阅读说明：本技术 一种基于弹性蒙皮的飞机除冰装置 (Aircraft defroster based on elastic skin ) 是由 顾兴士 易贤 柳庆林 赖庆仁 于 2021-02-24 设计创作，主要内容包括：本发明适用于飞行器除冰领域,尤其是涉及一种基于弹性蒙皮的飞机除冰装置,包括弹性蒙皮、执行机构、凸轮系和电机,所述弹性蒙皮和执行机构通过连接件固定在机翼上,执行机构包括上执行机构和下执行机构,上下执行机构上均设置平动件,所述凸轮系带动上下执行机构沿翼面做直线运动,从而带动弹性蒙皮的不同段周期性地拉伸变形,进而致使积冰与弹性蒙皮发生相对错位滑动从而使得积冰脱落。本发明的飞机除冰装置,执行机构的能量利用率高,不会影响电机寿命；并且弹性蒙皮沿机翼面周期性拉伸,翼型前缘的弹性蒙皮也会带动发生一定的弹性变形,除冰效果大大提升；本发明采用螺钉将弹性蒙皮与执行机构固定在机翼上,易于蒙皮更换且密封效果较好。(The invention is suitable for the field of aircraft deicing, and particularly relates to an elastic skin-based aircraft deicing device which comprises an elastic skin, an actuating mechanism, a cam system and a motor, wherein the elastic skin and the actuating mechanism are fixed on a wing through a connecting piece, the actuating mechanism comprises an upper actuating mechanism and a lower actuating mechanism, translational pieces are arranged on the upper actuating mechanism and the lower actuating mechanism, the cam system drives the upper actuating mechanism and the lower actuating mechanism to do linear motion along a wing surface, so that different sections of the elastic skin are driven to be periodically stretched and deformed, and accumulated ice and the elastic skin are caused to generate relative dislocation sliding, so that the accumulated ice falls off. The airplane deicing device has the advantages that the energy utilization rate of the actuating mechanism is high, and the service life of a motor is not influenced; the elastic skin stretches periodically along the wing surface, the elastic skin on the front edge of the wing profile can also drive the wing profile to generate certain elastic deformation, and the deicing effect is greatly improved; according to the invention, the elastic skin and the actuating mechanism are fixed on the wing by using the screws, so that the skin is easy to replace, and the sealing effect is good.)

1. An aircraft deicing device based on an elastic skin is characterized by comprising the elastic skin (1), an actuating mechanism (2), a cam system (3) and a motor (4);

the actuating mechanism (2) comprises an upper actuating mechanism (21) and a lower actuating mechanism (22);

the upper executing mechanism (21) is provided with a first upper translational part (2141) and a second upper translational part (2142);

the lower actuating mechanism (22) is provided with a first lower translational member (2241) and a second lower translational member (2242);

the cam system (3) comprises a first cam (31) and a second cam (32), the first cam (31) and the second cam (32) are coaxial, and the center lines of the two cams are non-parallel;

the first cam (31) is arranged between the first upper translational piece (2141) and the second lower translational piece (2242), and the second cam (32) is arranged between the first lower translational piece (2241) and the second upper translational piece (2142);

the motor (4) drives the cam system (3) to rotate;

the actuating mechanism (2) is fixed on the elastic skin (1).

2. Aircraft de-icing arrangement according to claim 1, characterised in that said upper actuator and said lower actuator comprise at least two connection frames and at least two connection rods, respectively.

3. Aircraft de-icing arrangement according to claim 2, characterised in that said upper actuator (21) further comprises: the connecting device comprises a first upper connecting frame (211), a second upper connecting frame (212) and a third upper connecting frame (213), wherein the first upper connecting frame (211), the second upper connecting frame (212) and the third upper connecting frame (213) are all U-shaped structures, and each U-shaped structure comprises a first supporting leg (2111) and a second supporting leg (2112);

the first upper connecting frame (211) and the second upper connecting frame (212) are connected through a first connecting rod (2151), a second connecting rod (2152), a third connecting rod (2153) and a fourth connecting rod (2154), the second upper connecting frame (212) and the third upper connecting frame (213) are connected through a fifth connecting rod (2155), a sixth connecting rod (2156), a seventh connecting rod (2157) and an eighth connecting rod (2158), and the connecting rods are parallel to each other; all the connecting frames are parallel to each other;

the first connecting rod (2151), the second connecting rod (2152), the fifth connecting rod (2155) and the sixth connecting rod (2156) are arranged on the first supporting leg (2111), and the third connecting rod (2153), the fourth connecting rod, the seventh connecting rod (2157) and the eighth connecting rod (2158) are arranged on the second supporting leg (2112).

4. Aircraft de-icing arrangement according to claim 2, characterized in that said lower actuator (22) further comprises: the connecting structure comprises a first lower connecting frame (221), a second lower connecting frame (222) and a third lower connecting frame (223), wherein the first lower connecting frame (221), the second lower connecting frame (222) and the third lower connecting frame (223) are all U-shaped structures, and each U-shaped structure comprises a third supporting leg (2211) and a fourth supporting leg (2212);

the first lower connecting frame (221) and the second lower connecting frame (222) are connected through a ninth connecting rod (2251), a tenth connecting rod (2252), an eleventh connecting rod (2253) and a twelfth connecting rod (2254), the second lower connecting frame (222) and the third lower connecting frame (223) are connected through a thirteenth connecting rod (2255), a fourteenth connecting rod (2256), a fifteenth connecting rod (2257) and a sixteenth connecting rod (2258), and the connecting rods are parallel to each other; all the connecting frames are parallel to each other;

the ninth connecting rod (2251), the tenth connecting rod (2252), the thirteenth connecting rod (2255), and the fourteenth connecting rod (2256) are disposed on the third leg (2211), and the eleventh connecting rod (2253), the twelfth connecting rod (2254), the fifteenth connecting rod (2257), and the sixteenth connecting rod (2258) are disposed on the fourth leg (2212).

5. Aircraft de-icing arrangement according to claim 3, characterised in that said first upper translator (2141) comprises a first support bar (21411) and a first plate (21412), said second upper translator (2142) comprises a second support bar (21421) and a second plate (21422), said first support bar (21411) and said second support bar (21421) being vertically connected between said seventh connecting bar (2157) and said eighth connecting bar (2158); the first plate (21412) corresponds to the first cam (31), and the second plate (21422) corresponds to the second cam (32).

6. Aircraft de-icing arrangement according to claim 4, characterised in that said first lower translation element (2241) comprises a third supporting bar (22411) and a third flat plate (22412), said second lower translation element (2242) comprises a fourth supporting bar (22421) and a fourth flat plate (22422), said third supporting bar (22411) and said fourth supporting bar (22421) being vertically connected between said fifteenth connecting bar (2257) and said sixteenth connecting bar (2258); the third flat plate (22412) corresponds to the second cam (32), and the fourth flat plate (22422) corresponds to the first cam (31).

7. Aircraft de-icing arrangement according to claim 3 or 4, characterised in that a connection is provided on said U-shaped structure, by means of which connection said upper actuator (21) and said lower actuator (22) are fixedly connected to the elastic skin (1).

8. Aircraft de-icing arrangement according to claim 7, characterised in that said connection elements are provided with threaded holes, and that said upper actuator (21) and said lower actuator (22) are fixedly connected to said elastic skin (1) by means of fastening screws.

9. Aircraft de-icing arrangement according to claim 1, characterised in that the centreline angle of said first cam (31) and said second cam (32) is 90 degrees.

Technical Field

The invention relates to the field of aircraft deicing, in particular to an aircraft deicing device based on an elastic skin.

Background

When the airplane flies in the air, if the airplane encounters icing meteorological conditions, icing phenomena can occur on the surfaces of wings, engine air inlet channels, various sensors exposed outside the airplane body and the like, and the flying safety is influenced. Therefore, the deicing of the airplane is a necessary condition for ensuring the normal flight of the airplane. The conventional deicing modes comprise liquid deicing, mechanical deicing, thermal deicing and the like, and although the deicing modes can achieve the deicing effect, the deicing modes have some defects, such as difficult skin manufacturing and complex liquid supply device in the liquid deicing mode; the air bag deicing in the mechanical deicing mode destroys the pneumatic appearance and the air supply device is complex, while the electric pulse deicing mode has high noise, large power supply volume and heavy weight; the thermal deicing mode has low efficiency and large energy consumption.

In addition, the elastic belt is also paid attention to deicing, and the deicing mode achieves the aim of deicing through deformation of the elastic belt in the direction perpendicular to or along the airfoil surface, for example, in patent CN109808897B, the elastic belt is wrapped on the outer surface of a wing leading edge skin, and a wing inner cavity drives the elastic belt to be dislocated with accumulated ice through a cam so as to perform deicing. But the method has poor deicing effect because the elastic skin has small deformation at the leading edge; the friction force between the elastic skin and the wing piece is large, so that the energy consumption is large and the efficiency is low; water and ice can enter the wing cavity from the gap between the deicing shovel and the skin, and the sealing property is difficult to ensure.

Patent US5681014A provides a torsion drive mechanism under the elastic skin that drives the elastic skin to deform as the torque tube rotates, thereby removing ice. The method still has the following defects: 1. the motor is required to rotate forward and backward continuously, so that the service life of the motor is influenced; 2. the deformation of the elastic skin in the patent is realized by being driven by the flexible ribs 25, so that the energy utilization rate is low; 3. typically, the leading edge of the wing is most icy, and the distortion is minimal here in the patent, and thus, the deicing effect is poor.

Therefore, even though some devices for deicing the elastic belt exist in the prior art, the existing deicing device has poor deicing effect, high energy consumption and difficult guarantee of sealing performance.

Disclosure of Invention

In order to solve the defects of the prior art, the invention aims to provide the aircraft deicing device based on the elastic skin, the energy utilization rate of an actuating mechanism is high, and the service life of a motor is not influenced; by adopting the deicing device, the elastic skin stretches periodically along the wing surface, the elastic skin at the front edge of the wing profile can also be driven to generate certain elastic deformation, and the deicing effect is greatly improved; according to the invention, the elastic skin and the actuating mechanism are fixed on the wing by using the screws, so that the skin is easy to replace, and the sealing effect is good.

The invention is realized in this way, an aircraft de-icing device based on elastic skin includes elastic skin, actuating mechanism, cam system and motor;

the actuating mechanism comprises an upper actuating mechanism and a lower actuating mechanism;

the upper executing mechanism is provided with a first upper translational member and a second upper translational member;

the lower executing mechanism is provided with a first lower translation piece and a second lower translation piece;

the cam system comprises a first cam and a second cam, the first cam and the second cam are coaxial, and the center lines of the two cams are non-parallel;

the first cam is arranged between the first upper translational member and the second lower translational member, and the second cam is arranged between the first lower translational member and the second upper translational member;

the motor drives the cam system to rotate;

the actuating mechanism is fixed to the elastic skin.

Further, the upper actuating mechanism and the lower actuating mechanism respectively comprise at least two connecting frames and at least two connecting rods.

Further, the upper actuator further comprises: the connecting device comprises a first upper connecting frame, a second upper connecting frame and a third upper connecting frame, wherein the first upper connecting frame, the second upper connecting frame and the third upper connecting frame are all U-shaped structures, and each U-shaped structure comprises a first supporting leg and a second supporting leg;

the first upper connecting frame and the second upper connecting frame are connected through a first connecting rod, a second connecting rod, a third connecting rod and a fourth connecting rod, the second upper connecting frame and the third upper connecting frame are connected through a fifth connecting rod, a sixth connecting rod, a seventh connecting rod and an eighth connecting rod, and the connecting rods are parallel to each other; all the connecting frames are parallel to each other;

the first connecting rod, the second connecting rod, the fifth connecting rod and the sixth connecting rod are arranged on the first supporting leg, and the third connecting rod, the fourth connecting rod, the seventh connecting rod and the eighth connecting rod are arranged on the second supporting leg.

Further, the lower actuator further comprises: the connecting device comprises a first lower connecting frame, a second lower connecting frame and a third lower connecting frame, wherein the first lower connecting frame, the second lower connecting frame and the third lower connecting frame are all U-shaped structures, and each U-shaped structure comprises a third supporting leg and a fourth supporting leg;

the first lower connecting frame and the second lower connecting frame are connected through a ninth connecting rod, a tenth connecting rod, an eleventh connecting rod and a twelfth connecting rod, the second lower connecting frame and the third lower connecting frame are connected through a thirteenth connecting rod, a fourteenth connecting rod, a fifteenth connecting rod and a sixteenth connecting rod, and the connecting rods are parallel to each other; all the connecting frames are parallel to each other;

the ninth connecting rod, the tenth connecting rod, the thirteenth connecting rod and the fourteenth connecting rod are arranged on the third supporting leg, and the eleventh connecting rod, the twelfth connecting rod, the fifteenth connecting rod and the sixteenth connecting rod are arranged on the fourth supporting leg.

Further, the first upper translational member comprises a first support rod and a first flat plate, the second upper translational member comprises a second support rod and a second flat plate, and the first support rod and the second support rod are vertically connected between the seventh connecting rod and the eighth connecting rod; the first plate corresponds to the first cam, and the second plate corresponds to the second cam.

Further, the first lower translational member comprises a third support rod and a third flat plate, the second lower translational member comprises a fourth support rod and a fourth flat plate, and the third support rod and the fourth support rod are vertically connected between the fifteenth connecting rod and the sixteenth connecting rod; the third plate corresponds to the second cam, and the fourth plate corresponds to the first cam.

Furthermore, a connecting piece is arranged on the U-shaped structure, and the upper actuating mechanism and the lower actuating mechanism are fixedly connected to the elastic skin through the connecting piece.

Furthermore, threaded holes are formed in the connecting piece, and the upper executing mechanism and the lower executing mechanism are fixedly connected to the elastic skin through fastening screws.

Further, the centerline angle of the first cam and the second cam is 90 degrees.

Further, the length of the first connecting rod, the second connecting rod, the third connecting rod and the fourth connecting rod is the same as or different from that of the fifth connecting rod, the sixth connecting rod, the seventh connecting rod and the eighth connecting rod.

Further, the ninth connecting rod, the tenth connecting rod, the eleventh connecting rod and the twelfth connecting rod are the same as or different from the thirteenth connecting rod, the fourteenth connecting rod, the fifteenth connecting rod and the sixteenth connecting rod in length.

Compared with the prior art, the airplane deicing device based on the elastic skin has the following beneficial effects:

1. the deicing device is simple in structure and light in weight, the motor drives the actuating mechanism to move through the cam, the energy consumption of the motor is reduced, the deicing energy consumption is low, and the deicing device can be used for airplanes with smaller power, particularly small unmanned planes;

2. the deicing device does not damage the aerodynamic appearance in the deicing process, has good sealing performance between the skin and the wing, and can prevent ice crystals or supercooled water from entering the inner cavity of the wing;

3. the actuating mechanism can drive the elastic skin of the airfoil leading edge to periodically stretch and deform, and the deicing effect is improved;

4. the deicing method of the deicing device is simple and easy to operate.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention or in the description of the prior art will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic illustration of an installation configuration of an aircraft de-icing apparatus based on an elastic skin according to an embodiment of the present invention;

FIG. 2 is an assembly view of an upper actuator and a lower actuator of an embodiment of the present invention;

FIG. 3 is a schematic structural diagram of an upper actuator according to an embodiment of the present invention;

FIG. 4 is a schematic structural diagram of a lower actuator according to an embodiment of the present invention;

FIG. 5 is a schematic view of the assembly of the translation member and the cam train of the present invention;

FIG. 6 is a schematic diagram of a cam system according to an embodiment of the present invention;

fig. 7 is a front view of a camming system in accordance with an embodiment of the present invention.

In the figure, 1-elastic skin, 11-first skin section, 12-second skin section, 13-third skin section, 14-fourth skin section, 2-actuator, 21-upper actuator, 211-first upper connecting frame, 212-second upper connecting frame, 213-third upper connecting frame, 2141-first upper translational member, 2142-second upper translational member, 21411-first supporting rod, 21412-first flat plate, 21421-second supporting rod, 21422-second flat plate, 2111-first leg, 2112-second leg, 2151-first connecting rod, 2152-second connecting rod, 2153-third connecting rod, 2154-fourth connecting rod, 2155-fifth connecting rod, 2156-sixth connecting rod, 2157-seventh connecting rod, 2158-eighth connecting rod; 22-lower actuator, 221-first lower link, 222-second lower link, 223-third lower link, 2241-first lower translation, 2242-second lower translation, 22411-third support bar, 22412-third plate, 22421-fourth support bar, 22422-fourth plate, 2211-third foot, 2212-fourth foot, 2251-ninth connecting rod, 2252-tenth connecting rod, 2253-eleventh connecting rod, 2254-twelfth connecting rod, 2255-thirteenth connecting rod, 2256-fourteenth connecting rod, 2257-fifteenth connecting rod, 2258-sixteenth connecting rod; 3-cam system, 31-first cam, 32-second cam, 33-rotating shaft, 4-motor and 5-wing.

Detailed Description

The following description provides many different embodiments, or examples, for implementing different features of the invention. The particular examples set forth below are illustrative only and are not intended to be limiting.

In the description of the present invention, it should be noted that when an element is referred to as being "fixed" or "disposed" to another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.

It will be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like, as used herein, refer to an orientation or positional relationship indicated in the drawings that is solely for the purpose of facilitating the description and simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and is therefore not to be construed as limiting the invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments.

The invention provides an airplane deicing device based on an elastic skin 1, which comprises the elastic skin 1, an actuating mechanism 2, a cam system 3 and a motor 4, wherein the actuating mechanism 2 is arranged on the elastic skin 1;

the inner surface profile of the elastic skin 1 is the same as the profile of the wing 5 to achieve a coincident fit of the two.

As shown in fig. 2-3, the actuator 2 includes an upper actuator 21 and a lower actuator 22;

the upper actuating mechanism 21 is provided with a first upper translation part 2141 and a second upper translation part 2142;

the lower actuating mechanism 22 is provided with a first lower translation member 2241 and a second lower translation member 2242;

the upper actuator 21 further includes: the first upper connecting frame 211, the second upper connecting frame 212 and the third upper connecting frame 213 are all in a U-shaped structure, and each of the first upper connecting frame 211, the second upper connecting frame 212 and the third upper connecting frame 213 comprises a first supporting leg 2111 and a second supporting leg 2112; the U-shaped structure is matched with the wing profile of the airplane.

The first upper connecting frame 211 and the second upper connecting frame 212 are connected through a first connecting rod 2151, a second connecting rod 2152, a third connecting rod 2153 and a fourth connecting rod 2154, the second upper connecting frame 212 and the third upper connecting frame 213 are connected through a fifth connecting rod 2155, a sixth connecting rod 2156, a seventh connecting rod 2157 and an eighth connecting rod 2158, and the connecting rods are parallel to each other; all the connecting frames are parallel to each other;

the first connecting rod 2151, the second connecting rod 2152, the fifth connecting rod 2155, and the sixth connecting rod 2156 are provided on the first leg 2111, and the third connecting rod 2153, the fourth connecting rod 2154, the seventh connecting rod 2157, and the eighth connecting rod 2158 are provided on the second leg 2112.

The lower actuator 22 further includes: the first lower connecting frame 221, the second lower connecting frame 222 and the third lower connecting frame 223 are also arranged in a U-shaped structure, and the U-shaped structure comprises a third supporting leg 2211 and a fourth supporting leg 2212;

the first lower connecting frame 221 and the second lower connecting frame 222 are connected by a ninth connecting rod 2251, a tenth connecting rod 2252, an eleventh connecting rod 2253 and a twelfth connecting rod 2254, and the second lower connecting frame 222 and the third lower connecting frame 223 are connected by a thirteenth connecting rod 2255, a fourteenth connecting rod 2256, a fifteenth connecting rod 2257 and a sixteenth connecting rod 2258, which are parallel to each other; all the connecting frames are parallel to each other;

a ninth connecting rod 2251, a tenth connecting rod 2252, a thirteenth connecting rod 2255 and a fourteenth connecting rod 2256 are provided on the third leg 2211, and an eleventh connecting rod 2253, a twelfth connecting rod 2254, a fifteenth connecting rod 2257 and a sixteenth connecting rod 2258 are provided on the fourth leg 2212.

As shown in fig. 2 to 5, the cam train 3 includes a first cam 31 and a second cam 32, the first cam 31 and the second cam 32 are connected by a rotating shaft 33, the first cam 31 and the second cam 32 are coaxial, and the center lines of the two cams are non-parallel, as shown in fig. 6, preferably, the center line angle of the first cam 31 and the second cam 32 is 90 degrees, as shown in fig. 7.

The first upper translational member 2141 includes a first supporting rod 21411 and a first flat plate 21412, the second upper translational member 2142 includes a second supporting rod 21421 and a second flat plate 21422, and the first supporting rod 21411 and the second supporting rod 21421 are vertically connected between the seventh connecting rod 2157 and the eighth connecting rod 2158; the first plate 21412 corresponds to the first cam 31, and the second plate 21422 corresponds to the second cam 32.

The first lower translational member 2241 comprises a third supporting rod 22411 and a third flat plate 22412, the second lower translational member 2242 comprises a fourth supporting rod 22421 and a fourth flat plate 22422, and the third supporting rod 22411 and the fourth supporting rod 22421 are vertically connected between a fifteenth connecting rod 2257 and a sixteenth connecting rod 2258; the third flat plate 22412 corresponds to the second cam 32, and the fourth flat plate 22422 corresponds to the first cam 31.

Thus, the first cam 31 is arranged between the first upper translational member 2141 and the second lower translational member 2242, and the second cam 32 is arranged between the first lower translational member 2241 and the second upper translational member 2142. As will be understood by those skilled in the art, in order to achieve the stretching deformation of the sections of skin, the first cam 31 is flanked by an upper translator and a lower translator, and likewise the second cam 32 is flanked by a lower translator and an upper translator. The first cam 31 and the second cam 32 are identical in shape and size, and are perpendicular to each other in the plane of rotation.

As can be understood by those skilled in the art, according to the structure of the upper actuator and the lower actuator of the present invention, as long as the upper actuator and the lower actuator respectively include at least two connecting frames and at least two connecting rods, the aircraft deicing mechanism of the present invention can perform the deicing function thereof; therefore, the number of the connecting frames and the connecting rods in the upper actuating mechanism and the lower actuating mechanism in the airplane deicing device can be determined according to the structure and the specific size of the airplane wing.

Thus, the actuator 2 is assembled in the inner cavity of the wing 5, the geometrical shape and the size of the actuator are related to the icing range and the wing profile of the wing, and the freedom of movement of the actuator is one, namely, the actuator can only do linear movement along the wing surface.

Further, the first connecting rod 2151, the second connecting rod 2152, the third connecting rod 2153, and the fourth connecting rod 2154 have the same or different lengths as the fifth connecting rod 2155, the sixth connecting rod 2156, the seventh connecting rod 2157, and the eighth connecting rod 2158. The ninth, tenth, eleventh, and twelfth connecting rods 2251, 2252, 2253, 2254 may be the same or different in length than the thirteenth, fourteenth, and fifteenth connecting rods 2255, 2256, 2257, 2258. Namely, the actuators 2 may be arranged at equal intervals or may be arranged at free intervals according to factors such as wing profile and icing range to segment the elastic skin 1, and each segment of the elastic skin 1 is subjected to tensile deformation under the action of the actuators 2 arranged at intervals.

Preferably, screw holes are provided in the connecting members, and the upper actuator 21 and the lower actuator 22 are fixedly connected to the elastic skin 1 by screws. Meanwhile, a through hole is reserved on the elastic skin 1 to realize the threaded connection between the elastic skin 1 and the connecting piece. The surface of the wing 5 is provided with a square groove, and the connecting piece passes through the square groove on the wing 5 to be connected with the elastic skin 1.

Those skilled in the art will appreciate that the connectors on the U-shaped structure may be uniformly spaced or non-uniformly spaced (i.e., freely spaced); when the elastic skin is uniformly arranged, the reserved through holes on the elastic skin of the airplane can be conveniently machined.

The deicing principle of the airplane deicing device based on the elastic skin 1 is as follows: the rotation of the first cam 31 causes the first upper translational member 2141 and the second lower translational member 2242 to respectively generate translational motions in different directions, so that the second skin segment 12 and the fourth skin segment 14 are stretched (as shown in fig. 2); the rotation of the second cam 32 causes the lower first lower translational member 2241 and the second upper translational member 2142 to respectively generate translational motions in different directions, so that the first skin section 11 and the third skin section 13 stretch. Because the first cam 31 and the second cam 32 are vertically arranged in the rotating plane, the first cam and the second cam alternately generate translation action in one rotating period, so that the second skin section 12 and the fourth skin section 14 and the first skin section 11 and the third skin section 13 alternately generate tensile deformation, the accumulated ice and the elastic skin 1 are subjected to relative dislocation sliding, and the accumulated ice is fallen off.

The movement of the actuator 2 of the deicer of the invention is controlled by a cam train 3, while the rotation of the cam train 3 is driven by a motor 4; the icing thickness of the wings 5 is continuously detected in the flying process of the airplane, and when the icing thickness meets the deicing requirement, the motor 4 is started, and the motor 4 drives the cam system 3 to rotate. When the first cam 31 rotates to contact the first upper translational member 2141 and the second lower translational member 2242, referring to fig. 5, the first upper translational member 2141 drives the upper actuator 21 to translate leftward, and the second lower translational member 2242 drives the lower actuator 22 to translate rightward, so that the second skin segment 12 and the fourth skin segment 14 in fig. 2 are gradually stretched; the cams continue to rotate, the stretching forces of the second skin section 12 and the fourth skin section 14 are gradually reduced, meanwhile, when the second cam 32 rotates to be in contact with the first lower translation piece 2241 and the second upper translation piece 2142, the first lower translation piece 2241 drives the lower actuating mechanism 22 to translate leftwards, the second upper translation piece 2142 drives the upper actuating mechanism 21 to translate rightwards, so that the first skin section 11 and the third skin section 13 in the figure 2 are gradually stretched, the cams continue to rotate, the stretching forces of the first skin section 11 and the third skin section 13 are gradually reduced, the next rotation period is started, and in such a reciprocating manner, the elastic skins 1 in each section are stretched and deformed to deice; and meanwhile, the deicing condition is detected, and when the icing is completely removed or the influence of the icing meets the flight requirement, the motor 4 is closed to stop deicing.

It will be appreciated by those skilled in the art that the embodiment of the present invention provides only one such de-icing assembly in the wing of an aircraft, but in practice, particularly for large aircraft, the de-icing assembly of the present invention may be provided in a plurality of locations on the wing, depending on the actual situation, and this is only a specific application of the de-icing assembly of the present invention and is not intended to limit the present invention.

The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.