CN217515375U

CN217515375U - Aircraft wing heating device

Info

Publication number: CN217515375U
Application number: CN202020892005.0U
Authority: CN
Inventors: 王�华; 孙勇
Original assignee: Beijing Jingdong Qianshi Technology Co Ltd
Current assignee: Beijing Jingdong Qianshi Technology Co Ltd
Priority date: 2020-05-25
Filing date: 2020-05-25
Publication date: 2022-09-30
Anticipated expiration: 2030-05-25

Abstract

The embodiment of the utility model provides an aircraft wing heating device, which comprises a wing, a heating device and a heat exchange device; the heating device is fixedly arranged in the wing and is close to the leading edge of the wing; the heat exchange device is fixedly arranged on the airplane body, two ends of the heating device are respectively communicated with two ends of the heat exchange device, and fluid media can circularly flow in the heating device and the heat exchange device. The wing heating device can utilize high-temperature gas discharged by the working of an engine to complete the heating of a fluid medium, so that a stable high-temperature fluid medium can exist in the device, the wing leading edge can be effectively heated, the anti-icing and deicing effects are good, and the wing heating device is suitable for various airplanes.

Description

Aircraft wing heating device

Technical Field

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

Background

At present, unmanned aerial vehicle obtains developing rapidly, when unmanned aerial vehicle flies under wet cold environment, has the aircraft wing risk of freezing, causes the influence to flight safety. Wherein, middle-size and small-size fixed wing unmanned aerial vehicle adopts piston engine as power device, does not generally have anti-icing, defroster, seriously influences its high altitude flight safety.

In the process of implementing the present invention, the inventor finds that there are at least the following problems in the prior art: the airplane adopting the piston engine is limited by power, cannot meet the requirements of electric heating anti-icing and deicing power, and does not have a large-flow high-temperature gas source, thereby causing the problem of no anti-icing and deicing devices.

SUMMERY OF THE UTILITY MODEL

In view of this, the embodiment of the utility model provides an aircraft wing heating device to solve the unmanned aerial vehicle that adopts piston engine among the prior art and receive power limitation, do not prevent and remove the ice device, and the aircraft of deicing is prevented to the mode that adopts the hot gas heating, and its engine can't provide stable large-traffic high temperature air supply, can't guarantee the problem of preventing and removing the ice effect of wing leading edge.

In order to achieve the above object, an embodiment of the present invention provides an aircraft wing heating device, which includes a wing, a heating device and a heat exchange device; the heating device is fixedly arranged in the wing and is close to the leading edge of the wing; the heat exchange device is fixedly arranged on the airplane body, two ends of the heating device are respectively communicated with two ends of the heat exchange device, and fluid media can circularly flow in the heating device and the heat exchange device.

Optionally, the aircraft wing heating device further includes a power device, and the power device is fixedly disposed between the heating device and the heat exchange device.

Optionally, in the above aircraft wing heating device, the heating device includes a flow tube, the flow tube is fixedly disposed in the wing, and the flow tube is close to the leading edge, and two ends of the flow tube are respectively communicated with two ends of the heat exchange device.

Optionally, in the aircraft wing heating device, the flow pipe includes a partition plate, and an inner cavity is formed in the wing body; the baffle is fixedly disposed within the interior chamber to form the flow tube.

Optionally, in the aircraft wing heating device, the heating device further includes a heating pipe; the heating pipe is fixedly arranged in the flow pipe, the heating pipe is communicated with the flow pipe, the first end of the heat exchange device is communicated with the heating pipe, and the second end of the heat exchange device is communicated with the flow pipe.

Optionally, in the aircraft wing heating device, the heating pipe includes an input pipe and an injection pipe; the input pipe and the jet pipe are fixedly arranged in the flow pipe, the input pipe is communicated with the jet pipe, the jet pipe is provided with a jet hole, the jet hole faces the front edge, and the first end of the heat exchange device is communicated with the input pipe.

Optionally, in the aircraft wing heating device, the number of the nozzle holes is multiple, and the plurality of nozzle holes are uniformly formed in the injection pipe.

Optionally, in the aircraft wing heating device, the heating pipe includes a connecting pipe; the connecting pipe is fixedly arranged between the input pipe and the injection pipe.

Optionally, the aircraft wing heating device further includes a pipeline, the heating device is communicated with the heat exchange device through the pipeline, and the pipeline is in a serpentine structure in the heat exchange device.

Optionally, the aircraft wing heating device further includes an engine, and the heat exchange device is fixedly disposed in an exhaust funnel of the engine.

According to the technical scheme of the utility model, an embodiment in the above-mentioned utility model has following advantage or beneficial effect: the heating device is internally provided with a flowing high-temperature medium which can heat the leading edge of the wing to prevent the icing of the leading edge or remove the icing on the leading edge. The temperature of the high-temperature fluid medium is reduced after the front edge is heated, and the fluid medium with lower temperature can flow into the heat exchange device to be heated, so that the fluid medium is ensured to be in a high-temperature state. The wing heating device can utilize high-temperature gas discharged by the working of an engine to complete the heating of fluid medium, so that stable high-temperature fluid medium can exist in the wing heating device, the front edge can be effectively heated, and the anti-icing and deicing effects are good.

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 diagram of an embodiment of the heating device for an aircraft wing according to the present invention;

FIG. 2 is a schematic structural view of a heating device according to an embodiment of the present invention;

FIG. 3 is a schematic structural view of a heat exchange device according to an embodiment of the heating device of an aircraft wing of the present invention;

fig. 4 is a schematic diagram of an embodiment of the heating device of the present invention.

Wherein the figures include the following reference numerals:

1-wing, 100-airplane body, 11-leading edge, 2-heating device, 21-flow pipe, 211-clapboard, 22-heating pipe, 221-input pipe, 222-jet pipe, 2221-jet orifice, 223-connecting pipe, 3-heat exchange device, 4-power device, 5-engine, 6-pipeline.

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 4, an aircraft wing heating device provided by an embodiment of the present invention includes a wing 1, a heating device 2, and a heat exchange device 3; the heating device 2 is fixedly arranged in the wing 1 and is close to the front edge 11 of the wing 1; the heat exchange device 3 is fixedly arranged on the aircraft body 100, two ends of the heating device 2 are respectively communicated with two ends of the heat exchange device 3, and fluid media can circularly flow in the heating device 2 and the heat exchange device 3.

In the above embodiment, the heating device 2 is fixedly arranged in the wing 1, and the heating device 2 has a flowing high-temperature medium therein, which can heat the leading edge 11 of the wing 1 to prevent the icing on the leading edge 11 or remove the icing on the leading edge 11. The heat exchanging device 3 is fixedly installed on the aircraft body 100 and is communicated with the heating device 2, and the heat exchanging device 3 can heat the fluid medium. The temperature of the front edge 11 is reduced after the high-temperature fluid medium heats the front edge, the fluid medium with the lower temperature can flow back to the heat exchange device 3 to be heated so as to ensure that the fluid medium is in a high-temperature state, the heated fluid medium continuously flows into the heating device 2 to heat the front edge 11, and the circulation work is carried out in such a way so as to prevent the front edge 11 from being frozen or remove the front edge 11 from being frozen. The fluid medium may be water or oil, which has a high thermal conductivity. The aircraft wing heating device can store stable high-temperature fluid medium, can effectively heat the leading edge 11, has good anti-icing and deicing effects, and is suitable for various aircrafts.

In order to make the fluid medium circulate more smoothly between the heating device 2 and the heat exchanging device 3, as shown in fig. 1 to 4, in an embodiment of the present invention, the fluid medium further includes a power device 4, and the power device 4 is fixedly disposed between the heating device 2 and the heat exchanging device 3. The power device 4 provides power for the fluid medium to flow circularly, the power device 4 can be fixedly arranged between the outlet of the heat exchange device 3 and the inlet of the heating device 2, and the power device 4 can press the high-temperature fluid medium heated by the heat exchange device 3 into the heating device 2 to heat the front edge 11. Optionally, in an embodiment of the present invention, the power device 4 selects an electric pump, that is, the electric pump is installed on the aircraft body 100 and is communicated between the outlet of the heat exchanging device 3 and the inlet of the heating device 2. The power of the electric pump can be controlled according to the heating requirement on the front edge 11, the temperature of the fluid medium flowing out of the outlet of the heating device 2 after heating the front edge 11 is set to be T2, the temperature of the fluid medium after being heated by the heat exchange device 3 is set to be T1, the control unit can adjust the power of the electric pump according to the numerical requirements on T1 and T2, and when the temperature of T1 is more than 50 ℃ and the temperature of T2 is more than 10 ℃, the power of the electric pump is reduced; increasing the electric pump power when T1<50 ℃ and T2<10 ℃; when the temperature is 90 ℃ to T1 to 50 ℃ and the temperature is T2 to 10 ℃, the power of the electric pump is increased; when T1>90 ℃ and T2<10 ℃, reducing electric pump power; when T1 is greater than 90 deg.C or T2<10 deg.C, an alarm signal is sent, and the problem of the device needs to be checked and maintained. The control unit can adjust the power of the electric pump and give an alarm, and comprises a computer, a controller and the like.

Heating device 2 heats leading edge 11 through the high temperature medium of inside flow, and heating device 2's structural selectivity is many, can be tubular structure or enable other structures that fluid medium flows, as shown in fig. 1 and fig. 2 the utility model discloses an embodiment, heating device 2 includes flow tube 21, and flow tube 21 is fixed to be set up in wing 1, and flow tube 21 is close to leading edge 11, and the both ends of flow tube 21 are linked together with heat transfer device 3's both ends. This allows the flow tube 21 to directly heat the leading edge 11, wherein, in order to save cost, in a preferred embodiment of the present invention, the partition 211 is fixed in the inner cavity formed in the wing 1, so that the partition 211 and the leading edge 11 form the flow tube 21 in front of each other, and thus the fluid medium can flow in the cavity of the wing 1 and directly contact with the leading edge 11 for heating.

In order to improve the heating efficiency of the fluid medium, as shown in fig. 1 to 3, in an embodiment of the present invention, the heating device 2 further includes a heating pipe 22; the heating pipe 22 is fixedly arranged in the flow pipe 21, the heating pipe 22 is communicated with the flow pipe 21, the first end of the heat exchange device 3 is communicated with the heating pipe 22, and the second end of the heat exchange device 3 is communicated with the flow pipe 21. The fluid medium heated by the heat exchanging device 3 directly flows into the heating pipe 22, and the heating pipe 22 can directly act on the leading edge 11 to heat the leading edge 11, so that heat loss caused by heating the part, not the leading edge 11, of the airfoil 1 by the fluid medium is reduced.

In order to allow the fluid medium in the heating tube 22 to act directly on the leading edge 11, as shown in fig. 1 and 2, in one embodiment of the invention, the heating tube 22 comprises an inlet tube 221 and an injection tube 222; the input pipe 221 is communicated with the injection pipe 222, the input pipe 221 and the injection pipe 222 are fixedly arranged in the flow pipe 21, the injection pipe 222 is provided with an injection hole 2221, the injection hole 2221 faces the front edge 11, and the first end of the heat exchange device 3 is communicated with the input pipe 221. The fluid medium heated by heat exchanging device 3 flows into input pipe 221, and then flows into injection pipe 222 through input pipe 221, the fluid medium in injection pipe 222 is sprayed on leading edge 11 through spray holes 2221 to heat leading edge 11, and the fluid medium completing heating leading edge 11 flows back into heat exchanging device 3 through flow pipe 21. In order to heat the front edge 11 uniformly, as shown in fig. 2, the number of the injection holes 2221 is plural, and the plural injection holes 2221 are uniformly provided on the injection pipe 222. In order to ensure that the fluid medium smoothly flows from the input pipe 221 into the injection pipe 222, as shown in fig. 1 and 2, a plurality of connection pipes 223 are provided between the input pipe 221 and the injection pipe 222, and the plurality of connection pipes 223 are fixedly communicated between the input pipe 221 and the injection pipe 222. The inlet pipe 221 and the injection pipe 222 may be fixedly installed in the flow pipe 21 by a fixing bracket, a pipe clamp, or the like.

The fluid medium circulates between the heating device 2 and the heat exchange device 3 through a pipe, for example a metal pipe resistant to high temperatures. Under the prerequisite that can heat fluid medium, heat transfer device 3's structure selectability is very many, as shown in fig. 1 to 4 the utility model discloses an embodiment still includes engine 5, and heat transfer device 3 is fixed to be set up in engine 5's aiutage. The pipeline is heated by high-temperature gas exhausted after the engine works, and then fluid media in the pipeline are heated, the heat exchange device 3 is fixedly arranged in an engine exhaust funnel, the heating efficiency is improved in order to increase the heating area of the pipeline, and the pipeline is of a snake-shaped structure in the heat exchange device 3. In order to save cost and improve heat exchange efficiency, a pipeline can be directly arranged in an exhaust cylinder of an engine 5, namely a heat exchange device 3 is a part of the exhaust cylinder, wherein the outer diameter scale of the exhaust cylinder is a, the diameter b of a coiled pipe, the bending number c of the coiled pipe and the inlet plane angle d of the coiled pipe and the exhaust cylinder are set, and according to calculation, when the ratio b/a of the diameter of the coiled pipe to the outer diameter of the exhaust cylinder is between 0.2 and 0.4, the bending number c is between 3 and 5, and the inlet plane angle d of the coiled pipe and the exhaust cylinder is between 150 degrees and 170 degrees, the performance parameters of the coiled pipe, such as exhaust vibration, heat exchange efficiency, exhaust back pressure loss and the like, are optimal.

The utility model provides a middle-sized unmanned aerial vehicle who uses aviation piston engine as power uses this wing heating device as the example below, explains the utility model provides a use of aircraft wing.

As shown in fig. 1 to 3, when the unmanned aerial vehicle equipped with the heating device flies in a cold and humid environment, a fluid medium flows into the input pipe 221 under the action of the electric pump, then the fluid medium flows into the injection pipe 222 through the connecting pipe 223, and is injected to the leading edge 11 through the injection holes 2221 on the injection pipe 222 to heat the leading edge 11, so as to prevent the leading edge 11 from icing or remove the icing of the leading edge 11, the flushed fluid medium falls into the flow pipe 21, and then flows back into the heat exchange device 3 through the flow pipe 21, i.e., flows into the serpentine pipe in the exhaust pipe of the engine 5, the fluid medium in the serpentine pipe is heated by high-temperature gas discharged from the engine 5, and the heated fluid medium is pressed into the input pipe 221 again by the electric pump, so that the circulation operation is performed, so as to prevent the leading edge 11 from icing or remove the icing of the leading edge 11. The wing heating device completes the heating of the fluid medium by utilizing high-temperature gas discharged by the working of the engine 5, so that the stable high-temperature fluid medium can exist in the wing heating device, the leading edge 11 can be effectively heated, and the anti-icing and deicing effects are good.

Therefore, in the aircraft wing heating device provided by the embodiment of the present invention, the flowing high temperature medium is provided in the heating device 2, and the leading edge 11 of the wing 1 can be heated, so as to prevent the leading edge 11 from icing or remove the icing on the leading edge 11. The temperature of the high-temperature fluid medium is reduced after the front edge 11 is heated, and the fluid medium with a lower temperature can flow back to the heat exchange device 3 to be heated, so that the fluid medium is ensured to be in a high-temperature state. The wing heating device can utilize high-temperature gas discharged by the working of the engine 5 to complete the heating of fluid medium, so that stable high-temperature fluid medium can exist in the device, the front edge 11 can be effectively heated, the anti-icing and deicing effects are good, and the wing heating device is suitable for various airplanes, for example, small and medium-sized unmanned planes provided with aviation piston engines.

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 or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. The aircraft wing heating device is characterized by comprising a wing (1), a heating device (2) and a heat exchange device (3);

the heating device (2) is fixedly arranged in the wing (1) and is close to the front edge (11) of the wing (1); the heating device (2) comprises a flow pipe (21), two ends of the flow pipe (21) are respectively communicated with two ends of the heat exchange device (3), the flow pipe (21) comprises a partition plate (211), an inner cavity is formed in the wing (1) body, and the partition plate (211) is fixedly arranged in the inner cavity to form the flow pipe (21);

the heat exchange device (3) is fixedly arranged on the airplane body (100), two ends of the heating device (2) are respectively communicated with two ends of the heat exchange device (3), and fluid media can circularly flow in the heating device (2) and the heat exchange device (3).

2. An aircraft wing heating device according to claim 1, further comprising a power device (4), the power device (4) being fixedly arranged between the heating device (2) and the heat exchanging device (3).

3. Aircraft wing heating device according to claim 1, characterized in that the flow duct (21) is fixedly arranged in the wing (1) and that the flow duct (21) is close to the leading edge (11).

4. An aircraft wing heating device according to claim 3, characterized in that the heating device (2) further comprises a heating tube (22);

the heating pipe (22) is fixedly arranged in the flow pipe (21), the heating pipe (22) is communicated with the flow pipe (21), the first end of the heat exchange device (3) is communicated with the heating pipe (22), and the second end of the heat exchange device (3) is communicated with the flow pipe (21).

5. Aircraft wing heating device according to claim 4, characterized in that the heating pipe (22) comprises an inlet pipe (221) and an injection pipe (222);

the input pipe (221) is communicated with the injection pipe (222), the input pipe (221) and the injection pipe (222) are fixedly arranged in the flow pipe (21), the injection pipe (222) is provided with a spray hole (2221), the spray hole (2221) faces the front edge (11), and the first end of the heat exchange device (3) is communicated with the input pipe (221).

6. The aircraft wing heating device of claim 5, characterized in that the number of the jet holes (2221) is multiple, and the plurality of jet holes (2221) are uniformly arranged on the jet pipe (222).

7. An aircraft wing heating device according to claim 5, characterized in that the heating tube (22) comprises a connecting tube (223);

the connecting pipe (223) is fixedly arranged between the input pipe (221) and the injection pipe (222).

8. An aircraft wing heating device according to claim 1, further comprising a conduit (6), the heating device (2) and the heat exchange device (3) being in communication via the conduit (6), the conduit (6) being of serpentine configuration within the heat exchange device (3).

9. An aircraft wing heating device according to claim 8, further comprising an engine (5), the heat exchange device (3) being part of an exhaust stack of the engine (5).

10. The aircraft wing heating device according to claim 9, wherein the outer diameter of the exhaust funnel of the engine (5) is a, the diameter of the serpentine pipeline is b, the bending coefficient is c, the included angle between the serpentine pipeline and the inlet plane of the exhaust funnel is d, the value of b/a ranges from 0.2 to 0.4, the value of c ranges from 3 to 5, and the value of d ranges from 150 ° to 170 °.

11. An aircraft wing heating device according to claim 1, further comprising an engine (5), the heat exchange device (3) being fixedly arranged in an exhaust stack of the engine (5).