CN103600846A - Maximum power tracking cell array mechanism for solar-powered airplane, and tracking method - Google Patents
Maximum power tracking cell array mechanism for solar-powered airplane, and tracking method Download PDFInfo
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- CN103600846A CN103600846A CN201310654113.9A CN201310654113A CN103600846A CN 103600846 A CN103600846 A CN 103600846A CN 201310654113 A CN201310654113 A CN 201310654113A CN 103600846 A CN103600846 A CN 103600846A
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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
- Y02T50/40—Weight reduction
Abstract
The invention discloses a maximum power tracking cell array mechanism for a solar-powered airplane, and a tracking method. An airfoil skeleton comprises a honeycomb sandwich type square main beam for load bearing, and honeycomb sandwich type ribs, wherein a plurality of honeycomb sandwich type rigid solar cell modules are arranged on each airfoil, vein type truss structures for fixing the solar cell modules and fixing and supporting connecting cables among the solar cell modules are arranged on the cell modules; stepper motor groups are arranged on the honeycomb sandwich type ribs; hinge mechanisms are fixedly arranged on the stepper motor groups; the vein type truss structures are connected with stepper motors through the hinge mechanisms; a maximum power direction sensing system for angle judgment and a flight control computer for control commanding are arranged on an airplane body. According to the scheme, a solar cell array is efficiently used; spatial structures of the airfoils of an airplane are fully utilized, so that the restrictions of the dimension and the weight of the solar-powered airplane on the feasibility of the design scheme are maximally reduced.
Description
Technical field
The invention provides maximal power tracing battery battle array mechanism and tracking for a kind of solar powered aircraft, belong 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 because solar power is inexhaustible, nexhaustible, does not produce any waste, there is no the pollutions such as noise, to environment, can not produce harmful effect, is desirable clean energy resource.On the other hand, usining solar power as auxiliary energy and even the main energy sources of future aircraft, is the important research target that human development has directivity and frontier nature.Solar powered aircraft is to occur along with the reduction of solar cell cost in the seventies in last century, because solar powered aircraft flight does not need from carrying fuel, during for long boat, condition has been created in flight, and therefore, many developed countries are all devoted to the research and development of the Altitude Long Endurance Unmanned Air Vehicle based on solar power utilization.
Altitude Long Endurance Unmanned Air Vehicle is as can be at the unmanned vehicle of advection layer and above height thereof operation, can carry out Intelligence, Surveillance, and Reconnaissance, communication repeating, assessment, telecommunications and TV service are indicated, injured to target, the multiple military affairs such as atmosphere environment supervision and weather forecast and Civil Affairs Mission, become the focus of current research.
Current solar power unmanned plane mainly adopts solar-energy photo-voltaic cell as main power supply part, is limited by aircraft surfaces area limited, must the solar cell on limited area efficiently be utilized.Efficient utilization for solar array, except selecting the rigidity solar cell that conversion efficiency is higher, for example gallium arsenide solar cell or monocrystaline silicon solar cell, also can utilize limited wing spatial structure, realizes to a certain extent the maximal power tracing of battery battle array.
For this reason, the present invention, by by the effective application with the appropriate design of maximal power tracing mechanism and efficient rigidity solar array to solar powered aircraft, realizes the efficient utilization to solar power on limited area from battery body and space mechanism.
Summary of the invention
The object of the present invention is to provide maximal power tracing battery battle array mechanism and tracking for a kind of solar powered aircraft, not destroying under the prerequisite of wing space structure and aerodynamic configuration, utilize to greatest extent the solar power on limited area.
The present invention solves the problems of the technologies described above the technical scheme adopting to be to provide maximal power tracing battery battle array mechanism for a kind of solar powered aircraft, wing skeleton comprises for the square girder of honeycomb interlayer type of load-bearing and honeycomb interlayer type rib, wing is provided with some honeycomb interlayer type rigidity solar modules, honeycomb interlayer type rigidity solar module be provided with for connection cable between fixed solar battery module and fixing and support solar battery module venation truss structure, honeycomb interlayer type rib is provided with stepper motor, in stepper motor, be fixed with linkage, venation truss structure is connected by hinge arrangement with stepping motor, airframe is provided with for the maximum power orientation sensory perceptual system of angle judgement with for the flight control computer of control command.
Maximal power tracing battery battle array mechanism described above, described venation truss structure comprises 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, and venation truss structure is synchronizeed and rotated with stepper motor.
Maximal power tracing battery battle array mechanism described above, the tilt adjustment instruction that described stepper motor sends according to flight control computer regulates the inclination angle of honeycomb interlayer type rigidity solar module fixing on venation truss structure.
Maximal power tracing battery battle array mechanism described above, described maximum power orientation sensory perceptual system comprises motor fixed rack, microminiature stepping motor, servo support, battery sampling module, data collection and analysis module; Motor fixed rack is used for fixedly microminiature stepping motor, microminiature stepping motor is connected with servo support, in servo support, be provided with battery sampling module, battery sampling module is connected with data collection and analysis module, and the rotating shaft of microminiature stepping motor is towards consistent with rotation direction and stepper motor.
Maximal power tracing battery battle array mechanism described above, described honeycomb interlayer type rigidity solar module comprises insulating protection coating, rigidity solar battery sheet, the first lightweight glued membrane, insulated substrate; Described insulating protection coating is located at the outside face of honeycomb interlayer type rigidity solar module, the 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.
Maximal power tracing battery battle array mechanism described above, described insulated substrate comprises insulation film, the first composite fiber plate, the second lightweight glued membrane, honeycomb core, the 3rd lightweight glued membrane, the second composite fiber plate stacking successively from top to bottom; Described insulation film is for insulation electrical, the first composite fiber plate and the second composite fiber plate are obtained after pre-compacted is processed by composite fiber prepreg, the 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.
Maximal power tracing battery battle array mechanism described above, insulating protection coating can adopt organic silicon insulating varnish or UV glue, light transmittance >=90%.
A solar powered aircraft maximum power tracking method, comprises the following steps:
S1. carry out after the control command of tilt adjustment and data collection and analysis receiving flight control computer, maximum power orientation sensory perceptual system carries out data acquisition and the comparison under different angle;
S2. by the Data Comparison after gathering being determined when set, inscribe the optimum angle of incidence of battery sampling module, and this dip angle parameter is fed back to flight control computer;
S3. flight control computer sends tilt adjustment control command according to feedback parameter to stepper motor;
S4. the honeycomb interlayer type rigidity solar module that stepper motor makes to be fixed on venation truss structure pole by tilt adjustment obtains maximum power output under corresponding inclination angle.
Maximum power tracking method described above, described maximum power orientation sensory perceptual system sent tilt adjustment, data acquisition and a comparison order to flight control computer every 0.5 hour.
The present invention is maximal power tracing battery battle array mechanism and tracking for a kind of solar powered aircraft, can not destroy under the prerequisite of wing space structure and aerodynamic configuration, utilize to greatest extent the solar power on limited area, reduce to a certain extent the physical dimension of solar powered aircraft, and then improve the feasibility of solar powered aircraft design plan.
Accompanying drawing explanation
In order to be illustrated more clearly in the technical scheme in the embodiment of the present invention, to the accompanying drawing of required use in embodiment be briefly described below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skills, do not paying under the prerequisite of creative work, can also obtain according to these accompanying drawings other accompanying drawing.
Fig. 1 is the structural representation of solar powered aircraft battery battle array of the present invention;
Fig. 2 is the structural representation of solar powered aircraft battery battle array steering gear of the present invention;
Fig. 3 is the structural representation of maximum power of the present invention orientation sensory perceptual system.
Number in the figure is described 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. maximum power orientation sensory perceptual system, 9. flight control computer, 10. linkage, 11. motor fixed racks, 12. microminiature stepping motors, 13. servo supports, 14. battery sampling modules, 15. data collection and analysis modules.
The specific embodiment
Below in conjunction with a kind of solar powered aircraft in Fig. 1,2,3 couples of the present invention, with maximal power tracing battery battle array mechanism and tracking, be further described:
As shown in Figure 1, maximal power tracing battery battle array mechanism for a kind of solar powered aircraft of the present invention, wing skeleton comprises the square girder 3 of honeycomb interlayer type and the honeycomb interlayer type rib 4 for load-bearing, wing is provided with some honeycomb interlayer type rigidity solar modules 2, honeycomb interlayer type rigidity solar module 2 be provided with for connection cable between fixed solar battery module and fixing and support solar battery module venation truss structure, honeycomb interlayer type rib 4 is provided with stepper motor 7, in stepper motor 7, be fixed with linkage 10, venation truss structure is connected by hinge arrangement 10 with stepping motor 7, airframe is provided with for the maximum power orientation sensory perceptual system 8 of angle judgement with for the flight control computer 9 of control command.Described 7 tilt adjustment instructions that send according to flight control computer 9 of stepper motor regulate the inclination angle of honeycomb interlayer type rigidity solar module 2 fixing on venation truss structure, and described stepper motor 7 is distributed microminiature stepping motor.
The present invention both can realize the object that solar array high efficiency is used, and again the wing space structure of aircraft was made full use of, and can reduce to greatest extent solar powered aircraft constraint to design plan feasibility in yardstick and weight.
As shown in Figure 2, described venation truss structure comprises 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, and venation truss structure is synchronizeed rotation with stepper motor 10.
Wherein, the rod member in this venation truss structure can pressurize through rolling up the mode of laying layer by carbon fiber prepreg or glass fibre prepreg, curing forming, and also can through winding, impregnation, curing mode, realize by carbon fibre tow or glass fiber strand; Rod member in venation truss structure is built-in connection cable as requested also, comprises power transmission cable and the communications cable; Linkage 10 in this venation truss structure can adopt aerolite to form through machinework.
As shown in Figure 3, described maximum power orientation sensory perceptual system 8 comprises motor fixed rack 11, microminiature stepping motor 12, servo-actuated 13, battery sampling module 14, data collection and analysis module 15, motor fixed rack 11 is for fixing microminiature stepping motor 12, microminiature stepping motor 12 is connected with servo support 13, in servo support 13, be provided with battery sampling module 14, battery sampling module 14 is connected 15 with data collection and analysis module, the rotating shaft of microminiature stepping motor 12 is towards consistent with rotation direction and stepper motor 7, microminiature stepping motor 12, the rotating shaft of stepper motor 7 is towards all consistent with wing 1 chord length direction, microminiature stepping motor 12 is fixed on fuselage interior by motor fixed rack 11, stepper motor 7 is when being connected with linkage 10, inside be embedded in honeycomb interlayer type rib 4.
Wherein, microminiature stepping motor 12 is fixed on motor fixed rack 11 by sleeve and bearing; Servo support 13 is fixed on machine shaft by sleeve, and guarantees 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 structure and the material identical with forming honeycomb interlayer type rigidity solar module 2 to form formation, can adopt the distribution form of monolithic, also can adopt the distribution form of multi-disc.
Described honeycomb interlayer type rigidity solar module 2 comprises insulating protection coating, rigidity solar battery sheet, the first lightweight glued membrane, insulated substrate; Described insulating protection coating is located at the outside face of honeycomb interlayer type rigidity solar module, the 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%, and XT-111 type organic silicon insulating varnish preferably, light transmittance is 93.6%.
Wherein, insulated substrate comprises insulation film, the first composite fiber plate, the second lightweight glued membrane, honeycomb core, the 3rd lightweight glued membrane, the second composite fiber plate stacking successively from top to bottom; Described insulation film is for insulation electrical, the first composite fiber plate and the second composite fiber plate are obtained after pre-compacted is processed by composite fiber prepreg, the 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'uses form consistent with material in honeycomb interlayer type rigidity solar module 2 insulated substrates.
Wherein, the PM550 type data acquisition module that this data collection and analysis module 15 adopts based on PC104 bus type, and digital signal processing unit that TMS320LF2808 is core carries out data processing and information is fed back by take.Data collection and analysis module 15 can adopt pci bus formula, also can adopt PC104 bus type.Wherein, this data collection and analysis module 15 is mainly by battery module output voltage in different azimuth, the collection of electric current, carry out the comparison of horsepower output in different azimuth, by above-mentioned relatively more definite orientation of not descending in the same time maximum power to produce, and by this bearing data feedback flight control computer 9, the corresponding control command of flight control computer 9 issue is to the control system of stepper motor 7, 7 rotations of control step group of motors are to corresponding angle, thereby each honeycomb interlayer type rigidity solar module 2 that guarantees to be fixed on venation truss structure pole 5 obtains maximum power stage,
Under service conditions, carry out after the control command of tilt adjustment and data collection and analysis receiving flight control computer 9, maximum power orientation sensory perceptual system 8 will carry out tilt adjustment to the servo support 13 being fixed on its microminiature stepping motor, and, in control process, the battery sampling module 14 of utilizing 15 pairs of data collection and analysis modules to be fixed on servo support 13 is carried out to collection and the contrast of power parameter.By Data Comparison, determine when set and inscribe, the optimum angle of incidence of battery sampling module 14, and this dip angle parameter is fed back to flight control computer 9, flight control computer 9 sends tilt adjustment control command according to this feedback information to stepper motor 7, and the honeycomb interlayer type rigidity solar module 2 that stepper motor 7 makes to be fixed on venation truss structure pole 5 by tilt adjustment obtains maximum power output under corresponding inclination angle.
For taking into account compromise between obtaining of energy consumption and maximum power, described maximum power orientation sensory perceptual system 8 sent tilt adjustment, data acquisition and a comparison order to flight control computer 9 every 0.5 hour.
Maximal power tracing battery battle array mechanism for a kind of solar powered aircraft of the present invention, it is by the comprehensive application of light rigidity solar module and maximal power tracing mechanism, can, not destroying under the prerequisite of wing space structure and aerodynamic configuration, utilize to greatest extent the solar power on limited area.Thereby, can reduce to a certain extent the physical dimension of solar powered aircraft, and then improve the feasibility of solar powered aircraft design plan.
It should be pointed out that this example just lists expressivity application process of the present invention is described, but not for limiting the present invention.Any personnel that are familiar with this kind of operation technique, 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 be as listed in claims.
Claims (9)
1. maximal power tracing battery battle array mechanism for a solar powered aircraft, it is characterized in that: wing skeleton comprises for the square girder of honeycomb interlayer type of load-bearing and honeycomb interlayer type rib, wing is provided with some honeycomb interlayer type rigidity solar modules, honeycomb interlayer type rigidity solar module be provided with for connection cable between fixed solar battery module and fixing and support solar battery module venation truss structure, honeycomb interlayer type rib is provided with stepper motor, in stepper motor, be fixed with linkage, venation truss structure is connected by hinge arrangement with stepping motor, airframe is provided with for the maximum power orientation sensory perceptual system of angle judgement with for the flight control computer of control command.
2. maximal power tracing battery battle array as claimed in claim 1 mechanism, it is characterized in that: described venation truss structure comprises 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, and venation truss structure is synchronizeed and rotated with stepper motor.
3. maximal power tracing battery battle array as claimed in claim 1 mechanism, is characterized in that: the tilt adjustment instruction that described stepper motor sends according to flight control computer regulates the inclination angle of honeycomb interlayer type rigidity solar module fixing on venation truss structure.
4. maximal power tracing battery battle array as claimed in claim 1 mechanism, is characterized in that: described maximum power orientation sensory perceptual system comprises motor fixed rack, microminiature stepping motor, servo support, battery sampling module, data collection and analysis module; Motor fixed rack is used for fixedly microminiature stepping motor, microminiature stepping motor is connected with servo support, in servo support, be provided with battery sampling module, battery sampling module is connected with data collection and analysis module, and the rotating shaft of microminiature stepping motor is towards consistent with rotation direction and stepper motor.
5. maximal power tracing battery battle array as claimed in claim 1 mechanism, is characterized in that: described honeycomb interlayer type rigidity solar module comprises insulating protection coating, rigidity solar battery sheet, the first lightweight glued membrane, insulated substrate; Described insulating protection coating is located at the outside face of honeycomb interlayer type rigidity solar module, the 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.
6. maximal power tracing battery battle array as claimed in claim 5 mechanism, is characterized in that: described insulated substrate comprises insulation film, the first composite fiber plate, the second lightweight glued membrane, honeycomb core, the 3rd lightweight glued membrane, the second composite fiber plate stacking successively from top to bottom; Described insulation film is for insulation electrical, the first composite fiber plate and the second composite fiber plate are obtained after pre-compacted is processed by composite fiber prepreg, the 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.
7. maximal power tracing battery battle array as claimed in claim 5 mechanism, is characterized in that: insulating protection coating can adopt organic silicon insulating varnish or UV glue, light transmittance >=90%.
8. a solar powered aircraft maximum power tracking method, is characterized in that, comprises the following steps:
S1. carry out after the control command of tilt adjustment and data collection and analysis receiving flight control computer, maximum power orientation sensory perceptual system carries out data acquisition and the comparison under different angle;
S2. by the Data Comparison after gathering being determined when set, inscribe the optimum angle of incidence of battery sampling module, and this dip angle parameter is fed back to flight control computer;
S3. flight control computer sends tilt adjustment control command according to feedback parameter to stepper motor;
S4. the honeycomb interlayer type rigidity solar module that stepper motor makes to be fixed on venation truss structure pole by tilt adjustment obtains maximum power output under corresponding inclination angle.
9. maximum power tracking method as claimed in claim 8, is characterized in that: described maximum power orientation sensory perceptual system sent tilt adjustment, data acquisition and a comparison order to flight control computer every 0.5 hour.
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| CN201310654113.9A CN103600846B (en) | 2013-12-04 | 2013-12-04 | Solar powered aircraft maximal power tracing cell array mechanism and tracking |
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| CN201310654113.9A CN103600846B (en) | 2013-12-04 | 2013-12-04 | Solar powered aircraft maximal power tracing cell array mechanism and tracking |
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| CN103600846B CN103600846B (en) | 2016-07-13 |
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| CN104267737A (en) * | 2014-09-22 | 2015-01-07 | 北京航空航天大学 | Solar four-rotor aircraft capable of tracking sun |
| 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 |
| CN107117294A (en) * | 2016-02-25 | 2017-09-01 | 鹦鹉无人机股份有限公司 | Provided with the unmanned plane for adding powerful 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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| CN104267737A (en) * | 2014-09-22 | 2015-01-07 | 北京航空航天大学 | Solar four-rotor aircraft capable of tracking sun |
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| 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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| CN103600846B (en) | 2016-07-13 |
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Effective date of registration: 20190301 Address after: 213000 No. 199 Fenglin South Road, Wujin High-tech Industrial Development Zone, Changzhou City, Jiangsu Province Co-patentee after: Xinyu Defense Technology Co., Ltd. Patentee after: New United Group Co., Ltd. Address before: 213164 Fenglin Road 68, hi tech Industrial Development Zone, Wujin District, Changzhou, Jiangsu Patentee before: New United Group Co., Ltd. |