W-shaped folding wing patrol flight unmanned aerial vehicle

Abstract

The invention provides a patrol flight unmanned aerial vehicle with W-shaped folding wings. The patrol flight unmanned aerial vehicle comprises a fuselage, inner-section wings, inner-section wing limiting structures, inner-side folding and unfolding mechanisms, outer-section wings, ailerons, outer-side folding and unfolding mechanisms, empennages, empennage folding and unfolding mechanisms and empennage protection structures. The fuselage is designed by adopting a flat lifting body configuration, the inner and outer sections of wings are designed by adopting low-speed friendly plane shapes such as rectangles and trapezoids, and the empennage is designed by adopting a V-shaped empennage / inverted V-shaped empennage. The inner section wing and the outer section wing of the unmanned aerial vehicle are integrally in a W shape in the unfolding process, and a folding wing layout with the larger aspect ratio and the higher aerodynamic efficiency can be derived based on the W-shaped layout. According to the layout, the extension length of the wings is slightly restrained by the length of the fuselage, the contradiction between the aerodynamic characteristic design of the wings and the storage space of the launch canister is well balanced and solved under the condition that the length of the fuselage is fixed, and the layout wings are large in aspect ratio, high in aerodynamic efficiency and simple in structural design.

Description

Technical Field

[0001] The present invention belongs to the technical field of tube-launched foldable unmanned aerial vehicles, and particularly relates to a W-shaped foldable wing loitering unmanned aerial vehicle. Background Art

[0002] As a prior and key link in the development process of aircraft, the aerodynamic layout plays a crucial role in the development of aircraft. For unmanned aerial vehicles with high requirements for endurance time, especially those with requirements for wing folding, while balancing and resolving the contradictions among the folding and unfolding scheme, wing design (sufficient lift surface design, high lift-drag ratio design), and the storage space of the launch tube, ensuring a high aspect ratio is the key to improving its aerodynamic performance and achieving excellent endurance performance. Although there are currently aerodynamic layout forms such as "X" layout, tandem wing layout, "Z" - type foldable wing conventional layout, telescopic wing conventional layout, and rotary wing foldable conventional layout available for loitering unmanned aerial vehicles to choose from, the above aerodynamic layouts still have many defects / problems to be solved.

[0003] Patent CN202410642696.1 discloses an aerodynamic shape structure of a small face-symmetric loitering missile, and patent CN201721902223.2 discloses an unmanned aerial vehicle based on the X-wing layout. The aerodynamic shapes of the above aircraft both adopt the X-X layout form. Although this layout form is flexible and maneuverable, the wingspan of its wings is strictly limited by the fuselage size, the overall aerodynamic efficiency of the aircraft is low, and it is difficult to fold, and the wing folding storage space is large.

[0004] Patent CN202411224955.5 discloses a variable-wing loitering missile. Although the missile has good aerodynamic efficiency after being fully unfolded, the wingspan of this configuration is still strictly limited by the fuselage size, the improvement of aerodynamic efficiency is limited, and the aerodynamic center is too far forward, making it difficult to achieve a static stability design for the center of gravity arrangement.

[0005] Patent CN202321217409.X discloses a foldable loitering missile. The layout of this loitering missile adopts a conventional V-tail layout design and has the folding and unfolding function, but the wingspan is still strictly limited by the fuselage size, and the improvement of aerodynamic performance is limited.

[0006] Patent CN202211397525.4 discloses a quickly disassembled and assembled tandem single-soldier loitering missile, and patent CN202021971446.6 discloses a multi-tube-launched loitering missile and its system. The above loitering missiles adopt the common tandem wing layout, and the wings have the folding and unfolding function, but the wingspan is still strictly limited by the fuselage size, and the improvement of aerodynamic performance is limited.

[0007] Patent CN202311183570.4 discloses a loitering munition weapon system capable of launching missiles from the air. This loitering munition adopts a telescopic wing conventional layout design; Patent CN201811601135.8 discloses a tube-launched folding-wing unmanned aerial vehicle and its launching method, and this unmanned aerial vehicle adopts a Z-shaped folding wing design. Similarly, the wingspan of the above layouts is strictly limited by the fuselage size, and the improvement of aerodynamic performance is restricted. Summary of the Invention

[0008] The purpose of the present invention is to provide an aerodynamic layout form of a "W"-type folding wing loitering unmanned aerial vehicle, mainly to solve the problems that in existing layout forms such as "X"-type layout, tandem wing layout, "Z"-type folding wing conventional layout, and rotary wing folding conventional layout, the wingspan is limited by the fuselage length, resulting in limited improvement of the aspect ratio closely related to aerodynamic efficiency, and further limited improvement of aerodynamic efficiency; the structural design of the telescopic wing conventional layout is complex, and the wingspan is still limited by the fuselage length.

[0009] The technical solution of the present invention is as follows:

[0010] A "W"-type folding wing loitering unmanned aerial vehicle includes a fuselage (1), an inner wing section (2), an inner wing section limiting structure (6), an inner folding and unfolding mechanism (4), an inner folding and unfolding mechanism rotating shaft (401), an outer wing section (3), ailerons (8), an outer folding and unfolding mechanism (5), an outer folding and unfolding mechanism rotating shaft (501), a tail wing (9), a tail wing folding and unfolding mechanism (10), a tail wing folding and unfolding mechanism rotating shaft (101), a tail wing protection structure (11), and a power system (16).

[0011] Preferably, the fuselage (1) adopts a flat lifting body configuration design. The inner wing section limiting structure (6) is located on the fuselage (1), and its rear end face is parallel to the leading edge of the inner wing section (2) for limiting the position of the inner wing section (2) after unfolding. The power system (16) is located at the rear of the fuselage (1).

[0012] Preferably, the inner folding and unfolding mechanism (4) is connected to the fuselage (1) through the inner folding and unfolding mechanism rotating shaft (401), and the inner folding and unfolding mechanism (4) is located at the root of the inner wing section (2); the outer folding and unfolding mechanism (5) is connected to the inner wing section (2) through the outer folding and unfolding mechanism rotating shaft (501), and the outer folding and unfolding mechanism (501) is located at the root of the outer wing section (3); the ailerons (8) are installed at the trailing edge of the wing.

[0013] Preferably, the inner wing section (2) can be folded and unfolded around the inner folding and unfolding mechanism rotating shaft (401) under the action of the inner folding and unfolding mechanism (4), and the outer wing section (3) can be folded and unfolded around the outer folding and unfolding mechanism rotating shaft (501) under the action of the outer folding and unfolding mechanism (5).

[0014] Preferably, the tail wing folding and unfolding mechanism (10) is fixed to the tail of the fuselage (1) through a rotating shaft (101). The tail wing (9) is connected to the fuselage through the tail wing folding and unfolding mechanism (10) and can be folded and unfolded around the rotating shaft (101) of the tail wing folding and unfolding mechanism (10) under the action of the tail wing folding and unfolding mechanism (10). The tail wing protection structure (11) is fixed to the tip of the tail wing, and the tail wing folding and unfolding mechanism (101) is located at the root of the tail wing.

[0015] Preferably, the position of the inner wing limiting structure (6) relative to the head of the fuselage (1) is determined by the extension length of the inner wing (2).

[0016] Preferably, the planar shapes of the inner wing (2) and the outer wing (3) adopt low-speed friendly planar shapes such as rectangles and trapezoids. The position and extension length of the inner wing (2) relative to the fuselage (1) are jointly determined by the center of gravity position and the longitudinal static stability margin. The extension length of the outer wing (3) is equal to the length of the fuselage (1).

[0017] Preferably, while the inner wing (2) unfolds outward around the rotating shaft (401) of the inner folding and unfolding mechanism (4), the outer wing (3) unfolds outward around the rotating shaft (501) of the outer folding and unfolding mechanism (5). During the unfolding process, the overall wing presents a "W" configuration.

[0018] Preferably, the tail wing (9) is designed as a V-shaped tail wing or an inverted V-shaped tail wing, and is specifically designed corresponding to the upper and lower single wings. That is, if the wing adopts an upper single wing design, in order to ensure that the unfolding process of the tail wing is not affected by the wing, the tail wing (9) adopts an inverted V-shaped tail wing design; similarly, if the wing adopts a lower single wing design, the tail wing (9) adopts a V-shaped tail wing design.

[0019] Preferably, while the inner wing (2) and the outer wing (3) unfold outward, the tail wing (9) folds and unfolds around the rotating shaft (101) under the action of the tail wing folding and unfolding mechanism (10) and unfolds completely before the wing, so as to ensure that the aircraft has a certain control ability before the wing is fully unfolded.

[0020] Preferably, a folding and unfolding mechanism (14) is designed and installed at the tip of the outer wing (3), which can be used to fixedly connect the folding and unfolding wing (12). Similarly, a folding and unfolding mechanism (15) and a connecting folding and unfolding wing (13) can also be installed at the outer tip of the folding and unfolding wing (12). Under the condition that the structural strength permits, a derivative layout design with a larger aspect ratio and higher aerodynamic efficiency can be realized on the basis of the W-shaped folding wing cruise UAV layout.

[0021] Compared with the prior art, the present invention has the following beneficial effects:

[0022] A W-shaped folding wing cruise UAV of the present invention has a wingspan that is not limited by the fuselage length, successfully solving the contradiction between the wing area of the tube-launched UAV and the storage space of the launch tube. Under the condition of having the same volume of storage space, the wingspan is less restricted by the fuselage length, the wing aspect ratio can be larger, and the aerodynamic efficiency of the whole aircraft is higher. The present invention can be applied to the overall aerodynamic shape design field of military and civilian tube-launched UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 Isometric view of the W-shaped folding wing cruise UAV proposed by the present invention;

[0024] Figure 2 Three-view drawing of the W-shaped folding wing cruise UAV proposed by the present invention;

[0025] Figure 3 Fuselage design drawing of the W-shaped folding wing cruise UAV proposed by the present invention;

[0026] Figure 4 Overall folding state diagram of the W-shaped folding wing cruise UAV proposed by the present invention;

[0027] Figure 5 Overall folding state diagram of the W-shaped folding wing cruise UAV proposed by the present invention;

[0028] Figure 6 Wing folding schematic diagram of the W-shaped folding wing cruise UAV proposed by the present invention;

[0029] Figure 7 Tail wing folding schematic diagram of the W-shaped folding wing cruise UAV proposed by the present invention;

[0030] Figure 8 Derivative layout schematic diagram of the W-shaped folding wing cruise UAV proposed by the present invention;

[0031] Figure 9 Deployment process schematic diagram of the W-shaped folding wing cruise UAV proposed by the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0032] For ease of understanding, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. The described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0033] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "parallel", "above", "below", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation. Therefore, it should not be construed as a limitation to the present invention.

[0034] In the present invention, unless otherwise clearly specified and limited, terms such as "installed", "connected", "connected to", "fixed", etc. should be understood in a broad sense. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] As Figures 1 to 9 shown, taking the above single-wing inverted V-tail W-type layout as an example, a W-type folding wing loitering unmanned aerial vehicle and its folding and unfolding scheme involved in the present invention will be described as follows:

[0036] S1. A W-type folding wing loitering unmanned aerial vehicle and its layout, including a fuselage 1, an inner-section wing 2, an inner-side folding and unfolding mechanism 4, an inner-side folding and unfolding mechanism rotating shaft 401, an outer-section wing 3, an outer-side folding and unfolding mechanism 5, an outer-side folding and unfolding mechanism rotating shaft 501, a V-type tail 9, a tail folding and unfolding mechanism 10, a tail folding and unfolding mechanism rotating shaft 101, a tail protection structure 11, and a power system 16. Among them, the wing root of the inner-section wing 2 is connected to the fuselage 1 through the rotating shaft 401 of the inner-side folding and unfolding mechanism 4, the wing root of the outer-section wing 3 is connected to the inner-section wing 2 through the rotating shaft 501 of the outer-side folding and unfolding mechanism 5, the V-type tail 9 is connected to the fuselage 1 through the rotating shaft 101 of the wing root folding and unfolding mechanism 10, and the power system 16 is located at the rear of the fuselage 1.

[0037] S2. The key geometric cross-section contour lines 101, 102, 103, 104, and 105 of the fuselage 1 are mainly in a flat geometric shape. The fuselage 1 as a whole has a lifting body configuration. A limiting structure end face 6 of the inner-section wing 2 is designed between the fuselage 1 and the inner-section wing 2.

[0038] S3. The inner-section wing 2 and the outer-section wing 3 are generally designed in a rectangular plane shape or a trapezoidal plane shape. The ratio of the span or the ratio of the areas of the inner-section wing 2 and the outer-section wing 3 should be given according to the position of the limiting structure 6 of the inner-section wing 2. In the folded state, the trailing edges of the inner-section wing 2 and the outer-section wing 3 are parallel to the central axis of the fuselage 1. The inner-section wing 2 is located above the fuselage 1, and the outer-section wing 3 is located above the inner-section wing 2.

[0039] After the drone is launched out of the launch tube, the inner-section wing 2 unfolds outward around the rotating shaft 401 of the inner folding and unfolding mechanism 4 until it reaches the rear end face 6 of the fuselage limiting structure. At the same time, the outer-section wing 3 unfolds outward around the rotating shaft 501 of the outer folding and unfolding mechanism 5 until the leading edge of the outer-section wing 3 is parallel to the leading edge of the inner-section wing 2. During the wing unfolding process, the inner-section wing 2 and the outer-section wing 3 as a whole present a "W" configuration.

[0040] S5. In the folded state, the wall of the launch tube serves as the limiting structure for the tail wing 9; during the unfolding process of the drone wings, the V-shaped tail wing 9 unfolds outward around the rotating shaft 101 of the tail wing folding and unfolding mechanism 10; the configuration of the tail wing 9 can be a V-shaped tail wing or an inverted V-shaped tail wing, and the specific form of the configuration of the tail wing 9 is determined according to the up-and-down relationship between the wing 2 and the fuselage 1.

[0041] S6. Based on the above layout, the "W"-type folding wing drone can further design folding and unfolding wings 12, wings 13, and folding and unfolding mechanisms 14 and 15 on the outer-section wing 3 to form a derivative layout with a larger aspect ratio and higher aerodynamic efficiency.

[0042] Furthermore, the specific steps of S2 are as follows:

[0043] S21. The minimum width of the fuselage 1 should be comprehensively designed according to the geometric size requirements restricted by the research and development mission statement (or the size restricted by the launch tube), the fuselage volume requirements, the lift required by the drone, and the safety margin strength that the wing can bear, so as to achieve the optimal lift-to-drag ratio design;

[0044] S22. Specifically, the total wing area S required is determined according to the following lift calculation formula

[0045]

[0046] where ρ is the air density, v is the oncoming flow velocity, Cl is the lift coefficient at the maximum lift-to-drag ratio state of the selected airfoil, and L is the lift required for cruising.

[0047] S23. Determine the total wing span, the span of the inner-section wing 2, the span of the outer-section wing 3, and determine the mean aerodynamic chord length of the wing according to the following formula

[0048]

[0049] where is the mean aerodynamic chord length of the wing, l is the fuselage length, l0 is the total span after the inner-section wing 2 and the outer-section wing 3 are unfolded, l1 is the span of the inner-section wing 2, l2 is the span of the outer-section wing 3, and l6 is the distance from the limiting structure of the inner-section wing 2 to the head of the fuselage;

[0050] S24. The distance of the inner wing limiting structure 6 from the nose of the fuselage 1 should be determined according to the center-of-gravity position of the whole aircraft, and can be determined with reference to a 10% static stability margin during the preliminary design stage, that is, the distance from the foremost edge point of the end face of the inner wing limiting structure to the nose of the fuselage is:

[0051]

[0052] where is the reference position of the center of gravity of the whole aircraft, and l cf is the reference length, and c max is the maximum chord length at the wing root;

[0053] S25. After the mean aerodynamic chord length of the wing is determined, the maximum chord length at the wing root is determined according to the designed wing planform. The maximum width of the fuselage 1 should not be less than twice the maximum chord length of the wing;

[0054] S26. The inner wing limiting structure is used to limit the position of the inner wing and position the sweep angle of the wing. The angle between the rear end face of the inner wing limiting structure and the fuselage axis should be the same as the sweep angle of the wing.

[0055] Furthermore, the specific steps of S3 are as follows:

[0056] S31. The planforms of the inner wing 2 and the outer wing 3 are determined according to the required lift and the lift coefficient of the selected airfoil. When there is sufficient designed lift, a trapezoidal planform should be preferred. When the wing area is determined, the mean aerodynamic chord length of the wing should be minimized as much as possible, so as to maximize the aspect ratio of the wing;

[0057] S32. The wing can be designed as a high wing or a low wing;

[0058] S33. Ailerons 8 for controlling the rolling motion of the UAV are designed on the wing. The ailerons 8 can be designed on the inner wing 2 or on the outer wing 3;

[0059] S34. The position of the inner wing limiting structure 6 directly determines the span of the inner wing 2. The maximum span of the inner wing 2 is:

[0060]

[0061] S35. The span of the outer wing 3 should not exceed the total length of the fuselage 1;

[0062] S36. In actual application, a wing protection structure should be designed for the outer wing to prevent the wing / rudder surface from being damaged by rubbing against the wall of the launch tube during the launch process;

[0063] Furthermore, the specific steps of S4 are as follows:

[0064] S41. The inner wing 2 is unfolded outward around the folding and unfolding rotation shaft 401 under the action of the inner folding and unfolding mechanism 4. During this period, air resistance acts as a damping force on its unfolding process;

[0065] S42. While the inner wing 2 is unfolding outward, the outer wing 3 is unfolded outward around the folding and unfolding rotation shaft 501 under the action of the outer folding and unfolding mechanism 5. During this period, air resistance acts as an assisting force on its unfolding process;

[0066] S43. During the unfolding process of the inner wing 2 and the outer wing 3, the aileron 8 is in the neutral position to prevent uncontrollable attitude changes of the UAV during the launch process;

[0067] Further, the specific steps of S5 are as follows:

[0068] S51. In the folded state, the wing tip of the tail wing 9 contacts the barrel wall of the launch tube. In actual application, a corresponding protection structure 11 is designed at the wing tip;

[0069] S52. The tail wing 9 is selected as a V-shaped tail wing or an inverted V-shaped tail wing, which is specifically determined with reference to the up-and-down relationship between the wing and the fuselage;

[0070] S53. If the wing is a high wing, to ensure that the UAV has a certain control ability after launch before the wing is fully unfolded, that is, the unfolding process of the tail wing 9 is not interfered by the unfolding process of the wing and the tail wing 9 unfolds before the wing is fully unfolded, the tail wing 9 should be selected as an inverted V-shaped tail wing;

[0071] S53. Similarly, if the wing is a low wing, to ensure that the UAV has a certain control ability after launch before the wing is fully unfolded, the tail wing 9 should be selected as a V-shaped tail wing;

[0072] S54. The planar shape of the tail wing can be rectangular or trapezoidal; it can be a straight wing or a swept-back wing; it can be a fully movable tail wing or a non-fully movable tail wing with control surfaces, which is specifically determined according to the engineering design requirements;

[0073] S55. The area of the tail wing 9 should be designed according to the tail capacity design requirements in combination with the longitudinal and lateral static stability margin requirements.

[0074] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A W-shaped folding wing loitering unmanned aerial vehicle, characterized in that, It includes a fuselage (1), an inner wing section (2), an inner wing section limiting structure (6), an inner folding and unfolding mechanism (4), an inner folding and unfolding mechanism rotating shaft (401), an outer wing section (3), ailerons (8), an outer folding and unfolding mechanism (5), an outer folding and unfolding mechanism rotating shaft (501), a tail (9), a tail folding and unfolding mechanism (10), a tail folding and unfolding mechanism rotating shaft (101), a tail protection structure (11), and a power system (16).

2. The W-shaped folding wing loitering UAV according to claim 1, characterized in that, The fuselage (1) is designed with a flat lifting body configuration. The inner wing section limiting structure (6) is located on the fuselage (1), and its rear end face is parallel to the leading edge of the inner wing section (2) for limiting the position of the inner wing section (2) after unfolding. The power system (16) is located at the rear of the fuselage (1).

3. The W-shaped folding wing cruise UAV according to claim 1, wherein, The inner folding and unfolding mechanism (4) is connected to the fuselage (1) through the inner folding and unfolding mechanism rotating shaft (401), and the inner folding and unfolding mechanism (4) is located at the root of the inner wing section (2); the outer folding and unfolding mechanism (5) is connected to the inner wing section (2) through the outer folding and unfolding mechanism rotating shaft (501), and the outer folding and unfolding mechanism (501) is located at the root of the outer wing section (3); the ailerons (8) are installed at the trailing edge of the wing.

4. The W-shaped folding wing loitering unmanned aerial vehicle according to claim 1, wherein, The inner wing section (2) can be folded and unfolded around the inner folding and unfolding mechanism rotating shaft (401) under the action of the inner folding and unfolding mechanism (4), and the outer wing section (3) can be folded and unfolded around the outer folding and unfolding mechanism rotating shaft (501) under the action of the outer folding and unfolding mechanism (5).

5. The W-shaped folding wing loitering unmanned aerial vehicle according to claim 1, characterized in that, The tail folding and unfolding mechanism (10) is fixed to the tail of the fuselage (1) through the rotating shaft (101). The tail (9) is connected to the fuselage through the tail folding and unfolding mechanism (10) and can be folded and unfolded around the tail folding and unfolding mechanism rotating shaft (101) under the action of the tail folding and unfolding mechanism (10). The tail protection structure (11) is fixed to the tip of the tail, and the tail folding and unfolding mechanism (101) is located at the root of the tail.

6. The W-shaped folding wing cruise UAV according to claim 2, wherein, The position of the inner wing section limiting structure (6) relative to the head of the fuselage (1) is determined by the extension length of the inner wing section (2).

7. The W-shaped folding wing cruise UAV according to claim 3, characterized in that, The planar shapes of the inner wing section (2) and the outer wing section (3) adopt low-speed friendly planar shapes such as rectangles and trapezoids. The position and extension length of the inner wing section (2) relative to the fuselage (1) are jointly determined by the center of gravity position and the longitudinal static stability margin. The extension length of the outer wing section (3) is equal to the length of the fuselage (1).

8. The W-shaped folding wing cruise UAV according to claim 4, wherein, While the inner wing section (2) unfolds outward around the rotating shaft (401) of the inner folding and unfolding mechanism (4), the outer wing section (3) unfolds outward around the rotating shaft (501) of the outer folding and unfolding mechanism (5). During the unfolding process, the overall wing presents a "W" configuration.

9. The W-shaped folding wing cruise unmanned aerial vehicle according to claim 5, wherein, The tail (9) is designed as a V-shaped tail or an inverted V-shaped tail, specifically corresponding to the upper and lower single-wing designs. That is, if the wing adopts an upper single-wing design, to ensure that the unfolding process of the tail is not affected by the wing, the tail (9) adopts an inverted V-shaped tail design; similarly, if the wing adopts a lower single-wing design, the tail (9) adopts a V-shaped tail design.

10. The W-shaped folding wing cruise UAV according to claim 5, characterized in that, While the inner wing section (2) and the outer wing section (3) are deployed outwardly, the tail wing (9) is folded and deployed about the rotating shaft (101) under the action of the tail wing folding and deploying mechanism (10), and is fully deployed prior to the wings to ensure that the aircraft has a certain control ability before the wings are fully deployed.

11. A W-shaped folding wing loitering unmanned aerial vehicle according to claim 1, characterized in that, A folding and deploying mechanism (14) is designed and installed at the wingtip of the outer wing section (3) to fixedly connect the folding and deploying wing (12); similarly, a folding and deploying mechanism (15) can also be installed at the outer tip of the folding and deploying wing (12) and the folding and deploying wing (13) can be connected. On the basis of the layout of the W-shaped folding wing cruise UAV, a derivative layout design with a larger aspect ratio and higher aerodynamic efficiency can be realized when the structural strength permits.

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