CN106143909B - A kind of modularized combination type solar energy unmanned aerial vehicle design scheme - Google Patents
A kind of modularized combination type solar energy unmanned aerial vehicle design scheme Download PDFInfo
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- CN106143909B CN106143909B CN201610559395.8A CN201610559395A CN106143909B CN 106143909 B CN106143909 B CN 106143909B CN 201610559395 A CN201610559395 A CN 201610559395A CN 106143909 B CN106143909 B CN 106143909B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Aviation & Aerospace Engineering (AREA)
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- Combustion & Propulsion (AREA)
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Abstract
The present invention provides a kind of modularized combination type solar energy unmanned aerial vehicle design scheme, the program designs multiple modules, each module is equipped with motor, propeller, undercarriage and aerial docking structure, each module can independent takeoff and landing, it flies after each module lift-off to low wind speed airspace, the position of each module is determined using GPS or Beidou navigation and positioning system, then each module orderly merges in the sky, aerial docking structure guarantees that modules stablize docking combination, the solar energy unmanned plane being composed carry out again height climb and cruising flight.Helios based on this alternatives formulation, can effectively solve existing airport due to runway size limitation can not landing ultra-large type solar powered aircraft suffering；It can use existing ground hangar storage ultra-large type solar energy unmanned plane, flexible arrangement home port simultaneously；Multimode design increases system redundancy, realizes high reliability, flight of leaving a blank when realizing long.
Description
One, technical field:
The present invention provides a kind of modularized combination type solar energy unmanned aerial vehicle design scheme, belongs to new concept aerospace vehicle system
System technical field.
Two, background technique:
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 using solar energy as the research and development of the high altitude long time aircraft in energy source.
Current Helios owner will be using solar-energy photo-voltaic cell as main power supply part, to obtain more
More solar energies, a feasible method is the laying area for increasing solar battery sheet, but this will certainly increase the sun
The outer dimension of energy aircraft.Fly however, the manufacture of the runway size on airport, solar powered aircraft and transport often limit solar energy
The size of machine.
For this purpose, the present invention provides a kind of modularized combination type solar energy unmanned aerial vehicle design scheme.
Three, summary of the invention:
(1) purpose: the present invention provides a kind of modularized combination type solar energy unmanned aerial vehicle design scheme, is designed using the program
Solar energy unmanned plane, be by multiple modules in the sky orderly docking be composed.Each module is independently taken off on ground, lift-off
After to low wind speed airspace, using GPS or BDStar navigation system, the position of each module is determined；Passage path planning
It realizes the engagement of modules skyborne ordered pair simultaneously, forms ultra-large type combination type solar unmanned plane, then this ultra-large type is too
It is positive can unmanned plane can realize again height climb and cruising flight；After completing preplanned mission or reaching the predetermined area, this
Ultra-large type solar energy unmanned plane can drop to low wind speed airspace, carry out Ordered Decomposition, form multiple modules, this multiple module can be suitable
Sequence drops to predetermined airport.
(2) technical solution: a kind of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention, modularized combination type is too
Positive energy unmanned plane is made of multiple equal modules, and each module uses high aspect ratio straight wing, and each module cancels level
The high aspect ratio straight wing top of empennage and vertical tail, each module is equipped with inverted V type wing, and inverted V type trailing edge is
Movable control surface, each module all have motor, undercarriage, propeller.
Wherein, each module can realize independent takeoff and landing.
Wherein, each module take off in descent pitching and yawing rotation can by inverted V type trailing edge
Dynamic control surface manipulation.
Wherein, after each module is taken off, lift-off to low wind speed airspace is determined using GPS or Beidou navigation and positioning system
Then the position of modules carries out sequential combination in the sky, form modularized combination type solar energy unmanned plane.
Wherein, the pitching and yawing rotation of the modularized combination type solar energy unmanned plane are by modules inverted V type wing
The movable control surface of rear is combined control.
A kind of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention, basic design scheme are as follows:
1) combine preset technical parameter and task parameters (including mission payload, airborne period, maximum flying speed and
Ceiling altitude etc.) and rise galassing weighing apparatus, push away resistance balance, energy balance principle, to modularized combination type solar energy unmanned plane
Conceptual design is carried out, determines the original dimension of modules, formulates design scheme, and design scheme is proved and emulated
Verifying and experimental verification；
2) according to design scheme make modules, including wing, inverted V type wing, intermodule connection mechanical device and
Other components；
3) on the upside of wing, solar battery sheet is laid on the outside of inverted V type wing, and analyze its aerodynamic characteristic and whether meet and want
It asks；
4) energy-storage battery is installed, the battery of high-energy density is selected, according to the calculating process of energy balance, reasonably selects storage
The weight of energy battery；
5) simultaneously with step (4), the position of reasonable Arrangement lithium battery guarantees the balance of fuselage；
6) the general assembly work of Helios individual module, including wing, inverted V type wing, undercarriage, spiral are carried out
Paddle, energy-storage battery etc.；
7) the compatible debugging of software and hardware simultaneously with step (6), is attached and carried out to the circuit of each inside modules,
Including aileron movement debugging, the debugging of inverted V type wing control deflecting facet, motor and propeller joint debugging, the machine being coupled for intermodule
Tool device debugging；
8) finally, making a flight test verifying to modularized combination type solar energy unmanned plane.
(3) advantage and effect: a kind of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention has following excellent
Point.Troposphere environment is complicated and changeable, high aspect ratio solar energy unmanned plane or ultra-large type solar energy unmanned plane in the environment by
Lower in overall stiffness, structure takes modularized design vulnerable to damage, allows each module of solar energy unmanned plane in troposphere liter
Sky, stratosphere combination, since each module size is smaller, rigidity is enough, this is to solution high aspect ratio solar energy unmanned plane or surpasses
Large solar unmanned aerial vehicles troposphere lift-off difficult problem is a very reliable scheme；Due to the energy of solar energy unmanned plane
The solar energy obtained from solar battery sheet, to obtain more solar energy, an effective method is to increase solar energy
The laying area of cell piece, but such method obviously will increase the overall dimensions of solar energy unmanned plane, for ultra-large type solar energy
Unmanned plane can not carry out landing under the conditions of existing airport, and modularized combination type solar energy unmanned plane scheme effectively solves
Certainly this problem completely can be under the conditions of existing airport since each module size of composition solar energy unmanned plane is smaller
Then landing goes up to the air and is combined into ultra-large type solar energy unmanned plane to low wind speed airspace, solve ultra-large type solar energy unmanned plane and exist
Existing airport can not landing the problem of；Modular design can preferably accomplish system redundancy, in severe troposphere environment
In lower take-off process, if some module is taken off, lift-off is broken down, and can take off spare module or solar energy unmanned plane are in sky
Some module breaks down in middle flight course, can carry out decomposition module in time, avoid causing because of the failure of part of module
Entire ultra-large type solar energy unmanned plane crashes.
Four, Detailed description of the invention:
Fig. 1 is a kind of individual module outline drawing of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention；
Fig. 2 is a kind of three block combiner mode shapes of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention
Figure；
Fig. 3 is a kind of three block combiner main views of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention；
Fig. 4 is a kind of three block combiner top views of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention.
Figure label is described as follows:
1. 2. flaperon of high aspect ratio straight wing, 3. wing of falling V
4. 6. No. two modules of movable 5. No.1 module of control surface
7. No. three 8. undercarriage of module, 9. propellers
Five, specific embodiment:
It is done further below with reference to a kind of modularized combination type solar energy unmanned aerial vehicle design scheme of couple present invention of Fig. 1,2,3,4
Explanation.
The present invention provides a kind of modularized combination type solar energy unmanned aerial vehicle design sides based on aerial module docking technique
Case, the program can sufficiently increase the irradiated area of sunlight, realize that solar energy unmanned plane is left a blank flight for a long time.Fig. 1 is shown
The solar energy unmanned plane individual module shape, the Helios individual module main component be high aspect ratio straight wing 1,
Inverted V type wing 3, wherein 1 rear of high aspect ratio straight wing be flaperon 2,3 rear of inverted V type wing be responsible for pitching movement and
The control surface 4 of yawing rotation；Fig. 2 show the solar energy unmanned plane outline drawing formed after three block combiners, No.1 mould in Fig. 2
5, No. two modules 6 of block and No. three modules 7 are combined into a solar energy unmanned plane under the action of docking mechanism in the sky；It is each in Fig. 3
The undercarriage 8 of a module has a road clearance, prevents propeller 9 in Fig. 4 from contacting to earth during individual module take-off and landing.
Three independent modules, 5, No. two modules 6 of No.1 module and No. three modules 7 are independently taken off on ground, are gone up to the air to low
After wind speed airspace, using GPS or BDStar navigation system, the position of each module is determined；Passage path planning is realized
5, No. two modules 6 of No.1 module and No. three modules 7 carry out ordered pair engagement simultaneously under the action of docking mechanism in the sky, form three moulds
Block combination type solar unmanned plane, then this three module combined types solar energy unmanned plane can realize climbing and patrolling for height again
Boat flight；After completing preplanned mission or reaching the predetermined area, this ultra-large type solar energy unmanned plane can drop to low wind speed airspace,
It carries out Ordered Decomposition under the action of docking mechanism in the sky, forms 5, No. two modules 6 of No.1 module and No. three modules 7, then one
Number 5, No. two modules 6 of module and No. three modules 7 can sequentially drop to predetermined airport.
A kind of modularized combination type solar energy unmanned aerial vehicle design scheme of the present invention, basic design scheme are as follows:
1) combine preset technical parameter and task parameters (including mission payload, airborne period, maximum flying speed and
Ceiling altitude etc.) and rise galassing weighing apparatus, push away resistance balance, energy balance principle, to modularized combination type solar energy unmanned plane
Conceptual design is carried out, determines the original dimension of modules, formulates design scheme, and design scheme is proved and emulated
Verifying and experimental verification；
2) according to design scheme make modules, including wing, inverted V type wing, intermodule connection mechanical device and
Other components；
3) on the upside of wing, solar battery sheet is laid on the outside of inverted V type wing, and analyze its aerodynamic characteristic and whether meet and want
It asks；
4) energy-storage battery is installed, the battery of high-energy density is selected, according to the calculating process of energy balance, reasonably selects storage
The weight of energy battery；
5) simultaneously with step (4), the position of reasonable Arrangement lithium battery guarantees the balance of fuselage；
6) the general assembly work of Helios individual module, including wing, inverted V type wing, undercarriage, spiral are carried out
Paddle, energy-storage battery etc.；
7) the compatible debugging of software and hardware simultaneously with step (6), is attached and carried out to the circuit of each inside modules,
Including aileron movement debugging, the debugging of inverted V type wing control deflecting facet, motor and propeller joint debugging, the machine being coupled for intermodule
Tool device debugging；
8) finally, making a flight test verifying to modularized combination type solar energy unmanned plane.
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 (4)
1. a kind of modularized combination type solar energy unmanned aerial vehicle design scheme, it is characterised in that:
Using modularized design, solar energy unmanned plane is made of multiple modules, and each module is equipped with power device, rises and falls
Frame, propeller, each module can independent takeoff and landing, and can independently rise to given area；
After modules rise to low wind speed airspace, by navigation positioning system, each module position, then passage path rule are determined
It draws, realizes the skyborne orderly merging of modules, be combined into a large-sized solar aircraft, then realize climbing for height
It rises and cruising flight, the navigation positioning system is GPS navigation positioning system or BDStar navigation system；
Each module is all made of high aspect ratio straight wing, cancels tailplane and vertical tail, in high aspect ratio straight wing
Top, is equipped with inverted V type wing, and inverted V type wing and high aspect ratio straight wing constitute triangle rock-steady structure；The inverted V type
Wing includes the first wing and the second wing being in tilted layout, the first end of first wing and the high aspect ratio flattener
The first end of the wing connects, and the first end of second wing is connect with the second end of the high aspect ratio straight wing, and described the
The second end of one wing is connected with the second end of second wing, the top airfoil of first wing and second wing
Top airfoil tilts obliquely upward.
2. a kind of modularized combination type solar energy unmanned aerial vehicle design scheme according to claim 1, it is characterised in that:
The inverted V type trailing edge of each module is equipped with movable aerofoil, this movable aerofoil serves as control surface, can replace tailplane
Pitching movement and yawing rotation are manipulated with vertical tail.
3. a kind of modularized combination type solar energy unmanned aerial vehicle design scheme according to claim 2, it is characterised in that:
During modules lift-off, if some module breaks down, the spare module that can go up to the air immediately is replaced；Such as
After modules orderly merge, some module breaks down fruit, can implement decomposition module in the sky, malfunctioning module is thrown
From remaining module reconsolidates into a large-sized solar aircraft.
4. a kind of modularized combination type solar energy unmanned aerial vehicle design scheme according to claim 1, it is characterised in that:
Its basic design scheme is as follows:
1) it weighs in conjunction with preset technical parameter and task parameters and liter galassing, push away resistance balance, energy balance principle, to modularization
Combination type solar unmanned plane carries out conceptual design, determines the original dimension of modules, formulates design scheme, and to design side
Case carries out demonstration and simulating, verifying and experimental verification, and wherein task parameters include mission payload, airborne period, maximum flight speed
Degree and ceiling altitude；
2) modules are made according to design scheme, including wing, inverted V type wing, the connection mechanical device of intermodule and other
Component；
3) on the upside of wing, solar battery sheet is laid on the outside of inverted V type wing, and analyze whether its aerodynamic characteristic meets the requirements；
4) energy-storage battery is installed, the battery of high-energy density is selected, according to the calculating process of energy balance, reasonably selects energy storage electricity
The weight in pond；
5) simultaneously with step (4), the position of reasonable Arrangement lithium battery guarantees the balance of fuselage；
6) the general assembly work of Helios individual module, including wing, inverted V type wing, undercarriage, propeller, storage are carried out
It can battery；
7) the compatible debugging of software and hardware simultaneously with step (6), is attached and carried out to the circuit of each inside modules, including
Aileron movement debugging, the debugging of inverted V type wing control deflecting facet, motor are filled with propeller joint debugging, the machinery being coupled for intermodule
Set debugging；
8) finally, making a flight test verifying to modularized combination type solar energy unmanned plane.
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| CN107272721B (en) * | 2017-07-11 | 2020-07-28 | 北京昶远科技有限公司 | Solar unmanned aerial vehicle track planning method based on day and night cyclic flight |
| CN107450576B (en) * | 2017-07-24 | 2020-06-16 | 哈尔滨工程大学 | Method for planning paths of bridge detection unmanned aerial vehicle |
| CN108216679B (en) * | 2017-12-26 | 2020-03-24 | 中国航天空气动力技术研究院 | Solar unmanned aerial vehicle overall parameter determination method and system |
| CN110816806B (en) * | 2019-10-28 | 2023-06-02 | 西北工业大学 | Cluster type bionic solar unmanned aerial vehicle |
| CN112093026A (en) * | 2020-09-25 | 2020-12-18 | 中国空气动力研究与发展中心 | Combined aircraft layout and connecting mechanism |
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| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
| CN105398561A (en) * | 2015-11-12 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Solar aircraft |
| CN105564638A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Special airplane pneumatic configuration |
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| CN101384481A (en) * | 2005-07-07 | 2009-03-11 | 杰弗里·S·索姆 | Modular articulated-wing aircraft |
| CN103863561A (en) * | 2014-02-19 | 2014-06-18 | 厦门大学 | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils |
| CN105564638A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Special airplane pneumatic configuration |
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