[0060] Considering that the inflatable wing 8 will have different deformation trends under different internal air pressures and ambient temperatures, an adjustment mechanism 6 for adjusting the length of the drawstring is designed at the fuselage pull point to achieve the adaptability of the conformal structure and design method in different working environments of the inflatable wing 8. The purpose of adjusting the length of the drawstring is achieved by rotating the extension length of the first threaded rod 61 and the second threaded rod 62 relative to the internal threaded sleeve 63, thereby changing the tension of the drawstring, and the inflatable wing is maintained in a safe flight state. In order to ensure that the force of each drawstring is basically uniform, the drawstring needs to calculate the prestress of the drawstring according to the aerodynamic load, and the load distribution of the wing along the span direction at the cruising speed needs to be calculated. The aerodynamic load at the tension point is calculated with the local pull point as the reference position, and then the force of the drawstring is calculated according to the number of drawstrings. On the basis of the calculated tension, the prestress of about 5% is increased to ensure the tension of the drawstring. Further, in order to ensure that the drawstring is fixed to the inflatable wing, the angle between the drawstring and the inflatable wing needs to be designed, which is usually selected between 25° and 60°. The angle here cannot be too small. If it is too small, the wing will be squeezed along the span direction under the action of prestress and multiple pull ropes, causing the span of the wing to change.

[0061] Optionally, the pulling member 7 is a pull rod with rigidity; the pulling member 7 can be a rigid body, such as a carbon fiber tube, or a high-strength flexible pull rope, such as a nylon rope. Considering that the weight of a flexible wing is generally light, the structural requirements for the pulling member 7 are not high. A rigid pull rod or a flexible pull rope can be used for different design schemes. If a rigid pull rod is used, it is preferably used for a lower wing or upper wing aircraft. A unilateral fixing method can be used, that is, only the upper and lower surfaces of the wing can be fixed unilaterally. If a flexible pull rope is selected for fixing, the tension of the pull rope will disappear due to the upper and lower deformation of the wing. Therefore, it is preferred to fix the upper and lower surfaces at the same time.

[0062] A design method for a conformal structure suitable for a flexible wing with a large wingspan, wherein the number of pull points to be set on the surface of the inflatable wing 8 is determined according to the wingspan of the inflatable wing 8, wherein the pull points on the inflatable wing 8 may be set at one, two, three or more locations in the wingspan direction of the wing, wherein at least one pull point is located at the wingtip of the wing, and the pull points on the inflatable wing 8 may also be set at one, two, three or more locations in the chord length direction of the wing;

[0063] A wing fixing part 9 is installed at each pulling point, and a fuselage fixing part 10 is installed on the surface of the fuselage 5;

[0064] Each wing fixing part 9 is fixedly connected to the fuselage fixing part 10 through a pulling part 7. The setting of the pulling point in the wingspan direction of the inflatable wing 8 needs to be determined according to the size of the wingspan of the inflatable wing. In order to ensure that the inflatable wing can maintain a good aerodynamic shape under gravity and aerodynamic load, it is necessary to pull and fix the inflatable wing in sections according to the stiffness characteristics of the inflatable wing along the span direction. For the inflatable wing 8 with a smaller wingspan, only the wingtip fixing method can be adopted, that is, only one pulling point is set at the wing tip. For the inflatable wing 8 with a larger wingspan, it is necessary to divide it into two or three sections for distributed fixation, that is, in addition to setting a pulling point at the wingtip, one or more pulling points can be set on the wing, so as to pull and fix the inflatable wing 8 in sections. The pulling points on the inflatable wing 8 can also be set at one, two, three or more places in the direction of the chord length of the wing, so as to avoid the inflatable wing 8 from twisting forward and backward and maintain the stability of the drone under various flight conditions.

[0065] The above is only an embodiment of the present invention, and the common sense such as the known specific technical solutions and / or characteristics in the scheme is not described in detail here. The conformal design details for the inflatable wing proposed in the scheme are just special cases of fixing by pull ropes. It should be pointed out that for technical personnel in related fields, without departing from the technical design ideas of the present invention, the specific details in the scheme can also be adjusted or improved, such as changing the percentage of the pull point along the span direction and the number of pull points at different positions. This case is to apply the inflatable wing to the conformal design of the UAV. This method can also be used in airships, large aspect ratio flexible aircraft and other aircraft. These should also be included in the protection scope of the present invention and belong to the effects that can be achieved by the present invention. In order to reduce the additional resistance brought by the attached components on the surface of the conformal design of the inflatable wing, the components are treated by a rectifier to reduce the resistance. This solution should also belong to the technical extension of the present invention and should also be protected.

[0066] The present invention is further described above in conjunction with the embodiments, but the present invention is not limited to the above-mentioned implementation modes, and various changes can be made within the knowledge scope of ordinary technicians in this field without departing from the purpose of the present invention.

Claims

1. A conformal structure suitable for a flexible wing with a large wingspan, comprising an unmanned aerial vehicle having a fuselage (5) and an inflatable wing (8), characterized in that: A fuselage fixing part (10) is installed on the surface of the fuselage (5), at least one pulling point is arranged on the surface of the inflatable wing (8) along the wingspan direction thereof, and at least one of the pulling points is located at the wing tip of the inflatable wing (8), and wing fixing parts (9) are installed at the pulling points, and the wing fixing parts (9) are connected to the fuselage fixing parts (10) via pulling parts (7).

2. The conformal structure suitable for a large-span flexible wing according to claim 1, characterized in that: The fuselage fixing member (10) and the wing fixing member (9) are both fixing patches, and the two are connected to the surfaces of the fuselage (5) and the inflatable wing (8) respectively by gluing or heat-sealing; The wing fixing parts (9) are each provided with a pull ring 1 (91), the fuselage fixing parts (10) are provided with a plurality of pull ring 2 (101), and the two ends of the pulling member (7) are respectively connected to the pull ring 1 (91) and the pull ring 2 (101).

3. The conformal structure suitable for a large-span flexible wing according to claim 2, characterized in that: An adjustment mechanism (6) is also provided between the fuselage fixing member (10) and the pulling member (7).

4. The conformal structure suitable for a large-span flexible wing according to claim 3, characterized in that: The adjusting mechanism (6) comprises a first threaded rod (61), a second threaded rod (62), and an internally threaded sleeve (63) threadedly sleeved on the first threaded rod (61) and the second threaded rod (62); the ends of the first threaded rod (61) and the second threaded rod (62) which are away from each other are respectively integrally connected with a connecting ring (64) and a hook (65); the threads on the first threaded rod (61) and the second threaded rod (62) are in opposite directions; and the threads at both ends of the internally threaded sleeve (63) are in opposite directions; One end of the pulling member (7) is fixedly connected to the connecting ring (64), and the hook (65) is connected to the second pull ring (101).

5. The conformal structure suitable for a large-span flexible wing according to claim 2, characterized in that: The pulling member (7) is a pull rope, and the two ends of the pull rope are respectively connected to the pull ring 1 (91) and the pull ring 2 (101).

6. The conformal structure suitable for a large-span flexible wing according to claim 5, characterized in that: The drawstring is detachably connected to the pull ring 1 (91) and the pull ring 2 (101) respectively by knotting or buckling.

7. The conformal structure suitable for a large-span flexible wing according to claim 2, characterized in that: The wing fixing members (9) are arranged in two rows along the chord direction of the inflatable wing (8), and the second pull ring (101) is also arranged in two corresponding rows.

8. The conformal structure suitable for a large-span flexible wing according to claim 2, characterized in that: The drawstring is a high-strength flexible drawstring with a circular cross section.

9. A conformal structure suitable for a large-span flexible wing according to any one of claims 1 to 8, characterized in that: The upper and lower surfaces of the fuselage (5) are symmetrically provided with the fuselage fixing parts (10), and the upper and lower surfaces of the inflatable wing (8) are symmetrically provided with the wing fixing parts (9).

10. A design method for a conformal structure suitable for a large-span flexible wing, characterized in that: According to the wingspan of the inflatable wing (8), the number of pulling points to be arranged on the surface of the inflatable wing (8) is determined. The pulling points on the inflatable wing (8) may be arranged at one, two, three or more locations in the direction of the wingspan, wherein at least one pulling point is located at the wing tip. The pulling points on the inflatable wing (8) may also be arranged at one, two, three or more locations in the direction of the chord length of the wing. A wing fixing part (9) is installed at each pulling point, and a fuselage fixing part (10) is installed on the surface of the fuselage (5); Each wing fixing member (9) is fixedly connected to the fuselage fixing member (10) via a pulling member (7).

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