CN212829034U - Aircraft wing - Google Patents

Abstract

The embodiment of the utility model provides an aircraft wing, including baffle, fin and back flow; an organic wing inner cavity is formed in the wing body, the partition plate is arranged in the wing inner cavity and is close to the wing leading edge, and the wing inner cavity is divided into a first cavity and a second cavity by the partition plate; the fin is arranged in the first cavity, the return pipe is arranged in the second cavity, and the first cavity is communicated with the return pipe. Stable high-temperature fluid can exist in the wing of the structure, the wing leading edge can be effectively heated, the anti-icing and deicing effects are good, and the wing structure is suitable for various airplanes, for example, a small and medium-sized unmanned aerial vehicle provided with an aviation piston engine.

Description

Aircraft wing

Technical Field

The utility model relates to a transportation technical field, concretely relates to aircraft wing.

Background

When the airplane flies in a wet and cold environment, the risk of wing icing exists, and the flight safety is affected. At present, a medium-sized fixed wing unmanned aerial vehicle adopting a piston engine as power generally does not have an anti-icing and deicing device, and the anti-icing and deicing device of a large-sized aircraft generally adopts high-temperature gas heating to realize the anti-icing and deicing functions.

In the process of implementing the present invention, the inventor finds that there are at least the following problems in the prior art: the unmanned aerial vehicle adopting the piston engine is limited by power, is not provided with an anti-icing and deicing device, and adopts a high-temperature gas heating mode to prevent and deice the aircraft, the engine of the unmanned aerial vehicle cannot provide a stable and large-flow high-temperature gas source, and the anti-icing and deicing effects of the front edge of the wing cannot be guaranteed.

SUMMERY OF THE UTILITY MODEL

In view of this, the embodiment of the utility model provides an aircraft wing to solve the unmanned aerial vehicle that adopts piston engine among the prior art and receive power limitation, do not have anti-icing, defroster, and adopt the high-temperature gas heating mode to come the aircraft of anti-icing, deicing, its engine can't provide stable large-traffic high temperature air supply, can't guarantee the problem of anti-icing, the deicing effect of wing leading edge.

In order to achieve the above object, an embodiment of the present invention provides an aircraft wing, including a partition plate, fins and a return pipe; an organic wing inner cavity is formed in the wing body, the partition plate is arranged in the wing inner cavity and is close to the wing leading edge, and the wing inner cavity is divided into a first cavity and a second cavity by the partition plate; the fin is arranged in the first cavity, the return pipe is arranged in the second cavity, and the first cavity is communicated with the return pipe.

Optionally, in the aircraft wing, the rib is arranged along a direction from a wing root of the wing to a wing tip of the wing, and a cross-sectional area of the rib increases as a distance from the cross-section to the wing tip decreases.

Optionally, in the aircraft wing, the cross-sectional area is linear with the distance of the cross-section from the wing tip.

Optionally, in the aircraft wing, the number of the fins is multiple, and the multiple fins are arranged in parallel.

Optionally, in the aircraft wing, the first cavity and the return duct communicate proximate to the wing tip.

Optionally, the aircraft wing further comprises a communicating pipe, the communicating pipe passes through the partition plate, and two ends of the communicating pipe are respectively communicated with the first cavity and the return pipe.

Optionally, in the aircraft wing, the number of the communicating tubes is at least one.

Optionally, in the aircraft wing, the return pipe has a circular pipe structure.

Optionally, in the aircraft wing, the return pipe is spaced from the bulkhead.

Optionally, in the aircraft wing, a distance is provided between the return pipe and the inner wall of the wing.

According to the technical scheme of the utility model, an embodiment in the above-mentioned utility model has following advantage or beneficial effect: in the wing with the structure, high-temperature fluid can circularly flow in the first cavity and the return pipe to heat the leading edge of the wing, so that the leading edge of the wing is prevented from being frozen or the ice on the leading edge of the wing is removed, the anti-icing and deicing effects are good, and the wing is suitable for various airplanes.

Further effects of the above-mentioned non-conventional alternatives will be described below in connection with the embodiments.

Drawings

The accompanying drawings are included to provide a better understanding of the present invention and are not intended to constitute an undue limitation on the invention. Wherein:

fig. 1 is a schematic structural view of an embodiment of an aircraft wing according to the present invention;

fig. 2 is a schematic structural view of another perspective of an embodiment of an aircraft wing according to the present invention;

fig. 3 is a schematic structural view of an embodiment of the rib of the aircraft wing of the present invention.

Wherein the figures include the following reference numerals:

1-partition board, 100-wing body, 11-first cavity, 12-second cavity, 13-wing root, 14-wing tip, 2-rib, 3-return pipe, 4-communicating pipe and 5-wing leading edge.

Detailed Description

Exemplary embodiments of the invention are described below with reference to the accompanying drawings, in which various details of embodiments of the invention are included to assist understanding, and which are to be considered exemplary only. Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope and spirit of the invention. Also, descriptions of well-known functions and constructions are omitted in the following description for clarity and conciseness.

As shown in fig. 1 to 3, an aircraft wing according to an embodiment of the present invention includes a partition plate 1, fins 2, and a return pipe 3; an organic wing inner cavity is formed in the wing body 100, the partition board 1 is arranged in the wing inner cavity and is close to the wing leading edge 5, and the wing inner cavity is divided into a first cavity 11 and a second cavity 12 by the partition board 1; the fins 2 are arranged in the first cavity 11, the return pipe 3 is arranged in the second cavity 12, and the first cavity 11 is communicated with the return pipe 3.

In the above embodiment, the wing of the structure may heat the wing leading edge 5 by using a high-temperature fluid, the partition board 1 divides the wing inner cavity into the first cavity 11 and the second cavity 12, the first cavity 11 is close to the wing leading edge 5, and the high-temperature fluid may flow in the first cavity 11 and the return pipe 3, that is, after the fluid flows into the first cavity 11, the fluid may flow in the first cavity 11 to heat the wing leading edge 5, so as to prevent the wing leading edge 5 from icing or remove the icing of the wing leading edge 5. The temperature of the wing leading edge 5 is reduced after the fluid heats the wing leading edge, and since the first cavity 11 is communicated with the return pipe 3 and the return pipe 3 is communicated with the heat exchange device of the airplane, the fluid with a lower temperature can return to the heat exchange device through the return pipe 3 to be heated, so that the fluid is ensured to be in a high-temperature state, the heated fluid continuously flows into the first cavity 11, and the circulation work is performed in such a way, so that the icing of the wing leading edge 5 is prevented or the icing of the wing leading edge 5 is removed. It should be noted that the heat exchange device is a device capable of heating fluid to ensure stable high-temperature fluid in the wing, for example, the heat exchange device may be a device composed of an engine exhaust system to heat fluid. In addition, the fluid is circulated outside the wing by means of pipes, for example, high-temperature-resistant metal pipes. The high temperature fluid may be a medium with good thermal conductivity such as water or oil. The fins 2 are fixedly arranged in the first cavity 11, so that the heat dissipation area can be increased, the heat exchange efficiency is improved, and the anti-icing and deicing effects are better. Stable high-temperature fluid can exist in the wing with the structure, the wing leading edge 5 can be effectively heated, the anti-icing and deicing effects are good, and the wing is suitable for various airplanes, for example, a small and medium-sized unmanned aerial vehicle provided with an aviation piston engine.

In order to improve the heat exchange efficiency of the fluid in the first cavity 11, as shown in fig. 1 to 3, in an embodiment of the present invention, the fins 2 are disposed along the direction from the wing root 13 of the wing to the wing tip 14 of the wing, and the cross-sectional area of the fins 2 increases as the distance from the cross-section to the wing tip 14 decreases. The fins 2 are arranged in the direction from the wing root 13 of the wing to the wing tip 14 of the wing, so that smooth flow of fluid can be ensured, the cross section of the fin 2 which is closer to the wing tip 14 is larger, and the heat exchange amount of the wing tip 14 can be ensured. The simulation experiment of the structure shows that when the cross-sectional area of the fin 2 is in a linear relationship with the distance from the cross section to the wing tip 14, the heat exchange efficiency of the fluid is highest, and the optimal heating effect on the wing leading edge 5 can be achieved.

In order to further improve the heat exchange efficiency of the fluid in the first cavity 11, as shown in fig. 1 and fig. 2, in an embodiment of the present invention, the number of the fins 2 is multiple, and the multiple fins 2 are arranged in parallel. The heat exchange amount is ensured by increasing the heat exchange area through arranging the plurality of fins 2, a better heating effect is realized, and the plurality of fins 2 are arranged in parallel, so that the stable flow of the fluid in the first cavity 11 can be ensured, namely, the high-temperature fluid flows into the first cavity 11 from the wing root 13 and flows towards the wing tip 14 direction in the first cavity 11 along the fins 2 to heat the wing leading edge 5.

In order to ensure uniform heating of the entire leading edge 5 of the wing, as shown in figures 1 and 2, in one embodiment of the invention the first cavity 11 and the return duct 3 communicate close to the wing tip 14. This ensures that the fluid will flow through the entire first cavity 11 and back into the heat exchange means, avoiding the problem of poor heating near the wing tip 14. Wherein, in order to make the fluid flow to the return pipe 3 better, in the preferred embodiment of the present invention, the present invention further comprises a communicating pipe 4, the communicating pipe 4 passes through the partition board 1, and both ends are respectively communicated with the first cavity 11 and the return pipe 3. So that the fluid in the first cavity 11 can flow into the return pipe 3 through the communicating pipe 4. In order to improve the backflow efficiency, the number of the communication pipes 4 is at least one, and the communication pipes 4 are disposed near the wing tips 14. In the present embodiment, the number of communication pipes 4 is one.

In order to reduce the loss of fluid heat in the wing, as shown in fig. 1 and 2, in an embodiment of the present invention, a distance is provided between the return pipe 3 and the partition board 1, and meanwhile, a distance is provided between the return pipe 3 and the inner wall of the wing. Therefore, the heat of the fluid in the return pipe 3 can be prevented from being absorbed by the wing shell, the skin and the like, and the heat of the fluid in the first cavity 11 can be prevented from being absorbed by the return pipe 3, so that the heating effect is ensured. The return pipe 3 is a tubular structure, and in this embodiment, the return pipe 3 is a circular pipe structure and is fixed in the second cavity 12 by a bracket or a pipe clamp. In order to further ensure that more heat of the fluid is transferred to the leading edge 5 of the wing and reduce the outward transfer of the heat of the fluid through the partition plate 1, simulation experiments on the structure show that the thickness of the partition plate 1 should not exceed 1.5 mm, so that the outward transfer of the heat of the fluid through the partition plate 1 can be effectively reduced.

The utility model provides a use of aircraft wing who provides is described below with this wing structure installation at the medium-sized unmanned aerial vehicle who uses aviation piston engine as power as the example.

As shown in fig. 1 and 2, when the unmanned aerial vehicle equipped with the wing structure flies in a cold and humid environment, high-temperature fluid flows into the first cavity 11 from the wing root 13 of the wing, flows along the fins 2 in the first cavity 11 toward the wing tip 14 of the wing to heat the wing leading edge 5, so that the icing of the wing leading edge 5 or the icing of the wing leading edge 5 can be prevented or removed, the fluid flows into the return pipe 3 through the communicating pipe 4 at the wing tip 14, then flows back into the heat exchanging device through the return pipe 3 to be heated, the heated fluid continuously flows into the first cavity 11 to heat the wing leading edge 5, and the circulation operation is performed in such a way to prevent the icing of the wing leading edge 5 or remove the icing of the wing leading edge 5. The stable high-temperature fluid can be stored in the wing, the wing leading edge 5 can be effectively heated, and the anti-icing and deicing effects are good.

Therefore, the embodiment of the utility model provides an among the aircraft wing, in the wing of this structure, high temperature fluid can come the heating to wing leading edge 5 at first cavity 11 and 3 inner loop flows of back flow, prevents that wing leading edge 5 from freezing or detach the freezing of wing leading edge 5, and its anti-icing and deicing are effectual, and are applicable to all kinds of aircraft.

The above detailed description does not limit the scope of the present invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions can occur, depending on design requirements and other factors. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. An aircraft wing is characterized by comprising a clapboard (1), fins (2) and a return pipe (3);

an organic wing inner cavity is formed in a wing body (100), the partition plate (1) is arranged in the wing inner cavity and is close to a wing leading edge (5), and the wing inner cavity is divided into a first cavity (11) and a second cavity (12) by the partition plate (1);

the fin (2) is arranged in the first cavity (11), the return pipe (3) is arranged in the second cavity (12), and the first cavity (11) is communicated with the return pipe (3).

2. An aircraft wing according to claim 1, characterized in that the ribs (2) are arranged in the direction of the wing root (13) to the wing tip (14) of the wing, and that the cross-sectional area of the ribs (2) increases with decreasing distance of the cross-section to the wing tip (14).

3. An aircraft wing as claimed in claim 2, characterized in that the cross-sectional area is linear with the distance of the cross-section from the wing tip (14).

4. The aircraft wing as claimed in claim 1, characterized in that the number of ribs (2) is a plurality, and a plurality of ribs (2) are arranged in parallel.

5. An aircraft wing as claimed in claim 1, characterized in that the first cavity (11) and the return duct (3) communicate close to the wing tip (14).

6. An aircraft wing according to claim 5, further comprising a communicating tube (4), the communicating tube (4) passing through the bulkhead (1) and communicating at both ends with the first cavity (11) and the return tube (3), respectively.

7. The aircraft wing as claimed in claim 6, characterized in that the number of communicating tubes (4) is at least one.

8. An aircraft wing according to claim 1, characterized in that the return duct (3) is of circular-tube construction.

9. An aircraft wing according to claim 1, characterised in that there is a spacing between the return duct (3) and the bulkhead (1).

10. An aircraft wing according to claim 1, characterised in that the return duct (3) is spaced from the inner wall of the wing.

Images