CN105480402B - A kind of novel layouts solar energy unmanned plane scheme - Google Patents
A kind of novel layouts solar energy unmanned plane scheme Download PDFInfo
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- CN105480402B CN105480402B CN201510801533.4A CN201510801533A CN105480402B CN 105480402 B CN105480402 B CN 105480402B CN 201510801533 A CN201510801533 A CN 201510801533A CN 105480402 B CN105480402 B CN 105480402B
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Abstract
The present invention provides a kind of novel layouts solar energy unmanned plane scheme, and this method, using adjustable double diamond structure, improves the overall stiffness of platform based on the straight wing, reduces the scale (reducing spanwise extent) of platform, realizes modular combination；By the adjusting of the upper bottom wing variable-angle of diamond shape, guarantee such aircraft under takeoff condition, center of gravity is located at internal body, will not cause to lean forward or after turn over；Effectively change sweepforward/sweepback angle in flight course, effectively increases the light-receiving area of aerofoil surface solar battery, while increasing the surface area for arriving wing, increase lift.Modularization Double Diamond solar energy unmanned plane scheme based on this method development can reduce the wing structure weight of solar energy unmanned plane to greatest extent, improve the flying quality and load-carrying ability of solar energy unmanned plane.
Description
One, technical field:
The present invention provides a kind of novel layouts solar energy unmanned plane scheme, belongs to aerospace vehicle housing construction technology neck
Domain.
Two, background technique:
Altitude Long Endurance Unmanned Air Vehicle as can stratosphere and its more than the unmanned vehicle that highly runs, can be used for feelings
Report, monitoring and scouting, communication relay, Target indication injure assessment, the various fields such as telecommunications and TV service.Atmospheric environment prison
It surveys and a variety of military and Civil Affairs Missions such as weather forecast, it has also become the hot spot studied now.
It is that human development has directionality with before using solar energy as the supplementary energy of future aircraft even main energy sources
Along the important research target of property.Solar powered aircraft is that occur in 1970s with the reduction of solar battery cost,
Since solar powered aircraft flight does not need to create condition from carrying fuel for the flight of long endurance.Therefore, many developed countries cause
Power is in the research and development of the Altitude Long Endurance Unmanned Air Vehicle based on solar energy.
Current solar energy unmanned plane mainly uses solar-energy photo-voltaic cell as main power supply part, is limited by aircraft table
Face limited area.While improving solar battery utilization rate, the laying area of solar panel can be increased.From aircraft
It has been biplane first since appearance；Developing deeply is to triplane；Develop monoplane later, till now always.Furthermore due to being too
Positive energy unmanned plane, in order to generate enough energy, often aspect ratio design is bigger.In other words, as solar energy nobody
After machine takes off, degree of deflecting is bigger on wing.To make solar panels that wing be followed to deflect, and then the sun can be made
The solar radiation total amount that energy plate receives reduces.Therefore can reduce solar panel output energy, be unfavorable for solar energy nobody
The cruise of captain's endurance.
For this purpose, the present invention provides a kind of novel layouts solar energy unmanned plane scheme, by combining biplane and monoplane
Constitute adjustable double diamond structure, and to proposing from the aspect of the reinforcement of airframe structure.Firstly, adjustable Double Diamond can increase
Big specific area can increase the laying area of solar panel in this way, generate more energy；Secondly, structure can be increased
Rigidity, reduce deformation of the wing in flight, so that wing is more conducive to solar panel and generate energy；Again, this structure can
To effectively reduce the height of unmanned plane, since the general span of solar energy unmanned plane is compared, when ground is parked, in order to prevent
The wing wing slightly contacts to earth, and needs the relatively high of height design, and this mechanism just effectively reduces wing when aircraft is parked and deforms；
Finally, this adjustable Double Diamond uses modularized design, it is readily transported installation.Solar energy is flown to be more in line in current designs
Machine structure light wt, the composite request for exporting energy efficient.
Three, summary of the invention:
(1) purpose: the purpose of the present invention is to provide a kind of novel layouts solar energy unmanned plane schemes, are ground based on this method
The solar energy unmanned plane wing of system can satisfy solar energy unmanned plane in battery conversion efficiency and unit area battery specific power two
The requirement of aspect, and can effectively solve solar energy unmanned plane wing large deformation problem.In addition, being based on this method, can effectively drop
Low solar energy unmanned plane configuration aspects loss, and then improve solar energy unmanned plane load-carrying ability.
(2) technical solution: a kind of novel layouts solar energy unmanned plane scheme of the present invention, the technical measures of this method are such as
Under: based on the straight wing, using adjustable double diamond structure, the overall stiffness of platform is improved, the scale for reducing platform (reduces the wing
Open up size), realize modular combination；By the adjusting of the upper bottom wing variable-angle of diamond shape, guarantee such aircraft in takeoff condition
Under, center of gravity is located at internal body, will not cause to lean forward or after turn over；Effectively change sweepforward/sweepback angle in flight course, effectively
Increase the light-receiving area of aerofoil surface solar battery, while increasing the surface area for arriving wing, increases lift.
Based on above scheme, can both meet solar powered aircraft to structure light wt, export energy efficient use purpose,
Meet the big rigidity requirement of solar energy unmanned plane wing again, can by reducing the height of solar energy unmanned plane to greatest extent,
To reduce its complete machine mechanism weight, the flight heart infarction and load-carrying ability of raising solar energy unmanned plane.
The adjustable double diamond structure mainly in the symmetrical position of unmanned plane, using wing be built into one it is adjustable
Diamond structure.Fuselage is set in each wing junction simultaneously, installation carries, thus distractive load.It is once from top to bottom: the sun
Energy solar panel, Double Diamond structure top half, adjustable double diamond structure driver, solar panel, middle outside wing, double water chestnuts
Shape mechanism lower half portion.It is successively from left to right: the left outside wing, left diamond structure, central wing, right diamond structure, starboard outboard.
A kind of novel layouts solar energy unmanned plane scheme of the present invention, basic step are as follows:
1. materials procurement is examined, guarantee that selected materials meet requirement and technological forming is wanted
2. asking, especially environmental adaptability requirement；
3. requiring to carry out production wing according to design scheme and machining allowance, while also to make the stringer of wing and indulge
Wall.
4. requiring to carry out production aerofoil profile according to design scheme and machining allowance, while also to make the stringer of aileron and indulge
Wall.
5. at the same time, the cutting for carrying out making skin material can be required according to design scheme and machining allowance；
6. requiring to be made to above and below diamond structure regulating device and diamond structure according to design scheme and machining allowance
The connection of intermediate two wings.
7. requiring to carry out production fuselage according to design scheme and machining allowance.
8. assembling according to design scheme to this solar energy unmanned plane, and shape is corrected, reduces interference drag.
9. fuselage is mounted on the wing junction of every downside two, reduce concentrfated load, together with distribution convenient for load in this way
When can also relatively reduce the amount of deflection of in-flight wing.This reduces the fatigue stresses flown every time, can play increasing
The service life of big unmanned plane.
10. being directed to the overlapping place of adjustable double rhombic solar unmanned plane intermodule, it is sealed filling using sealant, and
The processing that smoothly transits is carried out to it；
11. a pair entire wing element carries out fairing correction of the flank shape processing, guarantee that it, with good aerodynamic characteristic, ultimately forms machine
Wing unit simultaneously comes into operation.
(3) advantage and effect: a kind of novel layouts solar energy unmanned plane scheme of the present invention, based on the adjustable of this method development
Double Diamond solar energy unmanned plane construction module, can keep solar battery efficiently export while, effectively solve solar energy without
Fatigue problem caused by man-machine wing period large deformation.It is thus the lighting design and load-carrying ability of solar energy unmanned plane
It improves and technical support is provided
Four, Detailed description of the invention:
Fig. 1 is a kind of agent structure schematic diagram of novel layouts solar energy unmanned plane scheme, and the implementation case is using very
Rule layout, no horizontal tail and vertical fin；
Fig. 2 is the installation site of solar panel, aileron and propeller in the present embodiment；
Fig. 3 is the conciliation diamond structure device of one of the present embodiment novel layouts solar energy unmanned plane scheme；
Fig. 4 is a kind of basic design scheme of novel layouts solar energy unmanned plane scheme in the present embodiment.
Figure label is described as follows:
1. left 3. central wing of diamond structure of the left outside wing 2.
4. right 5. starboard outboard of diamond structure, 6. fuselage
7. 8. aileron of motor propeller, 9. solar panel
10. rhombic drive
Five, specific embodiment:
Below with reference to a kind of adjustable double rhombic solar unmanned plane scheme module pair of the invention of Fig. 1,2,3,4 and set
Meter is described further:
A kind of present invention adjustable double rhombic solar unmanned plane scheme, sub-module design.As shown in Figure 1 by entire wing
It is divided into 11 big modules, including the left outside wing, left diamond structure, central wing, right diamond structure, five major part of starboard outboard.Then
It is exactly motor propeller and fuselage.
Aerofoil surface disposes solar panel, and solar panels use hard and soft integral solar energy battery module, will be multiple
After solar panel welding, it is affixed directly on each section of wing.Surface applies one layer of preferable PET of light transmittance, to ensure Pneumatic light
Slip reduces resistance in-flight.
Wing adds the citation form of stringer using rib, and there is vertical wall in front and back, and centre is spar, bears main load.Even
After connecing, covering is exerted, then solar panel is installed on covering.
Fuselage, which is used, to be combined using bulkhead with edge strip, and outside applies the structure of covering.The layout of fuselage can place
Airborne equipment can also dispose energy-storage battery wherein.
Motor propeller piles face along standard of fuselage and installs, and the pulling force generated in this way is that will not generate pitching power in cruise
Square ensures flight safety.
A kind of novel layouts solar energy unmanned plane scheme of the present invention, basic development process are as follows: entire development process
It is as shown in Figure 4:
1. materials procurement is examined, it is suitable to guarantee that selected materials meet requirement and technological forming requirement, especially environment
Answering property requires；
2. welding of battery film: encapsulating efficient rigid solar battery sheet 8 used for hard and soft integrated solar cell module 1
Welding electrode line 7, process flow include monolithic welding and multi-disc series welding；In monolithic welding, on main gate line direction, welding
Length apart from solar battery sheet edge of starting, termination contact point be maintained at 2.5mm or so, the temperature of constant temperature electric iron is protected
It holds at 380 DEG C or so；Multi-disc series welding need to carry out in the concatenation template with pre-heating system, it is ensured that solar battery sheet to the greatest extent may be used
The small deformation of energy, to reduce fragment rate；
3. simultaneously with step 2, can be cut, cleaning process, comprising: cut and wipe required membrane system material, clean
The built-in fitting for processing mounting hole in advance cleans mold needed for preparing rib and girder, guarantees membrane system material, built-in fitting, mould
The semi-finished product that foreign, impurity layer are folded on tool, which are put into laminating machine, to be heated, is laminated, and heating ultimately forms solar battery mould
Block；
4. simultaneously with step 3, carbon fiber prepreg, lightweight glue film, honeycomb core, built-in fitting are set by set using mold
Meter scheme carries out lamination and prepares rib and girder, and specific as follows: the semi-finished product that will be laminated, which are put into vacuum hotpressing tank, to be added
Pressure, heat treatment, in 2 standard atmospheric pressures, heating time is 2 hours for pressure control；Temperature control is at 145 DEG C, the heating-up time
Control was at 45 minutes；In addition, for the planarization for ensuring surface tempered glass should be placed on the outside of upper and lower carbon fiber prepreg
Equal plates type objects；
5. simultaneously with step 4, being made to the bulkhead and edge strip of fuselage；
6. rib and girder are combined according to given design scheme and constitute wing element structure；
7. fuselage bulkhead and edge strip are combined composition fuselage according to given design scheme；
8. by design scheme it is positive can the edge of battery module output mounting hole, using retaining mechanism by the hard and soft integrated sun
Energy battery module is mounted in wing element structure；
9. being sealed filling using sealant, and carry out to it smooth for the overlapping place between solar cell module
Transition processing；
10. a pair entire wing element carries out fairing correction of the flank shape processing, guarantee that it, with good aerodynamic characteristic, ultimately forms machine
Wing unit simultaneously comes into operation.
11. each wing element and case unit are assembled according to design scheme.
It should be pointed out that only listing property illustrates application method of the invention to this example, and is not intended to limit the present invention.It is any ripe
Such personnel using technology are known, can be modified without departing from the spirit and scope of the present invention to above-described embodiment.Cause
This, the scope of the present invention should be as listed in the claims.
Claims (7)
1. a kind of novel layouts solar energy unmanned plane, it is characterised in that: based on straight wing, in the symmetrical position of unmanned plane
It sets, is built into an adjustable double diamond structure, the tune of the upper lower wing variable-angle of the adjustable double diamond structure using wing
Section, while fuselage is set in each wing junction, installation carries；
Unmanned plane is successively solar panel from top to bottom, the adjustable double diamond structure top half wing, described adjustable
Double Diamond fabric driver, solar panel, center and outside wing, adjustable double diamond structure lower half portion wing；
It is successively from left to right: left-external side wing, adjustable double diamond structure left-half wing, central wing, adjustable double diamond structure
Right half part wing, right outside wing.
2. novel layouts solar energy unmanned plane according to claim 1, it is characterised in that: the adjustable double diamond structure
A rotary drive mechanism is added between wing and two sides straight wing, the movement of the rotary drive mechanism will drive described
The change of adjustable double diamond structure shape, changes dehiscing for the adjustable double diamond structure, changes simultaneously the length of the span.
3. novel layouts solar energy unmanned plane according to claim 1, it is characterised in that: aerofoil surface disposes solar-electricity
Pond plate, solar panels use hard and soft integral solar energy battery module, after the welding of multiple solar panels, are affixed directly to each section
On wing.
4. novel layouts solar energy unmanned plane according to claim 1, it is characterised in that: wing adds stringer using rib
There are vertical wall in citation form, front and back, and centre is spar, after connection, exert covering, solar panel is installed to covering
On.
5. novel layouts solar energy unmanned plane according to claim 1, it is characterised in that: fuselage is using bulkhead and edge strip group
It closes, outside applies the structure of covering.
6. novel layouts solar energy unmanned plane according to claim 1, it is characterised in that: pile face along standard of fuselage and install
There is motor propeller.
7. novel layouts solar energy unmanned plane according to claim 1, it is characterised in that: its basic development process is as follows:
(1) materials procurement, inspection guarantee that selected materials meet requirement and technological forming requirement；
(2) it requires to carry out production wing according to design scheme and machining allowance, while also to make the stringer and vertical wall of wing；
(3) it requires to carry out production aileron according to design scheme and machining allowance, while also to make the stringer and vertical wall of aileron；
(4) at the same time, the cutting for carrying out making skin material can be required according to design scheme and machining allowance；
(5) according to design scheme and machining allowance requirement, regulating device and adjustable double diamond structure to adjustable double diamond structure
The connection of adjacent wing is made；
(6) it requires to carry out production fuselage according to design scheme and machining allowance；
(7) this solar energy unmanned plane is assembled according to design scheme, and corrects shape, reduce interference drag；
(8) fuselage is mounted on the wing junction of every downside two；
(9) it is directed to the overlapping place of adjustable double rhombic solar unmanned plane intermodule, is sealed filling using sealant, and to it
Carry out the processing that smoothly transits；
(10) fairing correction of the flank shape processing is carried out to entire wing element, guarantees that it, with good aerodynamic characteristic, ultimately forms wing
Unit simultaneously comes into operation.
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| Application Number | Priority Date | Filing Date | Title |
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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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| CN201510801533.4A CN105480402B (en) | 2015-11-19 | 2015-11-19 | A kind of novel layouts solar energy unmanned plane scheme |
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| CN105480402B true CN105480402B (en) | 2019-04-12 |
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| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102010048139A1 (en) * | 2010-10-11 | 2012-04-12 | Eads Deutschland Gmbh | Aircraft with variable geometry |
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2015
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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