An anti-icing device and aircraft based on phase change energy storage

Abstract

The present invention provides an anti-icing device and an aircraft based on phase change energy storage, which relate to the technical field of anti-icing, and include a photothermal component, a shell and a phase change layer. The cavity inside the shell is filled with the phase change layer, and a heating component is buried in the phase change layer; the heating component includes a heating wire and a piezoelectric element connected to the heating wire, the piezoelectric element fits the inner wall of the cavity, and the piezoelectric element is used to receive the action of the phase change layer and the shell to generate electric energy to supply to the heating wire; in view of the shortcomings of existing anti-icing technologies such as environmental pollution, high energy consumption, and complex device systems, a phase change energy storage material is used to perform autonomous heat release at low temperatures, accumulate energy during normal operation, and release heat at low temperatures to increase the surface temperature of the aircraft to achieve anti-icing and ice melting, and at the same time, the electric heating component and the photothermal conversion component are combined to maximize the energy utilization efficiency, thereby achieving simple, environmentally friendly and efficient anti-icing.

Description

Technical Field

[0001] The present invention relates to the field of anti-icing technology, and in particular to an anti-icing device and an aircraft based on phase change energy storage. Background Art

[0002] During the flight of aircraft, ice often accumulates on the windward surface due to condensation of water vapor or impact of supercooled water droplets. Aircraft ice accumulation destroys the smooth flow field on the aircraft surface, increases flight resistance, reduces the reliability of flight control and aircraft lift, and seriously affects flight safety. Severe ice accumulation may occur on all exposed positive surfaces of the aircraft, such as wings, windshields, tail fins, radomes, etc. Therefore, how to effectively remove ice from the aircraft surface has become one of the problems that need to be solved urgently.

[0003] Some effective anti-icing technologies have been studied and developed, such as liquid anti-icing technology, electric heating anti-icing technology, gas heating anti-icing technology, etc. However, the above technologies still have many defects, such as: liquid anti-icing technology has a short effective time, large amount of anti-icing liquid is used and it pollutes the environment; electric heating and gas heating anti-icing technology consumes a lot of energy, the system device is complex and easy to re-icing. Therefore, it is difficult to solve the problem of ice accumulation on the surface of aircraft under the premise of less pollution and low energy consumption. Summary of the invention

[0004] The purpose of the present invention is to address the defects of the prior art and provide an anti-icing and de-icing device and aircraft based on phase change energy storage. The structure utilizes phase change energy storage materials to release heat autonomously at low temperatures, accumulates energy during normal operation, and releases heat at low temperatures to increase the surface temperature of the aircraft to achieve anti-icing and ice melting. At the same time, electric heating components and photothermal conversion components are combined to maximize energy utilization efficiency, thereby achieving simple, environmentally friendly and efficient anti-icing and de-icing.

[0005] The first object of the present invention is to provide an anti-icing device based on phase change energy storage, which adopts the following scheme:

[0006] It includes a photothermal component, a shell and a phase change layer. The cavity inside the shell is filled with the phase change layer, and a heating component is buried in the phase change layer. The heating component includes a heating wire and a piezoelectric element connected to the heating wire. The piezoelectric element is attached to the inner wall of the cavity. The piezoelectric element is used to receive the force of the phase change layer and the shell to generate electrical energy to supply to the heating wire.

[0007] Furthermore, a channel with openings at both ends is provided inside the shell, and both ends of the channel are respectively blocked with end covers to form a cavity inside the shell.

[0008] Furthermore, along the axial direction of the channel, the shell has a curved structure, and the end cover and the shell are installed via a seal and a connector.

[0009] Furthermore, the photothermal assembly includes a light-emitting layer, a light-absorbing layer and a photothermal conversion layer stacked in sequence, the photothermal conversion layer is attached to the outer surface of the shell, and heat is exchanged with the phase change layer through the shell.

[0010] Furthermore, the phase change layer is wrapped around the heating wire, and the phase change temperature of the phase change layer is higher than the freezing point.

[0011] Furthermore, the phase change layer adopts microcapsule phase change material, the microcapsule phase change material includes capsule wall and capsule core, the capsule core is phase change energy storage material, and the capsule core is sealed in the capsule wall.

[0012] Furthermore, the middle portion of the heating wire is bent to form a U-shaped structure, one end of the heating wire corresponding to the opening of the U-shaped structure is electrically connected to a piezoelectric element, and the other end extends along the cavity and is fixed to another piezoelectric element.

[0013] Furthermore, piezoelectric elements are provided at both ends of the cavity, the heating wires are divided into two groups, the heating wires in each group are arranged in sequence and electrically connected to the same piezoelectric element, and the heating wires corresponding to the two piezoelectric elements are arranged alternately in sequence.

[0014] A second object of the present invention is to provide an aircraft, comprising the anti-icing device based on phase change energy storage as described above.

[0015] Furthermore, the anti-icing device based on phase change energy storage is installed on the skin of the aircraft, the shell is attached to the skin frame, and is connected to the aircraft through a support frame.

[0016] Compared with the prior art, the present invention has the following advantages and positive effects:

[0017] (1) In view of the shortcomings of existing anti-icing and de-icing technologies, such as environmental pollution, high energy consumption, and complex device systems, a phase change energy storage material is used to release heat autonomously at low temperatures. It accumulates energy during normal operation and releases heat at low temperatures to increase the surface temperature of the aircraft to prevent icing and melt ice. At the same time, it combines electric heating components and photothermal conversion components to maximize energy utilization efficiency, thereby achieving simple, environmentally friendly, and efficient anti-icing and de-icing.

[0018] (2) When there is sufficient sunlight, the solar thermal module can improve the utilization rate of solar energy. The solar thermal module will convert solar energy into thermal energy, which can increase the surface temperature of the solar thermal module body and avoid the formation of ice accumulation. At the same time, the heat is transferred to the interior through the high thermal conductivity shell and absorbed by the phase change energy storage material, thereby realizing energy storage.

[0019] (3) When the ambient temperature is lower than the phase change point of the phase change energy storage material, the phase change energy storage material releases the stored heat and transfers the heat to the photothermal component and the shell, increasing the surface temperature. At this time, the phase change energy storage material gradually changes from liquid to solid.

[0020] (4) While the phase change material releases heat and changes from liquid to solid, the volume of the microcapsule phase change material that constitutes the phase change layer increases. On the one hand, it can promote the deformation of the shell, change the contact state between the shell and the attached ice layer, and release the adhesion of the ice layer. On the other hand, with the expansion of the phase change microcapsules and the generation of vibrations during flight, the piezoelectric element converts mechanical energy into electrical energy, causing the heating wire to begin to generate heat, which effectively solves the problem of insufficient heat in the phase change energy storage material and no light at night.

[0021] (5) When there is sufficient sunlight, the surface temperature of the photothermal conversion material layer of the photothermal component increases, and the phase change energy storage material reabsorbs heat to restore the state before the phase change, changing from solid to liquid while reducing its volume. This change realizes the recycling of the anti-icing device. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The accompanying drawings in the specification, which constitute a part of the present invention, are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0023] Figure 1 Schematic diagram of the external structure of the anti-icing device based on phase change energy storage in Embodiment 1 or 2 of the present invention;

[0024] Figure 2 Schematic diagram of the internal structure of the anti-icing device based on phase change energy storage in Embodiment 1 or 2 of the present invention;

[0025] Figure 3 Schematic diagram of the arrangement of the heating wires in Embodiment 1 or 2 of the present invention;

[0026] Figure 4 Schematic diagram of the structure of the microcapsule phase change material in Example 1 or 2 of the present invention;

[0027] Figure 5 Schematic diagram of the photothermal assembly in Embodiment 1 or 2 of the present invention;

[0028] Figure 6 It is a schematic diagram of the operation principle of the anti-deicing device in Embodiment 1 or 2 of the present invention;

[0029] Figure 7 It is a schematic diagram of the anti-icing device in Embodiment 1 or 2 of the present invention installed on the surface of an aircraft.

[0030] In the figure, 1-shell; 2-phase change layer; 3-photothermal component; 4-heating wire; 5-piezoelectric element; 6-electrode plate; 7-insulating thermal conductive layer; 8-sealing ring; 9-end cover; 10-connector; 11-electrode end of heating wire; 12-capsule wall; 13-capsule core; 14-luminescent layer; 15-light absorbing layer; 16-photothermal conversion layer; 17-wing inner skin; 18-support frame. DETAILED DESCRIPTION

[0031] Example 1

[0032] In a typical embodiment of the present invention, Figure 1-Figure 7 As shown, an anti-icing device based on phase change energy storage is provided.

[0033] like Figure 1 , Figure 6 The anti-icing and de-icing device based on phase change energy storage shown is used for the surface areas prone to ice formation, and uses the structure of phase change energy storage materials to release heat autonomously at low temperatures to achieve anti-icing and de-icing of the areas prone to ice formation, especially for the anti-icing and de-icing of the aircraft surface. It accumulates energy when there is sufficient light, and releases heat at low temperatures to increase the surface temperature of the aircraft to achieve anti-icing and ice melting. At the same time, it combines electric heating components and light-heat conversion components to maximize energy utilization efficiency, thereby achieving simple, environmentally friendly and efficient anti-icing and de-icing.

[0034] like Figure 1 The anti-icing device based on phase change energy storage shown in the figure mainly includes a photothermal component 3, a shell 1, a phase change layer 2 and a heating component. A channel with openings at both ends is provided inside the shell 1, and end covers 9 are respectively blocked at both ends of the channel to form a cavity inside the shell 1. The photothermal component 3 is located outside the cavity and connected to the shell 1, and the phase change layer 2 and the heating component are both located in the cavity and isolated from the outside.

[0035] The cavity inside the shell 1 is filled with phase change material, and the phase change material serves as the phase change layer 2. A heating component is buried in the phase change material, and the heating component can heat the phase change material; at the same time, the heating component includes a heating wire 4 and a piezoelectric element 5 connected to the heating wire 4, and the piezoelectric element 5 is attached to the inner wall of the cavity. The piezoelectric element 5 is used to receive the force of the phase change layer 2 and the shell 1 to generate electrical energy to supply to the heating wire 4.

[0036] In this process, while the phase change material releases heat and changes from liquid to solid, the volume of the microcapsule phase change material constituting the phase change layer 2 increases. As the phase change microcapsules expand and vibrations are generated during flight, the piezoelectric element 5 converts mechanical energy into electrical energy, causing the heating wire 4 to begin to generate heat, which effectively solves the problem of insufficient heat in the phase change energy storage material and lack of light at night.

[0037] like Figure 1 As shown, with regard to the detailed structure of the shell 1, a channel with openings at both ends is provided inside the shell 1, and end covers 9 are respectively blocked at both ends of the channel to form a cavity inside the shell 1; along the axial direction of the channel, the shell 1 is a curved structure, and the end cover 9 and the shell 1 are installed via a seal and a connector 10.

[0038] Combination Figure 2The shell 1 is made of a high thermal conductivity material, and its appearance is a curved hollow structure, and the hollow position is a channel; the shell 1 can be made of a non-metallic material with good thermal conductivity and can be molded into different shapes to adapt to the shape and installation requirements of different parts of the aircraft.

[0039] At the same time, the sealing member can be a sealing ring 8, and the connecting member 10 can be a threaded fastener such as a bolt. The sealing ring 8 is selected according to the shape of the end face of the shell 1 to prevent leakage. The high thermal conductivity shell 1, the end cover 9, and the sealing ring 8 are connected and fastened by threaded fasteners.

[0040] For the photothermal component 3 outside the housing 1, Figure 1 and Figure 5 As shown, it includes a light-emitting layer 14 , a light-absorbing layer 15 and a light-to-heat conversion layer 16 which are stacked in sequence. The light-to-heat conversion layer 16 is attached to the outer surface of the shell 1 and performs heat exchange with the phase change layer 2 through the shell 1 .

[0041] In addition, if Figure 7 As shown, the photothermal component 3 in this embodiment is laid on the outer surface of the high thermal conductivity shell 1. When the shell 1 is used as the aircraft skin, the photothermal component 3 is laid on the outer surface of the aircraft; the light-emitting layer 14 adopts a light-emitting material, the light-absorbing layer 15 adopts a light-absorbing material, and the photothermal conversion layer 16 adopts a photothermal conversion film.

[0042] The luminescent material may be a rare earth doped up-conversion luminescent material, such as a rare earth doped molybdate, which can convert light in the near-infrared region into visible light, thereby increasing the absorption range of the light absorbing layer 15 for the solar spectrum and enhancing the solar energy absorption capacity.

[0043] The material of the light absorbing layer 15 is CH3NH3PbI3 material, which has a high absorption efficiency in the visible light region and almost no absorption in the near-infrared region.

[0044] The photothermal conversion film can be a surface texture structure absorption film, a metal ceramic film or other solar photothermal conversion film.

[0045] like Figure 2 , Figure 4 As shown, the phase change layer 2 is wrapped around the heating wire 4 and fills the internal cavity of the shell 1. The phase change temperature of the phase change layer 2 is higher than the freezing point. The phase change layer 2 adopts a microcapsule phase change material. The microcapsule phase change material includes a capsule wall 12 and a capsule core 13. The capsule core 13 is a phase change energy storage material, and the capsule core 13 is sealed in the capsule wall 12.

[0046] When the ambient temperature is higher than the phase change temperature, the capsule core 13 of the phase change energy storage microcapsule absorbs heat, changes from solid to liquid, and shrinks in volume; when the ambient temperature is lower than the phase change temperature, it releases heat, changes from liquid to solid, and increases in volume.

[0047] In this embodiment, the phase change energy storage material is a microcapsule phase change material, and the diameter of the microcapsule is ≤100 microns; the microcapsule phase change material includes a capsule core 13 and a capsule wall 12. The capsule core 13 is an organic or composite phase change energy storage material with high energy storage density, and the capsule wall 12 is a flexible high thermal conductivity material. The encapsulation of the microcapsule can solve the leakage and corrosion problems of the material after the phase change.

[0048] like Figure 3 , Figure 5 As shown, the middle part of the heating wire 4 is bent to form a U-shaped structure, the opening end of the heating wire 4 corresponding to the U-shaped structure is electrically connected to a piezoelectric element 5, and the other end extends along the cavity and is fixed to another piezoelectric element 5; piezoelectric elements 5 are respectively provided at both ends of the cavity, and the heating wire 4 is divided into two groups, each group of heating wires 4 is arranged in sequence and electrically connected to the same piezoelectric element 5, and the heating wires 4 corresponding to the two piezoelectric elements 5 are arranged alternately in sequence.

[0049] In this embodiment, the heating component is an electric heating component, including a heating wire 4, a piezoelectric element 5, an insulating heat-conducting layer 7, and an insulating material. The heating component is fixed to the inside of a high thermal conductivity housing by an adhesive.

[0050] by Figure 1 and Figure 2 Taking the orientation in as an example, the piezoelectric element 5 is located at one end close to the end cover 9, the two piezoelectric elements 5 are respectively an upper piezoelectric element 5 and a lower piezoelectric element 5, the end of the heating wire 4 is provided with a heating wire electrode terminal 11, and the two end surfaces of the piezoelectric element 5 are respectively coated with electrode materials to form electrode plates 6, and the electrode plates 6 are connected to the heating wire electrode terminals 11 to form a circuit, and when the piezoelectric element 5 generates electrical energy, it is supplied to the heating wire 4 to make the heating wire 4 heat up.

[0051] Specifically, Figure 3 As shown, the heating wire 4 is U-shaped, and a plurality of heating wires are evenly distributed inside the high thermal conductivity housing 1. The two ends of the opening end of the heating wire 4 are respectively connected to the pole plates 6 of the upper piezoelectric element 5 or the lower piezoelectric element 5. The bent end of the heating wire 4 is mounted inside the piezoelectric element 5, and the piezoelectric element 5 plays a certain supporting role for it.

[0052] The open ends and bent ends of adjacent heating wires 4 are arranged in a staggered manner, so that the single-sided piezoelectric element 5 can work and generate heat when it is pressurized, and the double-sided piezoelectric element 5 can increase the effect of heat generation when it is pressurized.

[0053] An insulating material is provided between the bent end of the heating wire 4 and the corresponding fixed piezoelectric element 5, and the two are bonded together by adhesive; at the same time, an insulating heat-conducting layer 7 is provided on the surface of the heating wire 4, and the two are bonded together by adhesive to avoid direct contact between the heating wire 4 and the phase change layer 2.

[0054] In this embodiment, the adhesive is a high-temperature resistant epoxy adhesive, and the insulating material is a heat-resistant resin material; the insulating thermal conductive layer 7 can be made of a heat-resistant resin filled with a high thermal conductivity material (such as one or more of graphene oxide, Al2O3, Si3N4); the piezoelectric material layer is a piezoelectric ceramic or an organic piezoelectric material; the heating wire 4 can be made of materials such as nickel-chromium alloy with good plasticity and non-magnetism.

[0055] like Figure 6 As shown, the working principle of the above anti-icing device based on phase change energy storage is:

[0056] When there is sufficient sunlight, the photothermal component 3 can improve the utilization rate of solar energy. The photothermal component 3 will convert solar energy into thermal energy, which can increase the surface temperature of the photothermal component 3 and avoid ice accumulation. At the same time, the heat is transferred to the interior through the high thermal conductivity shell 1 and absorbed by the phase change energy storage material, thereby realizing energy storage.

[0057] At the same time, when the ambient temperature is lower than the phase change point of the phase change energy storage material, the phase change energy storage material releases the stored heat and transfers the heat to the photothermal component 3 and the shell 1, increasing the surface temperature. At this time, the phase change energy storage material gradually changes from liquid to solid.

[0058] In addition, while the phase change material releases heat and changes from liquid to solid, the volume of the microcapsule phase change material constituting the phase change layer 2 increases. As the phase change microcapsules expand and vibrations are generated during flight, the piezoelectric element 5 converts mechanical energy into electrical energy, causing the heating wire 4 to begin to generate heat, which effectively solves the problem of insufficient heat in the phase change energy storage material and lack of light at night.

[0059] It can be understood that when there is sufficient sunlight, the photothermal conversion material layer of the photothermal component 3 will increase its surface temperature and at the same time, the phase change energy storage material will reabsorb heat and restore its form before the phase change, changing from solid to liquid while reducing its volume. This change realizes the recycling of the anti-icing device.

[0060] Example 2

[0061] In another typical embodiment of the present invention, Figure 1-Figure 7 As shown, an aircraft is given.

[0062] like Figure 7 As shown, the aircraft includes the anti-icing device based on phase change energy storage as described above; at the same time, the anti-icing device based on phase change energy storage is installed on the inner skin 17 of the wing of the aircraft, the shell 1 is attached to the skin frame, and is connected to the aircraft through the support frame 18.

[0063] It can be used for windward surfaces such as wings, windshields, tail fins, and radomes of aircraft.

[0064] The aircraft adopts the anti-icing device based on phase change energy storage as in Example 1, and the anti-icing device based on phase change energy storage is configured according to the working requirements of the aircraft.

[0065] like Figure 1-Figure 7 For the detailed structure of the anti-icing device based on phase change energy storage, please refer to Example 1. Since the aircraft adopts the anti-icing device based on phase change energy storage provided in the above Example 1, the beneficial effects brought by the anti-icing device based on phase change energy storage on the aircraft refer to the corresponding parts in the above Example 1 and will not be repeated here.

[0066] For other structures of the aircraft not mentioned, existing structures may be adopted.

[0067] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An anti-icing device based on phase change energy storage, characterized in that: It includes a photothermal component, a shell and a phase change layer. The cavity inside the shell is filled with the phase change layer, and a heating component is buried in the phase change layer. The heating component includes a heating wire and a piezoelectric element connected to the heating wire. The piezoelectric element is attached to the inner wall of the cavity. The piezoelectric element is used to receive the force of the phase change layer and the shell to generate electrical energy to supply to the heating wire. The phase change layer adopts microcapsule phase change material, the microcapsule phase change material includes capsule wall and capsule core, the capsule core is phase change energy storage material, and the capsule core is sealed in the capsule wall; The photothermal assembly comprises a light-emitting layer, a light-absorbing layer and a photothermal conversion layer which are stacked in sequence. The photothermal conversion layer is attached to the outer surface of the shell and performs heat exchange with the phase change layer through the shell.

2. The anti-icing device based on phase change energy storage according to claim 1, characterized in that: A channel with openings at both ends is provided inside the shell, and end covers are respectively provided at both ends of the channel to form a cavity inside the shell.

3. The anti-icing device based on phase change energy storage according to claim 2, characterized in that: Along the axial direction of the channel, the shell is in a curved structure, and the end cover is installed with the shell via a sealing member and a connecting member.

4. The anti-icing device based on phase change energy storage according to claim 1, characterized in that: The phase change layer is wrapped around the electric heating wire, and the phase change temperature of the phase change layer is higher than the freezing point.

5. The anti-icing device based on phase change energy storage according to claim 1, characterized in that: The middle part of the heating wire is bent to form a U-shaped structure. One end of the heating wire corresponding to the opening of the U-shaped structure is electrically connected to a piezoelectric element, and the other end extends along the cavity and is fixed to another piezoelectric element.

6. The anti-icing device based on phase change energy storage according to claim 5, characterized in that: Piezoelectric elements are respectively arranged at both ends of the cavity, and the heating wires are divided into two groups. The heating wires in each group are arranged in sequence and are electrically connected to the same piezoelectric element, and the heating wires corresponding to the two piezoelectric elements are arranged alternately in sequence.

7. An aircraft, characterized in that: It comprises an anti-icing device based on phase change energy storage as described in any one of claims 1-6.

8. The aircraft according to claim 7, characterized in that The anti-icing device based on phase change energy storage is installed on the skin of the aircraft, the shell is attached to the skin frame, and is connected to the aircraft through a support frame.

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