CN115009525A - Thermal control system and method for solar unmanned aerial vehicle based on thermal runaway state - Google Patents
Thermal control system and method for solar unmanned aerial vehicle based on thermal runaway state Download PDFInfo
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- CN115009525A CN115009525A CN202210838132.6A CN202210838132A CN115009525A CN 115009525 A CN115009525 A CN 115009525A CN 202210838132 A CN202210838132 A CN 202210838132A CN 115009525 A CN115009525 A CN 115009525A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
Abstract
The invention provides a thermal control system and a thermal control method of a solar unmanned aerial vehicle based on a thermal runaway state, wherein the thermal control system comprises a memory metal control structure, a flight control unit and a heat conduction assembly; the heat conduction assembly, the solar cell panel and the main wing form a heat conduction loop, so that the temperature of the whole main wing is kept uniform; the memory metal control structures are arranged at the front edge and the rear edge of the main wing, the shape of the wing can be automatically changed under the thermal runaway state, the camber of the wing is increased, the effective irradiation area of sunlight on the solar cell panel is reduced, and meanwhile, the holes are automatically deformed and opened near the front edge and the rear edge, so that air flows into the wing, the forced convection inside the wing is enhanced, and the temperature is reduced; in addition, the flight control unit can control the attitude of the airplane in a thermal runaway state, and the irradiation area of sunlight on the solar cell panel is reduced. The invention has the advantages of strong universality, high heat dissipation speed, multiple heat dissipation angles, large-scale equipment and the like.
Description
Technical Field
The invention relates to the technical field of solar unmanned aerial vehicles, in particular to a thermal control system and method of a solar unmanned aerial vehicle based on a thermal runaway state.
Background
Solar energy unmanned aerial vehicle utilizes solar cell to convert the light energy of sunlight into the electric energy, and has no pollution, characteristics when long voyage, and present solar cell's efficiency is only between 16% to 22%, wherein very big part energy can conversion used heat, bring certain problem for solar energy unmanned aerial vehicle is at the thermal management of the in-process that cruises, the temperature that the while used heat brought rises can further influence solar cell's efficiency, solar cell's efficiency reduces and can bring the increase of used heat again, and in the very big time quantum of solar altitude angle, whole unmanned aerial vehicle's energy input can further increase, make this positive feedback process aggravation, cause the thermal runaway easily.
Thermal runaway refers to a further increase in temperature caused by a change in the temperature rise within the system, resulting in a vicious circle and thus a destructive result. Conventional thermal management systems have been inadequate to cope with the positive feedback process of increasing temperature during thermal runaway. At present, a solar unmanned aerial vehicle thermal management system is designed aiming at thermal management under a general cruise condition, and processing aiming at a thermal runaway process is lacked. The thermal runaway process often leads to the failure of the whole electronic device, and further leads to the runaway of the flight, so how to radiate heat emergently under the thermal runaway state is very important for the extreme situation resistance of the solar unmanned aerial vehicle.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a thermal control system and a thermal control method of a solar unmanned aerial vehicle based on a thermal runaway state, and the specific technical scheme is as follows:
the thermal control system of the solar unmanned aerial vehicle based on the thermal runaway state comprises a memory metal control structure, a flight control unit and a heat conduction assembly;
the memory metal control structure is arranged at the front edge and the rear edge of the wing provided with the solar cell panel in the solar unmanned aerial vehicle; the shape of the wing can be automatically changed under the thermal runaway state, the camber of the wing is increased, the effective irradiation area of sunlight on the solar cell panel is reduced, and meanwhile, the holes are automatically deformed and opened near the front edge and the rear edge, so that air flows into the wing, the forced convection inside the wing is enhanced, and the temperature is reduced;
the heat conduction assembly, the solar cell panel and the wing provided with the solar cell panel form a heat conduction loop, so that the temperature of the whole wing provided with the solar cell panel is kept uniform;
the flight control unit can control the attitude of the airplane and reduce the irradiation area of sunlight on the solar cell panel in a thermal runaway state.
Further, a solar cell panel is also arranged on the memory metal control structure.
Further, the heat conducting component adopts high heat conducting carbon fiber bundles.
Furthermore, a pipeline beam and a truss are arranged in the wing, and the pipeline beam and the truss contain high-heat-conductivity carbon fiber bundles; the high-heat-conductivity carbon fiber bundles are densely distributed on the inner side of the wing through high-heat-conductivity silica gel; the high-heat-conduction carbon fiber bundles, the solar cell panel on the surface of the wing and the whole wing structure form a heat-conduction loop, so that the temperature of the whole wing is kept uniform.
Furthermore, the pipeline beams and the trusses are made of carbon materials.
The method for carrying out thermal control by utilizing the thermal control system comprises the following steps:
step 1: temperature sensors are arranged in the solar cell panel and the internal electronic equipment to monitor the temperature change of the surface of the solar cell panel and the internal electronic device, and when the temperature reaches a set high temperature and is kept for a set time, the airplane enters a thermal runaway state;
Advantageous effects
The thermal control system and the thermal control method of the solar unmanned aerial vehicle can automatically judge whether the solar unmanned aerial vehicle is used or not through the characteristics of the temperature sensor and the memory metal. Under the thermal runaway state, this thermal control system has the heat dissipation measure under three kinds of emergency, from flight control, wing deformation, the comprehensive solution that provides for the heat dissipation problem of solar energy unmanned aerial vehicle under the thermal runaway state of internal convection direction respectively.
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 side view perspective three-dimensional view of a solar drone;
FIG. 3 is a side view perspective three-dimensional view of a solar unmanned aerial vehicle changing attitude in an emergency state;
FIG. 4 is a side view of a wing without internal structure in a typical state;
FIG. 5 is a schematic side view of an airfoil in an emergency condition;
FIG. 6 is a schematic top view of a typical airfoil;
FIG. 7 is a schematic top view of an airfoil in an emergency;
FIG. 8 is a side view of an airfoil generally including internal tubular spars and trusses;
FIG. 9 is a side view of an airfoil including internal tubular spars and trusses in an emergency;
in the figure: 1. a main wing; 1A, a wing structure near a wing leading edge controlled by memory metal; 1B, a middle part wing structure; 1C, a wing structure near the trailing edge of the wing controlled by memory metal; 2. a solar panel; 3. a tail wing; 5. memory metal controlled wing openings; 6. a truss structure containing highly thermally conductive carbon fibers; 7. a pipe beam containing highly heat conductive carbon fibers.
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 9, the present embodiment provides a thermal control system and method for a solar unmanned aerial vehicle based on a thermal runaway state. The whole solar unmanned aerial vehicle comprises a main wing 1, a solar cell panel 2, a tail wing 3 and a flight control unit. The solar cell panel 2 is tightly attached to the outer side of the main wing 1, and the flight control unit can control the control surface of the airplane and adjust the flight attitude.
The thermal control system comprises a memory metal control structure, a flight control unit and a heat conduction assembly.
The heat conduction assembly adopts high-heat-conduction carbon fiber bundles, and has the characteristics of high heat conduction and light weight. One part of the high-thermal-conductivity carbon fiber bundles are tightly combined on the surface of the solar cell panel through high-thermal-conductivity silica gel, and the other part of the high-thermal-conductivity carbon fiber bundles are arranged inside the pipeline beam and the truss inside the main wing. The high-heat-conductivity carbon fiber bundles, the solar cell panel on the surface of the main wing and the whole main wing structure form a heat-conducting loop, so that the temperature of the whole main wing is kept uniform, and the heat irradiated to the solar cell panel by the sun is ensured not to be concentrated at a certain position. The truss and the pipeline beam are made of high-strength carbon materials, the structure is hollow, the hollow degree is that the inner diameter can contain a plurality of high-heat-conduction carbon fiber bundles for directional heat conduction, and the truss and the pipeline beam have the characteristics of high strength, light weight and high heat insulation.
The flight control unit can sense the surface temperature of the solar cell panel through the temperature sensor, can adjust the flight attitude of the solar unmanned aerial vehicle according to the surrounding environment in a thermal runaway state, and can adjust the irradiation area of sunlight in the process of ensuring normal flight to enable the irradiation area to reach the minimum. Fig. 3 is a side view perspective three-dimensional view of the solar unmanned aerial vehicle with changed posture in an emergency state, and the attack angle is increased by 30 degrees, so that the irradiation area of sunlight on the solar cell panel is reduced.
The memory metal control structure comprises a memory metal controlled wing structure near the leading edge of the wing, a wing trailing edge structure and a memory metal controlled wing opening structure. The memory metal control structure is also provided with a solar cell panel and can change the placing angle with the memory metal.
Under the thermal runaway condition, the shape of the memory metal is changed due to the rise of the temperature, so that the wing profile camber near the front edge and the rear edge of the main wing is increased, and meanwhile, the posture of the memory metal is adjusted by matching with a flight control system, the projection area of the wing to the sun is reduced, and the irradiation area of sunlight to the solar cell panel is reduced. Taking fig. 4 and 5 as examples, fig. 4 is a schematic side view of a wing without an internal structure in a general state, fig. 5 is a schematic side view of the wing in an emergency state, it can be seen that the camber of the wing mainly changes from a leading edge part and a trailing edge part, a part controlled by memory metal is that a wing structure 1A near the leading edge of the wing controlled by memory metal and a wing structure 1C near the trailing edge of the wing controlled by memory metal are bent downwards, and a middle part wing structure 1B, a conduit girder 7 containing high thermal conductive carbon fibers and a truss structure 8 containing high thermal conductive carbon fibers are connected without changing the camber.
In addition, under the thermal runaway condition, the memory metal is near leading edge and near trailing edge automatic deformation production hole 5, makes inside the air inflow wing, and inside forced convection of reinforcing reduces the inside temperature of unmanned aerial vehicle, and the position, the size and the quantity of trompil can be regulated and control according to solar cell panel surface temperature height. In this embodiment, the aperture size is as shown in the side view of the wing containing the internal tubular beams and trusses in the emergency situation of fig. 9, wherein the radius of the single aperture near the leading edge is 50mm, the aperture interval is 165mm, the radius of the single aperture near the trailing edge is 45mm, and the aperture interval is 174mm, and after the aperture is opened in the thermal runaway state, the forced convection inside can be enhanced, and the temperature rise caused by the solar cell panel 2 can be reduced from the inside.
In the embodiment, a thermal control method of the solar unmanned aerial vehicle based on a thermal runaway state is further provided, and the thermal control method uses the flight control unit, the wing structure 1A near the leading edge of the wing controlled by the memory metal, the wing structure 1C near the trailing edge of the wing controlled by the memory metal and the wing opening 5 controlled by the memory metal, the thermal control method is that a temperature sensor is arranged near a solar cell panel and connected with the flight control unit, when the temperature reaches a set value and is maintained or continuously increased within a certain time, the solar unmanned aerial vehicle is judged to reach the thermal runaway state, and the flight control unit adjusts the posture of the unmanned aerial vehicle according to the current flight state and environmental conditions so as to reduce the irradiation area of sunlight and reduce the energy input brought by the sunlight; under the thermal runaway state, the memory metal is subjected to morphological change according to temperature change, the bending degree of the memory metal is changed under the action of the memory metal near the front edge and the rear edge of the main wing, and therefore the irradiation area of sunlight is further reduced; under the thermal runaway state, the memory metal is changed according to the temperature change, the holes are automatically deformed near the front edge and the rear edge of the main wing, the internal convection effect is enhanced by the incoming flow entering the main wing, the forced convection is formed, and the temperature inside the solar unmanned aerial vehicle is reduced.
The embodiment shows that the invention has the characteristic of intelligent regulation. Under the thermal runaway state, the irradiation area of sunlight on the solar cell panel is automatically reduced; meanwhile, the memory metal changes the shape of the wing due to the rise of temperature, the camber of the wing is increased, the irradiation area of sunlight on the solar cell panel is further reduced, and the memory metal automatically deforms and opens holes near the front edge and the rear edge, so that air flows into the interior of the airplane, the forced convection in the airplane is enhanced, and the temperature of the main wing and the internal space of the main wing is reduced. The thermal control system and the thermal control method for the solar unmanned aerial vehicle in the thermal runaway state have the advantages of strong universality, high heat dissipation speed, multiple heat dissipation angles, large-scale equipment and the like.
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 (6)
1. The utility model provides a solar energy unmanned aerial vehicle thermal control system based on thermal runaway state which characterized in that: the aircraft comprises a memory metal control structure, a flight control unit and a heat conduction assembly;
the memory metal control structure is arranged at the front edge and the rear edge of a wing provided with a solar cell panel in the solar unmanned aerial vehicle; the shape of the wing can be automatically changed under the thermal runaway state, the camber of the wing is increased, the effective irradiation area of sunlight on the solar cell panel is reduced, and meanwhile, the holes are automatically deformed and opened near the front edge and the rear edge, so that air flows into the wing, the forced convection inside the wing is enhanced, and the temperature is reduced;
the heat conduction assembly, the solar cell panel and the wing provided with the solar cell panel form a heat conduction loop, so that the temperature of the whole wing provided with the solar cell panel is kept uniform;
the flight control unit can control the attitude of the airplane and reduce the irradiation area of sunlight on the solar cell panel in a thermal runaway state.
2. The thermal control system of the solar unmanned aerial vehicle based on the thermal runaway state according to claim 1, wherein: and a solar cell panel is also arranged on the memory metal control structure.
3. The thermal control system of the solar unmanned aerial vehicle based on the thermal runaway state according to claim 1, wherein: the heat conduction assembly adopts high-heat-conduction carbon fiber bundles.
4. The thermal control system of the solar unmanned aerial vehicle based on the thermal runaway state according to claim 3, wherein: a pipeline beam and a truss are arranged inside the wing, and the pipeline beam and the truss contain high-heat-conductivity carbon fiber bundles; the high-heat-conductivity carbon fiber bundles are densely distributed on the inner side of the wing through high-heat-conductivity silica gel; the high-heat-conduction carbon fiber bundles, the solar cell panel on the surface of the wing and the whole wing structure form a heat-conduction loop, so that the temperature of the whole wing is kept uniform.
5. The thermal control system of the solar unmanned aerial vehicle based on the thermal runaway state according to claim 4, wherein: the pipeline beams and the trusses are made of carbon materials.
6. A method for thermal control by using the thermal control system as claimed in claim 1 to 5, comprising the following steps:
step 1: temperature sensors are arranged in the solar cell panel and the internal electronic equipment to monitor the temperature change of the surface of the solar cell panel and the internal electronic device, and when the temperature reaches a set high temperature and is kept for a set time, the airplane enters a thermal runaway state;
step 2, in the thermal runaway condition, the flight control unit changes the posture of the unmanned aerial vehicle by adjusting the control surface of the unmanned aerial vehicle, and reduces the irradiation area of sunlight on the solar cell panel;
step 3, simultaneously, in a thermal runaway state, the heat of the solar cell panel is conducted to the whole part of the wing through the heat conducting assembly, so that local hot spots do not appear on the surface of the wing, and simultaneously, after the temperature rises to a certain value, the memory metals positioned at the front edge and the rear edge of the wing begin to deform, so that the camber of the wing increases, and the irradiation area of sunlight on the solar cell panel is further reduced; meanwhile, the memory metal at the front edge and the rear edge automatically deforms to generate holes, and the positions, sizes and number of the holes can be adjusted and controlled according to the temperature of the surface of the solar cell panel, so that incoming flow is adjusted to enter the wing, a forced convection effect is formed in the wing, and the temperature of the unmanned aerial vehicle is further reduced.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210838132.6A CN115009525B (en) | 2022-07-17 | 2022-07-17 | Solar unmanned aerial vehicle thermal control system and method based on thermal runaway state |
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| CN202210838132.6A CN115009525B (en) | 2022-07-17 | 2022-07-17 | Solar unmanned aerial vehicle thermal control system and method based on thermal runaway state |
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| CN115009525B CN115009525B (en) | 2023-10-10 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100213309A1 (en) * | 2007-09-14 | 2010-08-26 | Robert Parks | Non-planar adaptive wing solar aircraft |
| CN106828947A (en) * | 2017-03-22 | 2017-06-13 | 北京航空航天大学 | A kind of high-altitude vehicle solar panel and propeller motor combined radiating device |
| CN111942601A (en) * | 2020-07-20 | 2020-11-17 | 西北工业大学 | Thermal management module, thermal management system and thermal management method for solar unmanned aerial vehicle |
| CN112606994A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Integrated thermal control design method for wings of solar unmanned aerial vehicle |
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- 2022-07-17 CN CN202210838132.6A patent/CN115009525B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100213309A1 (en) * | 2007-09-14 | 2010-08-26 | Robert Parks | Non-planar adaptive wing solar aircraft |
| CN106828947A (en) * | 2017-03-22 | 2017-06-13 | 北京航空航天大学 | A kind of high-altitude vehicle solar panel and propeller motor combined radiating device |
| CN111942601A (en) * | 2020-07-20 | 2020-11-17 | 西北工业大学 | Thermal management module, thermal management system and thermal management method for solar unmanned aerial vehicle |
| CN112606994A (en) * | 2020-12-29 | 2021-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Integrated thermal control design method for wings of solar unmanned aerial vehicle |
Non-Patent Citations (1)
| Title |
|---|
| 高峰;朱德润;: "太阳能无人机热管理系统设计及优化", 制冷与空调, no. 11, pages 32 - 37 * |
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