An asymmetrically bent-wing unmanned aerial vehicle

Abstract

The present invention relates to an asymmetrically bent-wing unmanned aerial vehicle, which includes a fuselage, a front wing and a rear wing. The front wing and the rear wing are arranged on both sides of the fuselage in sequence, one in front of the other along the axial direction of the fuselage. The front wing has a sweep angle and includes an inner section of the front wing and an outer section of the front wing. The fuselage, the inner section of the front wing and the outer section of the front wing are connected in sequence. The inner section of the front wing has anhedral, and the outer section of the front wing has dihedral. The rear wing has a forward sweep angle and includes an inner section of the rear wing and an outer section of the rear wing. The fuselage, the inner section of the rear wing and the outer section of the rear wing are connected in sequence. The inner section of the rear wing has dihedral, and the outer section of the rear wing has anhedral. Compared with the prior art, the present invention has the advantages of strong lift-drag performance, good stealth performance, high mechanism reliability, high space utilization efficiency, light weight, etc.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to an asymmetrically bent-wing unmanned aerial vehicle. Background Art

[0002] In modern warfare, it is required that loitering munitions attack faster, farther, more suddenly and covertly. The rotary-structure unmanned aerial vehicle layout is widely used in dispensers and loitering munitions. Usually, the wings can be folded or rotated, so that the airframe can be folded into a small enough size to be placed in the cabin or the ground launch tube, and after being dropped or launched, it unfolds into an unmanned aerial vehicle for cruise flight.

[0003] Due to the extremely strict size and weight constraints of such products, in order to achieve a large load and range in a very small size, the tandem-wing, cruciform-wing and later-developed joined-wing layouts are widely favored, which can deploy a large wing area in a limited space. However, the tandem-wing, cruciform-wing or joined-wing layouts have the following disadvantages:

[0004] It brings great difficulties to the external shape stealth design, resulting in the inability to guarantee the survival ability and attack concealment of the loitering munition itself;

[0005] The multi-wing surface design is very unfavorable for improving the lift-drag performance, resulting in difficulty in achieving long endurance flight under the limited size and weight constraints;

[0006] The multi-wing surface layout requires more deployment mechanisms, which brings problems such as difficult structural design, increased weight and reduced reliability. Summary of the Invention

[0007] The purpose of the present invention is to overcome the defects of the above-mentioned existing technologies and provide an asymmetrically bent-wing unmanned aerial vehicle with strong lift-drag performance, good stealth performance, high mechanism reliability, high space utilization efficiency and light weight.

[0008] The purpose of the present invention can be achieved by the following technical solutions:

[0009] An asymmetrically bent-wing unmanned aerial vehicle, comprising a fuselage, a front wing and a rear wing, wherein the front wing and the rear wing are arranged on both sides of the fuselage in sequence along the axial direction of the fuselage;

[0010] The front wing has a sweep angle and comprises an inner section of the front wing and an outer section of the front wing. The fuselage, the inner section of the front wing and the outer section of the front wing are connected in sequence. The inner section of the front wing has an upward sweep angle, and the outer section of the front wing has a downward sweep angle;

[0011] The rear wing has a forward sweep angle and comprises an inner section of the rear wing and an outer section of the rear wing. The fuselage, the inner section of the rear wing and the outer section of the rear wing are connected in sequence. The inner section of the rear wing has a downward sweep angle, and the outer section of the rear wing has an upward sweep angle.

[0012] Furthermore, the front wing and the rear wing are respectively connected to the fuselage through folding mechanisms.

[0013] Furthermore, after the front wing and the rear wing are folded, they are attached to the fuselage, presenting a rotating envelope shape.

[0014] Furthermore, the center of gravity of the fuselage is located at the midpoint between the 1 / 4 chord length position of the front wing root and the 1 / 4 chord length position of the rear wing root.

[0015] Furthermore, the center of gravity of the fuselage is located at the geometric center of the fuselage cross-section.

[0016] Furthermore, the sweep angle and the forward sweep angle are equal.

[0017] Furthermore, the dihedral angle of the outer section of the front wing is equal to the dihedral angle of the inner section of the rear wing.

[0018] Furthermore, the anhedral angle of the inner section of the front wing is equal to the anhedral angle of the outer section of the rear wing.

[0019] Furthermore, the dihedral angle of the outer section of the front wing is 5 - 7° larger than the anhedral angle of the inner section of the front wing.

[0020] Furthermore, the dihedral angle of the inner section of the rear wing is 5 - 7° larger than the anhedral angle of the outer section of the rear wing.

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

[0022] (1) For the asymmetrically bent-wing UAV of the present invention, the front wing and the rear wing are arranged on both sides of the fuselage, one in front of the other along the axial direction of the fuselage. The front wing has a sweep angle, and the rear wing has a forward sweep angle. The front wing is in an inverted V shape, and the rear wing is in a positive V shape. The drag of the swept-wing is less than that of the forward-swept wing, and the drag of the positive V-shaped wing is less than that of the inverted V-shaped wing. Therefore, to a certain extent, drag balance can be achieved through this arrangement, preventing the aircraft from yawing due to the asymmetric wings. Moreover, through the arrangement of the positive V and inverted V-shaped wings, a certain degree of course stability can be achieved for the UAV without a vertical tail. The UAV adopts a tailless layout, eliminating the influence of the negative lift configuration of the tail of the ordinary layout UAV, and making the overall structure smoother, with better lift-to-drag performance. The tailless layout and the arrangement of one forward-swept and one swept wing reduce the strong echo directions when facing radar irradiation, and there are no mutually perpendicular wing surfaces such as horizontal tails and vertical tails, which can eliminate the dihedral effect and have better stealth performance;

[0023] (2) After the wings of the present invention are folded, they are respectively located in the upper and lower directions of the fuselage, reducing mutual interference, improving the reliability of the mechanism, and having a higher space utilization efficiency. It can accommodate a larger fuselage in a limited container. Conventional folding UAVs require multiple folding mechanisms such as wings and tails, while the asymmetrically bent-wing UAV only needs to set a folding mechanism at the connection between the wing and the fuselage. The fewer number of mechanisms makes the whole machine lighter and more reliable.

[0024] (3) The center of gravity of the fuselage of the present invention is located at the midpoint between the 1 / 4 chord length position of the front wing root and the 1 / 4 chord length position of the rear wing root. The center of gravity of the fuselage is located at the geometric center of the fuselage cross-section, thereby realizing that the acting points of the resultant aerodynamic force and gravity are the same, and realizing stable flight. Description of the Drawings

[0025] Figure 1 is a schematic structural diagram of the UAV when the front wing and the rear wing are deployed;

[0026] Figure 2 is a schematic structural diagram of the UAV when the front wing and the rear wing are folded;

[0027] Figure 3 is a top view of the UAV;

[0028] Figure 4 is a front view of the UAV;

[0029] Explanation of the reference numerals in the figures:

[0030] 1. Fuselage, 2. Front wing, 3. Rear wing, 21. Inner section of the front wing, 22. Outer section of the front wing, 31. Inner section of the rear wing, 32. Outer section of the rear wing. Detailed Embodiment

[0031] The present invention will be described in detail below with reference to the drawings and specific embodiments. This embodiment is implemented on the premise of the technical solution of the present invention, and gives the detailed implementation manner and specific operation process, but the protection scope of the present invention is not limited to the following embodiments.

[0032] An asymmetrically bent-wing UAV, as Figure 1 , includes a fuselage 1, a front wing 2 and a rear wing 3. The front wing 2 and the rear wing 3 are respectively arranged on both sides of the fuselage 1 in the front and the rear along the axial direction of the fuselage 1 through a folding mechanism. The axial arrangement positions of the front wing 2 and the rear wing 3 on the fuselage 1 are asymmetric, that is, the front wing 2 is in the front and the rear wing 3 is in the rear. The deployment and folding of the wings can be controlled by a corresponding control module;

[0033] As Figure 4, the front wing 2 has a sweep angle β, includes a front wing inner section 21 and a front wing outer section 22, the fuselage 1, the front wing inner section 21 and the front wing outer section 22 are sequentially connected, the front wing inner section 21 is close to the fuselage 1, the front wing inner section 21 has an upward dihedral angle α, and the front wing outer section 22 has a downward dihedral angle γ;

[0034] like Figure 4 , the rear wing 3 has a forward sweep angle ф, includes a rear wing inner section 31 and a rear wing outer section 32, the fuselage 1, the rear wing inner section 31 and the rear wing outer section 32 are sequentially connected, the rear wing inner section 31 is close to the fuselage 1, the rear wing inner section 31 has a downward dihedral angle λ, and the rear wing outer section 32 has an upward dihedral angle ω;

[0035] The sweep angle β is equal to the forward sweep angle ф.

[0036] The front wing 2 is in an inverted V shape, and the rear wing 3 is in a positive V shape. The drag of the swept-back wing is less than that of the forward-swept wing, and the drag of the positive V-shaped wing is less than that of the inverted V-shaped wing. Therefore, this arrangement can achieve a certain degree of drag balance, so that the aircraft will not yaw due to the asymmetric wings, and the positive V and inverted V wing arrangements can enable the UAV to achieve a certain degree of heading stability without a vertical tail.

[0037] like Figure 2 After being folded, the front wing 2 and the rear wing 3 fit closely with the fuselage 1, forming a rotating envelope shape.

[0038] like Figure 3 As shown, the center of gravity O of the fuselage 1 is located at the midpoint between the 1 / 4 chord length position of the wing root of the front wing 2 and the 1 / 4 chord length position of the wing root of the rear wing 3, and the center of gravity O of the fuselage 1 is located at the geometric center of the cross section of the fuselage 1, thereby achieving the same point of action of the aerodynamic force and the gravity, thereby achieving stable flight.

[0039] like Figure 4 The anhedral angle γ of the front wing outer section 22 is equal to the anhedral angle λ of the rear wing inner section 31, the dihedral angle α of the front wing inner section 21 is equal to the dihedral angle ω of the rear wing outer section 32, the anhedral angle γ of the front wing outer section 22 is 5 to 7° larger than the dihedral angle α of the front wing inner section 21, and the anhedral angle λ of the rear wing inner section 31 is 5 to 7° larger than the dihedral angle ω of the rear wing outer section 32, so as to achieve aerodynamic coupling balance.

[0040] This embodiment proposes an asymmetrically bent-wing unmanned aerial vehicle, which adopts a tailless layout (i.e., without components such as horizontal and vertical tails), eliminating the influence of the negative lift configuration of the tails of ordinary-layout unmanned aerial vehicles and making the overall structure smoother. Therefore, it has a higher lift-to-drag ratio. The tailless layout and the forward-swept and aft-swept arrangement of the wings reduce the strong echo directions when facing radar illumination, and there are no mutually perpendicular wing surfaces such as horizontal and vertical tails, which can eliminate the dihedral effect. Therefore, it has better stealth performance. After the wings are folded, they are respectively located in the upper and lower directions of the fuselage 1, reducing mutual interference, improving the reliability of the mechanism, and having a higher space utilization efficiency. It can accommodate a larger airframe in a limited container. Ordinary-layout folding unmanned aerial vehicles require multiple folding mechanisms for the wings, tails, etc. The asymmetrically bent-wing unmanned aerial vehicle only needs to set a folding mechanism at the connection between the wing and the fuselage 1. The fewer number of mechanisms makes the whole machine lighter and more reliable.

[0041] The preferred specific embodiments of the present invention have been described in detail above. It should be understood that those of ordinary skill in the art can make many modifications and variations based on the concept of the present invention without creative efforts. Therefore, all technical solutions that can be obtained by those skilled in the art in the technical field of the present invention based on the concept of the present invention through logical analysis, reasoning, or limited experiments on the basis of the prior art should fall within the protection scope determined by the claims.

Claims

1. An asymmetrically bent-wing unmanned aerial vehicle, characterized in that, A tailless layout is adopted, comprising a fuselage (1), a front wing (2) and a rear wing (3), wherein the front wing (2) and the rear wing (3) are arranged on both sides of the fuselage (1) in a front-rear direction along the axis of the fuselage (1); The front wing (2) has a sweep angle, comprises a front wing inner section (21) and a front wing outer section (22), the fuselage (1), the front wing inner section (21) and the front wing outer section (22) are connected in sequence, the front wing inner section (21) has an upward dihedral angle, and the front wing outer section (22) has a downward dihedral angle; The rear wing (3) has a forward sweep angle, comprises a rear wing inner section (31) and a rear wing outer section (32), the fuselage (1), the rear wing inner section (31) and the rear wing outer section (32) are connected in sequence, the rear wing inner section (31) has a downward dihedral angle, and the rear wing outer section (32) has an upward dihedral angle; The anhedral angle of the front wing outer section (22) is equal to the anhedral angle of the rear wing inner section (31), and the dihedral angle of the front wing inner section (21) is equal to the dihedral angle of the rear wing outer section (32); The front wing (2) and the rear wing (3) are respectively connected to the fuselage (1) via a folding mechanism; after being folded, the front wing (2) and the rear wing (3) are fitted to the fuselage (1) to form a rotating envelope shape.

2. The asymmetrically bent wing unmanned aerial vehicle according to claim 1, wherein, The center of gravity of the fuselage (1) is located at the midpoint between the 1 / 4 chord length position of the wing root of the front wing (2) and the 1 / 4 chord length position of the wing root of the rear wing (3).

3. An asymmetrically bent wing unmanned aerial vehicle according to claim 1, wherein The center of gravity of the fuselage (1) is located at the geometric center of the cross section of the fuselage (1).

4. The asymmetrically bent wing unmanned aerial vehicle according to claim 1, wherein The sweep back angle is equal to the sweep forward angle.

5. The asymmetrically bent wing unmanned aerial vehicle according to claim 1, wherein The anhedral angle of the front wing outer section (22) is 5 to 7 degrees greater than the anhedral angle of the front wing inner section (21).

6. The asymmetrically bent wing unmanned aerial vehicle according to claim 1, characterized in that, The anhedral angle of the rear wing inner section (31) is 5 to 7 degrees greater than the anhedral angle of the rear wing outer section (32).

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