Airplane deicing device and deicing method

Abstract

The invention belongs to the technical field of aviation deicing, and relates to an aircraft deicing device and a use method thereof. The airplane deicing device comprises an actuating module and a supporting rod module which are distributed on the inner surface of a wing skin, the actuating module is fixedly installed on a wing framework through an actuating module fixing support, and the supporting rod module is fixedly installed on the inner surface of the wing skin through a supporting rod support. The impact hammer is controlled to impact the impact block so as to push the supporting rod, impact kinetic energy is provided for the supporting rod to push the icebreaking plate to impact and crush ice covering the surface of the wing skin, and therefore the purpose of deicing is achieved. In order to reduce the impact of the actuating module on the wing skin in the deicing process and prolong the service life of the skin, the supporting rod module is specially designed to bear the impact kinetic energy of the actuating module, and the fatigue of the wing skin caused by the impact is reduced while deicing is realized. In addition, the installation positions and the number of the actuating modules and the supporting rod modules can be reasonably arranged according to icing areas of different wings.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft de-icing, relates to aircraft de-icing, and particularly relates to an aircraft de-icing device and a de-icing method. Background Art

[0002] The problem of aircraft icing has always been an important factor affecting aircraft flight safety. Developing new de-icing methods for aircraft is a key task to ensure flight safety. Aircraft icing mainly occurs on the surfaces of windward components, lift components, engine inlets, windshield glass, and various sensors, etc. If there are no anti / de-icing measures on the aircraft surface, the icing on the aircraft surface can lead to serious deterioration of the aircraft's aerodynamic characteristics and handling and stability characteristics, and ultimately have a serious impact on flight safety, such as reduced lift, increased drag, reduced stall angle of attack, and premature separation of the boundary layer, etc.

[0003] To overcome these effects, various anti / de-icing measures have been applied to the icing components to prevent aircraft icing or remove the ice layer on the aircraft icing surface. The electro-pulse de-icing technology is a widely used anti / de-icing technology at present, that is, during flight, an electro-pulse acts on the skin of the part to be protected on the aircraft surface, and the skin is rapidly agitated within the elastic deformation range, thereby breaking the ice layer on the skin surface. However, although this anti / de-icing technology can prevent / remove ice to a certain extent, its de-icing time is long, the energy storage capacitor is heavy, and due to long-term agitation, it is easy to cause skin fatigue, which is not conducive to the overall life and safe flight of the aircraft.

[0004] In view of this, the present invention is specifically proposed. Summary of the Invention

[0005] The purpose of the present invention is to overcome the above-mentioned disadvantages of the prior art and provide an aircraft de-icing device and a de-icing method, which can reduce the impact of the actuation module on the wing skin during de-icing and extend the service life of the skin while achieving de-icing.

[0006] To achieve the above purpose, the present invention provides the following technical solutions:

[0007] On the one hand, the present invention provides an aircraft de-icing device, including: an actuation module and a strut module distributed on the inner surface of the wing skin, the actuation module is fixedly installed on the wing skeleton through an actuation module fixing bracket, and the strut module is fixedly installed on the inner surface of the wing skin through a strut bracket;

[0008] The actuation module includes a hammer and a power storage mechanism for providing an impact force to the hammer. The power storage mechanism completes power storage in cooperation with the locking mechanism and ejects the hammer under the action of the triggering mechanism. The strut module includes an impact block, an ice-breaking plate, and a telescopic mechanism located between the two. The ice-breaking plate is embedded in the outer surface of the wing skin. A gap is reserved between the impact block and the hammer, and the length of the gap is less than the length of the hammer protruding from the actuation module to ensure that the hammer can hit the impact block when it ejects.

[0009] During de-icing, the hammer ejects under the action of the power storage mechanism and hits the impact block. The impact block drives the ice-breaking plate to extend under the action of the telescopic mechanism and impacts the ice covering on the outer surface of the wing skin. The ice covering is broken by mechanical vibration impact and blown away under the action of the airflow. After de-icing, the ice-breaking plate is retracted again and embedded in the outer surface of the wing skin under the action of the telescopic mechanism.

[0010] Specifically, the actuation module further includes a housing. Inside the housing, there are a locking block restraint cylinder and a mass block restraint cylinder arranged closely. The hammer is located at the top of the mass block restraint cylinder in a free state and can extend through an opening provided at the top of the housing.

[0011] The power storage mechanism includes: a mass block located inside the mass block restraint cylinder and a power storage motor located below the mass block restraint cylinder. The upper surface of the mass block is connected to the bottom of the hammer. A power storage spring is provided between the lower surface of the mass block and the bottom of the mass block restraint cylinder. The lower surface of the mass block is also connected to the power storage motor through a mass block traction wire. The power storage motor is located inside the housing.

[0012] The locking mechanism includes: a locking block located inside the locking block restraint cylinder. A first return spring is horizontally arranged between the end face a of the locking block and the inner wall of the locking block restraint cylinder. The end face a of the locking block is also connected to the triggering motor through a locking block traction wire. The triggering motor is located inside the housing. When subjected to a squeezing force from the horizontal direction, the inclined end face b of the locking block can retract along the barrel wall of the locking block restraint cylinder and, after the squeezing force disappears, extend along the barrel wall of the locking block restraint cylinder under the action of the first return spring to store power for the power storage mechanism.

[0013] Specifically, a lifting mechanism is also vertically arranged inside the housing. The locking block restraint cylinder is lifted and lowered under the action of the lifting mechanism. An opening is provided on the barrel wall of the locking block restraint cylinder to facilitate the extension / retraction of the inclined end face b of the locking block.

[0014] Further, the lifting mechanism includes a lifting conveyor belt vertically arranged inside the housing and located outside the locking block restraint cylinder. The lifting conveyor belt is connected to the output shaft of the lifting motor. The lifting motor is located inside the housing.

[0015] Preferably, the lifting motor and the triggering motor are both located below the locking block restraint cylinder.

[0016] Further, an induction switch bracket is fixed below the locking block, and a first induction switch for detecting whether the mass block is stuck by the locking block and a second induction switch for detecting whether the locking block has completely withdrawn from the mass block restraint cylinder are respectively installed on the induction switch bracket.

[0017] Specifically, the strut module includes: a strut, a strut bracket for fixing the strut and providing a movement space for it, the strut bracket is installed and fixed to the inner surface of the wing skin through a flange, and the impact block and the ice-breaking plate are respectively installed at both ends of the strut; the telescopic mechanism includes a limit block and a second return spring arranged on the strut, and the second return spring is located between the limit block and the ice-breaking plate.

[0018] Further, one end of the second return spring is connected to the ice-breaking plate, and the other end is connected to the limit block.

[0019] Specifically, a groove for facilitating the embedding of the ice-breaking plate is provided on the outer surface of the wing skin.

[0020] On the other hand, the present invention also provides an ice removal method using the above-mentioned partial or all of the aircraft ice removal device, which specifically includes,

[0021] Energy storage: The actuating module stores energy under the combined action of the energy storage mechanism and the locking mechanism;

[0022] Firing the hammer: Under the action of the triggering mechanism, the hammer pops out;

[0023] Impact ice removal: The popped hammer impacts the impact block and pushes the strut to move upward, pushing the ice-breaking plate to impact the ice covering the surface of the wing skin, and the ice covering is broken by mechanical vibration impact and blown away under the action of the air flow;

[0024] After ice removal, the ice-breaking plate is re-embedded into the outer surface of the wing skin under the action of the telescopic mechanism.

[0025] Compared with the prior art, the technical solution provided by the present invention has the following beneficial effects:

[0026] The aircraft deicing device provided by the present invention controls the hammer to hit the impact block and then push the strut, providing impact kinetic energy for the strut to push the icebreaker plate to impact the ice on the surface of the wing skin to break it, thereby achieving the purpose of deicing; in order to reduce the impact of the actuating module on the wing skin during the deicing process and extend the service life of the skin, the present invention specially designs a strut module to bear the impact kinetic energy of the actuating module, while achieving deicing and reducing the fatigue of the wing skin caused by the impact. In addition, the installation position and number of the actuating module and the strut module can be reasonably arranged according to the ice formation area of ​​different wings. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] The accompanying drawings are incorporated in and constitute a part of this specification and, together with the description, serve to explain the principles of the present invention.

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, for ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0029] Figure 1 The installation layout diagram of the aircraft deicing device provided by the present invention in the wing skin;

[0030] Figure 2 A schematic diagram of the structure of an actuating module in an aircraft deicing device provided by the present invention;

[0031] Figure 3 This is a schematic structural diagram of a strut module in an aircraft deicing device provided by the present invention.

[0032] Among them: A, actuation module; B, support rod module;

[0033] 1. Hammer; 2. Mass block; 3. Mass block constraint cylinder; 4. Storage spring; 5. Mass block traction line; 6. Storage motor; 7. Trigger motor; 8. Lifting motor; 9. Locking block traction line; 10. First induction switch; 11. Second induction switch; 12. Induction switch bracket; 13. Lifting conveyor belt; 14. First return spring; 15. Locking block; 16. Locking block constraint cylinder; 17. Shell; 20. Wing skin; 21. Fixing bolt; 22. Strut bracket; 23. Impact block; 24. Limit block; 25. Strut; 26. Second return spring; 27. Icebreaker; 28. Wing frame; 29. ​​Actuator module fixing bracket. DETAILED DESCRIPTION

[0034] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are merely examples consistent with some aspects of the present invention as detailed in the appended claims.

[0035] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0036] Example

[0037] See also Figures 1 to 3 As shown, this embodiment provides an aircraft deicing device, comprising: an actuating module A and a strut module B distributed on the inner surface of a wing skin 20, wherein the actuating module A is mounted and fixed to a wing frame 28 via an actuating module fixing bracket 29, and the strut module B is mounted and fixed to the inner surface of the wing skin 20 via a strut bracket 25;

[0038] The actuation module A includes a hammer 1 and a force storage mechanism for providing impact force to the hammer 1, the force storage mechanism completes force storage under the cooperation of the locking mechanism, and causes the hammer 1 to pop out under the action of the trigger mechanism; the strut module B includes a striker block 23, an icebreaker plate 27 and a telescopic mechanism located therebetween, the icebreaker plate 27 is embedded on the outer surface of the wing skin 20, a gap is reserved between the striker block 23 and the hammer 1, and the length of the gap is less than the length of the hammer 1 extending out of the actuation module A, so as to ensure that the hammer 1 can hit the striker block 23 when it pops out;

[0039] During de-icing, the hammer 1 pops out under the action of the force storage mechanism and hits the impact block 23. The impact block 23 drives the ice-breaking plate 27 to extend under the action of the telescopic mechanism and impact the ice on the outer surface of the wing skin 20. The ice is broken by mechanical vibration and blown away by the airflow, thereby achieving the de-icing effect. After de-icing is completed, the ice-breaking plate 27 is retracted and embedded in the outer surface of the wing skin 20 under the action of the telescopic mechanism.

[0040] Furthermore, the actuating module A further comprises a housing 17, wherein the housing 17 comprises a locking block constraint cylinder 16 and a mass block constraint cylinder 3 which are closely arranged, and the hammer 1 is located at the top of the mass block constraint cylinder 3 in a free state and can extend out along an opening arranged at the top of the housing 17;

[0041] The energy storage mechanism includes: a mass 2 located within the mass constraint cylinder 3 and an energy storage motor 6 located below the mass constraint cylinder 3. The upper surface of the mass 2 is connected to the bottom of the hammer 1. A energy storage spring 4 is provided between the lower surface of the mass 2 and the bottom of the mass constraint cylinder 3. The lower surface of the mass 2 is also connected to the energy storage motor 6 through a mass traction line 5. The energy storage motor 6 is located within the housing 17;

[0042] The locking mechanism includes: a locking block 15 located within the locking block constraint cylinder 16. A first return spring 14 is horizontally provided between the end face a of the locking block 15 and the inner wall of the locking block constraint cylinder 16. The end face a of the locking block 15 is also connected to the trigger motor 7 through a locking block traction line 9. The trigger motor 7 is located within the housing 17; When subjected to a squeezing force from the horizontal direction, the inclined end face b of the locking block 15 can retract along the wall of the locking block constraint cylinder 16 and, after the squeezing force disappears, extend along the wall of the locking block constraint cylinder 16 under the action of the first return spring 14 to store energy for the energy storage mechanism.

[0043] In this embodiment, the actuation module A pulls the mass traction line 5 through the energy storage motor 6 to compress the energy storage spring 4. When the mass 2 contacts the locking block 15 during the downward movement, the mass 2 will squeeze the inclined surface of the locking block 15 to cause it to contract towards the inside of the locking block constraint cylinder 16 until the mass 2 completely squeezes the locking block 15 out of the mass constraint cylinder 3 and continues to move downward until it completely passes over the locking block 15. Then, the locking block 15 will pop out under the action of the first return spring 14 and return to its original position. At this time, the mass 2 together with the hammer 1 will be constrained below the locking block 15 by the locking block 15, and the energy storage spring 4 is in an energy storage state. When the hammer 1 needs to be fired, the trigger motor 7 rotates to contract the locking block traction line 9, dragging the locking block 15 to contract towards the inside of the locking block constraint cylinder 16 until the locking block 15 completely exits the mass constraint cylinder 3. At this time, the constraint on the upper part of the mass 2 is released, and the mass 2 together with the hammer 1 quickly pops out under the action of the energy storage spring 4. The hammer 1 impacts the support rod 25, pushing the ice-breaking plate 27 to impact the ice covering the surface of the wing skin 20. The ice on the wing surface is broken by mechanical vibration impact and blown away under the action of the airflow. It should be added that the movement direction of the locking block 15 is perpendicular to the movement direction of the mass 2.

[0044] Specifically, the housing 17 further includes a vertically arranged lifting mechanism. The locking block constraint cylinder 16 is lifted and lowered under the action of the lifting mechanism. An opening is provided on the wall of the locking block constraint cylinder 16 to facilitate the extension / retraction of the inclined end face b of the locking block 15.

[0045] Further, the lifting mechanism includes a lifting conveyor belt 13 vertically disposed inside the housing 17 and outside the outer wall of the locking block restraint cylinder 16. The lifting conveyor belt 13 is connected to the output shaft of the lifting motor 8, and the lifting motor 8 is located inside the housing 17.

[0046] Preferably, both the lifting motor 8 and the trigger motor 7 are located below the locking block restraint cylinder 16.

[0047] Further, an induction switch bracket 12 is fixed below the locking block 15. A first induction switch 10 for detecting whether the mass block 2 is stuck by the locking block 15 and a second induction switch 11 for detecting whether the locking block 15 has completely withdrawn from the mass block restraint cylinder 3 are respectively installed on the induction switch bracket 12.

[0048] In this embodiment, the first induction switch 10 is used to detect whether the mass block 2 has been stuck by the locking block 15 and is in a compressed state, and the second induction switch 11 is used to detect whether the locking block 15 has completely withdrawn from the mass block restraint cylinder 3 and released the restraint on the mass block 2. The induction switch bracket 12 is fixedly installed on the locking block restraint cylinder 16, and both the first induction switch 10 and the second induction switch 11 are fixed on the induction switch bracket 12, so as to ensure that the positional relationship between the two induction switches and the objects to be detected remains unchanged. The motor shaft of the lifting motor 8 is connected to the lifting conveyor belt 13, which can drive the lifting conveyor belt 13 to rotate forward or backward, so as to realize the synchronous lifting of the locking block restraint cylinder 16 fixed on the lifting conveyor belt 13, the locking block 15 fixed inside the locking block restraint cylinder 16, the second return spring 26, the induction switch bracket 12, the first induction switch 10, and the second induction switch 11. The rising or falling of the lifting conveyor belt 13 can change the position of the locking block 15, thereby changing the compression degree of the energy storage spring 4 by the mass block 2 and adjusting the impact force intensity of the hammer 1.

[0049] It should be added that the contraction of the mass block traction wire 5 and the locking block traction wire 9 and the movement of the lifting conveyor belt 13 can be realized by the rotation of the lifting motor 8, or by driving a shape memory alloy wire (electric drive or thermal drive), an electromagnetic actuator, a pneumatic component or other types of actuators to realize contraction and then realize the lifting movement.

[0050] In this embodiment, the housing 17 is used to install and fix the components and structures of the actuating module A and the strut module B. A hole for the hammer 1 to extend out is opened at the top of the housing 17. The diameter of this hole is larger than the diameter of the hammer 1 and smaller than the diameter of the mass block 2, which can limit the mass block 2 while ensuring the extension of the hammer 1.

[0051] Further, to reduce the impact of the actuating module A on the wing skin 20 during de-icing and extend the service life of the skin, the strut module B includes: a strut 25, a strut bracket 22 for fixing the strut 25 and providing a movement space for it. The strut bracket 22 is fixedly installed on the inner surface of the wing skin 20 through a flange. The impact block 23 and the ice-breaking plate 27 are respectively installed at both ends of the strut 25. The telescopic mechanism includes a limit block 24 and a second return spring 26 provided on the strut 25. The second return spring 26 is located between the limit block 24 and the ice-breaking plate 27.

[0052] Preferably, one end of the second return spring 26 is connected to the ice-breaking plate 27, and the other end is connected to the limit block 24.

[0053] Preferably, a groove for facilitating the embedding of the ice-breaking plate 27 is provided on the outer surface of the wing skin 20.

[0054] In this embodiment, the strut bracket 22 is equipped with a flange and is connected to the wing skin 20 through bolts. The impact block 23 below the strut 25 is used to receive the impact kinetic energy when the hammer 1 of the actuating module A pops out. A limit block 24 is installed in the middle of the strut 25 to limit the strut 25 inside the strut bracket 22 under the action of the second return spring 26 in the non-operating state. The ice-breaking plate 27 connected to the top of the strut 25 is embedded in the groove on the surface of the wing skin 20, keeping flush with the wing skin 20 in terms of spatial position and structure and not affecting the aerodynamic characteristics of the wing in the non-operating state. During actual de-icing, after the strut 25 is impacted by the hammer 1 in the actuating module A, it pushes the strut 25 to move outward from the wing skin 20, pushing the ice-breaking plate 27 out of the groove, impacting the ice covering on the surface of the wing skin 20, and breaking the ice covering on the wing surface through mechanical vibration impact and blowing it away under the action of the airflow to complete de-icing. After the de-icing action of the strut module B ends, the strut 25 contracts towards the inside of the wing under the elastic restoring force of the second return spring 26 until the limit block 24 contacts the strut bracket 22, and the strut 25 returns to its initial state. The ice-breaking plate 27 is embedded in the groove on the surface of the wing skin 20 again.

[0055] For the aircraft de-icing device provided by the present invention, the installation positions and quantities of the actuating module A and the strut module B can be reasonably arranged according to the icing areas of different wings. Each actuating module A is powered and controlled by a cable, and the cable includes a power supply line and a control communication line. The power supply line and the control communication line can be laid along the actuating module fixing bracket 29 and the wing skeleton 28.

[0056] In addition, the present invention also provides a de-icing method using the above-mentioned part or all of the aircraft de-icing device, which specifically includes the following steps

[0057] Energy storage: The actuating module A stores energy under the combined action of the energy storage mechanism and the locking mechanism. Specifically, when the mass block 2 moves downward and contacts the locking block 15, the mass block 2 will squeeze the inclined surface of the locking block 15 to make it contract towards the inside of the locking block restraint cylinder 16 until the mass block 2 squeezes the locking block 15 completely out of the mass block restraint cylinder 3 and continues to move downward until it completely passes over the locking block 15. Then, the locking block 15 will pop out under the action of the first return spring 14 and return to its original position. At this time, the mass block 2 together with the hammer 1 will be constrained by the locking block 15 below the locking block 15, and the energy storage spring 4 is in the energy storage state.

[0058] Firing the hammer 1: Under the action of the triggering mechanism, the hammer 1 pops out. When the hammer 1 needs to be fired, the triggering motor 7 rotates to contract the locking block towing wire 9, dragging the locking block 15 to contract towards the inside of the locking block restraint cylinder 16 until the locking block 15 completely exits the mass block restraint cylinder 3. At this time, the restraint on the upper part of the mass block 2 is released, and the mass block 2 together with the hammer 1 quickly pops out under the action of the energy storage spring 4.

[0059] Impact de-icing: The popped-out hammer 1 impacts the impact block 23 and pushes the support rod 25 upward, pushing the ice-breaking plate 27 to impact the ice covering the surface of the wing skin 20. The ice is broken by mechanical vibration impact and blown away under the action of the airflow;

[0060] After de-icing, the ice-breaking plate 27 is re-embedded in the outer surface of the wing skin 20 under the action of the telescopic mechanism: After the de-icing action of the support rod module B is completed, the support rod 25 contracts towards the inside of the wing under the elastic restoring force of the second return spring 26 until the limiting block 24 contacts the support rod bracket 22, and the support rod 25 returns to its initial state. The ice-breaking plate 27 is retracted again and embedded in the groove on the surface of the wing skin 20.

[0061] The above are only the specific embodiments of the present invention, enabling those skilled in the art to understand or implement the present invention. Various modifications to these embodiments will be obvious to those skilled in the art. The general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention.

[0062] It should be understood that the present invention is not limited to the above-described content and can be modified and changed without departing from its scope. The scope of the present invention is only limited by the appended claims.

Claims

1. An aircraft deicing device, characterized in that: include: An actuating module (A) and a strut module (B) are distributed on the inner surface of a wing skin (20), wherein the actuating module (A) is mounted and fixed to a wing frame (28) via an actuating module fixing bracket (29), and the strut module (B) is mounted and fixed to the inner surface of the wing skin (20) via a strut bracket (25); The actuating module (A) comprises a hammer (1) and a force storage mechanism for providing impact force to the hammer (1), wherein the force storage mechanism completes force storage under the cooperation of a locking mechanism and causes the hammer (1) to pop out under the action of a trigger mechanism; the strut module (B) comprises an impact block (23), an icebreaker plate (27) and a telescopic mechanism located therebetween, wherein the icebreaker plate (27) is embedded on the outer surface of the wing skin (20), a gap is reserved between the impact block (23) and the hammer (1), and the length of the gap is less than the length of the hammer (1) extending out of the actuating module (A), so as to ensure that the hammer (1) can hit the impact block (23) when it pops out; During deicing, the hammer (1) is ejected under the action of the power storage mechanism and strikes the strike block (23); the strike block (23) drives the icebreaker plate (27) to extend under the action of the telescopic mechanism and strike the ice on the outer surface of the wing skin (20); the ice is broken by mechanical vibration and blown away under the action of airflow; after deicing is completed, the icebreaker plate (27) is retracted under the action of the telescopic mechanism and embedded in the outer surface of the wing skin (20).

2. The aircraft deicing device according to claim 1, characterized in that: The actuating module (A) further comprises a housing (17), wherein the housing (17) comprises a locking block constraint cylinder (16) and a mass block constraint cylinder (3) which are arranged closely together, and the hammer (1) is located at the top of the mass block constraint cylinder (3) in a free state and can extend out along an opening arranged at the top of the housing (17); The force storage mechanism comprises: a mass block (2) located in a mass block constraint cylinder (3) and a force storage motor (6) located below the mass block constraint cylinder (3); the upper surface of the mass block (2) is connected to the bottom of the hammer (1); a force storage spring (4) is arranged between the lower surface of the mass block (2) and the bottom of the mass block constraint cylinder (3); the lower surface of the mass block (2) is also connected to the force storage motor (6) via a mass block traction line (5); and the force storage motor (6) is located in a housing (17); The locking mechanism comprises: a locking block (15) located in a locking block constraint cylinder (16); a first return spring (14) is horizontally arranged between an end face a of the locking block (15) and an inner wall of the locking block constraint cylinder (16); the end face a of the locking block (15) is also connected to a trigger motor (7) via a locking block traction line (9); the trigger motor (7) is located in a housing (17); when subjected to a squeezing force from a horizontal direction, an inclined end face b of the locking block (15) can be retracted along the cylinder wall of the locking block constraint cylinder (16); and after the squeezing force disappears, the inclined end face b of the locking block (15) can be extended along the cylinder wall of the locking block constraint cylinder (16) under the action of the first return spring (14) to store force in the force storage mechanism.

3. The aircraft deicing device according to claim 2, characterized in that: The housing (17) also includes a vertically arranged lifting mechanism, and the locking block constraint cylinder (16) is lifted and lowered under the action of the lifting mechanism. The cylinder wall of the locking block constraint cylinder (16) is provided with an opening for facilitating the extension / retraction of the inclined end face b of the locking block (15).

4. The aircraft deicing device according to claim 3, characterized in that: The lifting mechanism comprises a lifting conveyor belt (13) vertically arranged in a shell (17) and located on the outer wall of a locking block constraint cylinder (16); the lifting conveyor belt (13) is connected to an output shaft of a lifting motor (8); and the lifting motor (8) is located in the shell (17).

5. The aircraft deicing device according to claim 4, characterized in that: The lifting motor (8) and the trigger motor (7) are both located below the locking block constraint cylinder (16).

6. The aircraft deicing device according to claim 2, characterized in that: An induction switch bracket (12) is fixed below the locking block (15), and a first induction switch (10) for detecting whether the mass block (2) is stuck by the locking block (15) and a second induction switch (11) for detecting whether the locking block (15) has completely exited the mass block restraining cylinder (3) are respectively installed on the induction switch bracket (12).

7. The aircraft deicing device according to claim 1, characterized in that: The strut module (B) comprises: a strut (25), a strut bracket (22) for fixing the strut (25) and providing a movement space for the strut (25), the strut bracket (22) being fixed to the inner surface of the wing skin (20) via a flange, the impact block (23) and the icebreaker plate (27) being respectively installed at both ends of the strut (25); the telescopic mechanism comprises a limit block (24) and a second return spring (26) arranged on the strut (25), the second return spring (26) being located between the limit block (24) and the icebreaker plate (27).

8. The aircraft deicing device according to claim 7, characterized in that: One end of the second return spring (26) is connected to the ice-breaking plate (27), and the other end is connected to the limit block (24).

9. The aircraft deicing device according to claim 1, characterized in that: The outer surface of the wing skin (20) is provided with a groove for facilitating the embedding of the icebreaker plate (27).

10. A deicing method using the aircraft deicing device according to any one of claims 1 to 9, characterized in that: Specifically include: Power storage: the actuating module (A) stores power under the joint action of the power storage mechanism and the locking mechanism; Firing hammer (1): under the action of the trigger mechanism, the hammer (1) pops out; Impact deicing: the ejected hammer (1) impacts the impact block (23) and pushes the support rod (25) to move upward, pushing the icebreaker plate (27) to impact the ice on the surface of the wing skin (20), breaking the ice through mechanical vibration impact and blowing it away under the action of airflow; After deicing is completed, the ice breaking plate (27) is retracted under the action of the telescopic mechanism and embedded into the outer surface of the wing skin (20).

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