CN109841692A - Heat management system, solar powered aircraft and thermal management algorithm for solar powered aircraft - Google Patents
Heat management system, solar powered aircraft and thermal management algorithm for solar powered aircraft Download PDFInfo
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Abstract
Disclose the heat management system for solar powered aircraft, solar powered aircraft and thermal management algorithm, heat management system includes the cooling film of the radiation of solar battery and arrangement on the solar cell, solar battery is layed in the upper surface of solar powered aircraft to absorb ultraviolet light and visible light to be converted into electric energy, it include surface layer and at least one layer of bottom for the cooling film of radiation through ultraviolet light and visible light, surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle, bottom is arranged between solar battery and surface layer, bottom includes high transmittance material, method includes the following steps, sunlight is absorbed through cooling film is radiated by solar battery, a part of ultraviolet light and visible light transformation are electric energy, another part energy is converted into thermal energy, a part of cooling thin film radiation thermal energy is radiated for reducing too Positive energy surface temperature, the remaining thermal energy for not radiated cooling thin film radiation can be stored in the intracavitary phase-change material in wing side by thermally conductive.
Description
Technical field
The present invention relates to solar powered aircraft field of heat management, especially a kind of heat management system for solar powered aircraft,
Solar powered aircraft and thermal management algorithm.
Background technique
Because in the military aspects such as border patrol, scouting, communication relay, electronic countermeasure and atmospheric research, weather forecast, ring
Border and the names such as disaster monitoring, crops telemetering, traffic control, telecommunications and TV service, nature reserve area monitoring, outer celestial body detecting
With aspect unique advantage, carry out solar powered aircraft and its related skill in last century end with developed countries such as the U.S., Switzerland, Russia
The research of art.
However, because the particularity of flight environment of vehicle and energy utilization type, causes solar powered aircraft awing because of heat
Stress, deformation is larger disintegrates.Solar powered aircraft work is in stratosphere mostly, and atmospheric temperature is about -60 DEG C~-50
DEG C, however reachable+60 DEG C of solar battery plate temperature of aerofoil surface are layed in, lead to solar panel and its internal electron
Component working efficiency is greatly reduced, and the huge temperature difference and temperature fluctuation are easy to cause thermal stress, deformation to increase, mechanical part
Service life reduces.And stratosphere rarefaction of air, solar panel and extraneous heat convection ability are extremely weak, are only about 5W/ (m2·
K), therefore the heat management of solar powered aircraft is particularly important.
For solar powered aircraft heat management, there are many embodiments.Such as CN 201110119982, CN
In the patents such as 201410485989.X, propose using the thermo-electric generation scheme complementary with solar energy to control heat, but temperature
Difference power generation purpose and heat management contradiction, thermo-electric generation need to maintain the biggish temperature difference in thermoelectric material both ends, and heat management and mention
And thermal control technology then need to reduce the temperature difference.In addition, limitation of the solar powered aircraft because of power supply capacity, each component part have very
The mode and mentality of designing of harsh weight indicator requirement, tradition addition thermoelectric material and its control system are unable to satisfy finger at all
Mark requires.
High vacuum degree is big, environment temperature is low, heat loss through convection inclement condition in the air, integrally considers for system, reduces the sun
Energy battery plate temperature, the stability for improving solar powered aircraft system temperature have greater significance.
Disclosed above- mentioned information are used only for enhancing the understanding to background of the present invention in the background section, it is thus possible to
Information comprising not constituting the prior art known to a person of ordinary skill in the art in home.
Summary of the invention
In view of the above problems, it is an object of the present invention to overcome the above-mentioned drawbacks of the prior art and provide one kind
Heat management system, solar powered aircraft and thermal management algorithm for solar powered aircraft.
The purpose of the present invention is be achieved by the following technical programs.
A kind of heat management system for solar powered aircraft includes,
Solar battery is layed in the upper surface of solar powered aircraft to absorb ultraviolet light and visible light to be converted into electricity
Energy；And
Cooling film is radiated, is arranged on the solar battery, it is cold for the radiation through ultraviolet light and visible light
But film includes,
Surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle, surface layer tool
There is micro-nano structure,
At least one layer of bottom, the bottom are arranged between solar battery and surface layer, and the bottom includes high transmission
Rate material.
In the heat management system for solar powered aircraft, surface layer has ultraviolet light and visible light high-transmission rate and 8-
13 μm of infrared light high-selenium corn/emissivity, with a thickness of 1/2,3/2 or 5/2 times of materials optical resonant wavelength.
In the heat management system for solar powered aircraft, radiating cooling film has ultraviolet and visible light high transmission
Rate and 8-13 μm of infrared light high-selenium corn/emissivity.
In the heat management system for solar powered aircraft, heat management system further includes connecting the solar battery
Energy-storage units and measurement solar battery temperature temperature sensor.
According to an aspect of the present invention, a kind of solar powered aircraft includes,
Fuselage；
Wing connects the fuselage, and the upper surface of the airfoil, which is equipped with, absorbs ultraviolet light and visible light to be converted into electricity
The solar battery of energy is arranged in the solar battery, spoke for the cooling film of radiation through ultraviolet light and visible light
Penetrating cooling film includes,
Surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle,
At least one layer of bottom, the bottom are arranged between solar battery and surface layer, and the bottom includes high transmission
Rate material.
In the solar powered aircraft, wing includes the cavity along the arrangement of its kernel of section line, fills phase transformation material in cavity
Material, solar battery are layed on cavity.
In the solar powered aircraft, cavity is to arrange by obtuse head to pointed tail size successively along Airfoil Sections center line
The truss structures to successively decrease, cavity is interior to run through wing control mechanism and take-off and landing device.
In the solar powered aircraft, fuselage head is in ellipsoidal structures, and inside is placed with energy-storage units and control system,
Control system includes sensor, controller and mechanical transfer mechanism, and the sensor includes being set to upper surface of the airfoil to measure the sun
The energy temperature sensor of battery temperature and the velocity sensor of the measurement flying speed equipped with fuselage front and back end, controller include logical
With processor, digital signal processor, application-specific integrated circuit ASIC or on-site programmable gate array FPGA, the mechanical transmissioning machine
Structure is connecting rod or hydraulic mechanism, and the streamlined structure in the section of wing, the propeller being set at the nearly head of wing includes blade
With the drive motor being located in wing.
In the solar powered aircraft, solar powered aircraft further includes empennage, and the empennage includes,
Parallel empennage, upper surface are equipped with solar battery, and the parallel empennage is configured to can be up and down with adjustment
Relative to the solar radiation incidence angle of solar battery, radiates cooling film and be arranged on the solar battery, for penetrating
The radiation of ultraviolet light and visible light cools down film,
Surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle, and surface layer is also
With micro-nano structure,
At least one layer of bottom, the bottom are arranged between solar battery and surface layer, and the bottom includes high transmission
Rate material；And
Vertical tail is connect by mechanical transmission mechanism with control system, and vertical tail can be deflected relative to fuselage.
According to another aspect of the invention, a kind of to include using the solar powered aircraft thermal management algorithm of the heat management system
Following steps,
First step, sunlight are absorbed through cooling film is radiated by solar battery, wherein a part of ultraviolet light with can
Light-exposed to be converted into electric energy, another part energy converts thermal energy,
Second step, radiates a part of thermal energy described in cooling thin film radiation to reduce solar energy surface temperature,
Third step, the remaining thermal energy for not radiated cooling thin film radiation pass through the thermally conductive phase being stored in the square chamber of wing
Become material.
Compared with prior art, the beneficial effects of the present invention are:
The present invention can the energy to solar energy different wave length carry out classification processing, and store a part of thermal energy, guaranteeing
The operating temperature of steady decrease battery while cell power generation efficiency.Solar cell power generation effect is able to ascend by the above method
Rate reduces aircraft thermal stress, prolongs the service life, to achieve the purpose that efficient and light weight, flying for long time.
The above description is only an overview of the technical scheme of the present invention, in order to make technological means of the invention clearer
Understand, reach the degree that those skilled in the art can be implemented in accordance with the contents of the specification, and in order to allow the present invention
Above and other objects, features and advantages can be more clearly understood, illustrated below with a specific embodiment of the invention
Explanation.
Detailed description of the invention
By reading the detailed description in hereafter preferred embodiment, various other advantages and benefits of the present invention
It will become apparent to those of ordinary skill in the art.Figure of description only for the purpose of illustrating preferred embodiments,
And it is not to be construed as limiting the invention.It should be evident that drawings discussed below is only some embodiments of the present invention,
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings
Other attached drawings.And throughout the drawings, identical component is presented with like reference characters.
In the accompanying drawings:
Fig. 1 is the structural schematic diagram of the heat management system according to an embodiment of the invention for solar powered aircraft；
Fig. 2 is a kind of schematic top plan view of solar powered aircraft heat management system according to an embodiment of the invention；
Fig. 3 is a kind of schematic side view of solar powered aircraft heat management system according to an embodiment of the invention；
Fig. 4 is that the wing structure signal of the heat management system according to an embodiment of the invention for solar powered aircraft is cutd open
View；
Fig. 5 is the step schematic diagram of thermal management algorithm according to an embodiment of the invention.
Below in conjunction with drawings and examples, the present invention will be further explained.
Specific embodiment
1 to the specific embodiment that the present invention will be described in more detail of attached drawing 5 below with reference to accompanying drawings.Although being shown in attached drawing
Specific embodiments of the present invention, it being understood, however, that may be realized in various forms the reality of the invention without that should be illustrated here
Example is applied to be limited.On the contrary, providing these embodiments is to be able to thoroughly understand the present invention, and can will be of the invention
Range is fully disclosed to those skilled in the art.
It should be noted that having used some vocabulary in the specification and claims to censure specific components.Ability
Field technique personnel it would be appreciated that, technical staff may call the same component with different nouns.This specification and right
It is required that not in such a way that the difference of noun is as component is distinguished, but with the difference of component functionally as differentiation
Criterion."comprising" or " comprising " as mentioned throughout the specification and claims are an open language, therefore should be solved
It is interpreted into " including but not limited to ".Specification subsequent descriptions are to implement better embodiment of the invention, so the description be with
For the purpose of the rule of specification, the range that is not intended to limit the invention.Protection scope of the present invention is when the appended right of view
It is required that subject to institute's defender.
In order to facilitate understanding of embodiments of the present invention, further by taking specific embodiment as an example below in conjunction with attached drawing to be solved
Explanation is released, and each attached drawing does not constitute the restriction to the embodiment of the present invention.
In order to better understand, Fig. 1 is the heat management system according to an embodiment of the invention for solar powered aircraft
Structural schematic diagram, a kind of heat management system for solar powered aircraft includes,
Solar battery 7 is layed in the upper surface of solar powered aircraft to absorb ultraviolet light and visible light to be converted into electricity
Energy；And
Cooling film 8 is radiated, is arranged on the solar battery 7, for the radiation through ultraviolet light and visible light
Cooling down film 8 includes,
Surface layer 9 polymerize via semiconductor material or adulterates via high transmittance material with nano particle, and surface layer is also
There are micro-nano structure, such as box shape, spherical, honeycomb, to improve 8-13 μm of infrared light high-selenium corn/emissivity,
At least one layer of bottom 10, the bottom 10 are arranged between solar battery 7 and surface layer 9, and the bottom 10 wraps
Include high transmittance material.
In one embodiment of the heat management system for solar powered aircraft, surface layer 9 have ultraviolet light with it is visible
Light high-transmission rate and 8-13 μm of infrared light high-selenium corn/emissivity, with a thickness of 1/2,3/2 or 5/2 times of materials optical resonant wavelength.
In one embodiment of the heat management system for solar powered aircraft, cooling film 8 is radiated with ultraviolet
With visible light high transmittance and 8-13 μm of infrared light high-selenium corn/emissivity.
In one embodiment of the heat management system for solar powered aircraft, heat management system further includes connection institute
State the energy-storage units of solar battery 7 and the temperature sensor of measurement 7 temperature of solar battery.
For a further understanding of the present invention, in one embodiment, Fig. 2 be it is according to an embodiment of the invention it is a kind of too
It is positive can aircraft heat management system schematic top plan view, a kind of solar powered aircraft heat management system includes,
Wing 1, upper part surface are laid with solar battery 7, absorb Uv and visible light, provide electric energy for aircraft,
It is laid on solar battery 7 and radiates cooling film 8, film is two layers and multilayered structure, and surface layer 9 is by a variety of semiconductors
Material polymerization is adulterated by high material thoroughly with nano particle, with ultraviolet light and visible light high-transmission rate, 8-13 μm infrared
Light high-selenium corn/emissivity, with a thickness of materials optical resonant wavelength 1/2,3/2,5/2... times, it is lower one or more layers by high transmission
Rate material composition, film integrally have ultraviolet and visible light high transmittance, 8-13 μm of infrared light high-selenium corn/emissivity,
The streamlined design in 1 section of wing, wing 1 is interior to arrange by obtuse head to pointed tail size successively along kernel of section line
The rectangular enclosure to successively decrease, cavity is interior to run through 1 operating mechanism of wing and take-off and landing device, and fills a certain amount of phase-change material, further
Stablize 1 temperature of wing,
Air-flow in the offline mode and flight course such as 1 tail end of two sides wing can be up and down, and reply is taken off, lands
Disturbance,
Propeller 2 is set at the nearly head of wing 1, is made of three pieces or multi-disc blade, drive motor is placed in thereafter
In wing 1,
3 head of fuselage is in ellipticity, and inside is placed with battery and solar powered aircraft control system, and control system is by sensing
Device, controller, mechanical transfer mechanism composition.The sensor includes temperature, velocity sensor, be distributed in 1 upper surface of wing with
Front and back end, controller include general processor, digital signal processor, application-specific integrated circuit ASIC or field programmable gate array
FPGA, the mechanical transmission mechanism be connecting rod or hydraulic mechanism,
Empennage is made of the parallel empennage 4 in left and right with vertical tail 5,
Parallel 4 upper surface of empennage is equipped with 7 plate of solar battery, and parallel empennage 4 can be up and down, and adjustment solar radiation enters
Firing angle guarantees 7 generating efficiency of solar battery,
Vertical tail 5 is connect by mechanical transmission mechanism with 3 control system of fuselage, by adjusting 5 deflection angle of vertical tail
Degree, provides the balance aerodynamic force of aircraft flight.
Fig. 3 is a kind of schematic side view of solar powered aircraft heat management system according to an embodiment of the invention, a kind of
Solar powered aircraft includes,
Fuselage 3；
Wing 1 connects the fuselage 3, and 1 upper surface of wing, which is equipped with, absorbs ultraviolet light and visible light to be converted into
The solar battery 7 of electric energy is arranged in the solar battery 7 for the cooling film 8 of radiation through ultraviolet light and visible light
On, radiating cooling film 8 includes,
Surface layer 9 polymerize via semiconductor material or adulterates via high transmittance material with nano particle,
At least one layer of bottom 10, the bottom 10 are arranged between solar battery 7 and surface layer 9, and the bottom 10 wraps
Include high transmittance material.
In one embodiment of the solar powered aircraft, Fig. 4 is according to an embodiment of the invention for solar energy
The wing structure schematic sectional view of the heat management system of aircraft, wing 1 include the cavity 6 along the arrangement of its kernel of section line, cavity
Interior filling phase-change material, solar battery 7 are layed on cavity 6.
In one embodiment of the solar powered aircraft, cavity 6 is to arrange by obtuse head extremely along 1 kernel of section line of wing
The truss structures 6 that pointed tail size is successively successively decreased, side is intracavitary to run through 1 operating mechanism of wing and take-off and landing device.
In one embodiment of the solar powered aircraft, 3 head of fuselage is in ellipsoidal structures, and inside is placed with energy storage list
Member and control system, control system include sensor, controller and mechanical transfer mechanism, and the sensor includes being set to wing 1
Upper surface measures the temperature sensor of 7 temperature of solar battery and the speed of the measurement flying speed equipped with 3 front and back end of fuselage passes
Sensor, controller include general processor, digital signal processor, application-specific integrated circuit ASIC or field programmable gate array
FPGA, the mechanical transmission mechanism are connecting rod or hydraulic mechanism, and the streamlined structure in the section of wing 1 is set to the nearly machine of wing 1
Propeller 2 at head includes blade and the drive motor in wing 1.
In one embodiment of the solar powered aircraft, solar powered aircraft further includes empennage, and the empennage includes,
Parallel empennage 4, upper surface are equipped with solar battery 7, and the parallel empennage 4 is configured to can be up and down to adjust
The whole solar radiation incidence angle relative to solar battery 7 radiates cooling film and is arranged on the solar battery, for saturating
The radiation for crossing ultraviolet light and visible light cools down film and includes,
Surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle,
At least one layer of bottom, the bottom are arranged between solar battery and surface layer, and the bottom includes high transmission
Rate material；And
Vertical tail 5 is connect by mechanical transmission mechanism with control system, and vertical tail 5 can be inclined relative to fuselage 3
Turn.
For a further understanding of the present invention, in one embodiment, a kind of solar powered aircraft includes,
Wing 1, upper part surface are laid with solar battery 7, absorb Uv and visible light, provide electric energy for aircraft,
Radiate cooling film 8 as shown in figure 3, being laid on solar battery 7, film is two layers and multilayered structure, surface layer 9 by
The polymerization of a variety of semiconductor materials is adulterated by high material thoroughly with nano particle, have ultraviolet light and visible light high-transmission rate,
8-13 μm of infrared light high-selenium corn/emissivity, with a thickness of material resonance wavelength 1/2,3/2,5/2... times, it is lower one or more layers by
High transmittance material composition, film integrally have ultraviolet and visible light high transmittance, 8-13 μm of infrared light high-selenium corn/emissivity,
The streamlined design in 1 section of wing, provides greater lift under identical wind speed,
The truss structures 66 successively to be successively decreased by obtuse head to pointed tail size in wing 1 along the arrangement of kernel of section line, cavity
It is interior to run through 1 operating mechanism of wing and take-off and landing device, and a certain amount of phase-change material is filled, further stablize 1 temperature of wing,
Air-flow in the offline mode and flight course such as 1 tail end of two sides wing can be up and down, and reply is taken off, lands
Disturbance,
Propeller 23 is set at the nearly head of wing 1, is made of three pieces or multi-disc blade, drive motor is placed in thereafter
Wing 1 in,
3 head of fuselage claims ellipticity, and inside is placed with battery and solar powered aircraft control system, and control system is by sensing
Device, controller, mechanical transfer mechanism composition.The sensor includes temperature, velocity sensor, be distributed in 1 upper surface of wing with
Front and back end, controller include general processor, digital signal processor, application-specific integrated circuit ASIC or field programmable gate array
FPGA, the mechanical transmission mechanism be connecting rod or hydraulic mechanism,
Empennage is made of the parallel empennage 4 in left and right with vertical tail 5,
Parallel 4 upper surface of empennage is equipped with 7 plate 1 of solar battery, and parallel empennage 4 can be up and down, adjusts solar radiation
Incidence angle guarantees 7 generating efficiency of solar battery,
Vertical tail 5 is connect by mechanical transmission mechanism with 3 control system of fuselage, by adjusting 5 deflection angle of vertical tail
Degree, provides the balance aerodynamic force of aircraft flight.
Fig. 5 is the step schematic diagram of thermal management algorithm according to an embodiment of the invention, a kind of to utilize the heat management
The solar powered aircraft thermal management algorithm of system includes the following steps,
First step S1, sunlight are absorbed through cooling film 8 is radiated by solar battery 7, wherein a part of ultraviolet light
It is electric energy with visible light transformation, another part energy converts thermal energy,
Second step S2 radiates cooling film 8 and radiates a part of the thermal energy to reduce solar energy surface temperature,
Third step S3, remaining not radiated the thermal energy that cooling film 8 radiates does not pass through the thermally conductive square chamber 6 for being stored in wing 1
In phase-change material.
For a further understanding of the present invention, in one embodiment, a kind of solar powered aircraft thermal management algorithm step packet
It includes:
The cooling film 8 of radiation that sunlight has through wing 1 and empennage upper surface, is absorbed by photovoltaic cell.It is wherein big
Part ultraviolet light and visible light transformation are electric energy, are stored in 3 battery of fuselage for using, another part energy is because of the non-spoke of semiconductor
Penetrate complex effect conversion thermal energy；
Cooling film 8 is radiated because it is in 8-13 μm of infrared light high-selenium corn/emissivity, atmospheric electricity is penetrated by irradiating infrared light
Mouth directly carries out radiations heat energy with universe cold source (4K) and exchanges, and is by most of thermal energy that 7 photo-thermal effect of solar battery generates
When radiate, substantially reduce 7 surface temperature of solar battery；
Another part thermal energy that 7 photo-thermal effect of solar battery generates is stored in inside wing 1 by thermally conductive along center line
Among the phase-change material filled in the truss structures 6 of arrangement, the temperature of 7 plate of solar battery and aircraft entirety is further decreased
Fluctuation.
The integrally streamlined design of solar powered aircraft heat management system, wing 1, empennage can be one in above-mentioned technical proposal
It is movable in range to determine, and can reduce the aerodynamic drag and frictional heat in aircraft flight, has better air-balance.
Solar powered aircraft thermal management algorithm can be classified the energy of solar energy different wave length in above-mentioned technical proposal
Processing, and a part of thermal energy is stored, the operating temperature of steady decrease battery while guaranteeing cell power generation efficiency.By above-mentioned
Method is able to ascend 7 generating efficiency of solar battery, reduces aircraft thermal stress, prolongs the service life, thus reach efficient and light weight,
The purpose of flying for long time.
The present invention is reached by the structure and performance of optimization solar powered aircraft efficiently using solar energy, in power generation storage
It radiates simultaneously, store thermal energy；New solar powered aircraft heat management system is proposed and devised, bulk temperature wave is not only reduced
It is dynamic, moreover it is possible to according to 1 deflection angle of environment conditioning wing, to reduce the aerodynamic drag in flight course, air-balance is improved,
Reach high efficiency smooth, for a long time uninterrupted flight.
Industrial applicibility
Heat management system, solar powered aircraft and separation method of the present invention for solar powered aircraft can be in aircraft
Field manufactures and uses.
The basic principle of the application is described in conjunction with specific embodiments above, however, it is desirable to, it is noted that in this application
The advantages of referring to, advantage, effect etc. are only exemplary rather than limitation, must not believe that these advantages, advantage, effect etc. are the application
Each embodiment is prerequisite.In addition, detail disclosed above is merely to exemplary effect and the work being easy to understand
With, rather than limit, it is that must be realized using above-mentioned concrete details that above-mentioned details, which is not intended to limit the application,.
In order to which purpose of illustration and description has been presented for above description.In addition, this description is not intended to the reality of the application
It applies example and is restricted to form disclosed herein.Although already discussed above multiple exemplary aspects and embodiment, this field skill
Its certain modifications, modification, change, addition and sub-portfolio will be recognized in art personnel.
Claims (10)
1. a kind of heat management system for solar powered aircraft comprising,
Solar battery is layed in the upper surface of solar powered aircraft to absorb ultraviolet light and visible light to be converted into electric energy；With
And
Cooling film is radiated, is arranged on the solar battery, it is thin for the radiation cooling through ultraviolet light and visible light
Film includes,
Surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle, and surface layer has micro-
Micro-nano structure, at least one layer of bottom, the bottom are arranged between solar battery and surface layer, and the bottom includes high transmittance
Material.
2. being used for the heat management system of solar powered aircraft as described in claim 1, wherein preferred, surface layer has ultraviolet light
With visible light high-transmission rate and 8-13 μm of infrared light high-selenium corn/emissivity, with a thickness of materials optical resonant wavelength 1/2,3/2 or
5/2 times.
3. being used for the heat management system of solar powered aircraft as described in claim 1, wherein radiate cooling film have it is ultraviolet with
Visible light high transmittance and 8-13 μm of infrared light high-selenium corn/emissivity.
4. being used for the heat management system of solar powered aircraft as described in claim 1, wherein heat management system further includes connection institute
State the energy-storage units of solar battery and the temperature sensor of measurement solar battery temperature.
5. a kind of solar powered aircraft comprising,
Fuselage；
Wing connects the fuselage, and the upper surface of the airfoil, which is equipped with, absorbs ultraviolet light and visible light to be converted into electric energy
Solar battery is arranged in the solar battery for the cooling film of radiation through ultraviolet light and visible light, radiates cold
But film includes,
Surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle,
At least one layer of bottom, the bottom are arranged between solar battery and surface layer, and the bottom includes high transmittance material
Material.
6. solar powered aircraft as claimed in claim 5, wherein wing includes the cavity along the arrangement of its kernel of section line, cavity
Interior filling phase-change material, solar battery are layed on cavity.
7. solar powered aircraft as claimed in claim 6, wherein cavity is to arrange along Airfoil Sections center line by obtuse head to point
The truss structures that shape tail size is successively successively decreased, side is intracavitary to run through wing control mechanism and take-off and landing device.
8. solar powered aircraft as claimed in claim 5, wherein fuselage head is in ellipsoidal structures, and inside is placed with energy storage list
Member and control system, control system include sensor, controller and mechanical transfer mechanism, and the sensor includes being set on wing
The velocity sensor of the temperature sensor of surface measurement solar battery temperature and the measurement flying speed equipped with fuselage front and back end,
Controller includes general processor, digital signal processor, application-specific integrated circuit ASIC or on-site programmable gate array FPGA, institute
Stating mechanical transmission mechanism is connecting rod or hydraulic mechanism, the streamlined structure in the section of wing, the spiral shell being set at the nearly head of wing
Revolving paddle includes blade and the drive motor in wing.
9. solar powered aircraft as claimed in claim 8, wherein solar powered aircraft further includes empennage, and the empennage includes,
Parallel empennage, upper surface are equipped with solar battery, and the parallel empennage is configured to can be up and down opposite to adjust
In the solar radiation incidence angle of solar battery, radiates cooling film and be arranged on the solar battery, for through ultraviolet
The radiation of light and visible light cools down film,
Surface layer polymerize via semiconductor material or adulterates via high transmittance material with nano particle,
At least one layer of bottom, the bottom are arranged between solar battery and surface layer, and the bottom includes high transmittance material
Material；And
Vertical tail is connect by mechanical transmission mechanism with control system, and vertical tail can be deflected relative to fuselage.
10. a kind of solar powered aircraft thermal management algorithm using heat management system described in any one of claim 1-4 comprising
Following steps,
First step, sunlight are absorbed through cooling film is radiated by solar battery, wherein a part of ultraviolet light and visible light
It is converted into electric energy, another part energy is converted into thermal energy,
Second step, radiates a part of thermal energy described in cooling thin film radiation to reduce solar energy surface temperature,
Third step, the remaining thermal energy for not radiated cooling thin film radiation can be stored in the intracavitary phase transformation material in wing side by thermally conductive
In material.
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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 |
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| CN109841692B (en) | 2021-01-22 |
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