Aircraft wing with deicing function and deicing method thereof

Abstract

The invention relates to the technical field of aviation, in particular to an aircraft wing with a deicing function and a deicing method thereof, and the aircraft wing comprises a wing assembly, a cam and a driving assembly; the wing assembly comprises a first wing, a second wing and a rotating shaft assembly, the rotating shaft assembly is connected with the first wing and the second wing, the driving assembly is connected with the second wing, and the output end of the driving assembly is connected with the cam; a cam groove is formed in the first wing, and the cam is arranged in the cam groove; when the driving assembly drives the cam to rotate in the cam groove, the first wing moves around the rotating shaft assembly, so that an ice layer on the wing assembly is removed. The unmanned aerial vehicle has the advantages that the cam is driven by the driving assembly, so that the first wing generates fluctuating vibration, and shearing force and vibration force generated by the vibration can rapidly break an ice layer attached to the wing assembly.

Description

Technical Field

[0001] The present invention relates to the field of aviation technology, and in particular to an aircraft wing with a deicing function and a deicing method thereof. Background Art

[0002] When an aircraft is flying, it will use wings with airfoil characteristics. The shape of the wing will directly affect the aerodynamic characteristics of the aircraft. At high altitudes, due to the low temperature and the frequent passage through cold clouds or humid areas, the wing surface will ice up. After ice forms, it will destroy the aerodynamic characteristics of the aircraft, reduce the performance of the aircraft, increase the resistance of the aircraft, and lead to increased fuel consumption. In severe cases, the lift of the aircraft will be insufficient to support its weight. At this time, the aircraft will stall, leading to serious consequences. Therefore, it is necessary to de-ice the wing surface in time during flight.

[0003] The Chinese patent publication number is CN112550665A, the publication date is March 26, 2021, and the patent name is "An aircraft deicing device with elastic skin". It discloses that the ice layer on the wing surface can be removed during flight. However, due to the elastic skin, the wing airfoil will change and then recover after deicing. The characteristics of the wing airfoil will inevitably be deformed, and the surface roughness of the elastic skin is also different from that of conventional aircraft skin, which will increase resistance.

[0004] The Chinese patent publication number is CN111731485A, the publication date is October 2, 2020, and the patent name is "An autonomous intermittent deicing device, its installation method and deicing method". It discloses an autonomous intermittent deicing device, which mainly relies on electric heating to heat the contact surface to melt the ice layer to achieve the deicing effect. The device can complete the deicing task without changing the aircraft's wing shape, but as far as aircraft are concerned, this high-power, surface heating method will undoubtedly increase the energy consumption of the aircraft, thereby reducing the aircraft's flight time and shortening the range. Summary of the invention

[0005] In view of this, the present invention aims to provide an aircraft wing with deicing function and a deicing method thereof, wherein a driving assembly drives a cam to drive a first wing to move around a rotation axis, thereby ensuring that the aircraft can be effectively de-iced in an icing state.

[0006] To achieve the above object, the technical solution of the present invention is achieved as follows: An aircraft wing with a de-icing function comprises a wing assembly, a cam and a driving assembly; the wing assembly comprises a first wing, a second wing and a rotating shaft assembly, the rotating shaft assembly connects the first wing and the second wing, the driving assembly is connected to the second wing, and the output end of the driving assembly is connected to the cam; a cam groove is provided in the first wing, and the cam is arranged in the cam groove; when the driving assembly drives the cam to rotate in the cam groove, the first wing moves around the rotating shaft assembly, thereby removing the ice layer on the wing assembly.

[0007] Furthermore, the first wing includes a first comb tooth group and a connecting rod, and the second wing includes a second comb tooth group; when the first wing is connected to the second wing, the first comb tooth group and the second comb tooth group are arranged crosswise and spaced apart, and the connecting rod connects each first comb tooth in the first comb tooth group into an integral structure to form the first wing, so that the first wing can move around the rotating shaft assembly; each first comb tooth is provided with a connecting hole and a first rotating shaft hole; the first comb teeth at both ends of the first comb tooth group are also provided with fixing holes, the connecting rod is connected to each first comb tooth through the connecting hole, and the first screw fixes the first wing to the connecting rod through the fixing hole.

[0008] Further, the cam groove is arranged inside the first comb tooth in the first comb tooth group adjacent to the second wing input end.

[0009] Furthermore, the cam groove includes a first cavity and a second cavity; when the cam is located in the second cavity, the driving assembly drives the cam to move the first wing around the rotating shaft assembly; when the cam is located in the first cavity, the first wing is located at an initial position and locked with the second wing.

[0010] Furthermore, the second wing is a comb-shaped structure, including a comb handle and a second comb tooth group, and each second comb tooth in the second comb tooth group is evenly arranged on the comb handle.

[0011] Furthermore, a limiting hole and a second rotating shaft hole are provided on each second comb tooth in the second comb tooth group; wherein, the limiting hole corresponds to the connecting hole on the first comb tooth and is used to limit the first wing; the second rotating shaft hole corresponds to the first rotating shaft hole on the first comb tooth; the rotating shaft assembly passes through the first rotating shaft hole and the second rotating shaft hole in sequence to connect the first wing with the second wing.

[0012] Furthermore, a threaded hole is provided on the second comb tooth located in the middle of the second comb tooth group, a spring is provided in the threaded hole, and the spring is connected to the connecting rod.

[0013] Furthermore, the driving assembly includes a motor and a telescopic mechanism, the fixed end of the telescopic mechanism is connected to the second wing, the output end of the telescopic mechanism is connected to the motor, the output end of the motor is connected to the cam, and the telescopic mechanism drives the cam to move in the cam groove through the motor.

[0014] Furthermore, the rotating shaft assembly includes a rotating shaft and a bearing. The rotating shaft passes through the first wing and the second wing in sequence. Both ends of the rotating shaft are fixed to both ends of the bearing wing assembly.

[0015] A deicing method for an aircraft wing is implemented based on the above-mentioned aircraft wing with deicing function, and the specific steps are as follows: S1: When the wing of the aircraft needs to be de-iced, the telescopic mechanism of the drive assembly drives the cam to move into the second cavity of the cam groove through the motor of the drive assembly.

[0016] S2: Start the motor to drive the cam to rotate and then drive the first wing to reciprocate up and down around the rotating shaft assembly along the limiting hole of each second comb tooth in the second comb tooth group, forming low-frequency vibration. The shear force generated by the low-frequency vibration breaks the ice layer; the up and down reciprocating motion of the first wing causes the ice layer on the wing assembly to separate from the wing assembly; then, the aerodynamic force generated by the aircraft during flight blows away the broken ice flakes.

[0017] S3: When de-icing is completed, the motor stops working; at this time, the spring connected to the connecting rod of the first wing drives the connecting rod to reset by its own elastic force, thereby returning the first wing to its initial position.

[0018] S4: The telescopic mechanism drives the motor again, driving the cam back to the cam groove; at this time, part of the motor is located in the first motor groove inside the first comb tooth of the first wing, and the other part is located in the second motor groove of the second comb tooth at the input end of the second wing, so that the wing assembly is in a locked state.

[0019] Compared with the prior art, the present invention can achieve the following beneficial effects: The cam is driven by the driving assembly to make the first wing vibrate. The shear force and vibration force generated by this vibration can quickly break the ice frozen on the wing assembly. Then, the broken ice flakes are blown away by the aerodynamic force generated by the aircraft during flight, which not only saves more energy, but also does not need to change the aerodynamic airfoil and consider the problems caused by the change of airfoil. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 is a schematic structural diagram of an aircraft wing with a deicing function provided according to an embodiment of the present invention; Figure 2 is a structural schematic diagram of an aircraft wing with a deicing function according to a first perspective provided by an embodiment of the present invention; Figure 3 According to an embodiment of the present invention, Figure 2 Sectional view obtained along AA; Figure 4 is a schematic structural diagram of a first wing provided according to an embodiment of the present invention; Figure 5 is a structural schematic diagram of a first wing from a first perspective provided by an embodiment of the present invention; Figure 6 According to an embodiment of the present invention, Figure 5 The cross-sectional view obtained along BB; Figure 7 is a schematic structural diagram of a second wing provided according to an embodiment of the present invention; Figure 8 is a schematic structural diagram of a cam and a driving assembly provided according to an embodiment of the present invention.

[0021] The reference numerals include: 1. wing assembly; 11. first wing; 111. cam groove; 112. first comb tooth group; 113. connecting rod; 114. connecting hole; 115. first rotating shaft hole; 116. fixing hole; 117. first cavity; 118. second cavity; 119. first motor groove; 12. second wing; 121. comb handle; 122. second comb tooth group; 123. limiting hole; 124. second rotating shaft hole; 125. second motor groove; 126. threaded hole; 13. rotating shaft assembly; 131. rotating shaft; 132. bearing; 2. cam; 3. driving assembly; 31. motor; 32. telescopic mechanism; 321. telescopic servo; 322. connecting flange; 323. servo fixing piece; 4. spring. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation of the present invention.

[0023] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0024] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0025] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0026] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0027] like Figure 1-Figure 3 As shown, an aircraft wing with deicing function provided by an embodiment of the present invention comprises a wing assembly 1, a cam 2 and a drive assembly 3. The wing assembly 1 comprises a first wing 11, a second wing 12 and a rotating shaft assembly 13, the rotating shaft assembly 13 connects the first wing 11 and the second wing 12, the drive assembly 3 is connected to the second wing 12, and the output end of the drive assembly 3 is connected to the cam 2. A cam groove 111 is provided in the first wing 11, and the cam 2 is arranged in the cam groove 111.

[0028] In this embodiment, the end of the second wing 12 connected to the driving assembly 3 is defined as the input end, and after the first wing 11 is connected to the second wing 12, the end of the first wing 11 away from the input end is defined as the free end.

[0029] like Figure 4-Figure 6As shown, the first wing 11 includes a first comb tooth group and a connecting rod 113, and each first comb tooth 112 in the first comb tooth group is provided with a connecting hole 114 and a first shaft hole 115. The first comb teeth at both ends of the first comb tooth group 112 are also provided with fixing holes 116. The first comb teeth adjacent to the input end of the second wing 12 in the first comb tooth group 112 are also provided with a cam groove 111 and a first motor groove 119. The cam groove 111 includes a first cavity 117 and a second cavity 118.

[0030] The second wing 12 is a comb-shaped structure, and its structure is as follows Figure 7 As shown, it includes a comb handle 121 and a second comb tooth group 122, and each second comb tooth in the second comb tooth group 122 is evenly arranged on the comb handle 121. Each second comb tooth in the second comb tooth group 122 is provided with a limiting hole 123 and a second shaft hole 124, and the limiting hole 123 is used to limit the first wing 11. A second motor slot 125 is also provided on the second comb tooth located at the input end of the second wing 12. A threaded hole 126 is also provided on the second comb tooth located in the middle position of the second comb tooth group 122, and the spring 4 is located in the threaded hole 126 and connected to the connecting rod 113. The second screw is screwed with the threaded hole 126, which not only limits the position of the spring 4, but also ensures that the spring 4 will not move out of the threaded hole 126 when subjected to force.

[0031] In this embodiment, the first wing 11 and the second wing 12 are both made of hard skin, and their outer contours are streamlined. The first comb tooth group 112 includes five first comb teeth, and the second comb tooth group 122 includes five second comb teeth. The spring 4 is a compression spring, the limiting hole 123 is an elongated hole, the first motor slot 119 can be round or square, and the second motor slot 125 can be a square hole or a round hole.

[0032] The rotating shaft assembly 13 includes a rotating shaft 131 and two bearings 132. One end of the rotating shaft 131 is fixed to the input end of the second wing 12 through the bearing 132, and the other end of the rotating shaft 131 is fixed to the free end of the first wing 11 through the bearing 132. The width of the first comb teeth and the second comb teeth is 50 mm.

[0033] In other embodiments, the width of the first comb teeth and the second comb teeth is greater than or equal to 30 mm and less than or equal to 100 mm. The number of the first comb teeth and the second comb teeth is increased or decreased according to the actual required span of the wing assembly 1.

[0034] The structure of the drive assembly 3 is as follows: Figure 8As shown, the telescopic mechanism 32 includes a motor 31 and a telescopic mechanism 32, wherein the telescopic mechanism 32 includes a telescopic steering gear 321, a connecting flange 322 and a steering gear fixing member 323, wherein the fixed end of the telescopic steering gear 321 is connected to the steering gear fixing member 323, and the steering gear fixing member 323 is fixed to the input end of the second wing 12. The output end of the telescopic steering gear 321 is connected to one end of the connecting flange 322, and the other end of the connecting flange 322 is connected to the fixed end of the motor 31.

[0035] The assembly process of the aircraft wing with deicing function is described in conjunction with the accompanying drawings: First, the first comb tooth group 112 of the first wing 11 and the second comb tooth group 122 of the second wing 12 are arranged in a cross-spaced manner, so that the second rotating shaft hole 124 of the second comb tooth group 122 corresponds to the first rotating shaft hole 115 on the first comb tooth group 112, and the limiting hole 123 of the second comb tooth group 122 corresponds to the connecting hole 114 on the first comb tooth group 112. Subsequently, the rotating shaft assembly 13 is passed through the second rotating shaft hole 124 and the first rotating shaft hole 115 in sequence. One end of the rotating shaft 131 is fixed to the input end of the second wing 12 through the bearing 132, and the other end of the rotating shaft 131 is fixed to the free end of the first wing 11 through the bearing 132.

[0036] Next, glue is evenly applied to the inner surface of the connection hole 114 of the first comb tooth group 112, and then the connection rod 113 is passed through the second comb teeth and the first comb teeth in sequence, and glued to the first comb tooth group 112, and then the first screw is used to fix the first comb tooth group 112 and the connection rod 113 through the fixing hole 116, so that the first wing 11 can move up and down around the rotation axis 131 along the limiting hole 123. The fixing hole 116 is a threaded hole, and the first screw is screwed to the fixing hole 116 so that the first screw is pressed against the surface of the connection rod 113 to fix the connection rod 113.

[0037] Next, the cam 2 is connected to the output end of the motor 31 of the driving assembly 3. Subsequently, the cam 2 is sent into the first cavity 117 of the cam slot 111 along the second motor slot 125 and the first motor slot 119, and the motor 31 is located in the second motor slot 125 and the first motor slot 119. After that, the steering gear fixing member 323 of the driving assembly 3 is fixed to the input end of the second wing 12.

[0038] Finally, the spring 4 is placed in the threaded hole 126 and connected to the connecting rod 113. A second screw is used to screw with the threaded hole 126 to complete the assembly of the aircraft wing.

[0039] The deicing method for the wing of an aircraft with deicing function is described in conjunction with the accompanying drawings. S1: When the aircraft wing needs to be de-iced, the telescopic mechanism 32 drives the cam 2 to move into the second cavity 118 of the cam groove 111 through the motor 31 .

[0040] S2: Start the motor 31, drive the cam 2 to rotate, and then drive the first wing 11 to reciprocate up and down around the rotation axis 131 along the limit hole 123, forming low-frequency vibration. The shear force generated by the low-frequency vibration breaks the ice layer. The up and down reciprocating motion of the first wing 11 causes the ice layer on the wing assembly 1 to separate from the wing assembly 1. Subsequently, the aerodynamic force generated by the aircraft during flight blows away the broken ice pieces.

[0041] S3: When deicing is completed, the motor 31 stops working. At this time, the spring 4 uses its own elastic force to drive the connecting rod 113 to return to its original position, thereby returning the first wing 11 to its initial position.

[0042] S4: The telescopic mechanism 32 drives the motor 31 again, driving the cam 2 back to the first cavity 117 of the cam slot 111. At this time, a part of the motor 31 is located in the first motor slot 119, and the other part is located in the second motor slot 125, so that the wing assembly 1 is in a locked state.

[0043] In this embodiment, when the first wing 11 and the second wing 12 are in a locked state, the position of the first wing 11 is defined as an initial position.

[0044] The above specific implementations do not constitute a limitation on the protection scope of the present invention. It should be understood by those skilled in the art that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft wing with deicing function, characterized in that: Includes a wing assembly, a cam, and a drive assembly; The wing assembly comprises a first wing, a second wing and a rotating shaft assembly, the rotating shaft assembly connects the first wing and the second wing, the driving assembly is connected to the second wing, and the output end of the driving assembly is connected to the cam; A cam groove is provided in the first wing, and the cam is arranged in the cam groove; When the driving assembly drives the cam to rotate in the cam groove, the first wing moves around the rotating shaft assembly, thereby removing the ice layer on the wing assembly.

2. The aircraft wing with deicing function according to claim 1, characterized in that: The first wing includes a first comb tooth group and a connecting rod; the second wing includes a second comb tooth group; when the first wing is connected to the second wing, the first comb tooth group and the second comb tooth group are arranged crosswise and at intervals, and the connecting rod connects each first comb tooth in the first comb tooth group into an integral structure to form the first wing, so that the first wing can move around the rotating shaft assembly; each of the first comb teeth is provided with a connecting hole and a first rotating shaft hole; the first comb teeth at both ends of the first comb tooth group are also provided with fixing holes, the connecting rod is connected to each of the first comb teeth through the connecting hole, and the first screw fixes the first wing to the connecting rod through the fixing hole.

3. The aircraft wing with deicing function according to claim 2, characterized in that: The cam groove is arranged inside the first comb tooth in the first comb tooth group adjacent to the second wing input end.

4. The aircraft wing with deicing function according to claim 3, characterized in that: The cam groove includes a first cavity and a second cavity; when the cam is located in the second cavity, the driving component drives the cam to make the first wing move around the rotating shaft component; when the cam is located in the first cavity, the first wing is located at an initial position and is locked with the second wing.

5. The aircraft wing with deicing function according to claim 2, characterized in that: The second wing is a comb-shaped structure, including a comb handle and a second comb tooth group, and each second comb tooth in the second comb tooth group is evenly arranged on the comb handle.

6. The aircraft wing with deicing function according to claim 5, characterized in that: A limiting hole and a second rotating shaft hole are provided on each second comb tooth in the second comb tooth group; wherein, the limiting hole corresponds to the connecting hole on the first comb tooth and is used to limit the first wing; the second rotating shaft hole corresponds to the first rotating shaft hole on the first comb tooth; the rotating shaft assembly passes through the first rotating shaft hole and the second rotating shaft hole in sequence to connect the first wing with the second wing.

7. The aircraft wing with deicing function according to claim 6, characterized in that: A threaded hole is also provided on the second comb tooth located in the middle of the second comb tooth group. A spring is provided in the threaded hole. The spring is connected to the connecting rod.

8. The aircraft wing with deicing function according to claim 1, characterized in that: The driving assembly includes a motor and a telescopic mechanism, wherein the fixed end of the telescopic mechanism is connected to the second wing, the output end of the telescopic mechanism is connected to the motor, the output end of the motor is connected to the cam, and the telescopic mechanism drives the cam to move in the cam groove through the motor.

9. The aircraft wing with deicing function according to claim 1, characterized in that: The rotating shaft assembly comprises a rotating shaft and a bearing. The rotating shaft passes through the first wing and the second wing in sequence. Two ends of the rotating shaft are connected to two ends of the wing assembly through the bearing.

10. A method for deicing an aircraft wing, implemented based on the aircraft wing with deicing function according to any one of claims 1 to 9, characterized in that: S1: When the wing of the aircraft needs to be de-iced, the telescopic mechanism of the drive assembly drives the cam to move into the second cavity of the cam groove through the motor of the drive assembly; S2: starting the motor to drive the cam to rotate, thereby driving the first wing to reciprocate up and down around the rotating shaft assembly along the limiting hole of each second comb tooth in the second comb tooth group of the second wing, thereby forming low-frequency vibration. The shear force generated by the low-frequency vibration breaks the ice layer; The up and down reciprocating motion of the first wing causes the ice layer on the wing assembly to separate from the wing assembly; then, the aerodynamic force generated by the aircraft during flight blows away the broken ice pieces; S3: When de-icing is completed, the motor stops working; at this time, the spring connected to the connecting rod of the first wing drives the connecting rod to reset by its own elastic force, thereby returning the first wing to its initial position; S4: The telescopic mechanism drives the motor again, driving the cam back into the cam groove; at this time, a part of the motor is located in the first motor groove inside the first comb tooth of the first wing, and the other part is located in the second motor groove of the second comb tooth at the input end of the second wing, so that the wing assembly is in a locked state.

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