Aircraft wing with deicing function

Abstract

The utility model relates to the technical field of aviation, in particular to an aircraft wing with a deicing function, which comprises a wing component, a cam and a driving component, 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 quickly break an ice layer attached to the wing assembly.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aviation technology, especially to a kind of aircraft wing with deicing function. BACKGROUND

[0002] Wings with airfoil characteristics are used when aircrafts fly, and the shape of the wings directly affects the aerodynamic characteristics of the aircraft. At high altitudes, the temperature is low, and the aircraft often passes through cold clouds or humid areas. At this time, the surface of the wing will freeze, and after freezing, the aerodynamic characteristics of the aircraft will be damaged, the performance of the aircraft will be reduced, the resistance of the aircraft will be increased, the fuel consumption will be increased, and in severe cases, the lift of the aircraft will be insufficient to support its weight. At this time, the aircraft will stall, causing serious consequences. Therefore, it is necessary to deice the surface of the wing in flight.

[0003] Chinese patent publication number CN112550665A, published on March 26, 2021, entitled "Aircraft deicing device with elastic skin", discloses a device that can remove ice from the surface of the wing during flight. However, due to the elastic skin, the wing shape will change after deicing and then recover. The characteristics of the wing shape will inevitably change, and the roughness of the surface of the elastic skin is also different from that of the conventional aircraft skin, which will increase the resistance.

[0004] Chinese patent publication number CN111731485A, published on October 2, 2020, entitled "Self-intermittent deicing device, installation method and deicing method", discloses a self-intermittent deicing device that mainly relies on electric heating to heat the contact surface to melt the ice layer and achieve the effect of deicing. The device can complete the deicing task without changing the aircraft wing shape. However, for aircrafts, this high-power surface heating method undoubtedly increases the energy consumption of the aircraft, which reduces the endurance time of the aircraft and shortens the flight range. UTILITY MODEL CONTENTS

[0005] Therefore, the utility model aims to provide an aircraft wing with deicing function. The cam is driven by the driving assembly to drive the first wing to move around the rotating shaft, which can effectively deice the aircraft in icing conditions.

[0006] To achieve the above-mentioned purpose, the technical solution of the utility model is as follows:

[0007] The application discloses an aircraft wing with a deicing function, which 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; the first wing is internally provided with a cam groove, 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 the ice layer on the wing assembly is removed.

[0008] Further, the first wing comprises a first comb tooth group and a connecting rod, and the second wing comprises a second comb tooth group; when the first wing is connected with the second wing, the first comb tooth group and the second comb tooth group are arranged in an intersecting and spaced manner, 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.

[0009] Further, each first comb tooth is provided with a connecting hole and a first rotating shaft hole; the first comb tooth at the two ends of the first comb tooth group is further provided with a fixing hole, the connecting rod is connected with each first comb tooth through the connecting hole, and a first screw is used for fixing the first wing and the connecting rod through the fixing hole.

[0010] Further, the cam groove is arranged in the interior of the first comb tooth adjacent to the input end of the second wing.

[0011] Further, the cam groove comprises a first cavity and a second cavity; when the cam is located in the second cavity, the driving assembly drives the cam to make the first wing move around the rotating shaft assembly; 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.

[0012] Further, the second wing is in a comb structure, comprising a comb handle and a second comb tooth group, and each second comb tooth in the second comb tooth group is uniformly arranged on the comb handle.

[0013] Further, each second comb tooth in the second comb tooth group is provided with a limiting hole and a second rotating shaft hole; the limiting hole corresponds to the connecting hole on the first comb tooth and is used for limiting 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 and the second wing.

[0014] Further, the second comb tooth located in the middle of the second comb tooth group is further provided with a threaded hole, a spring is arranged in the threaded hole, and the spring is connected with the connecting rod.

[0015] Further, the driving assembly comprises a motor and an extension mechanism, the fixed end of the extension mechanism is connected with the second wing, the output end of the extension mechanism is connected with the motor, the output end of the motor is connected with the cam, and the extension mechanism drives the cam to move in the cam groove through the motor.

[0016] Further, the rotating shaft assembly comprises a rotating shaft and bearings, the rotating shaft sequentially passes through the first wing and the second wing, and the rotating shaft is fixed at two ends of the wing assembly through the bearings.

[0017] Compared with the prior art, the wing of the aircraft provided by the present application can achieve the following beneficial effects:

[0018] The driving assembly drives the cam to make the first wing produce heaving vibration, and the shearing force and vibration force generated by the vibration can rapidly break the ice layer frozen on the wing assembly. Subsequently, the broken ice pieces are blown away by the aerodynamic force generated when the aircraft is flying, so that more energy can be saved, and the aerodynamic wing type does not need to be changed, and problems caused by the change of the wing type do not need to be considered. BRIEF DESCRIPTION OF DRAWINGS

[0019] The accompanying drawings, which form a part of the present application, are intended to provide further understanding of the present application, and the illustrative embodiments of the present application and their description serve the purpose of explaining the present application. The present application is not limited by the accompanying drawings.

[0020] Figure 1 is a structural schematic view of the aircraft wing with the deicing function according to the embodiment of the present application;

[0021] Figure 2 is a structural schematic view of the aircraft wing with the deicing function from the first perspective according to the embodiment of the present application;

[0022] Figure 3 is a structural schematic view of the first wing according to the embodiment of the present application; Figure 2 is a sectional view obtained along A-A;

[0023] Figure 4 is a structural schematic view of the first wing according to the embodiment of the present application;

[0024] Figure 5 is a structural schematic view of the first wing from the first perspective according to the embodiment of the present application;

[0025] Figure 6 is a structural schematic view of the second wing according to the embodiment of the present application; Figure 4 is a sectional view obtained along B-B;

[0026] Figure 7 is a structural schematic view of the second wing according to the embodiment of the present application;

[0027] Figure 8 is a structural schematic view of the cam and the driving assembly according to the embodiment of the present application.

[0028] The reference signs include: 1, wing assembly; 11, first wing; 111, cam groove; 112, first comb set; 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 set; 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 part; 4, spring. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical scheme and advantages of the utility model clearer and more understandable, the utility model will be further described in detail below in combination with the drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the utility model and do not constitute a limitation on the utility model.

[0030] It should be noted that the embodiments in the utility model and the features in the embodiments can be combined with each other without conflict.

[0031] In the description of the utility model, it should be understood that the orientation or position relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like is based on the orientation or position relationship shown in the drawings, and is only for the convenience of describing the utility model and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements indicated must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the utility model. In addition, the terms "first", "second" and the like are only for description purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features limited by "first", "second" and the like can explicitly or implicitly include one or more features. In the description of the utility model, unless otherwise specified, the meaning of "multiple" is two or more.

[0032] In the description of the utility model, it should be noted that, unless otherwise specified and limited, the terms "mounting", "connection" and "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the communication between the two elements inside. For ordinary skilled in the art, the specific meaning of the above terms in the utility model can be understood through specific circumstances.

[0033] The utility model will be explained in detail below with reference to the drawings and in combination with the embodiments.

[0034] As Figures 1-3 shown, the utility model discloses a kind of aircraft wings with deicing function, including wing component 1, cam 2 and drive component 3.Wing component 1 includes first wing 11, second wing 12 and rotating shaft component 13, rotating shaft component 13 connects first wing 11 and second wing 12, drive component 3 is connected with second wing 12, and the output end of drive component 3 is connected with cam 2.Cam groove 111 is equipped in first wing 11, and cam 2 is arranged in cam groove 111.

[0035] In the embodiment, the end that second wing 12 is connected with drive component 3 is defined as input end, after first wing 11 is connected with second wing 12, the end that first wing 11 is away from input end is defined as free end.

[0036] As Figures 4-6 shown, first wing 11 includes first comb set and connecting rod 113, and connecting hole 114 and first rotating shaft hole 115 are equipped on each first comb 112 in first comb set 112.Fixed hole 116 is also equipped on the first comb at both ends of first comb set 112.Inside the first comb adjacent to the input end of second wing 12 in first comb set 112 is also equipped with cam groove 111 and first motor groove 119.Cam groove 111 includes first cavity 117 and second cavity 118.

[0037] Second wing 12 is comb structure, and its structure is as Figure 7 shown, including comb handle 121 and second comb set 122, and each second comb is evenly arranged on comb handle 121 in second comb set 122.Each second comb in second comb set 122 is equipped with limiting hole 123 and second rotating shaft hole 124, and limiting hole 123 is used to limit first wing 11.Second motor groove 125 is also equipped on the second comb at the input end of second wing 12.Second threaded hole 126 is also equipped on the second comb at middle position in second comb set 122, and spring 4 is located in threaded hole 126 and connected with connecting rod 113.Second screw is screwed with threaded hole 126, which not only limits the position of spring 4, but also ensures that spring 4 will not be removed from threaded hole 126 when stressed.

[0038] In the embodiment, first wing 11 and second wing 12 are both made of hard skin, and the outer contour is streamline.First comb set 112 includes five first combs, and second comb set 122 includes five second combs.Spring 4 is compression spring, limiting hole 123 is long hole, first motor groove 119 can be circular or square, and second motor groove 125 can be square hole or round hole.

[0039] 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 and the second comb is 50mm.

[0040] In other embodiments, the width of the first comb and the second comb is greater than or equal to 30mm and less than or equal to 100mm. The number of first combs and second combs is increased or decreased according to the actual required span length of the wing assembly 1.

[0041] The structure of the driving assembly 3 is shown in Figure 8 The driving assembly 3 is shown in

[0042] The aircraft wing assembly process with deicing function is described in combination with the drawings:

[0043] First, the first comb group 112 of the first wing 11 and the second comb group 122 of the second wing 12 are arranged in cross interval, so that the second rotating shaft hole 124 of the second comb group 122 corresponds to the first rotating shaft hole 115 on the first comb group 112 one by one, and the limiting hole 123 of the second comb group 122 corresponds to the connecting hole 114 on the first comb group 112 one by one. Subsequently, the rotating shaft assembly 13 is sequentially inserted into the second rotating shaft hole 124 and the first rotating shaft hole 115. 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.

[0044] Then, the inner surface of the connecting hole 114 of the first comb group 112 is evenly coated with glue, then the connecting rod 113 is sequentially inserted into the second comb and the first comb, and the first comb group 112 is glued with the connecting rod 113, and then the first screw is used to fix the first comb group 112 and the connecting rod 113 through the fixed hole 116, so that the first wing 11 can move up and down along the limiting hole 123 around the rotating shaft 131. The fixed hole 116 is a threaded hole, and the first screw is screwed with the fixed hole 116 to make the first screw top to the surface of the connecting rod 113 to fix the connecting rod 113.

[0045] Next, the cam 2 is connected to the output end of the motor 31 of the driving assembly 3. Then, the cam 2 is sent into the first cavity 117 of the cam groove 111 along the second motor groove 125 and the first motor groove 119, and the motor 31 is located in the second motor groove 125 and the first motor groove 119. After that, the steering gear fixing piece 323 of the driving assembly 3 is fixed to the input end of the second wing 12.

[0046] Finally, the spring 4 is placed in the threaded hole 126 and connected to the connecting rod 113. The second screw is screwed with the threaded hole 126, so as to complete the assembly of the aircraft wing.

[0047] The working process of the aircraft wing with the deicing function is described in combination with the drawings. When the aircraft wing needs to be deiced, the telescopic mechanism 32 drives the cam 2 to move into the second cavity 118 of the cam groove 111 by the motor 31. Then, the motor 31 is started to drive the cam 2 to rotate and in turn drive the first wing 11 to reciprocate up and down along the limiting hole 123 around the rotating shaft 131, forming low-frequency vibration. The shear force generated by the low-frequency vibration breaks the ice layer. The up-and-down reciprocation of the first wing 11 makes the ice layer on the wing assembly 1 separate from the wing assembly 1. Then, the aerodynamic force generated when the aircraft flies blows away the broken ice pieces.

[0048] When the deicing is completed, the motor 31 stops working. At this time, the spring 4 drives the connecting rod 113 to reset by using the elastic force of the spring 4, and in turn makes the first wing 11 return to the initial position. Then, the telescopic mechanism 32 drives the motor 31 again, and in turn drives the cam 2 to return to the first cavity 117 of the cam groove 111. At this time, a part of the motor 31 is located in the first motor groove 119, and the other part is located in the second motor groove 125, so as to make the wing assembly 1 in the locked state.

[0049] In the embodiment, the position of the first wing 11 when the first wing 11 and the second wing 12 are in the locked state is defined as the initial position.

[0050] The above specific embodiments do not constitute a limitation on the protection scope of the utility model. 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 utility model should be included in the protection scope of the utility model.

Claims

1. An aircraft wing with de-icing function, characterized in that, Including wing components, cams, and drive components; The wing assembly includes a first wing, a second wing, and a rotating shaft assembly. The rotating shaft assembly connects the first wing and the second wing. The drive assembly is connected to the second wing, and the output end of the drive assembly is connected to the cam. The first wing is provided with a cam groove, and the cam is disposed in the cam groove; When the drive assembly drives the cam to rotate within the cam slot, the first wing moves about the rotation axis assembly, thereby removing the ice layer on the wing assembly.

2. The aircraft wing with de-icing function according to claim 1, characterized in that, 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 alternately. The connecting rod connects each first comb tooth in the first comb tooth group into an integral structure to form the first wing, thereby enabling the first wing to move around the rotating shaft assembly.

3. The aircraft wing with de-icing function according to claim 2, characterized in that, Each of the first comb teeth is provided with a connecting hole and a first pivot hole; at both ends of the first comb teeth of the first comb tooth group, there are also fixing holes. The connecting rod is connected to each of the first comb teeth through the connecting holes, and the first screw fixes the first wing to the connecting rod through the fixing holes.

4. The aircraft wing with de-icing function according to claim 3, characterized in that, The cam groove is located inside the first comb tooth in the first comb tooth group, which is adjacent to the input end of the second wing.

5. The aircraft wing with de-icing function according to claim 4, characterized in that, The cam groove includes a first cavity and a second cavity; when the cam is located in the second cavity, the drive assembly drives the cam to move the first wing around the rotation axis assembly; when the cam is located in the first cavity, the first wing is in the initial position and locked to the second wing.

6. The aircraft wing with de-icing function according to claim 3, characterized in that, The second wing has a comb-like structure, including a comb handle and a second comb tooth group, wherein each second comb tooth in the second comb tooth group is evenly disposed on the comb handle.

7. The aircraft wing with de-icing function according to claim 6, characterized in that, Each second comb tooth in the second comb tooth group is provided with a limiting hole and a second pivot hole; wherein, the limiting hole corresponds to the connecting hole on the first comb tooth and is used to limit the first wing; the second pivot hole corresponds to the first pivot hole on the first comb tooth; the rotating shaft assembly passes through the first pivot hole and the second pivot hole in sequence to connect the first wing and the second wing.

8. The aircraft wing with de-icing function according to claim 7, characterized in that, The second comb tooth located in the middle of the second comb tooth group is also provided with a threaded hole, and a spring is provided in the threaded hole. The spring is connected to the connecting rod.

9. The aircraft wing with de-icing function according to claim 1, characterized in that, The drive 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, and the output end of the motor is connected to the cam. The telescopic mechanism drives the cam to move within the cam groove via the motor.

10. The aircraft wing with de-icing function according to claim 1, characterized in that, The rotating shaft assembly includes a rotating shaft and bearings. The rotating shaft passes through the first wing and the second wing in sequence, and both ends of the rotating shaft are connected to the two ends of the wing assembly through the bearings.

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