CN113460282B

CN113460282B - Pneumatic layout of unmanned aerial vehicle

Info

Publication number: CN113460282B
Application number: CN202110722557.6A
Authority: CN
Inventors: 宋国磊; 司亮; 李金鸣; 李宇新; 钟路阳; 杨林谦; 王广银
Original assignee: Electronic Technology Research Institute Of China Aerospace; Aerospace Times Feihong Technology Co ltd
Current assignee: Electronic Technology Research Institute Of China Aerospace; Aerospace Times Feihong Technology Co ltd
Priority date: 2021-06-28
Filing date: 2021-06-28
Publication date: 2023-06-06
Anticipated expiration: 2041-06-28
Also published as: CN113460282A

Abstract

The invention relates to a pneumatic layout of an unmanned aerial vehicle, wherein a wing body is designed by adopting a wing body fusion design, and the pneumatic layout comprises a wing body fusion body, wings, a task load and an engine rainproof device; the front end of the wing body fusion body is connected with the task load; the rear end of the wing body fusion body is connected with the engine rainproof device; the left side and the right side of the wing body fusion body are respectively connected with two wings; the front end of the wing body fusion body is in conformal connection with the task load, and the engine rainproof device is connected with the wing body fusion body through rectification design. The engine rainproof device, the task load and the wing body fusion body are conformally designed, so that the high lift-drag ratio of the wing body fusion can be considered, and the problem of lift-drag ratio reduction caused by engine air filtration and exposed task load is solved.

Description

Pneumatic layout of unmanned aerial vehicle

Technical Field

The invention relates to the field of unmanned aerial vehicle design, in particular to the field of unmanned aerial vehicle pneumatic layout design.

Background

The fuselage fusion layout (BWB, blended Wing Body) integrates the wing and the fuselage without obvious demarcation lines in function and appearance. The wing body fusion layout can greatly reduce the infiltration area, reduce the structural weight and the induced resistance, increase the lifting surface and further improve the lift-drag ratio. However, for some small unmanned aerial vehicles, when the aerodynamic profile design is performed, on the premise of ensuring a smaller infiltration area of the airframe, the airframe is difficult to completely envelop the engine and the task load, and when the unmanned aerial vehicle is in actual use, the engine air filter and the task load are exposed, so that the lift-drag ratio benefit brought by the wing body fusion design is destroyed. Therefore, how to design is to realize conformal drag reduction design of engine air filtration, task load and a fuselage, and has important significance for improving the unmanned aerial vehicle lift-drag ratio of wing body fusion layout.

Disclosure of Invention

The invention aims to solve the defects in the prior art, and aims to provide a pneumatic layout of an unmanned aerial vehicle, which is used for solving the problems in the prior art.

The above technical object of the present invention is achieved by the following technical means.

An unmanned aerial vehicle pneumatic layout comprising a wing body fusion, a tail stay, a vertical tail, a horizontal tail, a task load and an engine rainproof device;

the front end of the wing body fusion body is connected with the task load;

the rear end of the wing body fusion body is connected with the engine rainproof device;

the left side and the right side of the wing body fusion body are respectively connected with two wings of the unmanned aerial vehicle;

the front end of the wing body fusion body is in conformal connection with the task load, and the engine rainproof device is an integral streamline type.

As described above, in one aspect and any one of the possible implementation manners, there is further provided an implementation manner, the aerodynamic layout of an unmanned aerial vehicle further includes a tail stay, a horizontal tail and a vertical tail, where the tail stay and the vertical tail are both provided with two, and are symmetrically distributed on two sides of the wing body fusion body, and one end of each tail stay is connected with the wing body fusion body, and the other end of each tail stay is vertically connected with one end of one of the vertical tails, and the other ends of the two vertical tails are connected with two ends of the horizontal tail.

In the aspect and any possible implementation manner as described above, further providing an implementation manner, the unmanned aerial vehicle aerodynamic layout further includes a rudder and an elevator, and the rudder is disposed on the vertical tail; the elevator is arranged on the horizontal tail.

Aspects and any possible implementation manner as described above, further provide an implementation manner, where a flap, an aileron and a winglet are disposed on both wings of the unmanned aerial vehicle, where the flap is disposed near a fuselage of the unmanned aerial vehicle, the aileron is disposed between the flap and the winglet, and the winglet is disposed at a tail end of the wing.

In accordance with aspects and any one of the possible implementations described above, there is further provided an implementation, the unmanned aerial vehicle aerodynamic layout further includes an air filter, the air filter being wrapped within the engine rain protection device.

In aspects and any one of the possible implementations described above, there is further provided an implementation, the engine rain shield is an engine rain shield including a top cover and a base.

In aspects and any one of the possible implementations described above, there is further provided an implementation in which the engine rain cover top cover profile is larger than the base profile, and a gap of 0.1-1cm is provided at a junction of the two.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the shapes of the base and the top cover are streamline.

In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the mission load is disposed at a front end of a fuselage of the unmanned aerial vehicle, and a bottom of the mission load is flush with a bottom of the fuselage of the unmanned aerial vehicle, and is integrally streamlined with the fuselage, and is connected in a conformal manner.

The invention also provides a conformal rectification design method which is used for the pneumatic layout of the unmanned aerial vehicle.

The beneficial technical effects of the invention

The unmanned aerial vehicle pneumatic layout provided by the embodiment of the invention comprises a wing body fusion body, wings, task loads and an engine rainproof device; the front end of the wing body fusion body is connected with the task load; the rear end of the wing body fusion body is connected with the engine rainproof device; the left side and the right side of the wing body fusion body are respectively connected with two wings of the unmanned aerial vehicle; the front end of the wing body fusion body is in conformal connection with the task load, and the left side and the right side of the wing body fusion body are integrally connected with the two wings. The invention adopts conformal design for the engine rainproof device, the task load and the wing body fusion body, combines the advantages of double-tail support type layout and wing body fusion type pneumatic layout, not only can give consideration to the high lift-drag ratio of the wing body fusion, but also solves the problem of lift-drag ratio reduction caused by engine air filtration and task load exposure. The tail stay bar is connected with the wing body fusion body, the horizontal tail is positioned on the slightly upper parts of the two vertical tail wings and connected with the two vertical tail wings, the task load is positioned at the front end of the machine body, the bottom of the task load is flush with the bottom of the machine body and is in conformal connection with the machine body, and the differential pressure resistance caused by separation is reduced; the engine rain cover is divided into a top cover and a base, the top cover and the base are in a streamline shape, the base is directly connected with the machine body, the top cover is connected with the base through an adapter, air enters the air filter from a gap between the top cover and the base, so that the resistance increase caused by the extension of the engine air filter can be reduced, and sufficient air can be ensured to enter the air filter; the wing body fusion body and the task load adopt conformal design, so that the resistance increase caused by the extension of the task load is reduced, and the resistance of the whole machine is further reduced.

Drawings

Embodiments of the present invention are described in detail below with reference to the attached drawing figures, wherein:

fig. 1 is a schematic diagram of a pneumatic layout of a drone in an embodiment of the present invention;

fig. 2 is a top view of a pneumatic layout of a drone in an embodiment of the present invention;

FIG. 3 is a side view of a pneumatic layout of a drone in an embodiment of the present invention;

fig. 4 is a schematic structural view of a rain cover in an embodiment of the present invention.

Reference numerals illustrate: wing body fusion-1; wing-2; tail stay bar-3; horizontal tail-4; flap-5; aileron-6; elevator-7; rudder-8; winglet-9; vertical fin-10; task load-11; an engine rain cover-12; a top cover-13; a base-14; air filtering-15.

Detailed Description

In order to make the technical problems, technical solutions and advantages to be solved by the present invention more apparent, the following detailed description will be given with reference to the accompanying drawings and specific examples, but the embodiments of the present invention are not limited thereto.

1-2, the aerodynamic layout of the middle unmanned aerial vehicle in the embodiment of the invention comprises a wing body fusion body 1, a wing 2, a task load 11 and an engine rainproof device, wherein the engine rainproof device is realized by an engine rainproof cover 12; wherein, the front end of the wing body fusion body 1 is connected with the task load 11; the rear end of the wing body fusion body 1 is connected with the engine rain cover 12; the left side and the right side of the wing body fusion body 1 are respectively connected with two wings 2; the front end of the wing body fusion 1 is connected with the task load 11 in a conformal way, and the engine rain cover 12 is of a rectifying design and is connected with the wing body fusion 1.

Preferably, the wing 2 and the fuselage of the unmanned aerial vehicle are designed in a wing body fusion manner, the wing and the fuselage of the unmanned aerial vehicle are integrated into a whole, and the wing body fusion body 1 and the wing 2 without a boundary line are formed. The head of wing body fusion 1 adopts conformal design with task load 11, task load 11 set up in the front end of unmanned aerial vehicle's fuselage, the bottom surface is inwards sunken into fan-shaped under the fuselage head, and fan-shaped radius wherein is the same or similar with task load 11 radius size, and this kind of setting up mode makes behind the installation task load 11 on unmanned aerial vehicle, task load 11's bottom with unmanned aerial vehicle's fuselage bottom flushes to realize unmanned aerial vehicle's fuselage and task load 11 conformal connection, reduce because task load 11 stretches out the resistance that unmanned aerial vehicle's fuselage outside arouses and increase, thereby further reduced unmanned aerial vehicle's complete machine resistance, improved the advantage that the wing body fuses the overall arrangement.

Preferably, the aerodynamic layout of the unmanned aerial vehicle further comprises a tail stay bar 3, a horizontal tail 4 and a vertical tail 10, as shown in fig. 1, wherein the tail stay bar 3 and the vertical tail 10 are both provided with two, symmetrically distributed on two sides of the wing body fusion body 1, one end of each tail stay bar 3 is connected with the wing body fusion body 1, and the other end of each tail stay bar 3 is vertically connected with one end of one of the vertical tails 10, namely, the two vertical tails 10 are of a vertical structure; the other ends of the two vertical tails 10 are respectively connected with the two ends of the horizontal tail 4, namely the horizontal tail 4 is positioned on the wing tips of the two vertical tails 10, and the arrangement mode avoids the fusion tail separating flow and the propeller slipstream, so that the influence of the fusion tail separating flow and the propeller slipstream on the longitudinal stability of the unmanned aerial vehicle is reduced.

Preferably, the aerodynamic layout of the unmanned aerial vehicle further comprises a rudder 8 and an elevator 7, wherein the rudder 8 is arranged on the vertical fin 10, and the rudder 8 can adjust the attitude of the unmanned aerial vehicle in the take-off and landing stage so as to lead the unmanned aerial vehicle to be aligned to the flight runway of the unmanned aerial vehicle; the elevator 7 is arranged on the horizontal tail 4 and is used for controlling the pitching characteristic of the unmanned aerial vehicle when the unmanned aerial vehicle flies, so that the longitudinal attitude control of the unmanned aerial vehicle is realized.

Preferably, a flap 5, an aileron 6 and a winglet 9 are arranged on both wings 2 of the unmanned aerial vehicle of the invention, wherein the flap 5 is arranged close to the fuselage of the unmanned aerial vehicle, the aileron 6 is arranged between the flap 5 and the winglet 9, and the winglet 9 is arranged at the tail end of the wings 2. The winged winglet 9 can effectively reduce the induced resistance and improve the lift-drag ratio of the whole unmanned aerial vehicle. The flap 5 can obviously shorten the landing and running distance in the wheel type landing process of the unmanned aerial vehicle; while the aileron 6 is in flight, the unmanned aerial vehicle roll and yaw can be corrected.

Preferably, the engine rainproof device is of a rectifying design, the engine rainproof cover 12 comprises a top cover 13 and a base 14, the engine air filter 15 is wrapped in the top cover 13 and the base 14, the top cover 13 and the base 14 are of streamline shapes, namely the engine rainproof cover 12 is of an integral streamline shape, and the structural design can weaken air flow separation caused by the exposure of the engine air filter 15, so that the resistance born by the whole unmanned aerial vehicle is reduced. Wherein the base 14 is directly connected with the machine body, the top cover 13 is connected with the base 14 through a switching device, and particularly through a switching piece, so that air enters the engine air filter 15 from a gap between the top cover 13 and the base 14. The design of the engine rain cover 12 can ensure that the engine air filter 15 is prevented from being drenched, and simultaneously, air can freely enter the engine air filter 15, and the additional resistance caused by the exposure of the engine air filter 15 can be reduced.

Preferably, the top cover contour of the engine rain cover 12 is larger than the base contour, and a gap of 0.1 cm to 1cm is arranged at the joint of the top cover contour and the base contour, specifically, the gap of the joint of the top cover of the engine rain cover and the base is 0.5cm, and the arrangement ensures that air can freely enter the engine air filter 15 arranged in the engine rain cover 12.

Preferably, the present invention further provides a conformal rectifying design method for pneumatic layout of an unmanned aerial vehicle, the conformal rectifying design method comprising: the wing body fusion body and the task load are designed to be in conformal connection, the bottom of the task load is flush with the bottom of the unmanned aerial vehicle body, and the wing body fusion body and the task load are also in conformal connection; the engine rainproof device is designed to be a rectifying type, and is particularly realized by an engine rainproof cover, wherein the engine rainproof cover comprises a top cover 13 and a base 14, and the top cover 13 and the base 14 are streamline, namely, the engine rainproof cover is of an integral streamline type.

While the foregoing description illustrates and describes the preferred embodiments of the present invention, it is to be understood that the invention is not limited to the forms disclosed herein, but is not to be construed as limited to other embodiments, and is capable of numerous other combinations, modifications and environments and is capable of changes or modifications within the scope of the claimed invention, either as a result of the foregoing teachings or as a result of knowledge in the relevant art. And that modifications and variations which do not depart from the spirit and scope of the invention are intended to be within the scope of the appended claims.

Claims

1. The unmanned aerial vehicle pneumatic layout is characterized by comprising a wing body fusion body, a tail stay bar, a vertical tail, a horizontal tail, a task load and an engine rainproof device;

the front end of the wing body fusion body is connected with the task load, the lower bottom surface of the head of the unmanned aerial vehicle is inwards sunken into a fan shape, and the radius of the fan shape is the same as or similar to the radius of the task load, so that the bottom of the task load is flush with the bottom of the unmanned aerial vehicle, and the conformal connection of the unmanned aerial vehicle and the task load is realized;

the rear end of the wing body fusion body is connected with the engine rainproof device, the engine rainproof device is of an integral streamline type and comprises a top cover and a base which are connected, an air filter of an engine is wrapped in the top cover and the base, the top cover and the base are of streamline shapes, the base is directly connected with a machine body, the top cover outline of the engine rainproof device is larger than the base outline, and a gap of 0.1-1cm is formed at the joint of the top cover outline and the base outline;

the left side and the right side of the wing body fusion body are respectively connected with two wings of the unmanned aerial vehicle.

2. The unmanned aerial vehicle aerodynamic layout of claim 1, further comprising a tail stay, a horizontal tail and a vertical tail, wherein the tail stay and the vertical tail are both provided with two, are symmetrically distributed on both sides of the wing body fusion, and one end of each tail stay is connected with the wing body fusion, the other end of each tail stay is vertically connected with one end of one of the vertical tails, and the other ends of the two vertical tails are connected with both ends of the horizontal tail.

3. The unmanned aerial vehicle aerodynamic layout of claim 2, further comprising a rudder and an elevator, the rudder disposed on the vertical tail; the elevator is arranged on the horizontal tail.

4. The unmanned aerial vehicle aerodynamic layout of claim 1 or 2, wherein a flap, an aileron and a winglet are provided on both wings of the unmanned aerial vehicle, wherein the flap is provided close to the fuselage of the unmanned aerial vehicle, the aileron is provided between the flap and the winglet, and the winglet is provided at the trailing end of the wing.

5. A conformal rectification design method for the unmanned aerial vehicle aerodynamic layout of any of claims 1-4.