CN103600846B - Solar powered aircraft maximal power tracing cell array mechanism and tracking - Google Patents

Solar powered aircraft maximal power tracing cell array mechanism and tracking Download PDF

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Publication number
CN103600846B
CN103600846B CN201310654113.9A CN201310654113A CN103600846B CN 103600846 B CN103600846 B CN 103600846B CN 201310654113 A CN201310654113 A CN 201310654113A CN 103600846 B CN103600846 B CN 103600846B
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venation
truss
interlayer type
honeycomb interlayer
cell array
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CN103600846A (en
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孙康文
祝明
郑泽伟
徐伟强
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Xinyu Defense Technology Co., Ltd.
New United Group Co Ltd
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New United Group Co Ltd
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    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/40Weight reduction

Abstract

The invention discloses a kind of solar powered aircraft maximal power tracing cell array mechanism and tracking, wing skeleton includes the square girder of honeycomb interlayer type for load-bearing and honeycomb interlayer type rib, wing is provided with some pieces of honeycomb interlayer type rigidity solar modules, battery module is provided with for fixing solar module and venation truss structure that is fixing and that be connected cable between support solar module, honeycomb interlayer type rib is provided with stepper motor, stepper motor is fixed with linkage, venation truss structure is connected by hinge arrangement with motor, airframe is provided with the peak power orientation sensory perceptual system for angle judgement and the flight control computer for control instruction.The program had both achieved the efficient use of solar array, again the wing space structure of aircraft had been made full use of, and can reduce solar powered aircraft constraint to design feasibility on yardstick and weight to greatest extent.

Description

Solar powered aircraft maximal power tracing cell array mechanism and tracking
Technical field
The present invention provides a kind of solar powered aircraft maximal power tracing cell array mechanism and tracking, belongs to solar-photovoltaic technology field.
Background technology
Photovoltaic generation is a kind of generally acknowledged with high content of technology, rising new energy technology.This is owing to solar energy is inexhaustible, nexhaustible, does not produce any garbage, it does not have noise etc. pollute, and environment will not be produced harmful effect, be desirable clean energy resource.On the other hand, using solar energy as the supplementary energy of future aircraft or even main energy sources, it it is the human development important research target with directivity and frontier nature.Solar powered aircraft is to occur in the seventies in last century of the reduction along with solaode cost, owing to solar powered aircraft flight need not from carrying fuel, during for long boat, flight creates condition, and therefore, many developed countries are all devoted to the research and development of the Altitude Long Endurance Unmanned Air Vehicle based on Solar use.
Altitude Long Endurance Unmanned Air Vehicle is as the unmanned vehicle that can run at stratosphere and level above thereof, Intelligence, Surveillance, and Reconnaissance can be performed, communication relay, Target indication, injure assessment, telecommunications and TV service, multiple military affairs and the Civil Affairs Missions such as atmosphere environment supervision and weather forecast, it has also become the focus of current research.
Current solar energy unmanned plane mainly adopts solar-energy photo-voltaic cell as main power supply part, is limited by aircraft surfaces limited area, it is necessary to the solaode on limited areal is efficiently utilized.Efficient utilization for solar array, except selecting the rigidity solaode that conversion efficiency is higher, such as gallium arsenide solar cell or monocrystaline silicon solar cell, be also with limited wing stereochemical structure, realize the maximal power tracing of cell array to a certain extent.
For this, the present invention will pass through the effective application to the solar powered aircraft appropriate design with maximal power tracing mechanism and efficient rigidity solar array, realize the efficient utilization of solar energy on limited areal from battery body and space mechanism.
Summary of the invention
It is an object of the invention to provide a kind of solar powered aircraft maximal power tracing cell array mechanism and tracking, under not destroying the premise of wing space structure and aerodynamic configuration, utilize the solar energy on limited areal to greatest extent.
The present invention solves above-mentioned technical problem and offer a kind of solar powered aircraft maximal power tracing cell array mechanism is provided, wing skeleton includes the square girder of honeycomb interlayer type for load-bearing and honeycomb interlayer type rib, wing is provided with some pieces of honeycomb interlayer type rigidity solar modules, honeycomb interlayer type rigidity solar module be provided with for fix solar module and fixing with support be connected between solar module cable venation truss structure, honeycomb interlayer type rib is provided with stepper motor, stepper motor is fixed with linkage, venation truss structure is connected by hinge arrangement with motor, airframe is provided with the peak power orientation sensory perceptual system for angle judgement and the flight control computer for control instruction.
Described above maximal power tracing cell array mechanism, described venation truss structure includes venation truss structure pole and venation truss structure mobile jib, venation truss structure is composite fiber rod member, the mode that venation truss structure is bolted or screw connects is connected with the linkage being fixed in stepper motor, venation truss structure and stepper motor synchronous axial system.
Described above maximal power tracing cell array mechanism, the inclination angle of honeycomb interlayer type rigidity solar module fixing on venation truss structure is adjusted by the tilt adjustment instruction that described stepper motor then sends according to flight control computer.
Described above maximal power tracing cell array mechanism, described peak power orientation sensory perceptual system includes motor fixed rack, microminiature motor, servo support, battery sampling module, data collection and analysis module;Motor fixed rack is used for fixing microminiature motor, microminiature motor is connected with servo support, being provided with battery sampling module in servo support, battery sampling module is connected with data collection and analysis module, and the rotating shaft of microminiature motor is towards consistent with stepper motor with rotation direction.
Described above maximal power tracing cell array mechanism, described honeycomb interlayer type rigidity solar module includes insulating protection coating, rigidity solar battery sheet, the first lightweight glued membrane, insulated substrate;Described insulating protection coating is located at the outer surface of honeycomb interlayer type rigidity solar module, first lightweight glued membrane is filled among the gap of rigidity solar battery sheet lower surface and insulated substrate, insulated substrate is located at the bottom of honeycomb interlayer type rigidity solar module, and insulated substrate adopts honeycomb interlayer type structure.
Described above maximal power tracing cell array mechanism, insulation film that described insulated substrate includes stacking successively from top to bottom, the first composite fiber plate, the second lightweight glued membrane, honeycomb core, the 3rd lightweight glued membrane, the second composite fiber plate;Described insulation film is used for insulation electrical, first composite fiber plate and the second composite fiber plate are obtained after pre-compacted processes by composite fiber prepreg, second lightweight glued membrane is used for connecting the first composite fiber plate and honeycomb core, and the 3rd lightweight glued membrane is used for connecting honeycomb core and the 3rd composite fiber plate.
Described above maximal power tracing cell array mechanism, insulating protection coating can adopt organic silicon insulating varnish or UV glue, light transmittance >=90%.
A kind of solar powered aircraft maximum power tracking method, comprises the following steps:
S1., after receiving flight control computer and carry out the control instruction of tilt adjustment and data collection and analysis, peak power orientation sensory perceptual system carries out data acquisition under different angle and compares;
S2. by the Data Comparison after gathering is determined the optimum angle of incidence of battery sampling module under given moment, and this dip angle parameter is fed back to flight control computer;
S3. stepper motor is sent tilt adjustment control instruction according to feedback parameter by flight control computer;
S4. stepper motor makes the honeycomb interlayer type rigidity solar module being fixed on venation truss structure pole obtain maximum power output under corresponding inclination angle by tilt adjustment.
Maximum power tracking method described above, described peak power orientation sensory perceptual system is every tilt adjustment of transmission in 0.5 hour, data acquisition and compares instruction to flight control computer.
One solar powered aircraft maximal power tracing cell array mechanism of the present invention and tracking, can under not destroying the premise of wing space structure and aerodynamic configuration, utilize the solar energy on limited areal to greatest extent, reduce the physical dimension of solar powered aircraft to a certain extent, and then improve the feasibility of solar powered aircraft design.
Accompanying drawing explanation
In order to be illustrated more clearly that the technical scheme in the embodiment of the present invention, the accompanying drawing used required in embodiment will be briefly described below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the premise not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the structural representation of solar powered aircraft cell array of the present invention;
Fig. 2 is the structural representation of solar powered aircraft cell array steering gear of the present invention;
Fig. 3 is the structural representation of peak power orientation of the present invention sensory perceptual system.
Number in the figure illustrates as follows:
1. wing, 2. honeycomb interlayer type rigidity solar module, the 3. square girder of honeycomb interlayer type, 4. honeycomb interlayer type rib, 5. venation truss structure pole, 6. venation truss structure mobile jib, 7. stepper motor, 8. peak power orientation sensory perceptual system, 9. flight control computer, 10. linkage, 11. motor fixed rack, 12. microminiature motors, 13. servo supports, 14. battery sampling module, 15. data collection and analysis modules.
Detailed description of the invention
It is further described below in conjunction with a kind of solar powered aircraft maximal power tracing cell array mechanism in couple present invention of Fig. 1,2,3 and tracking:
As shown in Figure 1, one of the present invention solar powered aircraft maximal power tracing cell array mechanism, wing skeleton includes the square girder 3 of the honeycomb interlayer type for load-bearing and honeycomb interlayer type rib 4, wing is provided with some pieces of honeycomb interlayer type rigidity solar modules 2, honeycomb interlayer type rigidity solar module 2 be provided with for fix solar module and fixing with support be connected between solar module cable venation truss structure, honeycomb interlayer type rib 4 is provided with stepper motor 7, stepper motor 7 is fixed with linkage 10, venation truss structure is connected by hinge arrangement 10 with motor 7, airframe is provided with the peak power orientation sensory perceptual system 8 for angle judgement and the flight control computer 9 for control instruction.The inclination angle of honeycomb interlayer type rigidity solar module 2 fixing on venation truss structure is adjusted by the tilt adjustment instruction that described stepper motor 7 then sends according to flight control computer 9, and described stepper motor 7 is distributed microminiature motor.
The present invention both can realize the purpose that solar array high efficiency uses, and again the wing space structure of aircraft has been made full use of, and can reduce solar powered aircraft constraint to design feasibility on yardstick and weight to greatest extent.
As shown in Figure 2, described venation truss structure includes venation truss structure pole 5 and venation truss structure mobile jib 6, venation truss structure is composite fiber rod member, the mode that venation truss structure is bolted or screw connects is connected with the linkage 10 being fixed in stepper motor 7, venation truss structure and stepper motor 10 synchronous axial system.
Wherein, the rod member in this venation truss structure can be pressurizeed through the mode rolling up laying layer by carbon fiber prepreg or glass fibre prepreg, solidify and form, it is possible to by carbon fibre tow or glass fiber strand through winding, impregnation, solidification mode realize;Rod member in venation truss structure also can built-in connection cable as requested, including power transmission cable and the communications cable;Linkage 10 in this venation truss structure can adopt aerolite to be machined formation.
As it is shown on figure 3, described peak power orientation sensory perceptual system 8 includes motor fixed rack 11, microminiature motor 12, servo-actuated 13 frame, battery sampling module 14, data collection and analysis module 15;Motor fixed rack 11 is used for fixing microminiature motor 12, microminiature motor 12 is connected with servo support 13, battery sampling module 14 it is provided with in servo support 13, battery sampling module 14 is connected 15 with data collection and analysis module, the rotating shaft of microminiature motor 12 is towards consistent with stepper motor 7 with rotation direction, microminiature motor 12, the rotating shaft of stepper motor 7 is towards all consistent with wing 1 chord length direction, microminiature motor 12 is fixed on fuselage interior by motor fixed rack 11, stepper motor 7 is while being connected with linkage 10, inside it is embedded in honeycomb interlayer type rib 4.
Wherein, microminiature motor 12 is fixed on motor fixed rack 11 by sleeve and bearing;Servo support 13 is fixed on machine shaft by sleeve, and ensures the rotation of servo support 13 and towards the rotation with honeycomb interlayer type rigidity solar module 2 and towards consistent;Wherein, this battery sampling module 14 adopts the structure identical with constituting honeycomb interlayer type rigidity solar module 2 to constitute with material composition, can adopt the distribution form of monolithic, it is possible to adopt the distribution form of multi-disc.
Described honeycomb interlayer type rigidity solar module 2 includes insulating protection coating, rigidity solar battery sheet, the first lightweight glued membrane, insulated substrate;Described insulating protection coating is located at the outer surface of honeycomb interlayer type rigidity solar module, first lightweight glued membrane is filled among the gap of rigidity solar battery sheet lower surface and insulated substrate, insulated substrate is located at the bottom of honeycomb interlayer type rigidity solar module, and insulated substrate adopts honeycomb interlayer type structure.Insulating protection coating can adopt organic silicon insulating varnish or UV glue, light transmittance >=90%, it is preferred that XT-111 type organic silicon insulating varnish, and light transmittance is 93.6%.
Wherein, insulated substrate includes stacking successively from top to bottom insulation film, the first composite fiber plate, the second lightweight glued membrane, honeycomb core, the 3rd lightweight glued membrane, the second composite fiber plate;Described insulation film is used for insulation electrical, first composite fiber plate and the second composite fiber plate are obtained after pre-compacted processes by composite fiber prepreg, second lightweight glued membrane is used for connecting the first composite fiber plate and honeycomb core, and the 3rd lightweight glued membrane is used for connecting honeycomb core and the 3rd composite fiber plate.
Described honeycomb interlayer type rib 4 materials'use is consistent with material composition in honeycomb interlayer type rigidity solar module 2 insulated substrate.
Wherein, this data collection and analysis module 15 adopts the PM550 type data acquisition module of Based PC 104 bus type, and processes and information feedback by carrying out data with the TMS320LF2808 digital signal processing unit being core.Data collection and analysis module 15 can adopt pci bus formula, it is possible to adopts PC104 bus type.Wherein, this data collection and analysis module 15 is mainly by different azimuth upper battery modules output voltage, the collection of electric current, carry out the comparison of output in different azimuth, the orientation not descending peak power to produce in the same time is determined by above-mentioned comparison, and this bearing data is fed back flight control computer 9, flight control computer 9 issues corresponding control instruction to the control system of stepper motor 7, control stepper motor 7 to rotate to corresponding angle, thus ensureing that each honeycomb interlayer type rigidity solar module 2 being fixed on venation truss structure pole 5 obtains maximum power output;
Under working condition, after receiving flight control computer 9 and carry out the control instruction of tilt adjustment and data collection and analysis, the servo support 13 being fixed on its microminiature motor will be carried out tilt adjustment by peak power orientation sensory perceptual system 8, and, in adjustment process, by utilizing data collection and analysis module 15, the battery sampling module 14 being fixed on servo support 13 is carried out collection and the contrast of power parameter.Determine under given moment by Data Comparison, the optimum angle of incidence of battery sampling module 14, and this dip angle parameter is fed back to flight control computer 9, stepper motor 7 is sent tilt adjustment control instruction according to this feedback information by flight control computer 9, and stepper motor 7 makes the honeycomb interlayer type rigidity solar module 2 being fixed on venation truss structure pole 5 obtain maximum power output under corresponding inclination angle by tilt adjustment.
For taking into account trading off between energy expenditure and peak power acquisition, described peak power orientation sensory perceptual system 8 sent tilt adjustment, a data acquisition and compares instruction to flight control computer 9 every 0.5 hour.
One of the present invention solar powered aircraft maximal power tracing cell array mechanism, it is by the comprehensive utilization of light rigidity solar module with maximal power tracing mechanism, under not destroying the premise of wing space structure and aerodynamic configuration, the solar energy on limited areal can be utilized to greatest extent.Thus, the physical dimension of solar powered aircraft can be reduced to a certain extent, and then improve the feasibility of solar powered aircraft design.
It should be pointed out that, that this example only listing property illustrates the application process of the present invention, not for the restriction present invention.Any personnel being familiar with this kind of use technology, all can without departing from the spirit and scope of the present invention, modify to above-described embodiment.Therefore, the scope of the present invention, should as listed by claims.

Claims (6)

1. solar powered aircraft maximal power tracing cell array mechanism, it is characterized in that: wing skeleton includes the square girder of honeycomb interlayer type for load-bearing and honeycomb interlayer type rib, wing is provided with some pieces of honeycomb interlayer type rigidity solar modules, honeycomb interlayer type rigidity solar module be provided with support for fixed cellular sandwich type rigidity solar module and being fixed on connect between honeycomb sandwich type rigidity solar module cable venation truss structure, honeycomb interlayer type rib is provided with stepper motor, stepper motor is fixed with linkage, venation truss structure is connected by hinge arrangement with stepper motor, airframe is provided with the peak power orientation sensory perceptual system for angle judgement and the flight control computer for control instruction;
Described venation truss structure includes venation truss structure pole and venation truss structure mobile jib, venation truss structure is composite fiber rod member, the mode that venation truss structure is bolted or screw connects is connected with the linkage being fixed in stepper motor, venation truss structure and stepper motor synchronous axial system.
2. as claimed in claim 1 maximal power tracing cell array mechanism, it is characterised in that: the inclination angle of the tilt adjustment instruction that described stepper motor sends according to the flight control computer honeycomb interlayer type rigidity solar module to fixing on venation truss structure is adjusted.
3. as claimed in claim 1 maximal power tracing cell array mechanism, it is characterised in that: described peak power orientation sensory perceptual system includes motor fixed rack, microminiature motor, servo support, battery sampling module, data collection and analysis module;Motor fixed rack is used for fixing microminiature motor, microminiature motor is connected with servo support, being provided with battery sampling module in servo support, battery sampling module is connected with data collection and analysis module, and the rotating shaft of microminiature motor is towards consistent with stepper motor with rotation direction.
4. as claimed in claim 1 maximal power tracing cell array mechanism, it is characterised in that: described honeycomb interlayer type rigidity solar module includes insulating protection coating, rigidity solar battery sheet, the first lightweight glued membrane, insulated substrate;Described insulating protection coating is located at the outer surface of honeycomb interlayer type rigidity solar module, first lightweight glued membrane is filled among the gap of rigidity solar battery sheet lower surface and insulated substrate, insulated substrate is located at the bottom of honeycomb interlayer type rigidity solar module, and insulated substrate adopts honeycomb interlayer type structure.
5. as claimed in claim 4 maximal power tracing cell array mechanism, it is characterised in that: insulation film that described insulated substrate includes stacking successively from top to bottom, the first composite fiber plate, the second lightweight glued membrane, honeycomb core, the 3rd lightweight glued membrane, the second composite fiber plate;Described insulation film is used for insulation electrical, first composite fiber plate and the second composite fiber plate are obtained after pre-compacted processes by composite fiber prepreg, second lightweight glued membrane is used for connecting the first composite fiber plate and honeycomb core, and the 3rd lightweight glued membrane is used for connecting honeycomb core and the 3rd composite fiber plate.
6. as claimed in claim 4 maximal power tracing cell array mechanism, it is characterised in that: insulating protection coating can adopt organic silicon insulating varnish or UV glue, light transmittance >=90%.
CN201310654113.9A 2013-12-04 2013-12-04 Solar powered aircraft maximal power tracing cell array mechanism and tracking Active CN103600846B (en)

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CN104267737B (en) * 2014-09-22 2017-07-14 北京航空航天大学 One kind can be to day solar battery quadrotor
CN105460201A (en) * 2015-11-13 2016-04-06 中国人民解放军国防科学技术大学 Wing leading edge of multifunctional solar aircraft
FR3048187A1 (en) * 2016-02-25 2017-09-01 Parrot Drones DRONE WITH BATTERY PACK
CN107745819A (en) * 2017-09-27 2018-03-02 重庆科创职业学院 A kind of fixed-wing solar powered aircraft

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