CN115009524A - Solar airplane thermal control system and method based on normal operation state - Google Patents
Solar airplane thermal control system and method based on normal operation state Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 239000012621 metal-organic framework Substances 0.000 claims abstract description 73
- 239000000463 material Substances 0.000 claims abstract description 68
- 239000002918 waste heat Substances 0.000 claims abstract description 14
- 230000033228 biological regulation Effects 0.000 claims abstract description 11
- 230000008569 process Effects 0.000 claims abstract description 11
- 238000003795 desorption Methods 0.000 claims abstract description 7
- 238000010438 heat treatment Methods 0.000 claims abstract description 7
- 238000001179 sorption measurement Methods 0.000 claims abstract description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 17
- 239000004917 carbon fiber Substances 0.000 claims description 17
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 7
- 238000004321 preservation Methods 0.000 claims description 6
- 238000010521 absorption reaction Methods 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 239000003575 carbonaceous material Substances 0.000 claims description 3
- 239000000741 silica gel Substances 0.000 claims description 3
- 229910002027 silica gel Inorganic materials 0.000 claims description 3
- 239000004020 conductor Substances 0.000 claims description 2
- 230000009467 reduction Effects 0.000 abstract description 2
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 229910002092 carbon dioxide Inorganic materials 0.000 description 2
- 239000001569 carbon dioxide Substances 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
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- 238000002336 sorption--desorption measurement Methods 0.000 description 1
- 239000005437 stratosphere Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention provides a solar airplane thermal control system and method based on a normal operation state, wherein the thermal control system comprises a heat conduction part, an MOFs material temperature control assembly and a heat conduction switch; part of the heat conducting parts are tightly attached and fixed on the inner sides of the main wings, the other part of the heat conducting parts are arranged in the hollow truss and pipeline beam structures, and the heat conducting ports can freely gather beams according to the heat distribution requirement; the MOFs temperature control assembly can automatically regulate and control the desorption/adsorption process according to the critical temperature of the battery and the electronic equipment to realize temperature reduction/heating, and realize 'daytime heating and night use' or other cross-space-time heat regulation and control. The thermal control system is small in size and light in weight, waste heat of the solar cell panel can be efficiently led out, intelligent temperature control of the solar cell panel, an electronic device and a battery can be ingeniously achieved, and optimal efficiency work is achieved.
Description
Technical Field
The invention relates to the technical field of solar unmanned aerial vehicles, in particular to a solar airplane thermal control system and method based on a normal operation state.
Background
With the proposal of carbon peak reaching and carbon neutralization targets, the efficient utilization of solar energy has become a core target in various military/civil fields.
Particularly in the field of solar aircrafts, the aircrafts are generally in a stratosphere during continuous voyage, only part of solar wave band energy is converted into electric energy by a solar panel, and most of solar energy is converted into heat energy (waste heat) on the surface of the panel, so that the temperature of the solar panel laid on the upper surface of the wing can reach 60 ℃, and the working efficiency of the solar panel is severely restricted.
For electronic devices such as antennas integrated in the wings, the electronic devices have the characteristics of small volume and high power, and the heat flow density generated in the working process of the electronic devices is high, so that the local temperature is usually high (can reach 60 ℃); the working environment temperature of part of electronic devices is sometimes at-60 ℃ (high altitude environment), and the service life of the devices is seriously influenced by such large temperature fluctuation; meanwhile, when the storage battery of the solar unmanned aerial vehicle is in a low-temperature environment (-60 ℃), the discharge capacity is greatly reduced and the low-temperature start of the battery is difficult due to the fact that the electrochemical activity of the battery is reduced, the impedance of the battery is increased and the discharge polarization of the battery is obvious.
Therefore, how to regulate and control the heat of the solar unmanned aerial vehicle across the region in a normal operation state is of great importance to the efficient and safe work of the solar unmanned aerial vehicle.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a solar airplane thermal control system and method based on a normal operation state, and the specific technical scheme is as follows:
the solar airplane thermal control system based on the normal operation state comprises a heat conduction component, an MOFs material temperature control assembly and a heat conduction switch;
part of the heat conduction components are tightly attached and fixed on the inner sides of main wings of the solar aircraft, wherein solar panels are arranged in the solar aircraft, and the other part of the heat conduction components are arranged in a hollow truss and pipeline beam structure of the solar aircraft; the heat conducting parts fixed on the inner sides of the main wings collect heat generated by the solar panels and conduct the heat to the heat conducting parts arranged in the hollow truss and pipeline beam structures of the solar airplane;
an MOFs material temperature control assembly and a heat conduction switch are embedded and installed in heat conduction components in hollow truss and pipeline beam structures of the solar aircraft to form a plurality of heat channels connected in series and/or in parallel; in the heat passage, two ends of the heat conducting part are respectively connected with the MOFs material temperature control assembly and the heat conducting switch; the MOFs temperature control component is further connected with an electronic device and/or a battery on the solar airplane through a heat conduction material or directly connected with the electronic device and/or the battery on the solar airplane; the heat conduction switch can control heat transfer of the heat path; the MOFs material temperature control assembly can be controlled to realize heat absorption or heating in a desorption or adsorption process.
Furthermore, the heat conducting material adopted by the heat conducting part is high heat conducting carbon fiber, and the high heat conducting silica gel is densely covered on the inner side of the main wing provided with the solar panel.
Furthermore, the hollow truss and the pipeline beam structure of the solar airplane are made of carbon materials.
Furthermore, the MOFs temperature control assembly is provided with a temperature sensing element and the MOFs material, wherein the temperature sensing element senses the surface temperature of an electronic device or a battery connected with the MOFs temperature control assembly; the MOFs material temperature control assembly controls the MOFs material to desorb or adsorb CO according to a set critical temperature condition and temperature data acquired by the temperature sensing element 2 Or the water vapor, thereby realizing the heat absorption or heating process and realizing the temperature regulation and control of the electronic device or the battery connected with the MOFs material temperature control component.
Furthermore, the MOFs material is MOF-801 and/or MOF-841.
Further, the heat conduction switch determines whether the heat conduction switch is turned on according to temperature data acquired by a temperature sensing element in the MOFs material temperature control assembly in the same heat path; when the temperature data is higher than the upper limit of the set temperature interval or lower than the lower limit of the set temperature interval, the heat conducting switch of the heat path is switched off, and the heat path is not in heat conduction with the external heat conducting component.
Further, the heat conduction switch also determines whether the heat conduction switch is turned on according to the temperature data of the solar panel, and if the temperature of the solar panel is higher than a set limit temperature, the heat conduction switch is also turned off, and the heat of the external heat conduction component does not enter the heat passage.
The method for realizing thermal control by utilizing the thermal control system comprises the following steps:
step 1: in the daytime with higher temperature, sunlight irradiates the solar cell panel to generate waste heat, when the temperature of the solar cell panel is higher than a set critical temperature value but not higher than a set limit temperature, the heat conduction switch is opened, the heat conduction part transmits the waste heat to the MOFs material temperature control assembly part, the MOFs material temperature control assembly is controlled to realize a desorption process, the waste heat generated by the solar cell panel is absorbed, and an electronic device or a battery is kept in a proper temperature interval; when the temperature of the solar panel is higher than the set limit temperature, all the heat conduction switches are turned off; when the surface temperature of an electronic device or a battery connected with the MOFs material temperature control assembly is higher than the upper limit of a set temperature interval, a heat conduction switch which is positioned in the same heat path with the MOFs material temperature control assembly is closed, heat cannot be further transferred to the battery or the electronic device of the heat path, and at the moment, the MOFs material temperature control assembly and the battery or the electronic device perform heat balance in a self-forming system;
step 2: at night with lower temperature, the solar cell panel cannot work, and the unmanned aerial vehicle provides kinetic energy through an internal battery; the battery and the electronic device are in a low-temperature environment at night, when the temperature of the battery and the electronic device is lower than the lower limit of a set temperature interval, the MOFs material temperature control assembly is controlled to realize that heat is released in the adsorption process, and a heat conduction switch which is in the same heat passage with the MOFs material temperature control assembly is closed, so that the unidirectional directional heat preservation of the electronic device or the battery is realized.
Advantageous effects
The thermal control system and the thermal control method for the solar unmanned aerial vehicle have the characteristic of intelligent regulation, and under a normal operation state, the thermal control system can realize dynamic regulation of heat of a solar cell panel, an MOFs material temperature control assembly, electronic equipment or a power supply, can realize efficient utilization of solar energy, and can ensure that a battery and an electronic device operate in an optimal temperature range. The thermal control system and the thermal control method for the solar unmanned aerial vehicle have the advantages of strong universality, super-long space-time energy self-maintenance, cross-regional heat regulation inside the vehicle body, large-scale equipment and the like, and can provide a brand-new solution for the efficient use of light, electricity and heat in the field of solar aircrafts in China.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic view of the external surface of a solar drone structure;
FIG. 2 is a top view of the internal structure of the solar unmanned aerial vehicle;
FIG. 3 is a three-dimensional view of a solar drone structure;
FIG. 4 is a three-dimensional view of the internal structure of the solar unmanned aerial vehicle;
FIG. 5 is a side view perspective three-dimensional view of the internal structure of the solar unmanned aerial vehicle;
FIG. 6 is a partial enlarged side view of the internal structure of the solar unmanned aerial vehicle;
FIG. 7 is a partial enlarged view of a side view cell of the internal structure of the solar unmanned aerial vehicle;
in the figure: 1. a main wing; 2. a solar panel; 3. a tail wing; 4. an electronic device; 5. MOFs material temperature control components; 6. a battery; 7. a pipe beam; 8. a truss; 9. a heat conducting switch.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
As shown in fig. 1 to 7, the solar unmanned aerial vehicle in the present embodiment includes a main wing 1, a solar panel 2, a tail wing 3, an electronic device 4, and a battery 6; the inside pipeline roof beam 7 and the truss 8 that adopt of solar energy unmanned aerial vehicle support. Because the solar unmanned aerial vehicle needs to work at high altitude for a long time, sunlight irradiates the solar cell panel during daytime, most solar energy is converted into heat energy (waste heat) on the surface of the solar cell panel, so that the temperature of the solar cell panel laid on the upper surface of the wing reaches 60 ℃, and the working efficiency of the solar cell panel is seriously restricted; the heat flux density generated in the working process of electronic devices such as antennas integrated in the wings is large, which usually results in high local temperature; meanwhile, the working environment temperature of the electronic devices and the storage battery is sometimes-60 ℃, and the service life of the devices is seriously influenced by large temperature fluctuation, so that how to regulate and control the heat of the solar unmanned aerial vehicle in a transregional manner in a normal running state is very important for the efficient and safe work of the solar unmanned aerial vehicle.
The solar unmanned aerial vehicle thermal control system based on the normal operation state provided in the embodiment comprises a heat conduction component, an MOFs material temperature control assembly and a heat conduction switch.
The heat conducting component is made of high-heat-conductivity carbon fibers, the high-heat-conductivity carbon fibers have excellent heat conducting performance and light weight, and a solar cell panel, the MOFs material temperature control assembly, electronic equipment and a battery are communicated to form a heat channel.
On the solar unmanned aerial vehicle, a solar panel is arranged on the outer side of the main wing; a part of high heat conduction carbon fiber utilizes heat conduction silica gel to closely cling to the inner side of a main wing provided with a solar cell panel in a dense mode, so that the thermal resistance is reduced, the heat generated by the solar cell panel is collected to the maximum degree, the waste heat of the solar cell panel is instantly and quickly conducted away by relying on the high-efficiency heat conduction capability of the high heat conduction carbon fiber, and the purpose is to enable the temperature of the whole solar cell panel to be in a reasonable temperature range.
The other part of the high-thermal-conductivity carbon fibers are arranged in the hollow truss and pipeline beam structure of the solar airplane and can be freely bunched according to the heat distribution requirement; the truss and the pipeline beam are made of carbon materials, the structure is hollow, the hollow degree is multiple of the diameter of the high-heat-conduction carbon fiber cluster, and the truss and the pipeline beam have the characteristics of high strength, light weight and high heat insulation. After the high-heat-conductivity carbon fibers uniformly and densely distributed on the inner side of the main wing collect heat, the heat is conducted to the high-heat-conductivity carbon fibers in the pipeline beam and the truss.
The MOFs material temperature control assembly and the heat conduction switch are embedded in the high heat conduction carbon fibers in the pipeline beam and the truss, so that a plurality of heat channels which are connected in series and/or in parallel are formed; in the heat channel, two ends of the high-heat-conductivity carbon fiber are respectively connected with the MOFs material temperature control assembly and the heat conduction switch, and the MOFs material temperature control assembly is further connected with an electronic device or a battery on the solar airplane through the high-heat-conductivity carbon fiber or directly connected with the electronic device or the battery on the solar airplane.
Under the normal operation state, the thermal control system can realize the dynamic intelligent regulation and control of the heat of the solar panel, the MOFs material temperature control assembly, the electronic equipment and the battery, a heat conduction switch in a heat passage is controlled to be automatically switched on and off to control heat transfer, the MOFs material temperature control assembly is controlled to automatically regulate and control the desorption or adsorption process according to the temperature requirement set by the electronic equipment and the battery to realize temperature reduction or temperature rise, in addition, on the distribution of high-heat-conductivity carbon fibers, parts needing important heat preservation can be wrapped by the high-heat-conductivity carbon fibers in a proper density mode, the instant and high-efficiency regulation and control of the heat are realized, the temperature regulation and control contrast effect in daytime and night is very obvious, and the electronic equipment and the battery can operate in a set temperature interval.
In this embodiment, the MOFs material temperature control assembly has a temperature sensing element and a MOFs material, wherein the temperature sensing element can sense the surface temperature of an electronic device or a battery connected with the MOFs material temperature control assembly through high thermal conductivity carbon fibers; the MOFs material temperature control assembly controls the MOFs material to desorb or adsorb CO according to a set critical temperature condition and temperature data acquired by the temperature sensing element 2 Or the water vapor, thereby realizing the heat absorption or heating process and realizing the temperature regulation and control of the electronic device or the battery connected with the MOFs material temperature control component. The MOFs material is optimized according to the working temperature of the solar cell panel and the airborne electronic device, so that the desorption/adsorption process is automatically regulated and controlled according to a set temperature interval, and heat regulation and control are realized. In the embodiment, MOFs material is MOF-801 and/or MOF-841, has the characteristics of light weight and high adsorption/desorption efficiency, and is uniformly arranged around the required heat-preservation electronic device or battery. Generally, at least two sides of the cell are individually coated with a fabricAnd a MOFs material temperature control assembly is arranged to realize uniform load distribution.
The heat conduction switch is mainly actively closed at night when the temperature of the solar cell panel is higher than the limit temperature or the temperature measured by the MOFs material temperature control assembly is higher than the upper limit of a set temperature interval, the heat channel is unidirectionally closed to the solar cell panel at the moment, and heat can only circulate between the electronic device and the battery, so that directional heat preservation is realized.
Specifically, the following logic is employed:
the heat conduction switch determines whether the heat conduction switch is conducted according to temperature data acquired by a temperature sensing element in the MOFs material temperature control assembly in the same heat path; when the temperature data is higher than the upper limit of the set temperature interval or lower than the lower limit of the set temperature interval (at night), the heat conducting switch of the heat path is switched off, and the heat path is not in heat conduction with the external heat conducting component. For example, when the temperature data is higher than the upper limit of the set temperature interval, it indicates that the temperature of the electronic device at the end of the heat path is higher, and no external heat can be introduced at this time, so the heat conduction switch is turned off, and the heat balance is performed with the battery or the electronic device self-formation system through the MOFs material temperature control assembly; and when the temperature data is lower than the lower limit of the set temperature range, the external environment temperature is lower, the heat conduction switch also needs to be switched off, and the unidirectional directional heat preservation of the electronic device is realized by utilizing the MOFs material temperature control assembly.
In addition, when the temperature data of the solar cell panel is higher than the set limit temperature, all the heat conduction switches are closed, and the damage of the electronic device caused by the overhigh heat of the solar cell panel is avoided.
The following steps of the method for realizing thermal control by using the thermal control system are provided:
step 1: in the daytime with higher temperature, sunlight irradiates the solar cell panel to generate waste heat, when the temperature of the solar cell panel is higher than a set critical temperature value but not higher than a set limit temperature, the heat conduction switch is switched on, the high-heat-conduction carbon fibers transfer the waste heat to the MOFs material temperature control assembly part, the MOFs material temperature control assembly is controlled to automatically desorb carbon dioxide, the waste heat generated by the solar cell panel is absorbed, an electronic device or a battery is kept in a proper temperature range, and efficient and accurate utilization of heat is realized; when the temperature of the solar cell panel is higher than the set limit temperature, all the heat conducting switches are closed, heat cannot be further transferred to the battery and the electronic device, and at the moment, the MOFs material temperature control assembly-battery/electronic device self-forming system carries out heat balance; when the surface temperature of an electronic device or a battery connected with the MOFs material temperature control assembly is higher than the upper limit of a set temperature interval, a heat conduction switch which is positioned in the same heat path with the MOFs material temperature control assembly is closed, heat cannot be further transferred to the battery or the electronic device of the heat path, and at the moment, the MOFs material temperature control assembly and the battery or the electronic device perform heat balance in a self-forming system;
step 2: at night with lower temperature, the solar cell panel cannot work, and the unmanned aerial vehicle provides kinetic energy through an internal battery; the battery and the electronic device are in a low-temperature environment at night, when the temperature of the battery and the electronic device is lower than the lower limit of a set temperature interval, the MOFs material temperature control assembly is controlled to adsorb carbon dioxide or water vapor to release heat, and a heat conduction switch which is in the same heat passage with the MOFs material temperature control assembly is closed, so that the electronic device or the battery is directionally insulated in a single direction, and the day-heat night use is realized.
The thermal control system of the embodiment is small in size and light in weight, waste heat of the solar cell panel can be efficiently led out, intelligent temperature control of the solar cell panel, an electronic device and a battery can be ingeniously achieved, and optimal efficiency work is achieved.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (8)
1. The utility model provides a solar energy aircraft thermal control system based on under normal operating condition which characterized in that: the MOFs temperature control device comprises a heat conduction component, an MOFs material temperature control assembly and a heat conduction switch;
part of the heat conduction components are tightly attached and fixed on the inner sides of main wings of the solar airplane, wherein the solar panels are arranged on the main wings, and the other part of the heat conduction components are arranged in a hollow truss and pipeline beam structure of the solar airplane; the heat conducting parts fixed on the inner sides of the main wings collect heat generated by the solar panels and conduct the heat to the heat conducting parts arranged in the hollow truss and pipeline beam structures of the solar airplane;
an MOFs material temperature control assembly and a heat conduction switch are embedded and installed in heat conduction components in hollow truss and pipeline beam structures of the solar aircraft to form a plurality of heat channels connected in series and/or in parallel; in the heat passage, two ends of a heat conducting part are respectively connected with the MOFs material temperature control assembly and the heat conducting switch; the MOFs temperature control component is further connected with an electronic device and/or a battery on the solar airplane through a heat conduction material or directly connected with the electronic device and/or the battery on the solar airplane; the heat conduction switch can control heat transfer of the heat path; the MOFs material temperature control assembly can be controlled to realize heat absorption or heating in a desorption or adsorption process.
2. The solar aircraft thermal control system based on the normal operation state as claimed in claim 1, wherein: the heat conducting material adopted by the heat conducting part is high heat conducting carbon fiber and is closely attached to the inner side of the main wing with the solar panel through high heat conducting silica gel dense distribution.
3. The solar aircraft thermal control system based on the normal operation state is characterized in that: the hollow truss and the pipeline beam structure of the solar airplane are made of carbon materials.
4. The solar aircraft thermal control system based on the normal operation state as claimed in claim 1, wherein: the MOFs material temperature control assembly is provided with a temperature sensing element and an MOFs material, wherein the temperature sensing element senses the surface temperature of an electronic device or a battery connected with the MOFs material temperature control assembly; the MOFs material temperature control assembly controls the MOFs material to desorb or adsorb CO according to a set critical temperature condition and temperature data acquired by the temperature sensing element 2 Or water vapor to realize the heat absorption or heating process and realize the temperature control assembly of the MOFs materialTemperature regulation of connected electronics or batteries.
5. The solar aircraft thermal control system based on the normal operation state according to claim 4, wherein: the MOFs material is MOF-801 and/or MOF-841.
6. The solar aircraft thermal control system based on the normal operation state as claimed in claim 1, wherein: the heat conduction switch determines whether the heat conduction switch is conducted according to temperature data acquired by a temperature sensing element in the MOFs material temperature control assembly in the same heat path; when the temperature data is higher than the upper limit of the set temperature interval or lower than the lower limit of the set temperature interval, the heat conducting switch of the heat path is switched off, and the heat path is not in heat conduction with the external heat conducting component.
7. The solar aircraft thermal control system based on the normal operation state according to claim 6, wherein: the heat conduction switch also determines whether the heat conduction switch is conducted or not according to the temperature data of the solar panel, if the temperature of the solar panel is higher than the set limit temperature, the heat conduction switch is also closed, and the heat of the external heat conduction part does not enter the heat passage.
8. The method for realizing thermal control by using the thermal control system of claims 1-7, comprising the following steps:
step 1: in the daytime with higher temperature, sunlight irradiates the solar cell panel to generate waste heat, when the temperature of the solar cell panel is higher than a set critical temperature value but not higher than a set limit temperature, the heat conduction switch is opened, the heat conduction part transmits the waste heat to the MOFs material temperature control assembly part, the MOFs material temperature control assembly is controlled to realize a desorption process, the waste heat generated by the solar cell panel is absorbed, and an electronic device or a battery is kept in a proper temperature interval; when the temperature of the solar panel is higher than the set limit temperature, all the heat conduction switches are closed; when the surface temperature of an electronic device or a battery connected with the MOFs material temperature control assembly is higher than the upper limit of a set temperature interval, a heat conduction switch which is positioned in the same heat path with the MOFs material temperature control assembly is closed, heat cannot be further transferred to the battery or the electronic device of the heat path, and at the moment, the MOFs material temperature control assembly and the battery or the electronic device perform heat balance in a self-forming system;
step 2: at night with lower temperature, the solar cell panel cannot work, and the unmanned aerial vehicle provides kinetic energy through an internal battery; the battery and the electronic device are in a low-temperature environment at night, when the temperature of the battery and the electronic device is lower than the lower limit of a set temperature interval, the MOFs material temperature control assembly is controlled to realize that heat is released in the adsorption process, and a heat conduction switch which is in the same heat passage with the MOFs material temperature control assembly is closed, so that the unidirectional directional heat preservation of the electronic device or the battery is realized.
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