Aerodynamic layout of fixed-wing unmanned aerial vehicle

Abstract

The utility model discloses an aerodynamic layout of a fixed-wing unmanned aerial vehicle, and belongs to the field of fixed-wing unmanned aerial vehicles. The air inlet channel is connected with the machine body; the wings and the strake wings are both connected with the fuselage, and the wings are connected with the strake wings; the horizontal tail and the vertical tail are both connected with the fuselage, and the first distance between the horizontal tail and the wings is larger than the second distance between the vertical tail and the wings. The wing has the technical effects that the maximum lift coefficient of the wing can be conveniently increased, and the pneumatic coupling of the horizontal tail and the vertical tail can be conveniently reduced.

Description

Technical Field

[0001] The utility model relates to a fixed-wing unmanned aerial vehicle, in particular to an aerodynamic layout of a fixed-wing unmanned aerial vehicle. Background Art

[0002] A fixed-wing unmanned aerial vehicle is an unmanned aerial vehicle that generates forward thrust or pulling force by a power device and generates lift by a fixed wing of the fuselage. It is widely used to simulate the stealth and maneuver characteristics of military combat objects, test and assess new missiles and radar equipment, and train the weapon and equipment systems of troops.

[0003] In order to prevent the relatively large width of the relevant fixed-wing unmanned aerial vehicle, the wingspan generally needs to be controlled within a certain range, which easily leads to a small wing area, resulting in a small maximum lift coefficient of the wing. Moreover, the horizontal tail and vertical tail of the relevant fixed-wing unmanned aerial vehicle are prone to interference, resulting in a large aerodynamic coupling. Summary of the Utility Model

[0004] Purpose of the utility model: The purpose of the utility model is to provide an aerodynamic layout of a fixed-wing unmanned aerial vehicle, which is not only convenient for increasing the maximum lift coefficient of the wing, but also convenient for reducing the aerodynamic coupling between the horizontal tail and the vertical tail.

[0005] Technical solution: An aerodynamic layout of a fixed-wing unmanned aerial vehicle, comprising:

[0006] A fuselage;

[0007] An air inlet duct connected to the fuselage;

[0008] A wing and a strake wing both connected to the fuselage, and the wing and the strake wing are connected;

[0009] A horizontal tail and a vertical tail both connected to the fuselage, and a first distance between the horizontal tail and the wing is greater than a second distance between the vertical tail and the wing.

[0010] Optionally, along the vertical direction of the intake direction, the fuselage forms a first cross-section, and the first cross-section includes a first arc segment, a first straight segment, a second arc segment, and a second straight segment that are sequentially and closedly connected.

[0011] Optionally, the length of the first arc segment is greater than the length of the second arc segment, and the first arc segment and the second arc segment are sequentially arranged along the gravity direction.

[0012] Optionally, it further includes a aileron rotatably connected to the wing.

[0013] Optionally, the aileron is rotatably connected to one end of the wing close to the fuselage.

[0014] Optionally, it further includes an elevator rotatably connected to the horizontal tail.

[0015] Optionally, it further includes a rudder rotatably connected to the vertical tail.

[0016] Optionally, the air inlet of the air intake duct is deflected by a first angle towards the direction of the air outlet of the air intake duct.

[0017] Optionally, the air inlet of the air intake duct is crescent-shaped.

[0018] Optionally, it further includes a fairing connected to the fuselage, and the fairing is sleeved outside the air intake duct.

[0019] Advantageous effects:

[0020] 1) The wing and the strake wing are both used to generate lift. Since the wing and the strake wing are connected, it is convenient to increase the overall area of the wing and the strake wing, thereby facilitating the increase of the maximum lift coefficient, and without increasing the wingspan. For the sake of increasing integrity, the connection mode between the wing and the strake wing is preferably integrally formed connection;

[0021] 2) Since the first distance between the horizontal tail and the wing is greater than the second distance between the vertical tail and the wing, which is equivalent to the horizontal tail and the vertical tail being staggered, it is convenient to prevent interference between the horizontal tail and the vertical tail, thereby facilitating the reduction of the aerodynamic coupling between the horizontal tail and the vertical tail. Description of the drawings

[0022] Figure 1 One of the structural schematic diagrams of the aerodynamic layout of a fixed-wing unmanned aerial vehicle according to Embodiment 1 of the present invention;

[0023] Figure 2 Another structural schematic diagram of the aerodynamic layout of a fixed-wing unmanned aerial vehicle according to Embodiment 1 of the present invention;

[0024] Figure 3 Another structural schematic diagram of the aerodynamic layout of a fixed-wing unmanned aerial vehicle according to Embodiment 1 of the present invention;

[0025] Figure 4 Another structural schematic diagram of the aerodynamic layout of a fixed-wing unmanned aerial vehicle according to Embodiment 1 of the present invention;

[0026] In the figure: 1, fuselage; 11, first cross-section; 111, first arc segment; 112, first straight segment; 113, second arc segment; 114, second straight segment; 12, nose cowling; 13, tail cowling; 2, wing; 21, aileron; 3, strake wing; 4, horizontal tail; 41, elevator; 5, vertical tail; 51, rudder; 6, air intake duct; 61, air inlet; 62, air outlet; 7, fairing. Detailed implementation manners

[0027] To make the technical solution of the present utility model clearer, the following further describes the present utility model in detail with reference to the accompanying drawings and specific embodiments.

[0028] Embodiment 1

[0029] As Figure 1 and 3 This embodiment provides an aerodynamic layout of a fixed-wing unmanned aerial vehicle, including: a fuselage 1; an air intake 6 connected to the fuselage 1; a wing 2 and a strake 3 both connected to the fuselage 1, with the wing 2 and the strake 3 connected; a horizontal tail 4 and a vertical tail 5 both connected to the fuselage 1, and the first spacing between the horizontal tail 4 and the wing 2 is greater than the second spacing between the vertical tail 5 and the wing 2.

[0030] Specifically, the fuselage 1 is used to load airborne equipment, fuel, mission equipment, etc.; the air intake 6 is used for air intake, so as to facilitate the generation of forward thrust or pull; both the wing 2 and the strake 3 are used to generate lift. Since the wing 2 and the strake 3 are connected, it is convenient to increase the overall area of the wing 2 and the strake 3, thereby facilitating the increase of the maximum lift coefficient without increasing the wingspan of the wing 2. For the sake of increasing integrity, the connection method between the wing 2 and the strake 3 is preferably integrally formed. Among them, the shape of the wing 2 is preferably a swept trapezoid. By adjusting the wingspan and area, the aspect ratio can be controlled at a relatively small level. By appropriately increasing the leading-edge sweep angle γ, the leading-edge sweep angle γ is preferably 40°, which is beneficial to reducing transonic drag and reducing forward radar scattering. The number of both the wing 2 and the strake 3 is two, and they are respectively located on both sides of the fuselage 1; the horizontal tail 4 is used to adjust the longitudinal aerodynamic center position. The horizontal tail 4 is preferably deflected by a second angle β along the gravity direction, and the second angle β is preferably 13°, which is convenient for reducing the downwash effect of the wing 2 on the horizontal tail 4. The number of the horizontal tails 4 is two, and they are respectively located on both sides of the fuselage 1; the vertical tail 5 is used to ensure the course stability of the fixed-wing unmanned aerial vehicle of the present application. The number of the vertical tails 5 is one, and it is located between the two horizontal tails 4. Since the first spacing between the horizontal tail 4 and the wing 2 is greater than the second spacing between the vertical tail 5 and the wing 2, it is equivalent to staggering the horizontal tail 4 and the vertical tail 5, which is convenient for preventing interference between the horizontal tail 4 and the vertical tail 5, and thus convenient for reducing the aerodynamic coupling between the horizontal tail 4 and the vertical tail 5.

[0031] Further, as Figure 4 , along the vertical direction of the intake direction, the fuselage 1 forms a first cross-section 11, and the first cross-section 11 includes a first arc segment 111, a first straight segment 112, a second arc segment 113, and a second straight segment 114 that are sequentially and closedly connected. Specifically, through the staggered arrangement of the arc segment and the straight segment, it is not only convenient for the first cross-section 11 of the fuselage 1 to have good aerodynamic characteristics, but also convenient for improving the internal volume utilization rate of the fuselage 1. The design length of the nose cover 12 of the fuselage 1 can be adjusted to match the specific mission equipment to be loaded, and the design length of the tail cover 13 of the fuselage 1 can also be extended to adapt to the minimum flight resistance requirement.

[0032] Further, as shown in Figure 4 , the length of the first arc segment 111 is greater than that of the second arc segment 113, and the first arc segment 111 and the second arc segment 113 are arranged in sequence along the gravity direction. Specifically, the length of the first arc segment 111 is relatively large, and the length of the second arc segment is relatively small. Since the first arc segment 111 and the second arc segment 113 are arranged in sequence along the gravity direction, it is convenient to make the flight performance of the fixed-wing UAV of the present application good.

[0033] Further, as shown in Figure 1 , it further includes ailerons 21 rotatably connected to the wings 2. Specifically, the ailerons 21 are rotated specifically by the first servos. The first servos are arranged in the fuselage 1, and the number of both the ailerons 21 and the first servos is two. By the differential movement of the two ailerons 21, the lift forces of the two wings 2 are different, which is convenient for generating a rolling moment.

[0034] Further, as shown in Figure 1 , the ailerons 21 are rotatably connected to one end of the wings 2 close to the fuselage 1. Specifically, it is equivalent to that the distance between the ailerons 21 and the fuselage 1 is small, that is to say, the distance between the ailerons 21 and the first servos is small, which is convenient for making the transmission distance between the ailerons 21 and the first servos small, thereby facilitating the improvement of the transmission stiffness.

[0035] Further, as shown in Figure 1 , it further includes elevators 41 rotatably connected to the horizontal tail 4. Specifically, the elevators 41 are used for longitudinal pitch control, and are rotated specifically by the second servos. The second servos are arranged in the fuselage 1, so as to realize the increase and decrease of the lift force of the horizontal tail 4, and further generate a pitching moment. The elevators 41 are arranged at the trailing edge of the horizontal tail 4, and the area size of the elevators 41 meets the maneuvering requirements within the flight envelope. The number of the elevators 41 is two and corresponds to the horizontal tail 4.

[0036] Further, as shown in Figure 1 , it further includes rudders 51 rotatably connected to the vertical tail 5. Specifically, the rudders 51 are used for yaw control, and are rotated specifically by the third servos. The third servos are arranged in the fuselage 1, which is convenient for increasing and decreasing the lateral force of the vertical tail 5 and generating a yaw moment.

[0037] Further, as shown in Figure 3 , the air inlet 61 of the air inlet duct 6 is deflected by a first angle α towards the direction of the air outlet 62 of the air inlet duct 6. Specifically, the first angle α is convenient for reflecting the forward electromagnetic wave to other directions, preventing the forward electromagnetic wave from generating a strong echo scattering. The first angle α is preferably 30°.

[0038] Further, as shown in Figure 4 , the air inlet 61 of the air inlet duct 6 is crescent-shaped. Specifically, the crescent shape is convenient for reducing the scattering of the air inlet duct 6, which is beneficial to reducing the radar cross section.

[0039] Further, as Figure 3 , it further includes a fairing 7 connected to the fuselage 1, and the fairing 7 is sleeved outside the air inlet 6. Specifically, the fairing 7 can not only reduce the resistance caused by airflow separation, but also facilitate the protection of the air inlet 6.

[0040] The above embodiments only represent several implementation manners of the present utility model, and the description thereof is relatively specific and detailed, but it should not be construed as a limitation on the scope of the patent of the present utility model. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present utility model, several modifications and improvements can still be made, and these all belong to the protection scope of the present utility model. Therefore, the protection scope of the patent of the present utility model shall be subject to the appended claims.

Claims

1. An aerodynamic layout of a fixed-wing unmanned aerial vehicle, characterized in that, Comprising: Fuselage; An inlet duct connected to the fuselage; A wing and a strake wing both connected to the fuselage, the wing and the strake wing being connected; A horizontal tail and a vertical tail both connected to the fuselage, a first distance between the horizontal tail and the wing being greater than a second distance between the vertical tail and the wing.

2. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to claim 1, wherein, In a direction perpendicular to the intake direction, the fuselage forms a first cross-section, the first cross-section comprising a first arc segment, a first straight segment, a second arc segment, and a second straight segment that are sequentially and closedly connected.

3. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to claim 2, characterized in that, The length of the first arc segment is greater than the length of the second arc segment, and the first arc segment and the second arc segment are sequentially arranged along the gravity direction.

4. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to any one of claims 1 to 3, characterized in that, It further includes an aileron rotatably connected to the wing.

5. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to claim 4, characterized in that, The aileron is rotatably connected to one end of the wing close to the fuselage.

6. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to any one of claims 1 to 3, characterized in that, It further includes an elevator rotatably connected to the horizontal tail.

7. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to any one of claims 1 to 3, characterized in that, It further includes a rudder rotatably connected to the vertical tail.

8. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to any one of claims 1 to 3, characterized in that, The air inlet of the inlet duct is deflected by a first angle towards the direction of the air outlet of the inlet duct.

9. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to claim 8, characterized in that, The air inlet of the inlet duct is crescent-shaped.

10. The aerodynamic layout of a fixed-wing unmanned aerial vehicle according to any one of claims 1 to 3, characterized in that, It further includes a fairing connected to the fuselage, the fairing being sleeved outside the inlet duct.

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