A de-icing device for an aircraft

Abstract

This invention discloses a de-icing device for aircraft, relating to the field of aircraft de-icing technology. It includes a thermal vibration assembly comprising a housing and a main piezoelectric ceramic column. The main piezoelectric ceramic column is disposed inside the housing, with a heat insulation pad on top and a resistance heating element on top of the heat insulation pad. The heat insulation pad is in a two-tiered stepped shape, with several side cavities formed on the upper outer wall of the heat insulation pad. Secondary piezoelectric ceramic columns are disposed within these side cavities, and a pressure hammer is disposed on the inner top surface of each side cavity. The secondary piezoelectric ceramic columns are electrically connected to the resistance heating element. This device, through the thermal vibration assembly, utilizes the generation of localized ice gaps and a small amount of melt water, combined with repeated mechanical pulling on the ice layer, causing the ice gaps to expand rapidly in both the longitudinal and transverse directions. This significantly reduces the adhesion strength of the ice layer, quickly removing it. The secondary piezoelectric ceramic columns and the pressure hammer generate instantaneous current through compression, reducing unnecessary energy dissipation and accelerating ice gap formation.

Description

Technical Field

[0001] This invention relates to the field of aircraft de-icing technology, specifically to a de-icing device for aircraft. Background Technology

[0002] Aircraft icing is primarily caused by the impact of supercooled water droplets. The troposphere contains a wide variety of supercooled water droplets with temperatures below freezing but still in a liquid state. When the surface temperature of an aircraft falls below its freezing point, these droplets freeze instantly upon impacting the wings, nose, and tail, forming icing. Freezing rain, wet snow, and water vapor sublimation are also common contributing factors. Aircraft icing drastically alters its aerodynamic shape, increasing drag, decreasing lift, and potentially leading to stall, posing a significant threat to flight safety.

[0003] Existing aircraft de-icing technologies are mainly divided into two types: ground de-icing and onboard de-icing. Ground de-icing primarily relies on the physical removal and protection achieved by spraying ethylene glycol or propylene glycol-based anti-icing fluids. Onboard de-icing, based on energy form, mainly includes thermal de-icing and mechanical de-icing. Among these, thermal de-icing is the mainstream solution, including hot gas and electric heating, which removes the ice layer by heating the surface. Mechanical de-icing uses vibration and inertial force to remove ice.

[0004] However, ground de-icing cannot be performed during flight and is mostly a post-flight maintenance task. Thermal de-icing generally consumes a lot of energy, and its heat is easily dissipated, resulting in low energy utilization. Mechanical de-icing using inertial force has limited effectiveness for de-icing ice layers with high adhesion strength and has poor applicability. In summary, existing aircraft de-icing technologies generally suffer from the problem of being unable to achieve both de-icing efficiency and low energy consumption, which urgently needs to be improved. Summary of the Invention

[0005] The purpose of this invention is to provide a de-icing device for aircraft, in order to solve the problem mentioned in the background art that existing aircraft de-icing technologies generally cannot simultaneously achieve de-icing efficiency and low energy consumption.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a de-icing device for an aircraft, comprising a thermal vibration assembly, the thermal vibration assembly comprising a housing and a main piezoelectric ceramic column, the main piezoelectric ceramic column being disposed inside the housing, a heat insulation pad being disposed on the top of the main piezoelectric ceramic column, a resistance heating element being disposed on the top of the heat insulation pad, the heat insulation pad being in a two-layer stepped shape, a plurality of side cavities being formed on the upper outer side wall of the heat insulation pad, a secondary piezoelectric ceramic column being disposed in the side cavity, a pressure hammer being disposed on the inner top surface of the side cavity, the pressure hammer being in contact with the top surface of the secondary piezoelectric ceramic column, and the secondary piezoelectric ceramic column being electrically connected to the resistance heating element; It also includes a pulse power supply, which is electrically connected to the main piezoelectric ceramic column and the resistance heating element via a first wire and a second wire, respectively. The thermal vibration components are provided in several units and are arranged in an array on the inner side of the aircraft skin to remove the ice layer covering the outer side of the skin.

[0007] Preferably, the lower part of the heat insulation pad is rotatably connected to an inner rotating ring, and a column is provided at the top of the inner rotating ring and outside the piezoelectric ceramic column. A crossbar is provided at the top of the column facing away from the thermal vibration assembly.

[0008] Preferably, the side wall of the crossbar has several grooves.

[0009] Preferably, an L-shaped hollow rod is provided on the top surface of the heat insulation pad and above the piezoelectric ceramic column, and the L-shaped hollow rod is fastened to the top surface of the resistance heating element.

[0010] Preferably, the piezoelectric ceramic column and the resistance heating element are electrically connected by a third wire, which passes through the cavity inside the L-shaped hollow rod from the inner top surface of the side cavity and is electrically connected to the resistance heating element.

[0011] Preferably, a top recess is provided at the center of the top surface of the main piezoelectric ceramic column.

[0012] Preferably, the bottom surface of the outer casing has a bottom opening, through which the first wire passes out of the outer casing.

[0013] Preferably, several of the thermal vibration components are disposed on the wings of the aircraft.

[0014] Preferably, the wing includes a wing box and a skin, and the bottom surface of the outer shell is located on the outer side of the wing box.

[0015] Preferably, the lower part of the heat insulation pad is provided with an annular inner groove, and the inner rotating ring is disposed in the annular inner groove.

[0016] Compared with the prior art, the beneficial effects of the present invention are: 1. This device utilizes a thermal vibration assembly. The heat generated by the resistance heating element first forms a local ice gap and produces a small amount of melt water on the contact surface between the skin and the ice layer. The main piezoelectric ceramic column drives the skin to vibrate at high frequency, thereby applying repeated mechanical stretching to the ice layer. This causes the initial ice gap to expand rapidly in both the longitudinal and lateral directions, and melt water fills the space between the skin and the ice layer, greatly reducing the adhesion strength of the ice layer. Combined with the friction between the ice layer and the air during flight, the ice layer can be removed quickly. In addition, during the high-frequency vibration of the main piezoelectric ceramic column, the secondary piezoelectric ceramic column and the pressure hammer are squeezed and generate instantaneous current due to the piezoelectric effect. This current is fed back to the resistance heating element through the third wire and converted into heat energy. This realizes the recovery and utilization of the kinetic energy of the main piezoelectric ceramic column, which reduces unnecessary energy dissipation and accelerates the formation of ice gaps. Thus, while ensuring efficient de-icing, the overall energy consumption of the device is significantly reduced.

[0017] 2. This device uses several thermal vibration components arranged in an array on the skin. The density of these components can be adjusted according to the icing probability in different areas of the aircraft, thereby effectively controlling the overall weight while ensuring de-icing effect. Simultaneously, a pulse power supply activates the resistance heating element in the thermal vibration component in a specific area, causing the heat generated to melt the ice layer above, creating an ice gap. The main piezoelectric ceramic pillars in the thermal vibration components on both sides or around the ice gap begin high-frequency vibration, set to opposite initial vibration directions. Due to the opposite vibration directions, the ice layer above the ice gap is subjected to alternating shear stress, which easily generates ice cracks, thereby mechanically breaking up the thicker ice layer on the outer side of the skin. This collaborative ice-breaking mechanism has an ingenious structure and a significant ice-breaking effect, especially suitable for areas with thick ice layers, greatly improving the de-icing efficiency and reliability of this device under severe icing conditions. Attached Figure Description

[0018] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments in conjunction with the following drawings. It is obvious that the drawings described below are merely some embodiments of the present invention, and other drawings can be obtained by those skilled in the art based on these drawings without any inventive effort. Wherein: Figure 1 This is a three-dimensional structural diagram of the thermal vibration component in this invention; Figure 2 This is a front view of the thermal vibration assembly in this invention; Figure 3 This is a cross-sectional view of the thermal vibration assembly in this invention; Figure 4 This is a schematic diagram showing the connection between the pulse power supply and the thermal vibration component in this invention; Figure 5 This is a schematic diagram showing the installation of the thermal vibration component and the wing in this invention; Figure 6 This is a schematic diagram illustrating the working principle of the thermal vibration assembly in this invention. Figure 7 This is another schematic diagram of the working principle of the thermal vibration component in this invention; Figure 8 This is a schematic diagram showing the distribution of the thermal vibration component on the skin in this invention; Figure 9 This is another schematic diagram showing the distribution of the thermal vibration component on the skin in this invention.

[0019] In the diagram: 1. Main piezoelectric ceramic column; 101. Top notch; 2. Outer shell; 201. Bottom opening; 3. Heat insulation pad; 301. Side cavity; 302. Pressure hammer; 303. Inner rotating ring; 304. Column; 305. Crossbar; 306. Groove; 307. L-shaped hollow rod; 4. Resistance heating element; 5. Secondary piezoelectric ceramic column; 6. Wing; 601. Wing box; 602. Skin; 603. Ice layer; 7. Thermal vibration assembly; 8. Pulse power supply; 801. First conductor; 802. Second conductor. Detailed Implementation

[0020] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] In the description of this invention, it should be understood that the orientation descriptions, such as up, down, front, back, left, right, etc., are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0022] In the description of this invention, "several" means one or more, "more than" means two or more, "greater than," "less than," and "exceeding" are understood to exclude the stated number, while "above," "below," and "within" are understood to include the stated number. The use of "first" and "second" in the description is merely for distinguishing technical features and should not be construed as indicating or implying relative importance, or implicitly indicating the number of indicated technical features, or implicitly indicating the order of the indicated technical features.

[0023] Reference Figure 1-9 As shown, the present invention provides a technical solution for an aircraft de-icing device: A de-icing device for aircraft includes a thermal vibration assembly 7. The thermal vibration assembly 7 includes a housing 2 and a main piezoelectric ceramic column 1. The main piezoelectric ceramic column 1 is disposed inside the housing 2. A heat insulation pad 3 is disposed on the top of the main piezoelectric ceramic column 1. A resistance heating element 4 is disposed on the top of the heat insulation pad 3. The heat insulation pad 3 can be made of a high resistivity metal material, such as nickel-chromium alloy or titanium. The heat insulation pad 3 is in the form of a two-layer stepped structure. Several side cavities 301 are opened on the upper outer side wall of the heat insulation pad 3. A secondary piezoelectric ceramic column 5 is disposed in the side cavity 301. A pressure hammer 302 is disposed on the inner top surface of the side cavity 301. The pressure hammer 302 is in contact with the top surface of the secondary piezoelectric ceramic column 5. The secondary piezoelectric ceramic column 5 is electrically connected to the resistance heating element 4. It should be noted that the main piezoelectric ceramic column 1 can generate high-frequency vibration after being energized. Since the outer shell 2 is fitted on the outer and bottom surfaces of the main piezoelectric ceramic column 1, it restricts the circumferential and downward vibration of the main piezoelectric ceramic column 1, thus enabling the main piezoelectric ceramic column 1 to primarily vibrate upwards at high frequency. The heat insulation pad 3 not only blocks the heat generated by the resistance heating element 4 from being transferred to the main piezoelectric ceramic column 1 and the secondary piezoelectric ceramic column 5, preventing high temperature from affecting their piezoelectric performance, but also allows the heat generated by the resistance heating element 4 to be mainly transferred to the ice layer 603 on top, thereby improving the efficiency of melting the ice layer 603.

[0024] It should be noted that the secondary piezoelectric ceramic column 5 is inserted into the side cavity 301 to improve the stability of its relative position with the main piezoelectric ceramic column 1. When the main piezoelectric ceramic column 1 generates high-frequency vibration, the vibration is transmitted upward, causing the secondary piezoelectric ceramic column 5 to collide with the hammer 302. Due to the piezoelectric effect, the secondary piezoelectric ceramic column 5 will generate an instantaneous current. The instantaneous current is transmitted to the resistance heating element 4 through the third wire, which increases the instantaneous power of the resistance heating element 4 on the basis of the original heating and raises the instantaneous heating temperature. This further causes the ice layer 603 on the outside of the skin 602 where the thermal vibration component 7 is located to melt rapidly and form an ice gap, recovering the kinetic energy of the main piezoelectric ceramic column 1, thus greatly improving the energy utilization rate of this device.

[0025] This device also includes a pulse power supply 8, which is electrically connected to the main piezoelectric ceramic column 1 and the resistance heating element 4 via a first wire 801 and a second wire 802, respectively. It should be noted that during the operation of the thermal vibration assembly 7, when the main piezoelectric ceramic column 1 and the resistance heating element 4 are simultaneously connected to the pulse power supply 8, the resistance heating element 4 generates heat to heat the skin 602 in that area, creating an ice gap between the skin 602 and the outer ice layer 603. The main piezoelectric ceramic column 1 will then generate high-frequency vibration, causing the skin 602 in that area to follow suit. Since the ice layer 603 is solid, the high-frequency vibration of the skin 602 will repeatedly pull on its contact surface with the ice layer 603, forming a gap. At this time, due to the presence of melting ice in the ice gap... After being heated by the resistance heating element 4, the water continuously impacts the ice gap under the high-frequency vibration of the skin 602, accelerating the expansion of the ice gap. At the same time, the heated water will flow into the gap between the skin 602 and the ice layer 603, thereby expanding the lateral expansion of the ice gap. This allows water to fill the space between the skin 602 and the ice layer 603, greatly reducing the strength of the ice layer 603 adhering to the outside of the skin 602 and reducing the bonding force between the two. Combined with the high-frequency vibration of the skin 602 and the friction between the aircraft and the air during flight, the ice layer 603 is removed quickly and efficiently.

[0026] It should be further noted that this device can also adjust the output parameters of the pulse power supply 8 according to the actual thickness of the ice layer 603 on the outer side of the aircraft skin 602. This allows it to provide the matching heating power of the resistance heating element 4 as needed, and also adjust the vibration frequency of the main piezoelectric ceramic column 1 to adapt to different de-icing conditions. When the ice layer 603 is thin, only the vibration of the main piezoelectric ceramic column 1 can be activated, further reducing energy consumption; when the ice layer is thick, both the main piezoelectric ceramic column 1 and the resistance heating element 4 can be activated simultaneously to ensure de-icing effectiveness, thus adapting to the de-icing requirements of different flight scenarios. It should be noted that the method for adjusting the output parameters of the pulse power supply 8 is existing technology and will not be elaborated upon here.

[0027] Several thermal vibration components 7 are arranged in an array on the inner side of the aircraft skin 602 to remove the ice layer 603 covering the outer side of the skin 602. It should be noted that the array distribution of several thermal vibration components 7 can cover the icing-prone areas of the aircraft, avoiding de-icing blind spots. At the same time, the array density can be adjusted according to the icing probability of different areas of the aircraft, with the thermal vibration components 7 denser in areas with high icing probability and sparser in areas with low icing probability. This ensures the de-icing effect while further controlling the overall weight and energy consumption of the device, thereby balancing de-icing requirements with the aircraft's flight performance.

[0028] It should be noted that each thermal vibration component 7 is independently connected to the control circuit of the pulse power supply 8. When icing occurs in a local area, only the thermal vibration component 7 in the corresponding area can be activated for operation, without having to activate all the thermal vibration components 7, thus further reducing unnecessary energy consumption.

[0029] Reference Figure 8 and Figure 9 As shown in the figure, "negative" and "positive" represent that the initial vibration directions of the main piezoelectric ceramic column 1 in the thermal vibration assembly 7 are opposite, that is, one is an up-down-up vibration, and the other is a down-up-down-up vibration. "Flat" means that only the resistance heating element 4 in the thermal vibration assembly 7 in this area is activated, and the heat generated by its operation melts the ice layer 603 above it, creating an ice gap. Figure 7 As shown, at this time, the main piezoelectric ceramic column 1 in the thermal vibration component 7, represented by the "positive" and "negative" on both sides or around the thermal vibration component 7 in this area, begins to vibrate at high frequency. Since the vibration direction is opposite, the ice layer 603 is more likely to generate ice layer cracks above the ice gap, thereby breaking the ice layer 603 on the outside of the skin 602, which greatly improves the de-icing efficiency of this device. The structure is ingenious and the ice-breaking effect is significant. Its application advantage is even more prominent in areas where the ice layer 603 is thicker.

[0030] Reference Figure 1-9 As shown, in an optional embodiment: an inner rotating ring 303 is rotatably connected to the lower part of the heat insulation pad 3. A column 304 is provided at the top of the inner rotating ring 303 and outside the secondary piezoelectric ceramic column 5. A crossbar 305 is provided at the top of the column 304 facing away from the thermal vibration assembly 7. It should be noted that the arrangement of the inner rotating ring 303, the column 304, and the crossbar 305 allows the thermal vibration assembly 7 to press the secondary piezoelectric ceramic column 5 into the side cavity 301 by rotating the inner rotating ring 303 to offset the column 304 from the side cavity 301. Then, by rotating the inner rotating ring 303, the column 304 is positioned outside the secondary piezoelectric ceramic column 5, thereby blocking and limiting the secondary piezoelectric ceramic column 5, preventing the secondary piezoelectric ceramic column 5 from displacing during the high-frequency vibration of the main piezoelectric ceramic column 1, ensuring its normal operation. At the same time, it also simplifies the assembly of the thermal vibration assembly 7 and facilitates efficient production.

[0031] Reference Figure 1-9As shown, in an optional embodiment, the side wall of the crossbar 305 is provided with several grooves 306. It should be noted that the crossbar 305 is designed to increase the range of vibration of the skin 602 following the high-frequency vibration of the thermal vibration assembly 7, thereby increasing the contact surface between the repeatedly stretched skin 602 and the ice layer 603, further accelerating the lateral expansion of the ice gap, and thus improving the de-icing efficiency of the device. The grooves 306 also increase the friction between the crossbar 305 and the skin 602, thereby improving the efficiency of the high-frequency vibration of the thermal vibration assembly 7 in transmitting to the skin 602, effectively saving energy and improving the energy utilization efficiency of the device.

[0032] Reference Figure 1-9 As shown, in an optional embodiment: an L-shaped hollow rod 307 is provided on the top surface of the heat insulation pad 3, above the secondary piezoelectric ceramic column 5, and the L-shaped hollow rod 307 is fastened to the top surface of the resistance heating element 4. It should be noted that the setting of the L-shaped hollow rod 307 can not only further enhance the stability of the resistance heating element 4, but also prevent the resistance heating element 4 from shifting its position when the main piezoelectric ceramic column 1 vibrates at high frequency, or even cause its power circuit to be interrupted, which is conducive to the stable operation of this device.

[0033] Reference Figure 1-9 As shown, in an optional embodiment, the subpiezoelectric ceramic column 5 and the resistance heating element 4 are electrically connected via a third wire. The third wire passes through the cavity within the L-shaped hollow rod 307 from the inner top surface of the side cavity 301. It should be noted that this arrangement optimizes the wiring layout of the device, making it more streamlined. Simultaneously, it protects the third wire, preventing damage to the external third wire due to external forces when the device is installed on an aircraft, which could lead to poor contact and affect the stable operation of the device.

[0034] Reference Figure 1-9 As shown, in an optional embodiment, a top recess 101 is provided at the center of the top surface of the main piezoelectric ceramic column 1. It should be noted that when the main piezoelectric ceramic column 1 vibrates at high frequency after being energized, the top recess 101 can accommodate the minute deformations generated during the high-frequency vibration of the main piezoelectric ceramic column 1, reducing the probability of cracking and damage due to long-term repeated deformation, further improving the structural reliability of the main piezoelectric ceramic column 1, extending its service life, and thus extending the service life of this device.

[0035] Reference Figure 1-9As shown, in an optional embodiment: a bottom opening 201 is provided on the bottom surface of the housing 2, and the first wire 801 passes through the bottom opening 201 and exits the housing 2. It should be noted that passing the first wire 801 through the bottom opening 201 on the bottom surface of the housing 2 can conform to the overall installation layout of the device, making the wiring more neat and orderly, reducing the overall assembly difficulty of the device, and facilitating subsequent inspection and maintenance work.

[0036] Reference Figure 1-9 As shown, in an optional embodiment, several thermal vibration components 7 are disposed on the aircraft wing 6. It should be noted that the aircraft wing 6 is a key area for icing. This device can not only be installed on the wing 6, but also on other easily icing parts such as the nose and tail of the aircraft, adapting to the de-icing needs of different locations on the aircraft and expanding the applicability of this device.

[0037] Reference Figure 1-9 As shown, in an optional embodiment: the wing 6 includes a wing box 601 and a skin 602, with the bottom surface of the outer shell 2 located on the outer side of the wing box 601. It should be noted that the wing box 601, as the core load-bearing structure of the wing 6, has high structural strength and can provide a stable and reliable mounting foundation for this device. By directly abutting the bottom surface of the outer shell 2 against the outer side of the wing box 601, the structural rigidity of the wing box 601 can further limit the downward vibration of the main piezoelectric ceramic column 1, reduce the downward consumption of vibration energy, improve energy utilization, and ensure the response efficiency and final effect of the de-icing process.

[0038] Reference Figure 1-9 As shown, in one optional embodiment: the lower part of the heat insulation pad 3 has an annular inner groove, and the inner rotating ring 303 is disposed in the annular inner groove. It should be noted that this is a specific embodiment in which the lower part of the heat insulation pad 3 is rotatably connected to the inner rotating ring 303. The structure is simple and can achieve stable rotation of the inner rotating ring 303.

[0039] The working principle of this device will now be explained through its working process: When an ice layer 603 forms on the outer side of the aircraft skin 602, the pulse power supply 8 supplies power to the main piezoelectric ceramic column 1 and the resistance heating element 4 inside the thermal vibration assembly 7 through the first wire 801 and the second wire 802, respectively. In the initial stage of power-on, the resistance heating element 4 directly generates heat, which is transferred upward to the skin 602, causing its surface temperature to rise. This first leads to the formation of local ice gaps on the contact surface between the skin 602 and the ice layer 603, and produces a small amount of melted water. At the same time, the main piezoelectric ceramic column 1 generates high-frequency mechanical vibration under the excitation of the pulse power supply 8. Since the main piezoelectric ceramic column 1 is confined inside the shell 2, its circumferential and downward vibrations are constrained. Therefore, the vibration effect is mainly transmitted upward, ultimately causing the skin 602 in the corresponding area to generate high-frequency reciprocating vibration. This high-frequency vibration applies repeated mechanical pulling to the solid ice layer 603, further expanding the initial ice gaps longitudinally and laterally, allowing water to fill between the skin 602 and the ice layer 603. This greatly reduces the strength of the ice layer 603 adhering to the outside of the skin 602, reducing the bonding force between the two. Combined with the high-frequency vibration of the skin 602 and the friction between the aircraft and the air during flight, the ice layer 603 is removed quickly and efficiently.

[0040] It is important to note that the thermal vibration component 7 in this device can recover vibration energy, that is, recover the kinetic energy of the main piezoelectric ceramic column 1. This is because during the high-frequency vibration of the main piezoelectric ceramic column 1, it will be squeezed against the skin 602. The secondary piezoelectric ceramic column 5 will generate an instantaneous current due to the piezoelectric effect caused by the compression, which will be converted into electrical energy. Finally, it will be converted into heat energy through the resistance heating element 4 to achieve energy recovery. This not only reduces the unnecessary dissipation of vibration energy to other non-de-icing areas, but also improves the overall energy utilization efficiency of this device and greatly reduces the overall energy consumption requirements of this device. At the same time, the conversion into heat energy through the resistance heating element 4 significantly accelerates the formation of ice gaps between the skin 602 and the ice layer 603, thereby improving the de-icing efficiency of this device.

[0041] When several thermal vibration components 7 are distributed in an array on the skin 602 of the aircraft, the several thermal vibration components 7 have a cooperative de-icing capability. (Refer to...) Figure 8 and Figure 9 As shown, the thermal vibration component 7, represented by "flat", is activated by the pulse power supply 8, and the control circuit of the resistance heating element 4 is turned on, causing the heat generated by its operation to melt the ice layer 603 above it, creating an ice gap. (Refer to...) Figure 7As shown, at this time, the main piezoelectric ceramic column 1 in the thermal vibration component 7, represented by the "positive" and "negative" on both sides or around the thermal vibration component 7 in this area, begins to vibrate at high frequency. Since the vibration direction is opposite, the ice layer 603 is more likely to generate ice layer cracks above the ice gap, thereby breaking the ice layer 603 on the outside of the skin 602, which greatly improves the de-icing efficiency of this device. The structure is ingenious and the ice-breaking effect is significant. Its application advantage is even more prominent in areas where the ice layer 603 is thicker.

[0042] This device, through the setting of the thermal vibration component 7, utilizes the heat generated by the resistance heating element 4 to first form a local ice gap and generate a small amount of melt water on the contact surface between the skin 602 and the ice layer 603. The main piezoelectric ceramic column 1 drives the skin 602 to generate high-frequency vibration, thereby applying repeated mechanical stretching to the ice layer 603, causing the initial ice gap to expand rapidly in the longitudinal and transverse directions. Melt water fills the space between the skin 602 and the ice layer 603, greatly reducing the adhesion strength of the ice layer 603. Combined with the friction between the ice layer 603 and the air during flight, the ice layer 603 can be quickly removed. In addition, during the high-frequency vibration of the main piezoelectric ceramic column 1, the secondary piezoelectric ceramic column 5 and the pressure hammer 302 are squeezed and generate instantaneous current due to the piezoelectric effect. This current is fed back to the resistance heating element 4 through the third wire and converted into heat energy, realizing the recovery and utilization of the kinetic energy of the main piezoelectric ceramic column 1. This reduces unnecessary energy dissipation and accelerates the formation of ice gaps, thereby significantly reducing the overall energy consumption of the device while ensuring efficient de-icing.

[0043] This device uses several thermal vibration components 7 arranged in an array on the skin 602. The arrangement density can be adjusted according to the icing probability of different areas of the aircraft, thereby effectively controlling the overall weight while ensuring the de-icing effect. At the same time, the resistance heating element 4 in the thermal vibration component 7 in a specific area is activated by the pulse power supply 8. The heat generated melts the ice layer 603 above, creating an ice gap. The main piezoelectric ceramic columns 1 in the thermal vibration components 7 on both sides or around the ice gap start to vibrate at high frequency and are set to opposite initial vibration directions. Due to the opposite vibration directions, the ice layer 603 above the ice gap is subjected to alternating shear stress, which easily produces ice cracks, thereby mechanically breaking the thicker ice layer 603 on the outside of the skin 602. This collaborative ice-breaking mechanism has an ingenious structure and a significant ice-breaking effect. It is especially suitable for areas with thicker ice layers 603, greatly improving the de-icing efficiency and reliability of this device under harsh icing conditions.

[0044] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A de-icing device for aircraft, characterized in that, The device includes a thermal vibration assembly (7), which includes a housing (2) and a main piezoelectric ceramic column (1). The main piezoelectric ceramic column (1) is located inside the housing (2). A heat insulation pad (3) is provided on the top of the main piezoelectric ceramic column (1). A resistance heating element (4) is provided on the top of the heat insulation pad (3). The heat insulation pad (3) is in the form of a two-layer stepped structure. Several side cavities (301) are opened on the upper outer side wall of the heat insulation pad (3). A secondary piezoelectric ceramic column (5) is provided in the side cavity (301). A pressure hammer (302) is provided on the inner top surface of the side cavity (301). The pressure hammer (302) is in contact with the top surface of the secondary piezoelectric ceramic column (5). The secondary piezoelectric ceramic column (5) is electrically connected to the resistance heating element (4). It also includes a pulse power supply (8), which is electrically connected to the main piezoelectric ceramic column (1) and the resistance heating element (4) through a first wire (801) and a second wire (802), respectively. The thermal vibration components (7) are provided in several units and are arranged in an array on the inner side of the aircraft skin (602) to remove the ice layer (603) covering the outer side of the skin (602).

2. The de-icing device for an aircraft according to claim 1, characterized in that: The lower part of the heat insulation pad (3) is rotatably connected to an inner rotating ring (303). A column (304) is provided on the top of the inner rotating ring (303) and outside the piezoelectric ceramic column (5). A crossbar (305) is provided on the top of the column (304) facing away from the thermal vibration assembly (7).

3. A de-icing device for an aircraft according to claim 2, characterized in that: The side wall of the crossbar (305) is provided with several grooves (306).

4. A de-icing device for an aircraft according to claim 1, characterized in that: An L-shaped hollow rod (307) is provided on the top surface of the heat insulation pad (3) and above the sub-piezoelectric ceramic column (5), and the L-shaped hollow rod (307) is fastened to the top surface of the resistance heating element (4).

5. A de-icing device for an aircraft according to claim 4, characterized in that: The subpiezoelectric ceramic column (5) and the resistance heating element (4) are electrically connected by a third wire. The third wire passes through the cavity inside the L-shaped hollow rod (307) from the inner top surface of the side cavity (301) and is electrically connected to the resistance heating element (4).

6. A de-icing device for an aircraft according to claim 1, characterized in that: A top recess (101) is provided at the center of the top surface of the main piezoelectric ceramic column (1).

7. A de-icing device for an aircraft according to claim 1, characterized in that: The bottom surface of the outer casing (2) is provided with a bottom opening (201), through which the first wire (801) passes out of the outer casing (2).

8. A de-icing device for an aircraft according to claim 1, characterized in that: Several of the aforementioned thermal vibration components (7) are mounted on the wings (6) of the aircraft.

9. A de-icing device for an aircraft according to claim 8, characterized in that: The wing (6) includes a wing box (601) and a skin (602), and the bottom surface of the outer shell (2) is located on the outer side of the wing box (601).

10. A de-icing device for an aircraft according to claim 2, characterized in that: The lower part of the heat insulation pad (3) is provided with an annular inner groove, and the inner rotating ring (303) is disposed in the annular inner groove.

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