Aircraft deicing device
By adopting a combination design of an enclosing shell, an electric heating component and a hot air component on the edge of the aircraft flap, the problems of sealing and uneven heat conduction of the flap de-icing device are solved, and a fast and uniform de-icing effect is achieved.
Patent Information
- Application Number
- CN202422746648.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-11
- Publication Date
- 2025-09-19
- Estimated Expiration
- 2034-11-11
AI Technical Summary
Existing aircraft flap de-icing devices have problems such as difficulty in ensuring the sealing of chemical anti-icing devices and uneven heat conduction of heating anti-icing devices, resulting in incomplete de-icing or local overheating.
It adopts a combined design of an enclosing shell, electric heating components and hot air components, uses thermal adhesive and thermal wire to conduct heat at the edge of the flap, and combines with the hot air component of the guide fan to ensure even heat distribution.
It achieves rapid and uniform heating of the flap edge, improves de-icing efficiency, avoids local overheating and incomplete de-icing, and ensures the normal movement of the flap.
Smart Images
Figure CN223355902U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aircraft, in particular to an aircraft deicing device. Background Art
[0002] During winter operations, cold weather and rainy and snowy weather can cause ice to form on the aircraft surface, which is a major hidden danger to flight safety. Ice and snow attached to the aircraft surface will directly affect the aircraft's aerodynamic performance, such as lift reduction, stall angle of attack changes, etc. In severe cases, it may even lead to tragic aircraft crashes and casualties. Therefore, in order to ensure flight safety, de-icing operations must be carried out before the aircraft takes off.
[0003] Winter cold waves often bring strong winds, cooling temperatures, rain and snow, which provide the necessary environment for aircraft icing. When an aircraft is parked in a cold and humid environment, frost, snow or ice is easily formed on the surface of the aircraft. These ice and snow attachments not only increase the weight and resistance of the aircraft, but also damage the smooth appearance of the aircraft.
[0004] In response to the problem of aircraft icing, the aviation industry has continuously developed a variety of de-icing devices and technologies; these devices can be roughly divided into three categories: heating anti-icing devices, chemical anti-icing devices and mechanical de-icing devices; heating anti-icing devices use a heating system to raise the surface temperature of ice-prone parts of the aircraft to above 0 degrees to prevent ice accumulation; chemical anti-icing devices spray antifreeze to lower the freezing temperature of water droplets to avoid ice accumulation; mechanical de-icing devices use mechanical methods to remove ice from the aircraft surface.
[0005] Flaps specifically refer to a type of wing-shaped movable device on the edge of a modern wing. Flaps can be installed on the trailing or leading edge of the wing and can be deflected downward or slid forward and backward. Their basic function is to increase lift during flight. The structure of flaps is relatively thin, making chemical anti-icing devices difficult to install and ensuring structural sealing. Some heated anti-icing devices have poor heat conduction uniformity, which can easily lead to local overheating or incomplete de-icing. Therefore, a new aircraft de-icing device is now provided to address the above problems. Utility Model Content
[0006] The purpose of the present utility model is to provide an aircraft de-icing device that can solve the problems raised by the above-mentioned background technology.
[0007] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: an aircraft de-icing device, comprising an enclosing shell, an electric heating component and a hot air component, the enclosing shell being a frame structure with a V-shaped cross-section, the V-shaped opening on the enclosing shell facing outward, the enclosing shell being fit with the inner side of the aircraft flap, the electric heating component being arranged inside the enclosing shell and being used to perform electric heating treatment on the edge of the aircraft flap, the hot air component being arranged on the inner side of the enclosing shell and cooperating with the electric heating component to heat the surface of the aircraft flap.
[0008] Preferably, the electric heating component includes an electric heating wire and thermally conductive adhesive. The interior of the surrounding shell is provided with an electric heating wire that coincides with the axis of the surrounding shell. The cavity formed after the surrounding shell is docked with the inner edge of the aircraft flap is filled with thermally conductive adhesive, which surrounds the electric heating wire.
[0009] Preferably, the electric heating component further includes a glue injection nozzle and a sealing cover. The glue injection nozzle communicating with the interior of the surrounding shell is integrally provided on the outer wall of the surrounding shell, and a sealing cover is detachably installed at the port of the glue injection nozzle away from the surrounding shell to seal it.
[0010] Preferably, the hot air assembly includes a mounting seat and a guide fan, and multiple groups of mounting seats distributed horizontally are installed at the inner edge of the surrounding shell. The mounting seats are installed in an array, and a guide fan with the output end facing the inner side of the surrounding shell is installed in the mounting seat.
[0011] Preferably, multiple groups of heat conducting wires are connected between the inner and outer walls of the surrounding shell, and the multiple groups of heat conducting wires are staggered with the multiple groups of hot air components; both ends of the heat conducting wires extend to the interior of the surrounding shell and can be in contact with the thermal conductive glue.
[0012] Compared with the prior art, the beneficial effects of the present invention are as follows: the aircraft de-icing device uses a highly conductive thermal adhesive as a heat-conducting medium between the heating wire and the edge of the flap, which can ensure that the heat generated by heating can be quickly and evenly conducted to the edge of the flap, thereby improving the de-icing efficiency. In addition, the setting of the hot air component and the thermal wire can improve the uniformity of heat conduction for the relatively thin structure of the flap, thereby preventing local overheating or incomplete de-icing; considering the complexity of the trailing edge structure, the device is cleverly integrated into the internal structure of the flap to avoid affecting the normal movement of the flap. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] The present invention will be further described below with reference to the accompanying drawings and embodiments:
[0014] Figure 1 It is a three-dimensional diagram of the utility model;
[0015] Figure 2 It is a top view of the utility model;
[0016] Figure 3 It is the AA cross-sectional view of the present utility model;
[0017] Figure 4 This is an enlarged view of part A of the present utility model;
[0018] Figure 5 This is an enlarged view of part B of the present invention.
[0019] Figure numerals: 1. surrounding shell; 2. electric heating component; 21. electric heating wire; 22. thermal adhesive; 23. adhesive injection nozzle; 24. sealing cover; 3. hot air component; 31. mounting seat; 32. guide fan; 4. thermal wire;. DETAILED DESCRIPTION
[0020] In the description of the present invention, it should be understood that descriptions involving orientations, such as up, down, front, back, left, right, etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as limitations on the present invention.
[0021] See also Figure 1-5 The utility model provides a technical solution: an aircraft de-icing device, comprising an enclosure 1, an electric heating component 2 and a hot air component 3. The enclosure 1 is a frame structure with a V-shaped cross section. The V-shaped opening on the enclosure 1 faces outward and is installed in the aircraft flap. The enclosure 1 can fit the inner side of the aircraft flap. The electric heating component 2 is arranged inside the enclosure 1 and is used to perform electric heating treatment on the edge of the aircraft flap. The hot air component 3 is arranged on the inner side of the enclosure 1 and cooperates with the electric heating component 2 to heat the surface of the aircraft flap. The electric heating component 2 includes a heating wire 21 and a heat-conducting adhesive 22. The interior of the enclosure 1 is provided with a heating wire 21 that coincides with the axis of the enclosure 1. The enclosure 1 and the aircraft flap are in close contact. The cavity formed after the inner edges are connected is filled with thermally conductive glue 22, which surrounds the heating wire 21. The electric heating component 2 also includes a glue injection nozzle 23 and a sealing cover 24. The outer wall of the surrounding shell 1 is integrally provided with a glue injection nozzle 23 that is connected to the interior of the surrounding shell 1. It is used to fill the cavity formed after the surrounding shell 1 is connected to the inner edge of the aircraft flap with thermally conductive glue 22. The glue injection nozzle 23 is detachably installed with a sealing cover 24 that seals it away from the port of the surrounding shell 1. Between the heating wire 21 and the flap edge, a highly thermally conductive glue 22 is used as a heat conduction medium to ensure that the heat generated by the heating can be quickly and evenly transferred to the flap edge, thereby improving the de-icing efficiency.
[0022] Secondly, the hot air component 3 includes a mounting seat 31 and a guide fan 32. A plurality of horizontally distributed mounting seats 31 are installed at the inner edge of the surrounding shell 1. The mounting seats 31 are installed in an array. A guide fan 32 with the output end facing the inner side of the surrounding shell 1 is installed in the mounting seat 31. A plurality of groups of thermal wires 4 are connected between the inner and outer walls of the surrounding shell 1. The plurality of groups of thermal wires 4 are staggered with the plurality of groups of hot air components 3 and the thermal wires 4 can be fitted with the inner surface of the aircraft flap; both ends of the thermal wires 4 extend to the interior of the surrounding shell 1 and can contact the thermal adhesive 22. In addition, the arrangement of the hot air component 3 and the thermal wires 4 can improve the uniformity of heat conduction for a relatively thin structure such as the flap, and prevent local overheating or incomplete de-icing.
[0023] The embodiments of the present invention are described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Various changes can be made within the scope of knowledge possessed by ordinary technicians in the technical field without departing from the purpose of the present invention.
Claims
1. An aircraft de-icing device, characterized in that: include: The enclosing shell (1), the electric heating component (2) and the hot air component (3) are provided. The enclosing shell (1) is a frame structure with a V-shaped cross section. The V-shaped opening on the enclosing shell (1) faces outward. The enclosing shell (1) can be fitted with the inner side of an aircraft flap. The electric heating component (2) is arranged inside the enclosing shell (1) and is used to perform electric heating treatment on the edge of the aircraft flap. The hot air component (3) is arranged on the inner side of the enclosing shell (1) and cooperates with the electric heating component (2) to perform heating treatment on the surface of the aircraft flap.
2. The aircraft de-icing device according to claim 1, characterized in that: The electric heating component (2) includes an electric heating wire (21) and a heat-conducting adhesive (22). The interior of the surrounding shell (1) is provided with the electric heating wire (21) which coincides with the axis of the surrounding shell (1). The cavity formed after the surrounding shell (1) is connected to the inner edge of the aircraft flap is filled with the heat-conducting adhesive (22), and the heat-conducting adhesive (22) surrounds the electric heating wire (21).
3. The aircraft de-icing device according to claim 2, characterized in that: The electric heating component (2) further comprises a glue injection nozzle (23) and a sealing cover (24); the glue injection nozzle (23) communicating with the interior of the surrounding shell (1) is integrally formed on the outer wall of the surrounding shell (1); and the sealing cover (24) for sealing the glue injection nozzle (23) is detachably mounted at the port away from the surrounding shell (1).
4. The aircraft de-icing device according to claim 3, characterized in that: The hot air assembly (3) comprises a mounting seat (31) and a guide fan (32); a plurality of horizontally distributed mounting seats (31) are mounted on the inner edge of the surrounding shell (1); the mounting seats (31) are arranged in an array; and a guide fan (32) is mounted in the mounting seat (31) with its output end facing the inner side of the surrounding shell (1).
5. The aircraft de-icing device according to claim 4, characterized in that: Multiple groups of heat-conducting wires (4) are connected between the inner and outer walls of the surrounding shell (1); the multiple groups of heat-conducting wires (4) and the multiple groups of hot air components (3) are staggered and distributed; and the heat-conducting wires (4) can be fitted with the inner surface of the aircraft flap.
6. The aircraft de-icing device according to claim 5, characterized in that: Both ends of the heat-conducting wire (4) extend to the interior of the surrounding shell (1) and can be in contact with the heat-conducting glue (22).