Heating device for aircraft wing

Abstract

The utility model discloses a heating device for an aircraft wing, and particularly relates to the field of aircraft heaters, which comprises an aircraft wing, a connecting piece fixedly connected to the bottom of the aircraft wing, an engine fixedly connected to the bottom of the connecting piece, a heating ring fixedly mounted on one side of the engine, and a connecting pipe fixedly connected to the outer wall of the heating ring. One end of the connecting pipe is fixedly connected with a water inlet of a circulating water pump, a water outlet of the circulating water pump is fixedly connected with a heating pipe, a protective sleeve is fixedly installed on the outer wall of the circulating water pump and fixedly installed on one side of the connecting piece, and the connecting pipe and the heating pipe are inserted into the protective sleeve. The heating ring and the heating pipe are arranged, waste hot air of an engine can heat liquid through the heating ring, the high-temperature liquid is driven by the circulating water pump to heat the front edge of the aircraft wing through the heating pipe, the front edge of the aircraft wing is prevented from freezing, and the effect of heating the aircraft wing to prevent freezing is achieved.

Description

Technical Field

[0001] The utility model relates to the field of aircraft heaters, and more specifically, to a heating device for aircraft wings. Background Art

[0002] Aircraft heater is a broad concept for aircraft, mainly referring to the heating system on the aircraft, also called the warming system, which plays the role of heating the entire aircraft. Aircraft heater is mainly aimed at low-speed aircraft.

[0003] Chinese utility model CN217515375U discloses an aircraft wing heating device, including a wing, a heating device and a heat exchange device; the heating device is fixedly arranged in the wing and close to the leading edge of the wing; the heat exchange device is fixedly arranged on the aircraft body, and the two ends of the heating device are respectively connected to the two ends of the heat exchange device, and the fluid medium can circulate in the heating device and the heat exchange device. The wing heating device can use the high-temperature gas discharged from the working engine to complete the heating of the fluid medium, so that a stable high-temperature fluid medium can exist in the device, which can effectively heat the leading edge of the wing, has good anti-icing and deicing effects, and is suitable for various types of aircraft.

[0004] However, when this arrangement heats the aircraft wing with liquid, the leading edge will be heated by the liquid directly from the inside of the aircraft wing, which will cause the liquid to affect the internal components of the aircraft wing. To address this problem, it is necessary for technicians in this field to develop a heating device for aircraft wings. Utility Model Content

[0005] In order to overcome the above-mentioned defects of the prior art, an embodiment of the utility model provides a heating device for aircraft wings. By providing a heating ring and a heating pipe, the exhaust heat of the engine will heat the liquid through the heating ring, so that the high-temperature liquid will heat the leading edge of the aircraft wing through the heating pipe under the drive of a circulating water pump to prevent the leading edge of the aircraft wing from freezing, thereby achieving the effect of heating the aircraft wing to prevent freezing, thereby solving the problems raised in the above-mentioned background technology.

[0006] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a heating device for an aircraft wing, comprising an aircraft wing, a connecting piece is fixedly connected to the bottom of the aircraft wing, an engine is fixedly connected to the bottom of the connecting piece, a heating ring is fixedly installed on one side of the engine, a connecting pipe is fixedly connected to the outer wall of the heating ring, one end of the connecting pipe is fixedly connected to the water inlet of a circulating water pump, a heating pipe is fixedly connected to the water outlet of the circulating water pump, a protective cover is fixedly installed on the outer wall of the circulating water pump, the protective cover is fixedly installed on one side of the connecting piece, the connecting pipe and the heating pipe are plugged into the inside of the protective cover, the heating pipe is plugged into the inside of the aircraft wing, and the heating pipe is fixedly connected to the outer wall of the heating ring.

[0007] In a preferred embodiment, a side pipe is fixedly connected to the outer wall of the heating pipe, and one end of the side pipe is fixedly connected to a connection box.

[0008] In a preferred embodiment, the connection box is fixedly installed inside the connection piece and the protective cover, and a sealing piece is slidably connected inside the connection box.

[0009] In a preferred embodiment, a piston member is fixedly connected to the top of the sealing member, and the piston member is inserted into the interior of the connection box.

[0010] In a preferred embodiment, a pressure spring is fixedly mounted on the top of the piston member, and the pressure spring is fixedly mounted inside the connection box.

[0011] In a preferred embodiment, a heat conducting plate is fixedly mounted on one side of the connection box, the heat conducting plate is arranged on one side of the sealing member and the piston member, and a heat dissipation fin is fixedly connected to the outer wall of the heat conducting plate.

[0012] In a preferred embodiment, the outer wall of the heat dissipation fin is provided with a chamfer, and the top of the connection box is provided with an exhaust port.

[0013] Technical effects and advantages of the utility model:

[0014] 1. The utility model is provided with a heating ring and a heating pipe, so that after the engine is working, the waste heat of the engine will heat the liquid through the heating ring, and then the high-temperature liquid will heat the leading edge of the aircraft wing through the heating pipe under the drive of the circulating water pump, so as to prevent the leading edge of the aircraft wing from icing, thereby preventing ice from increasing the resistance of the aircraft, reducing the lift of the aircraft, and reducing the flight control performance, and preventing ice on the aircraft wing from falling off and being drawn into the interior of the engine, causing damage to the internal parts of the engine, so as to achieve the effect of heating the aircraft wing and preventing icing;

[0015] 2. The utility model can reduce the temperature of boiling liquid by arranging heat conduction plates and heat dissipation fins, and prevent the excessive temperature of the liquid from damaging the heating ring, connecting pipe, circulating water pump, and heating pipe, thereby affecting the service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the overall structure of the utility model.

[0017] Figure 2 It is a cross-sectional view of the slide bar structure of the utility model.

[0018] Figure 3 For this utility model Figure 2 A-section structure enlarged view.

[0019] The accompanying drawings are marked as follows: 1. Aircraft wing; 2. Connecting part; 3. Engine; 4. Heating ring; 5. Connecting pipe; 6. Circulating water pump; 7. Heating pipe; 8. Protective cover; 9. Side pipe; 10. Connecting box; 11. Seal; 12. Piston; 13. Pressure spring; 14. Heat conduction plate; 15. Heat dissipation fin; 16. Chamfer; 17. Exhaust port. DETAILED DESCRIPTION

[0020] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0021] Example 1: Refer to the attached specification Figure 1-3 The utility model is a heating device for an aircraft wing, comprising an aircraft wing 1, see Figure 1 The bottom of the aircraft wing 1 is fixedly connected with a connecting piece 2, the bottom of the connecting piece 2 is fixedly connected with an engine 3, and a heating ring 4 is fixedly installed on one side of the engine 3, see Figure 3 The outer wall of the heating ring 4 is fixedly connected with a connecting pipe 5, one end of the connecting pipe 5 is fixedly connected with a water inlet of a circulating water pump 6, the water outlet of the circulating water pump 6 is fixedly connected with a heating pipe 7, the outer wall of the circulating water pump 6 is fixedly installed with a protective cover 8, the protective cover 8 is fixedly installed on one side of the connecting piece 2, the connecting pipe 5 and the heating pipe 7 are plugged into the inside of the protective cover 8, the heating pipe 7 is plugged into the inside of the aircraft wing 1, and the heating pipe 7 is fixedly connected to the outer wall of the heating ring 4;

[0022] The outer wall of the heating pipe 7 is fixedly connected to a side pipe 9, one end of the side pipe 9 is fixedly connected to a connection box 10, the connection box 10 is fixedly installed inside the connecting piece 2 and the protective cover 8, the inside of the connection box 10 is slidably connected to a seal 11, the top of the seal 11 is fixedly connected to a piston 12, the piston 12 is inserted into the inside of the connection box 10, the top of the piston 12 is fixedly installed with a pressure spring 13, the pressure spring 13 is fixedly installed inside the connection box 10, a heat conducting plate 14 is fixedly installed on one side of the connection box 10, the heat conducting plate 14 is arranged on one side of the seal 11 and the piston 12, the outer wall of the heat conducting plate 14 is fixedly connected to a heat dissipation fin 15, the outer wall of the heat dissipation fin 15 is provided with a chamfer 16, and the top of the connection box 10 is provided with an exhaust port 17.

[0023] It should be noted that, when the aircraft starts the engine 3, the engine 3 will work to generate a large amount of hot exhaust gas discharged from the tail, and the discharged hot exhaust gas will heat the heating ring 4, so that the liquid inside the heating ring 4 is heated, and then the staff can start the circulating water pump 6. The operation of the circulating water pump 6 will drive the liquid inside the heating ring 4, the connecting pipe 5, and the heating pipe 7 to circulate. At this time, the heated liquid inside the heating ring 4 will circulate into the interior of the heating pipe 7 through the connecting pipe 5 and the circulating water pump 6, so that the high-temperature liquid heats the leading edge of the aircraft wing 1 from the inside through the heating pipe 7, so as to prevent the leading edge of the aircraft wing 1 from condensing. Ice or melt the ice that has already formed on the leading edge of the aircraft wing 1 to prevent the ice from increasing the resistance of the aircraft, reducing the lift of the aircraft, and reducing the flight control performance, and to prevent the ice on the aircraft wing 1 from falling off and being drawn into the interior of the engine 3 to damage the internal parts of the engine 3. After the high-temperature liquid heats the leading edge of the aircraft wing 1 through the heating pipe 7, its own heat decreases, and then it continues to slide along the inside of the heating pipe 7 and is discharged into the inside of the heating ring 4 to be heated again. Driven by the circulating water pump 6, it continues to circulate to heat the leading edge of the aircraft wing 1, so as to achieve the effect of heating the aircraft wing 1 and preventing ice from forming;

[0024] Furthermore, when the leading edge temperature of the aircraft wing 1 is heated to a normal level and no longer freezes, the liquid heated to a high temperature will begin to boil, increasing the pressure inside the heating ring 4, the connecting pipe 5, the circulating water pump 6, and the heating pipe 7, thereby causing the liquid to be discharged into the interior of the connecting box 10 through the side pipe 9 and pushing the seal 11 and the piston 12 to slide up along the interior of the connecting box 10 and squeeze the pressure spring 13 to contract, allowing the heat conducting plate 14 blocked by the seal 11 to contact the liquid. At this time, the heat in the liquid is absorbed by the heat conducting plate 14 and transferred to the cooling fins 15, so that the external wind force quickly carries the heat on the cooling fins 15, thereby reducing the temperature of the liquid, preventing the liquid from boiling due to excessive temperature and causing damage to the heating ring 4, the connecting pipe 5, the circulating water pump 6, and the heating pipe 7, thereby affecting the service life. When the temperature of the liquid returns to normal, the pressure spring 13 will push the piston 12 and the seal 11 to reset, so that the seal 11 will discharge the liquid back into the heating ring 4, the connecting pipe 5, the circulating water pump 6, and the heating pipe 7.

[0025] Finally, a few points should be explained: First, in the description of this application, it should be noted that, unless otherwise specified and limited, the terms "installed", "connected" and "connected" should be understood in a broad sense, which can be a mechanical connection or an electrical connection, or the internal communication of two components, or a direct connection. "upper", "lower", "left" and "right" are only used to indicate relative positional relationships. When the absolute position of the object being described changes, the relative positional relationship may change;

[0026] Secondly: In the drawings of the embodiments disclosed in the present utility model, only the structures related to the embodiments disclosed in the present utility model are involved, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present utility model can be combined with each other;

[0027] Finally: The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present utility model should be included in the protection scope of the present utility model.

Claims

1. A heating device for an aircraft wing, comprising an aircraft wing (1), characterized in that: The bottom of the aircraft wing (1) is fixedly connected to a connecting piece (2), the bottom of the connecting piece (2) is fixedly connected to an engine (3), a heating ring (4) is fixedly mounted on one side of the engine (3), a connecting pipe (5) is fixedly connected to the outer wall of the heating ring (4), one end of the connecting pipe (5) is fixedly connected to the water inlet of a circulating water pump (6), the water outlet of the circulating water pump (6) is fixedly connected to a heating pipe (7), a protective sleeve (8) is fixedly mounted on the outer wall of the circulating water pump (6), the protective sleeve (8) is fixedly mounted on one side of the connecting piece (2), the connecting pipe (5) and the heating pipe (7) are plugged into the inside of the protective sleeve (8), the heating pipe (7) is plugged into the inside of the aircraft wing (1), and the heating pipe (7) is fixedly connected to the outer wall of the heating ring (4).

2. The aircraft wing heating device according to claim 1, characterized in that: The outer wall of the heating pipe (7) is fixedly connected to a side pipe (9), and one end of the side pipe (9) is fixedly connected to a connection box (10).

3. The aircraft wing heating device according to claim 2, characterized in that: The connection box (10) is fixedly installed inside the connection piece (2) and the protective cover (8), and a sealing piece (11) is slidably connected inside the connection box (10).

4. The aircraft wing heating device according to claim 3, characterized in that: The top of the sealing member (11) is fixedly connected to a piston member (12), and the piston member (12) is inserted into the interior of the connection box (10).

5. The aircraft wing heating device according to claim 4, characterized in that: A pressure spring (13) is fixedly mounted on the top of the piston member (12), and the pressure spring (13) is fixedly mounted inside the connection box (10).

6. The aircraft wing heating device according to claim 5, characterized in that: A heat conducting plate (14) is fixedly mounted on one side of the connection box (10), the heat conducting plate (14) is arranged on one side of the sealing member (11) and the piston member (12), and a heat dissipation fin (15) is fixedly connected to the outer wall of the heat conducting plate (14).

7. The aircraft wing heating device according to claim 6, characterized in that: The outer wall of the heat dissipation fin (15) is provided with a chamfer (16), and the top of the connection box (10) is provided with an exhaust port (17).

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