CN105480402A - Scheme of solar energy unmanned aerial vehicle with novel layout - Google Patents
Scheme of solar energy unmanned aerial vehicle with novel layout Download PDFInfo
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- CN105480402A CN105480402A CN201510801533.4A CN201510801533A CN105480402A CN 105480402 A CN105480402 A CN 105480402A CN 201510801533 A CN201510801533 A CN 201510801533A CN 105480402 A CN105480402 A CN 105480402A
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Abstract
The invention provides a scheme of solar energy unmanned aerial vehicle with a novel layout. According to the method, a straight wing is used as a base, and an adjustable double-rhombus structure is adopted, so that the whole rigidity of a platform is improved, the dimension of the platform is reduced(a wingspan dimension is reduced ), and modularized combination is realized; the adjustable angle of an upper rhombic wing and a lower rhombic wing is adjusted, so that the center of gravity of such an unmanned aerial vehicle is guaranteed to be positioned in a vehicle body in the taking-off state without causing bending forwards or turning-over backwards; in the flying process, a swept forward/swept backward angle is effectively changed, so that the light-receiving areas of solar batteries on the surfaces of wings are effectively enlarged; besides, the surface areas of the wings are enlarged, so that the lifting force is improved; according to the modularized double-rhombus solar energy unmanned aerial vehicle scheme developed based on the method, the weight of wing structures of the solar energy unmanned aerial vehicle can be reduced to the furthest extent, and the flying performance and the load capacity of the solar energy unmanned aerial vehicle are improved.
Description
One, technical field:
The invention provides a kind of novel layouts solar power unmanned plane scheme, belong to aerospace vehicle housing construction technical field.
Two, background technology:
Altitude Long Endurance Unmanned Air Vehicle, as the unmanned vehicle that can run at advection layer and above height thereof, can be used for Intelligence, Surveillance, and Reconnaissance, communication repeating, Target indication, injures assessment, the various fields such as telecommunications and TV service.The multiple military affairs such as atmosphere environment supervision and weather forecast and Civil Affairs Mission, become the focus of current research.
Using solar power as the auxiliary energy of future aircraft even main energy sources, it is the important research target that human development has directivity and frontier nature.Solar powered aircraft occurs 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, for flight during long boat creates condition.Therefore, many developed countries are all devoted to the research and development of the Altitude Long Endurance Unmanned Air Vehicle based on solar power.
Current solar power unmanned plane mainly adopts solar-energy photo-voltaic cell as main power supply part, is limited by aircraft surfaces limited area.While raising solar cell degree of utilization, the laying area of solar panel can be increased.Since coming out from aircraft, it has first been biplane; Developing deeply is to triplane; Develop monoplane afterwards, until now.Moreover owing to being solar power unmanned plane, in order to produce enough energy, often aspect ratio design is larger.In other words, be exactly that after solar power unmanned plane takes off, on wing, degree of deflecting is larger.Thus solar panels can be made to follow wing deflect, and then the solar radiation total amount that solar panels can be made to accept reduces.Therefore can reduce the energy that solar panel exports, cruise when being unfavorable for that the unmanned captain of solar power navigates.
For this reason, the invention provides a kind of novel layouts solar power unmanned plane scheme, by biplane and monoplane are bonded adjustable double diamond structure, and the reinforcement aspect consideration of airframe structure is proposed.First, adjustable double rhombus can increase specific floor area, can increase the laying area of solar panel like this, produce more energy; Secondly, the rigidity of structure can be increased, reduce the distortion of wing when flying, making wing be more conducive to solar panel produce power; Again, this structure can effectively reduce the height of unmanned plane, because the general span of solar power unmanned plane is compared, when ground is parked, in order to prevent the wing wing from slightly contacting to earth, need higher by what highly design, and this mechanism just effectively reduce wing distortion when aircraft is parked; Finally, this adjustable double rhombus adopts modular design, is convenient to transport and installs.Thus more meet in current designs solar powered aircraft structure light wt, the composite request exporting energy efficient.
Three, summary of the invention:
(1) object: the object of the present invention is to provide a kind of novel layouts solar power unmanned plane scheme, solar power unmanned plane wing based on the method development can meet the requirement of solar power unmanned plane in battery conversion efficiency and unit area battery specific power two, and effectively can solve solar power unmanned plane wing large deformation problem.In addition, based on the method, effectively can reduce the loss of solar power unmanned plane in configuration aspects, and then improve the load capacity of solar power unmanned plane.
(2) technical scheme: a kind of novel layouts solar power of the present invention unmanned plane scheme, the technical measures of the method is as follows: based on the straight wing, utilize adjustable double diamond structure, improve the integral rigidity of platform, reduce the yardstick (reduction spanwise extent) of platform, realize modular combination; By the adjustment of the upper bottom wing variable-angle of rhombus, ensure that such aircraft is under takeoff condition, center of gravity is positioned at internal body, unlikely cause lean forward or after turn over; Effectively change the angle of sweepforward/sweepback in flight course, effectively increase the light-receiving area of aerofoil surface solar cell, increase the face area to wing simultaneously, increase lift.
Based on such scheme, both solar powered aircraft can have been met to structure light wt, the application target exporting energy efficient, meet again the large rigidity requirement of solar power unmanned plane wing, by reducing the height of solar power unmanned plane to greatest extent, reduce its complete machine mechanism weight, improve flight heart stalk and the load capacity of solar power unmanned plane.
Described adjustable double diamond structure, mainly in the position of unmanned plane symmetry, utilizes wing to be built into an adjustable diamond structure.Arrange fuselage in each wing junction, installation is carried simultaneously, thus distractive load.From top to bottom once: solar panel, Double Diamond structure the first half, adjustable double diamond structure actuator, solar panel, middle outside wing, Double Diamond mechanism the latter half.From left to right successively: the left outside wing, left diamond structure, central wing, right diamond structure, starboard outboard.
A kind of novel layouts solar power of the present invention unmanned plane scheme, basic step is as follows:
1. materials procurement, inspection, ensure that selected materials meets operating needs and technological forming is wanted
2. ask, especially compatible with environment requirement;
3. require to carry out making wing according to design plan and stock left for machining, also will make the stringer of wing and vertical wall simultaneously.
4. require to carry out making aerofoil profile according to design plan and stock left for machining, also will make the stringer of aileron and vertical wall simultaneously.
5. meanwhile, can require according to design plan and stock left for machining the cutting carrying out making skin material;
6. the connection carrying out making diamond structure control apparatus and upper and lower middle two wings of diamond structure is required according to design plan and stock left for machining.
7. require to carry out making fuselage according to design plan and stock left for machining.
8. according to design plan, this solar power unmanned plane is assembled, and revise profile, reduce interference drag.
9. fuselage is arranged on two wing junctions, every downside, be convenient to like this load all with distribution, reduction concentrated load, while also relatively can reduce the amount of deflection of wing in-flight.This reduces the fatigue stress of each flight, the service life increasing unmanned plane can be played.
10., for the overlapping place of adjustable double rhombic solar unmanned plane intermodule, utilize sealant to carry out sealing and fill, and smooth transition process is carried out to it;
11. pairs of whole wing element carry out fairing correction of the flank shape process, ensure that it has good aerodynamic characteristic, finally form wing element and place in operation.
(3) advantage and effect: a kind of novel layouts solar power of the present invention unmanned plane scheme, based on the adjustable double rhombic solar unmanned plane construction module of the method development, can while solar cell efficiently export in maintenance, effectively solve solar power unmanned plane wing cycle large deformation and the fatigue problem that causes.Thus for the lighting design of solar power unmanned plane and the raising of load capacity provide technical support
Four, accompanying drawing illustrates:
Fig. 1 is a kind of agent structure schematic diagram of novel layouts solar power unmanned plane scheme, and the implementation case adopts unconventional layout, without horizontal tail and vertical fin;
Fig. 2 is the installation site of solar panel, aileron and screw propeller in the present embodiment;
Fig. 3 is the conciliation diamond structure device of a kind of novel layouts solar power unmanned plane scheme in the present embodiment;
Fig. 4 is the basic design scheme of a kind of novel layouts solar power unmanned plane scheme in the present embodiment.
Number in the figure is described as follows:
1. the left outside wing 2. left diamond structure 3. central wing
4. right diamond structure 5. starboard outboard 6. fuselage
7. electrical motor screw propeller 8. aileron 9. solar panel
10. rhombic drive
Five, specific embodiments:
Below in conjunction with Fig. 1,2,3,4, a kind of adjustable double rhombic solar unmanned plane scheme module of the present invention and design are described further:
A kind of adjustable double rhombic solar of the present invention unmanned plane scheme, sub-module designs.As shown in Figure 1 whole wing is divided into 11 large modules, comprises the left outside wing, left diamond structure, central wing, right diamond structure, starboard outboard five major part.Then be exactly electrical motor screw propeller and fuselage.
Aerofoil surface settles solar panel, and solar panels adopt hard and soft integral solar energy battery module, after multiple cell panel welding, is directly fixed on each section of wing.Surface applies the good PET of one deck light transmittance, ensures Pneumatic light slip, reduces aloft resistance.
Wing adopts rib to add the base model of stringer, and there is vertical wall front and back, and centre is spar, bears main load.After connection, exert covering, then solar panel is installed on covering.
Fuselage adopts bulkhead and edge strip to combine, and outside applies the structure of covering.The layout of fuselage can lay some airborne equipments, also energy-storage battery can be placed in wherein.
Electrical motor screw propeller piles face along standard of fuselage and installs, and the pulling force produced like this is to produce pitching moment cruising, and ensures flight safety.
A kind of novel layouts solar power of the present invention unmanned plane scheme, its basic development flow process is as follows: whole development flow process as shown in Figure 4:
1. materials procurement, inspection, ensure that selected materials meets operating needs and technological forming requirement, especially compatible with environment requirement;
2. welding of battery film: for hard and soft one solar module 1 encapsulates efficient rigidity solar battery sheet 8 grid for welding line 7 used, its technological process comprises monolithic welding and multi-disc series welding; When monolithic welds, on main gate line direction, the length that is initial, that stop contact point distance solar battery sheet edge of welding remains on about 2.5mm, and the temperature of constant temperature electric iron remains on about 380 DEG C; Multi-disc series welding need carry out in the serial connection template of band pre-heating system, can ensure the distortion that solar battery sheet is little as far as possible, thus reduces fragment rate;
3. the while of with step 2, cutting, cleaning process can be carried out, comprise: cutting film based material needed for wiping, clean the built-in fitting processing mounting hole in advance, clean the mould prepared needed for rib and girder, ensure that the half-blank that on film based material, built-in fitting, mould, foreign, impurity layer are folded puts into laminating machine heating, lamination, heating, finally forms solar module;
4. the while of with step 3, utilize mould that carbon fiber prepreg, lightweight glued membrane, honeycomb core, built-in fitting are carried out lamination by set design plan and prepare rib and girder, specific as follows: stacked good half-blank to be put into vacuum hotpressing tank carries out pressurizeing, heat treatment, Stress control is at 2 standard atmospheres, and time of heat is 2 hours; Temperature controls at 145 DEG C, and the temperature rise time controls at 45 minutes; In addition, for guaranteeing the planarization on surface, the flat-type objects such as case hardened glass should be placed in the outside of upper and lower carbon fiber prepreg;
5. with step 4 simultaneously, the bulkhead of fuselage and edge strip are made;
6. rib and girder are carried out combination according to given design scheme and form wing element structure;
7. fuselage bulkhead and edge strip are carried out combination according to given design scheme and form fuselage;
8. output mounting hole by design plan at the edge of sun energy battery module, utilize catch gear to be arranged in wing element structure by hard and soft one solar module;
9., for the overlapping place between solar module, utilize sealant to carry out sealing and fill, and smooth transition process is carried out to it;
10. pair whole wing element carries out fairing correction of the flank shape process, ensures that it has good aerodynamic characteristic, finally forms wing element and place in operation.
Each wing element and case unit are assembled according to design plan by 11..
It should be pointed out that this example only listing property application process of the present invention is described, but not for limiting the present invention.Any personnel being 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 listed by claims.
Claims (4)
1. a novel layouts solar power unmanned plane scheme, is characterized in that:
Based on the straight wing, utilize adjustable double diamond structure, improve the integral rigidity of platform, reduce the yardstick (reduction spanwise extent) of platform, realize modular combination; By the adjustment of the upper bottom wing variable-angle of rhombus, ensure that such aircraft is under takeoff condition, center of gravity is positioned at internal body, unlikely cause lean forward or after turn over; Effectively change the angle of sweepforward/sweepback in flight course, effectively increase the light-receiving area of aerofoil surface solar cell, increase the face area to wing simultaneously, increase lift.
2. a novel layouts solar power unmanned plane scheme, is characterized in that:
Described adjustable double diamond structure, mainly in the position of unmanned plane symmetry, utilizes wing to be built into an adjustable diamond structure.Arrange fuselage in each wing junction, installation is carried simultaneously, thus distractive load.From top to bottom once: solar panel, Double Diamond structure the first half, adjustable double diamond structure actuator, solar panel, middle outside wing, Double Diamond mechanism the latter half.From left to right successively: the left outside wing, left diamond structure, central wing, right diamond structure, starboard outboard.
3. a novel layouts solar power unmanned plane scheme, is characterized in that:
The adjustment of the upper bottom wing variable-angle of described Double Diamond installs a rotary drive mechanism additional between the flat wing of the diamond structure wing and both sides.The sport of this mechanism drives the change of rhombus-mechanism shape, namely changes dehiscing of rhombus-mechanism, also can change the length of the span simultaneously.
4. a novel layouts solar power unmanned plane scheme, is characterized in that: it is as follows that it develops flow process substantially:
(1) materials procurement, inspection, ensure that selected materials meets operating needs and technological forming requirement, especially compatible with environment requirement;
(2) require to carry out making wing according to design plan and stock left for machining, also will make the stringer of wing and vertical wall simultaneously.
(3) require to carry out making aerofoil profile according to design plan and stock left for machining, also will make the stringer of aileron and vertical wall simultaneously.
(4) meanwhile, can require according to design plan and stock left for machining the cutting carrying out making skin material;
(5) connection carrying out making diamond structure control apparatus and upper and lower middle two wings of diamond structure is required according to design plan and stock left for machining.
(6) require to carry out making fuselage according to design plan and stock left for machining.
(7) according to design plan, this solar power unmanned plane is assembled, and revise profile, reduce interference drag.
(8) fuselage is arranged on two wing junctions, every downside, be convenient to like this load all with distribution, reduction concentrated load, while also relatively can reduce the amount of deflection of wing in-flight.This reduces the fatigue stress of each flight, the service life increasing unmanned plane can be played.
(9) for the overlapping place of adjustable double rhombic solar unmanned plane intermodule, utilize sealant to carry out sealing and fill, and smooth transition process is carried out to it;
(10) fairing correction of the flank shape process is carried out to whole wing element, ensure that it has good aerodynamic characteristic, finally form wing element and place in operation.
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| CN201510801533.4A CN105480402B (en) | 2015-11-19 | 2015-11-19 | A kind of novel layouts solar energy unmanned plane scheme |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109919391A (en) * | 2019-03-19 | 2019-06-21 | 北京航空航天大学 | A kind of autonomous optimizing path planning method of solar powered aircraft and system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120085858A1 (en) * | 2010-10-11 | 2012-04-12 | Eads Deutschland Gmbh | Aircraft Having a Variable Geometry |
| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
| CN104890859A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Solar drone |
| CN105109668A (en) * | 2015-09-23 | 2015-12-02 | 燕山大学 | Variable airfoil parallel mechanism |
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2015
- 2015-11-19 CN CN201510801533.4A patent/CN105480402B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120085858A1 (en) * | 2010-10-11 | 2012-04-12 | Eads Deutschland Gmbh | Aircraft Having a Variable Geometry |
| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
| CN104890859A (en) * | 2015-06-23 | 2015-09-09 | 中国航空工业集团公司西安飞机设计研究所 | Solar drone |
| CN105109668A (en) * | 2015-09-23 | 2015-12-02 | 燕山大学 | Variable airfoil parallel mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109919391A (en) * | 2019-03-19 | 2019-06-21 | 北京航空航天大学 | A kind of autonomous optimizing path planning method of solar powered aircraft and system |
| CN109919391B (en) * | 2019-03-19 | 2021-01-08 | 北京航空航天大学 | Solar airplane autonomous optimization flight path planning method and system |
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| CN105480402B (en) | 2019-04-12 |
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