CN109841692B - Thermal management system for solar aircraft, solar aircraft and thermal management method - Google Patents
Thermal management system for solar aircraft, solar aircraft and thermal management method Download PDFInfo
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Abstract
公开了用于太阳能飞机的热管理系统、太阳能飞机及热管理方法，热管理系统包括太阳能电池和布置在太阳能电池上的辐射冷却薄膜，太阳能电池铺设于太阳能飞机的上表面以吸收紫外光和可见光以转化为电能，用于透过紫外光和可见光的辐射冷却薄膜包括表层和至少一层底层，表层经由半导体材料聚合或经由高透过率材料与纳米颗粒掺杂而成，底层布置在太阳能电池和表层之间，底层包括高透过率材料，方法包括以下步骤，太阳光透过辐射冷却薄膜被太阳能电池吸收，一部分紫外光与可见光转化为电能，另一部分能量转化为热能，辐射冷却薄膜辐射热能的一部分用于降低太阳能表面温度，剩余未被辐射冷却薄膜辐射的热能可通过导热储存于机翼方腔内的相变材料中。
Disclosed are a thermal management system for a solar aircraft, a solar aircraft and a thermal management method, the thermal management system includes a solar cell and a radiative cooling film arranged on the solar cell, the solar cell is laid on the upper surface of the solar aircraft to absorb ultraviolet light and visible light In order to convert into electrical energy, the radiation cooling film for transmitting ultraviolet light and visible light includes a surface layer and at least one bottom layer. The surface layer is polymerized by a semiconductor material or doped with nanoparticles through a high transmittance material. Between the bottom layer and the surface layer, the bottom layer includes a high transmittance material. The method includes the following steps: sunlight is absorbed by the solar cell through the radiation cooling film, part of the ultraviolet light and visible light is converted into electrical energy, and the other part of the energy is converted into thermal energy, and the radiation cooling film radiates A part of the thermal energy is used to reduce the surface temperature of the solar energy, and the remaining thermal energy not radiated by the radiative cooling film can be stored in the phase change material in the square cavity of the wing through heat conduction.
Description
Technical Field
The invention relates to the field of thermal management of solar aircrafts, in particular to a thermal management system for a solar aircraft, the solar aircraft and a thermal management method.
Background
Due to the unique advantages of military aspects such as border patrol, reconnaissance, communication relay and electronic countermeasure and famous aspects such as atmospheric research, weather forecast, environment and disaster monitoring, crop remote measurement, traffic control, telecommunication and television service, natural protection area monitoring, foreign planet detection and the like, the solar aircrafts and related technologies thereof are researched by developed countries such as America, Swiss, Russia and the like at the end of the last century.
However, because of flight environment and energy utilizationDue to the particularity of the form, the solar airplane is decomposed due to large thermal stress and deformation in flight. Most of solar aircrafts work in stratosphere, the atmospheric environment temperature is about minus 60 ℃ to minus 50 ℃, however, the temperature of a solar panel laid on the surface of a wing can reach plus 60 ℃, so that the working efficiency of the solar panel and internal electronic components thereof is greatly reduced, the thermal stress and deformation are easily increased due to huge temperature difference and temperature fluctuation, and the service life of mechanical components is shortened. And the air of the stratosphere is thin, the heat convection capability of the solar cell panel and the outside is extremely weak, and is only about 5W/(m)2K), thermal management of the solar aircraft is particularly important.
There have been many embodiments for solar aircraft thermal management. For example, in patents CN 201110119982, CN 201410485989.X, etc., a complementary scheme of thermoelectric generation and solar energy is proposed to control heat, but the purpose of thermoelectric generation is contradictory to thermal management, thermoelectric generation needs to maintain a large temperature difference between two ends of thermoelectric material, and thermal management and the mentioned thermal control technology need to reduce the temperature difference. In addition, due to the limitation of power supply capacity, all components of the solar aircraft have very strict requirements on weight indexes, and the traditional mode and design idea of adding thermoelectric materials and control systems thereof cannot meet the requirements on the indexes at all.
The high-altitude medium vacuum degree is large, the environment temperature is low, the convection heat dissipation condition is severe, the temperature of the solar cell panel is reduced due to the overall consideration of the system, and the stability of the temperature of the solar airplane system is improved, so that the system has great significance.
The above information disclosed in this background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not form the prior art that is already known in this country to a person of ordinary skill in the art.
Disclosure of Invention
In view of the above problems, it is an object of the present invention to provide a thermal management system for a solar aircraft, a solar aircraft and a thermal management method, which overcome the above disadvantages of the prior art.
The purpose of the invention is realized by the following technical scheme.
A thermal management system for a solar powered aircraft includes,
a solar cell laid on an upper surface of the solar aircraft to absorb ultraviolet light and visible light to convert into electric energy; and
a radiation cooling film disposed on the solar cell, the radiation cooling film for transmitting ultraviolet light and visible light including,
a surface layer formed by polymerizing a semiconductor material or doping nanoparticles with a high-transmittance material, the surface layer having a micro-nano structure,
at least one bottom layer disposed between the solar cell and the top layer, the bottom layer comprising a high transmittance material.
In the thermal management system for the solar airplane, the surface layer has high transmission rate of ultraviolet light and visible light and high absorption/emissivity of 8-13 mu m infrared light, and the thickness is 1/2, 3/2 or 5/2 times of the optical resonance wavelength of the material.
In the thermal management system for the solar airplane, the radiation cooling film has high ultraviolet and visible light transmittance and high 8-13 mu m infrared light absorption/emissivity.
In the thermal management system for the solar airplane, the thermal management system further comprises an energy storage unit connected with the solar battery and a temperature sensor for measuring the temperature of the solar battery.
According to one aspect of the present invention, a solar powered aircraft includes,
a body;
a wing connected to the fuselage, a solar cell for absorbing ultraviolet light and visible light to convert into electric energy being laid on the upper surface of the wing, a radiation cooling film for transmitting the ultraviolet light and the visible light being arranged on the solar cell, the radiation cooling film including,
a surface layer formed by polymerizing a semiconductor material or doping nanoparticles with a high-transmittance material,
at least one bottom layer disposed between the solar cell and the top layer, the bottom layer comprising a high transmittance material.
In the solar airplane, the wings comprise cavities distributed along the central line of the cross sections of the wings, phase-change materials are filled in the cavities, and the solar cells are laid on the cavities.
In the solar airplane, the cavity is a rectangular square cavity which is arranged along the central line of the section of the wing and gradually decreases from the blunt head to the sharp tail, and the wing control mechanism and the landing gear penetrate through the cavity.
The solar airplane is characterized in that the head of the airplane body is of an oval structure, an energy storage unit and a control system are placed inside the solar airplane, the control system comprises a sensor, a controller and a mechanical transmission mechanism, the sensor comprises a temperature sensor for measuring the temperature of a solar cell on the upper surface of the wing and a speed sensor for measuring the flying speed of the front end and the rear end of the airplane body, the controller comprises a general processor, a digital signal processor, an Application Specific Integrated Circuit (ASIC) or a Field Programmable Gate Array (FPGA), the mechanical transmission mechanism is a connecting rod or a hydraulic mechanism, the cross section of the wing is of a streamline structure, and a propeller arranged at the position of the near-nose of the wing comprises a paddle and a driving motor positioned.
In the solar airplane, the solar airplane further comprises an empennage, the empennage comprises,
a parallel rear wing having a solar cell laid on an upper surface thereof, the parallel rear wing being configured to be movable up and down to adjust an incident angle of solar radiation with respect to the solar cell, a radiation cooling film disposed on the solar cell, the radiation cooling film for transmitting ultraviolet light and visible light including,
a surface layer formed by polymerizing a semiconductor material or doping nanoparticles with a high-transmittance material, the surface layer further having a micro-nano structure,
at least one bottom layer disposed between the solar cell and the skin layer, the bottom layer comprising a high transmittance material; and
and the vertical tail wing is connected with the control system through a mechanical transmission mechanism and can deflect relative to the fuselage.
According to a further aspect of the invention, a method for thermal management of a solar aircraft using said thermal management system comprises the following steps,
the first step, sunlight is absorbed by the solar cell through the radiation cooling film, wherein, a part of ultraviolet light and visible light are converted into electric energy, and the other part of energy is converted into heat energy,
a second step of radiating a portion of the thermal energy by a radiation cooling film to reduce the solar surface temperature,
and thirdly, storing the residual heat energy which is not radiated by the radiation cooling film in the phase change material in the square cavity of the wing through heat conduction.
Compared with the prior art, the invention has the beneficial effects that:
the solar cell can carry out grading treatment on the energy of different wavelengths of the solar light, and stores a part of heat energy, thereby ensuring the generating efficiency of the cell and stably reducing the working temperature of the cell. By the method, the power generation efficiency of the solar cell can be improved, the thermal stress of the airplane is reduced, and the service life is prolonged, so that the purposes of light weight, high efficiency and long-time flight are achieved.
The above description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly apparent, and to make the implementation of the content of the description possible for those skilled in the art, and to make the above and other objects, features and advantages of the present invention more obvious, the following description is given by way of example of the specific embodiments of the present invention.
Drawings
Various other advantages and benefits of the present invention will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort. Also, like parts are designated by like reference numerals throughout the drawings.
In the drawings:
FIG. 1 is a schematic structural diagram of a thermal management system for a solar aircraft according to one embodiment of the present invention;
FIG. 2 is a schematic top view of a solar aircraft thermal management system according to one embodiment of the invention;
FIG. 3 is a schematic side view of a solar aircraft thermal management system according to one embodiment of the invention;
FIG. 4 is a schematic cross-sectional view of a wing structure of a thermal management system for a solar aircraft according to one embodiment of the invention;
FIG. 5 is a schematic diagram of the steps of a thermal management method according to one embodiment of the present invention.
The invention is further explained below with reference to the figures and examples.
Detailed Description
Specific embodiments of the present invention will be described in more detail below with reference to fig. 1 to 5. While specific embodiments of the invention are shown in the drawings, it should be understood that the invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
It should be noted that certain terms are used throughout the description and claims to refer to particular components. As one skilled in the art will appreciate, various names may be used to refer to a component. This specification and claims do not intend to distinguish between components that differ in name but not function. In the following description and in the claims, the terms "include" and "comprise" are used in an open-ended fashion, and thus should be interpreted to mean "include, but not limited to. The description which follows is a preferred embodiment of the invention, but is made for the purpose of illustrating the general principles of the invention and not for the purpose of limiting the scope of the invention. The scope of the present invention is defined by the appended claims.
For the purpose of facilitating understanding of the embodiments of the present invention, the following description will be made by taking specific embodiments as examples with reference to the accompanying drawings, and the drawings are not to be construed as limiting the embodiments of the present invention.
For a better understanding, fig. 1 is a schematic structural view of a thermal management system for a solar aircraft according to one embodiment of the invention, a thermal management system for a solar aircraft comprising,
a solar cell 7 laid on the upper surface of the solar aircraft to absorb ultraviolet light and visible light to convert into electric energy; and
a radiation cooling film 8 disposed on the solar cell 7, the radiation cooling film 8 for transmitting ultraviolet light and visible light including,
a surface layer 9 formed by polymerizing a semiconductor material or doping a high-transmittance material and nanoparticles, and having a micro-nano structure such as a square frame, a sphere, a honeycomb and the like to improve the high absorption/emission rate of infrared light of 8-13 μm,
at least one underlayer 10, said underlayer 10 being arranged between the solar cell 7 and the skin layer 9, said underlayer 10 comprising a high transmittance material.
In one embodiment of the described thermal management system for a solar aircraft, the skin 9 has a high transmission of ultraviolet and visible light and a high absorption/emission of 8-13 μm infrared light, with a thickness of 1/2, 3/2 or 5/2 times the optical resonance wavelength of the material.
In one embodiment of the described thermal management system for a solar aircraft, the radiant cooling film 8 has a high transmission of ultraviolet and visible light and a high absorption/emission of 8-13 μm infrared light.
In an embodiment of the thermal management system for a solar aircraft, the thermal management system further comprises an energy storage unit connected to the solar cell 7 and a temperature sensor for measuring the temperature of the solar cell 7.
To further understand the present invention, and in one embodiment, fig. 2 is a schematic top view of a solar aircraft thermal management system, in accordance with one embodiment of the present invention, a solar aircraft thermal management system comprising,
the upper surface of the wing 1 is paved with a solar cell 7 which absorbs ultraviolet and visible light to provide electric energy for the airplane,
a radiation cooling film 8 is laid on a solar cell 7, the film is of a two-layer or multi-layer structure, a surface layer 9 is formed by polymerizing various semiconductor materials or doping high-transmittance materials and nano particles, has high transmittance of ultraviolet light and visible light and high absorption/emissivity of infrared light of 8-13 mu m, the thickness is 1/2, 3/2 and 5/2 times of the optical resonance wavelength of the material, the next layer or layers are made of high-transmittance materials, the whole film has high transmittance of ultraviolet light and visible light and high absorption/emissivity of infrared light of 8-13 mu m,
the section of the wing 1 is in a streamline design, rectangular cavities with the sizes decreasing from a blunt head to a sharp tail are distributed in the wing 1 along the central line of the section, an operating mechanism and a landing gear of the wing 1 penetrate through the cavities, a certain amount of phase change materials are filled in the cavities, the temperature of the wing 1 is further stabilized,
the tail ends of the wings 1 at the two sides can move up and down to respond to the flying modes of takeoff, landing and the like of the airplane and the airflow disturbance in the flying process,
the propeller 2 is arranged at the position of the wing 1 close to the nose and consists of three or more blades, the driving motor is arranged in the wing 1 behind the driving motor,
the head of the machine body 3 is elliptical, a storage battery and a solar airplane control system are arranged in the machine body, and the control system is composed of a sensor, a controller and a mechanical transmission mechanism. The sensors comprise temperature and speed sensors distributed on the upper surface and the front and rear ends of the wing 1, the controller comprises a general processor, a digital signal processor, an Application Specific Integrated Circuit (ASIC) or a Field Programmable Gate Array (FPGA), the mechanical transmission mechanism is a connecting rod or a hydraulic mechanism,
the tail wing consists of a left parallel tail wing 4, a right parallel tail wing 4 and a vertical tail wing 5,
the solar cell 7 plate is laid on the upper surface of the parallel tail wing 4, the parallel tail wing 4 can move up and down to adjust the incident angle of solar radiation and ensure the generating efficiency of the solar cell 7,
the vertical tail wing 5 is connected with a control system of the airplane body 3 through a mechanical transmission mechanism, and the balance aerodynamic force of airplane flight is provided by adjusting the deflection angle of the vertical tail wing 5.
Fig. 3 is a schematic side view of a solar aircraft thermal management system, a solar aircraft including,
a body 3;
the aircraft comprises a wing 1 connected with the fuselage 3, a solar cell 7 for absorbing ultraviolet light and visible light and converting the ultraviolet light and the visible light into electric energy is paved on the upper surface of the wing 1, a radiation cooling film 8 for transmitting the ultraviolet light and the visible light is arranged on the solar cell 7, the radiation cooling film 8 comprises,
a surface layer 9, which is formed by polymerizing a semiconductor material or doping nanoparticles with a high-transmittance material,
at least one underlayer 10, said underlayer 10 being arranged between the solar cell 7 and the skin layer 9, said underlayer 10 comprising a high transmittance material.
In an embodiment of the solar aircraft, fig. 4 is a schematic cross-sectional view of a wing structure of a thermal management system for a solar aircraft according to an embodiment of the present invention, where the wing 1 includes a cavity 6 arranged along a center line of a cross-section thereof, the cavity is filled with a phase change material, and a solar cell 7 is laid on the cavity 6.
In one embodiment of the solar airplane, the cavity 6 is a rectangular square cavity 6 which is arranged along the central line of the section of the wing 1 and gradually decreases from a blunt head to a sharp tail, and an operating mechanism and a landing gear of the wing 1 penetrate through the square cavity.
In one embodiment of the solar airplane, the head of the airplane body 3 is of an oval structure, an energy storage unit and a control system are placed in the airplane body, the control system comprises a sensor, a controller and a mechanical transmission mechanism, the sensor comprises a temperature sensor which is arranged on the upper surface of the wing 1 and used for measuring the temperature of the solar cell 7 and a speed sensor which is arranged at the front end and the rear end of the airplane body 3 and used for measuring the flight speed, the controller comprises a general processor, a digital signal processor, an Application Specific Integrated Circuit (ASIC) or a Field Programmable Gate Array (FPGA), the mechanical transmission mechanism is a connecting rod or a hydraulic mechanism, the cross section of the wing 1 is of a streamline structure, and a propeller 2 which is arranged at the position, close to the nose, of the.
In one embodiment of the solar powered aircraft, the solar powered aircraft further comprises an empennage, the empennage comprising,
a parallel rear wing 4 on the upper surface of which a solar cell 7 is laid, the parallel rear wing 4 being configured to be movable up and down to adjust an incident angle of solar radiation with respect to the solar cell 7, a radiation cooling film being disposed on the solar cell, the radiation cooling film for transmitting ultraviolet light and visible light including,
a surface layer formed by polymerizing a semiconductor material or doping nanoparticles with a high-transmittance material,
at least one bottom layer disposed between the solar cell and the skin layer, the bottom layer comprising a high transmittance material; and
a vertical tail 5, which is connected to the control system via a mechanical transmission, the vertical tail 5 being deflectable relative to the fuselage 3.
To further understand the present invention, in one embodiment, a solar powered aircraft includes,
the upper surface of the wing 1 is paved with a solar cell 7 which absorbs ultraviolet and visible light to provide electric energy for the airplane,
as shown in fig. 3, a radiation cooling film 8 is laid on the solar cell 7, the film has a two-layer or multi-layer structure, the surface layer 9 is formed by polymerizing a plurality of semiconductor materials or doping high-transmittance materials and nanoparticles, has high transmittance of ultraviolet light and visible light, high absorption/emissivity of 8-13 μm infrared light, and has a thickness of 1/2, 3/2 and 5/2 times of the resonant wavelength of the material, the next layer or layers are formed by high-transmittance materials, the whole film has high transmittance of ultraviolet light and visible light, high absorption/emissivity of 8-13 μm infrared light,
the section of the wing 1 is in a streamline design, and provides larger lift force under the same wind speed,
rectangular square cavities 66 with the size decreasing from a blunt head to a sharp tail are distributed in the wing 1 along the central line of the section, the cavity penetrates through the wing 1 operating mechanism and the landing gear and is filled with a certain amount of phase change material to further stabilize the temperature of the wing 1,
the tail ends of the wings 1 at the two sides can move up and down to respond to the flying modes of takeoff, landing and the like of the airplane and the airflow disturbance in the flying process,
the propeller 23 is arranged at the position of the wing 1 close to the nose and consists of three or more blades, the driving motor is arranged in the wing 1 behind the driving motor,
the head of the machine body 3 is in an elliptical shape, a storage battery and a solar airplane control system are arranged in the machine body, and the control system is composed of a sensor, a controller and a mechanical transmission mechanism. The sensors comprise temperature and speed sensors distributed on the upper surface and the front and rear ends of the wing 1, the controller comprises a general processor, a digital signal processor, an Application Specific Integrated Circuit (ASIC) or a Field Programmable Gate Array (FPGA), the mechanical transmission mechanism is a connecting rod or a hydraulic mechanism,
the tail wing consists of a left parallel tail wing 4, a right parallel tail wing 4 and a vertical tail wing 5,
the solar cell 7 plate 1 is laid on the upper surface of the parallel tail wing 4, the parallel tail wing 4 can move up and down to adjust the incident angle of solar radiation and ensure the generating efficiency of the solar cell 7,
the vertical tail wing 5 is connected with a control system of the airplane body 3 through a mechanical transmission mechanism, and the balance aerodynamic force of airplane flight is provided by adjusting the deflection angle of the vertical tail wing 5.
Fig. 5 is a schematic representation of the steps of a thermal management method according to one embodiment of the present invention, a solar aircraft thermal management method utilizing the thermal management system comprising the steps of,
in a first step S1, sunlight is absorbed by the solar cell 7 through the radiant cooling film 8, wherein a portion of the ultraviolet light and visible light is converted into electrical energy, another portion of the energy is converted into thermal energy,
a second step S2, the radiant cooling film 8 radiates a portion of the thermal energy to reduce the solar surface temperature,
in a third step S3, the remaining thermal energy not radiated by the radiation cooling film 8 is stored in the phase change material in the square cavity 6 of the airfoil 1 by conduction.
To further understand the present invention, in one embodiment, a solar aircraft thermal management method comprises:
sunlight penetrates through the wing 1 and the radiation cooling film 8 attached to the upper surface of the empennage and is absorbed by the photovoltaic cell. Most ultraviolet light and visible light are converted into electric energy and stored in a storage battery of the machine body 3 for use, and the other part of energy is converted into heat energy due to the non-radiative compound effect of the semiconductor;
the radiation cooling film 8 has high absorption/emissivity in infrared light of 8-13 microns, and directly exchanges radiation heat with a cosmic cold source (4K) by radiating the infrared light through an atmospheric window, so that most of heat energy generated by the photothermal effect of the solar cell 7 is radiated in time, and the surface temperature of the solar cell 7 is greatly reduced;
another part of heat energy generated by the photothermal effect of the solar cell 7 is stored in the phase-change material filled in the rectangular square cavity 6 arranged along the central line in the wing 1 through heat conduction, so that the temperature fluctuation of the solar cell 7 plate and the whole airplane is further reduced.
According to the technical scheme, the whole solar aircraft thermal management system is in a streamline design, the wings 1 and the empennage can move in a certain range, aerodynamic resistance and frictional heat in the flight process of the aircraft can be reduced, and the solar aircraft thermal management system has better aerodynamic balance.
According to the technical scheme, the solar airplane heat management method can be used for carrying out grading treatment on the energy of different wavelengths of the solar light, storing a part of heat energy, and stably reducing the working temperature of the battery while ensuring the power generation efficiency of the battery. By the method, the power generation efficiency of the solar cell 7 can be improved, the thermal stress of the airplane is reduced, and the service life is prolonged, so that the purposes of light weight, high efficiency and long-time flight are achieved.
According to the invention, through optimizing the structure and performance of the solar airplane, the purposes of efficiently utilizing solar energy, radiating and storing heat energy while generating electricity and storing electricity are achieved; a novel solar airplane heat management system is provided and designed, so that the overall temperature fluctuation is reduced, and the deflection angle of the wing 1 can be regulated and controlled according to the environment, so that the aerodynamic resistance in the flying process is reduced, the aerodynamic balance is improved, and efficient, stable and long-time uninterrupted flight is achieved.
Industrial applicability
The thermal management system for the solar aircraft, the solar aircraft and the separation method can be manufactured and used in the field of aircraft.
The foregoing describes the general principles of the present application in conjunction with specific embodiments, however, it is noted that the advantages, effects, etc. mentioned in the present application are merely examples and are not limiting, and they should not be considered essential to the various embodiments of the present application. Furthermore, the foregoing disclosure of specific details is for the purpose of illustration and description and is not intended to be limiting, since the foregoing disclosure is not intended to be exhaustive or to limit the disclosure to the precise details disclosed.
The foregoing description has been presented for purposes of illustration and description. Furthermore, the description is not intended to limit embodiments of the application to the form disclosed herein. While a number of example aspects and embodiments have been discussed above, those of skill in the art will recognize certain variations, modifications, alterations, additions and sub-combinations thereof.
Claims (6)
1. A thermal management system for a solar aircraft, comprising,
the solar cell is laid on the upper surface of the solar airplane to absorb ultraviolet light and visible light to be converted into electric energy, wherein the wings of the solar airplane comprise cavities distributed along the central line of the cross section of the wings, phase-change materials are filled in the cavities, and the solar cell is laid on the cavities; and
a radiation cooling film disposed on the solar cell, the radiation cooling film having high ultraviolet and visible light transmittance and high 8-13 μm infrared light absorption/emission rate, the radiation cooling film for transmitting ultraviolet light and visible light including,
a surface layer formed by polymerizing a semiconductor material or doping a high-transmittance material and nanoparticles, wherein the surface layer has a micro-nano structure, the thickness of the micro-nano structure is 1/2, 3/2 or 5/2 times of the optical resonance wavelength of the material, the surface layer has high transmittance of ultraviolet light and visible light and high absorption/emissivity of 8-13 mu m infrared light,
at least one bottom layer disposed between the solar cell and the top layer, the bottom layer comprising a high transmittance material,
the thermal management system further comprises an energy storage unit connected with the solar battery and a temperature sensor for measuring the temperature of the solar battery.
2. A solar powered aircraft, comprising a plurality of solar powered aircraft,
a body;
a wing connected to the fuselage, a solar cell for absorbing ultraviolet light and visible light to convert into electric energy being laid on the upper surface of the wing, a radiation cooling film for transmitting the ultraviolet light and the visible light being arranged on the solar cell, the radiation cooling film including,
a surface layer polymerized via a semiconductor material or doped via a high transmittance material and nanoparticles, the surface layer having high transmittance of ultraviolet and visible light and high absorption/emissivity of 8-13 μm infrared light, at least one bottom layer disposed between the solar cell and the surface layer, the bottom layer comprising a high transmittance material;
the wing comprises a cavity distributed along the central line of the section of the wing, phase-change materials are filled in the cavity, and the solar cell is laid on the cavity.
3. The solar powered aircraft as defined in claim 2, wherein the cavity is a rectangular square cavity arranged along the centerline of the wing section and sequentially decreasing from the blunt tip to the sharp tail, and the wing control mechanism and landing gear are inserted into the square cavity.
4. The solar airplane as claimed in claim 2, wherein the nose of the airplane body is an oval structure, the energy storage unit and the control system are placed in the fuselage, the control system comprises a sensor, a controller and a mechanical transmission mechanism, the sensor comprises a temperature sensor arranged on the upper surface of the wing for measuring the temperature of the solar cell and speed sensors arranged at the front end and the rear end of the fuselage for measuring the flying speed, the controller comprises a general processor, a digital signal processor, an Application Specific Integrated Circuit (ASIC) or a Field Programmable Gate Array (FPGA), the mechanical transmission mechanism is a connecting rod or a hydraulic mechanism, the cross section of the wing is of a streamline structure, and a propeller arranged at the position of the wing close to the nose comprises a blade and a driving motor positioned in the wing.
5. The solar powered aircraft of claim 4, wherein the solar powered aircraft further comprises an empennage, the empennage comprising,
a parallel rear wing having a solar cell laid on an upper surface thereof, the parallel rear wing being configured to be movable up and down to adjust an incident angle of solar radiation with respect to the solar cell, a radiation cooling film disposed on the solar cell, the radiation cooling film for transmitting ultraviolet light and visible light including,
a surface layer formed by polymerizing a semiconductor material or doping nanoparticles with a high-transmittance material,
at least one bottom layer disposed between the solar cell and the skin layer, the bottom layer comprising a high transmittance material; and
and the vertical tail wing is connected with the control system through a mechanical transmission mechanism and can deflect relative to the fuselage.
6. A method of thermal management of a solar aircraft using the thermal management system of claim 1, comprising the steps of,
the first step, sunlight is absorbed by the solar cell through the radiation cooling film, wherein, a part of ultraviolet light and visible light are converted into electric energy, the other part of energy is converted into heat energy,
a second step of radiating a part of the heat energy by the radiation cooling film to lower the surface temperature of the solar cell,
and thirdly, storing the residual heat energy which is not radiated by the radiation cooling film in the phase change material in the cavity of the wing through heat conduction.
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| CN111718584A (en) * | 2020-06-18 | 2020-09-29 | 上海交通大学 | Radiation cooling film, preparation method and application thereof |
| CN115847982B (en) * | 2022-11-25 | 2024-11-15 | 马鞍山东毅新材料科技有限公司 | Bending-resistant insulating epoxy composite heat dissipation film for solar energy and production process thereof |
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