CN105015785A - Micro solar reconnaissance flight vehicle incorporated with Coanda effect - Google Patents
Micro solar reconnaissance flight vehicle incorporated with Coanda effect Download PDFInfo
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- CN105015785A CN105015785A CN201510398999.4A CN201510398999A CN105015785A CN 105015785 A CN105015785 A CN 105015785A CN 201510398999 A CN201510398999 A CN 201510398999A CN 105015785 A CN105015785 A CN 105015785A
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- solar
- flight vehicle
- control unit
- coanda effect
- propeller
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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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
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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
- Y02T50/50—On board measures aiming to increase energy efficiency
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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
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention relates to a micro solar reconnaissance flight vehicle incorporated with a Coanda effect. The micro solar reconnaissance flight vehicle comprises a propeller, a plurality of solar cell panels, a power control unit and a balance control unit, wherein the plurality of solar cell panels are symmetrically erected with a rotating shaft as center; an edge frame of each solar cell panel is fixedly arranged on a carbon fiber ring; the gaps of the solar cell panels are uniform and connected with a bottom circular framework of the flight vehicle; the axis of the propeller coincides with the rotating shaft on which the plurality of solar cell panels are erected; the propeller is positioned at the top; the areas of the erected solar cell panels are greater than that of the surface of the propeller; the plurality of solar cell panels are erected beyond an airflow area generated by the propeller; and total center-of-mass of motors in the power control unit and the balance control unit coincides with a symmetric line of a frame. The micro solar reconnaissance flight vehicle incorporated with the Coanda effect, provided by the invention, is advantaged in that full solar endurance is realized; the volume of the micro solar reconnaissance flight vehicle is small; the weight of the micro solar reconnaissance flight vehicle is light; the heat value of the micro solar reconnaissance flight vehicle in operation process is less; and the micro solar reconnaissance flight vehicle flies stably, hovers in the air for a long time and can be used for transmitting passenger flow and traffic flow in real time.
Description
Technical field
The present invention relates to a kind of aircraft, particularly a kind of miniature solar power reconnaisance flight vehicle in conjunction with Coanda effect.
Background technology
The current structure that can complete the aircraft of hovering and vertical takeoff and landing mainly contains single-rotor helicopter, twin-rotor helicopter, tiltrotor, Multi-axis aircraft etc.Be Large Scale Space Vehicle, need pilot driver, and flying power is subject to the restriction of tank capacity.
Existing four-axle aircraft flying power is poor, and aircraft constantly consumes the energy of storage awing, and energy can not be supplemented in flight course, and the capacity of aircraft battery determines the maximum flying distance of aircraft.
Small aircraft roughly has three kinds, fixed-wing type on the market at present, and scope of investigation is little, and cruise duration is shorter.Rotor type, power source cannot solve efficiency utilization, and driving engine proportion is larger.The bionical type of flapping wing, the air dynamic behaviour problem under low reynolds number is still in the research and probe stage, and antijamming capability solves not yet very well, and flying power is poor, mostly flight duration about 20 minutes.
Helios and the application's motion of Jilin University are the most close, but his Flight Vehicle Structure too complexity, operating difficulties, assembled extremely inconvenient, and a whole set of aircraft is expensive.
Summary of the invention
The present invention be directed to present small aircraft Problems existing, propose a kind of miniature solar power reconnaisance flight vehicle in conjunction with Coanda effect, that one is entirely solar powered, can aloft hover for a long time, and the real-time Transmission of flow of the people, vehicle flowrate can be carried out, hidden performance is good, cheap miniature reconnaisance flight vehicle.
Technical scheme of the present invention is: a kind of miniature solar power reconnaisance flight vehicle in conjunction with Coanda effect, comprise screw propeller, several piece solar panel, power control unit, balance control unit, several piece solar panel is with rotating shaft center's symmetry erection, the edge frame of every block solar panels is fixedly placed on carbon fiber ring, the gap uniformity of every block solar panels is also connected with aircraft bottom circular skeleton, the S. A. that propeller axis sets up with several piece solar panel overlaps, screw propeller is positioned at top, after erection, the area of several piece solar panel is greater than the oar face of screw propeller, several piece solar panel is erected at outside the flow area of screw propeller generation, power control unit overlaps with frame symmetric line with total barycenter of motor in balance control unit.
Described power control unit comprises brushless motor, Hexamermis spp receiver, electronic governor and storage battery, Hexamermis spp receiver and remote controller wireless telecommunications, Hexamermis spp receiver exports and controls brushless motor work by electronic governor, solar panels charge a battery, and storage battery is powered to all parts in power control unit.
Described balance control unit comprises gyroscope, the arduino pro mini chip being with self-balancing program, amplifier and four hollow-cup motors, gyroscope signal send arduino pro mini chip, and arduino pro mini chip exports control signal controls symmetrical four hollow-cup motors placed rotating speed by amplifier.
Described solar panel adopts frivolous flexible solar panel.
The described miniature solar power reconnaisance flight vehicle in conjunction with Coanda effect, also comprises camera and image passes system, and camera collection image passes system by image and graphicinformation sent.
Beneficial effect of the present invention is: the present invention is in conjunction with the miniature solar power reconnaisance flight vehicle of Coanda effect, and full solar energy is continued a journey; Reduce idle work consumption in conjunction with Coanda effect and utilize pressure reduction to increase the lift of aircraft; Energy-saving and emission-reduction, effectively reduce the non-renewable energy resources consumption of road monitoring, geophysical surveying, tactical reconnaissance in reality, biomass energy consumption and manpower financial capacity and consume, effectively reduce useless sound simultaneously relative to Multi-axis aircraft; Volume is little, lightweight, good concealment.In operational process, cal val is few, can reduce the probability found by infrared detecting set; Have a smooth flight.Designed, designed auxiliary balance system, has Self-balancing.
Accompanying drawing explanation
Fig. 1 is the miniature solar power reconnaisance flight vehicle principle schematic of the present invention in conjunction with Coanda effect;
Fig. 2 is that birds-eye view laid by flexible solar plate of the present invention;
Fig. 3 is circuit interconnect pattern of the present invention;
Fig. 4 is that flying height of the present invention steadily tests trend graph;
Fig. 5 is lift of the present invention test trend graph.
Detailed description of the invention
Coanda effect refers to that the fluid smoothly flowed is in time having the nonreentrant surface of certain camber, the trend of oriented nonreentrant surface absorption.As shown in Figure 1 in conjunction with the miniature solar power reconnaisance flight vehicle principle schematic of Coanda effect, adopt novel frivolous flexible solar panel symmetrical laying at aircraft surface, and adopt the series connection of cell panel that eight pieces of voltages are 2V jointly to provide energy source needed for whole aircraft, reach in conjunction with Koln the lift that effect makes the screw propeller of 8*6 size produce simultaneously and obtain maximum using.
As stopped by below loading greatly among the lift air-flow that Fig. 1 produces due to screw propeller, appearance curved surface is just because Coanda effect changes lift air flow line, make air-flow change direction along the outside face that curvature is less, walk around the obstruction of below loading dexterously.Birds-eye view laid by flexible solar plate as shown in Figure 2, and solar panel is below screw propeller, and the area of solar panel is greater than the oar face of screw propeller, and is erected at outside flow area, considerably reduces the obstruction of lift air-flow, reduces Internal Force Working.Simultaneously because outer surface of outer cover air-flow velocity is fast, inside face flow velocity is almost nil, therefore also additionally creates difference of pressure, provides extra lift.
Brushless motor, storage battery are connected with Hexamermis spp receiver, by remote controller to the control of FLY-30A electronic governor to reach the adjustment various flight attitude of aircraft and action.
The erection of flexible solar plate is with reference to Fig. 2, adopt 8 pieces of 18cm*4cm*0.1cm (2V) solar panels 1 Central Symmetry erections, facilitate barycentre steadiness, do not block air port, the edge frame 2 of solar panels is located on carbon fiber ring 3, makes it to do enough firmly but reaches flexible and soft, convenient bending, to reduce resistance when flight is risen, do not lose effective area of shining light simultaneously.Eight pieces of solar panels 1 are evenly erected on aircraft bottom circular skeleton 4, and area opposed helical oar is comparatively large, is conducive to barycentre steadiness, reduce lift air-flow simultaneously and hinder.Coaxial 5 counter rotating propellers are adopted also to solve the problems such as anti-twisted.
Adopt image transmission system: the signal wire (SW) that figure passes is connected with the signal wire (SW) of camera, the power lead of figure biography and camera connects the both positive and negative polarity of 12V power supply respectively, camera gathers image by camera lens and launches graphicinformation by scheming to pass, receiving device accepts graphicinformation, is gathered graphicinformation and be optimized graphicinformation process and output on read-out by collector.
Circuit interconnect pattern as shown in Figure 3, self-balancing program is write based on C language, the signal transacting to gyro module feedback is realized by arduino pro mini chip, judge whether aircraft reaches state of equilibrium, four output pins on arduino pro mini plate are outputted to again by amplifier amplifies signals, control the rotating speed of symmetrical four hollow-cup motors placed, reach the function that aircraft is balanced, the lift utilizing hollow-cup motor (iron-core-free rotor direct current, permanent magnetism, servo small and special electric machine) to provide is enough to the balance controlling aircraft.
The design calculation of solar electric power supply system:
Because the slurry span of 8*6 size should at more than 60CM, so add the span after solar panel to be decided to be 60CM.Select to test with the flexible solar battery of the match parameters of 3s storage battery (parameter is 2V, 0.37AH-0.40AH, is of a size of 18CM*4CM*0.1CM) and record, electric current 450MA-470MA under solar noon sun light.Solar panels running current is 350MA, and eight pieces of solar panels series connection provide power:
P=8*2V*350MA=5.6W>4.59W(motor power demand).
In addition, 2V (solar cell panel voltages) * 8 (solar panels number) > 11.1V (power storage cell voltage) * 1.4 (battery charge multiplying power) charging valtage is within 3S battery charge multiplying power, eligible.
The design calculation of macro simplified model:
After all parts minifications, can use Xin Xida A1510 motor, its dimensional parameters is:
KV:2200; Size: Φ 18mm x 17.5mm (not containing axle); Weight: 16.1g/0.57oz; Output shaft diameter: Φ 2mm; Output shaft length: 8mm; Internal resistance: 0.52 Ω; Maximal efficiency electric current: 2A to 6A, >70%;
Maximum operating currenbt: 8.5A; IO:0.5A/10V; Calculate conservative power (be 4A by electric current, efficiency is 70%) then power P=4*4*0.52*70%=5.824W
.
Solar power supply circuit design calculation:
By solar panel U
max≈ 2V, I ≈ 370mA-400mA:
A. 3*680k Ω both end voltage ≈ 16V
B. because series connection voltage divider principle obtains
C. in the middle of, two potential points obtain pressure 16/3V, 32/3V respectively
D. the balance of voltage charging principle such as 3S lithium cell on meeting
E. due to 3*680k Ω >>R
in 3S
F. shunt resistance is less, reduces the loss of electricity
G. because internal resistance of cell <25m Ω, so current loss is less than 1/27.2
*10
6
If h. during stall with solar recharging, about 1300mAh/400 mA=3.25h
I. can be full of
J. but battery itself can not discharge into too 10.6V, then charging duration is less than 2h.
IN5399 MIC can adopt a greater variety of diode to replace, because charging current and reverse voltage little, does not need 5399 so large current flux and peak reverse voltage, also can reduce tube voltage drop simultaneously.
Lift calculates:
Formula: pulling force (kilogram)=diameter (rice) × pitch (rice) × slurry width (rice) × rotating speed 2 (revolutions per second) × 1 bar pressure (1 standard atmosphere) × empirical coefficient (0.25)
This aircraft parameters substitutes into F=0.2032 × 0.1524 (geometrical pitch)/1.2 × 0.02 × (16000*0.45/60) 2 (revolutions per second) × 1 × 0.25 × 0.45 (correction drag coefficient)=0.836127 (kilogram) and is more or less the same with test bit 830 grams, suffices to show that data are reasonable.
Adopt novel frivolous flexible solar panel packaging technology, be laid on aircraft surface, decrease the impact on flight vehicle aerodynamic profile, alleviate weight simultaneously.
Using solar power as continuation of the journey power resources, machine is loaded with energy storage equipment to store the power surplus of solar panel, realizes flying when low latitude is long navigates.Meet the normal operation of all parts of aircraft.
Material property is analyzed: it is the poly-mer with very strong light transmission that component package have employed the ETEE that UV cure polymer and this encapsulation poly-mer mainly comprise EVA and fluoropolymer ETEE(high endurance), advantage be lightweight, resistance to fall resistance toly to step on, collapsible, portable, easy configuration, elasticity be good.There is good cushion characteristic, ensure that the safety performance of Flight Vehicle Structure; Very high durability makes greatly lengthen the service life of solar power electroplax on the other hand, shortens the cycle changing battery, finally can realize computer terminal and control.
Performance analysis of electric machine: brushless motor speed wide ranges, can under any rotating speed capacity operation; Efficiency is high, especially under underloading situation, still can keep higher efficiency, and this is very important to the energy content of battery of preciousness, and this kind of comparable permanent magnet direct current motor of motor raises the efficiency more than 10%, raises the efficiency more than 20% than Y-series electrical motor; Volume is little, lightweight, specific power is large, can effectively expendable weight, save space.
Through a series of experiment test, aircraft altitude progressively improves along with the process improved and tends towards stability, and tests and records flying height as shown in Figure 4.
Through a series of experiment test, aircraft load-carrying progressively improves along with the process improved and tends towards stability, and tests and records load carrying ability as shown in Figure 5.
Stability is analyzed: the landing being controlled aircraft by remote controller.Control the balance adjustments of gyroscope parameters realization to aircraft by bluetooth module, greatly improve the wind resistance of aircraft.Auxiliary balance system, when different wind direction and wind velocities, automatically can adjust the rotating speed of four hollow-cup motors, reach the effect of balance, thus ensure the stabilized flight of aircraft.
Claims (5)
1. the miniature solar power reconnaisance flight vehicle in conjunction with Coanda effect, it is characterized in that, comprise screw propeller, several piece solar panel, power control unit, balance control unit, several piece solar panel is with rotating shaft center's symmetry erection, the edge frame of every block solar panels is fixedly placed on carbon fiber ring, the gap uniformity of every block solar panels is also connected with aircraft bottom circular skeleton, the S. A. that propeller axis sets up with several piece solar panel overlaps, screw propeller is positioned at top, after erection, the area of several piece solar panel is greater than the oar face of screw propeller, several piece solar panel is erected at outside the flow area of screw propeller generation, power control unit overlaps with frame symmetric line with total barycenter of motor in balance control unit.
2. according to claim 1 in conjunction with the miniature solar power reconnaisance flight vehicle of Coanda effect, it is characterized in that, described power control unit comprises brushless motor, Hexamermis spp receiver, electronic governor and storage battery, Hexamermis spp receiver and remote controller wireless telecommunications, Hexamermis spp receiver exports and controls brushless motor work by electronic governor, solar panels charge a battery, and storage battery is powered to all parts in power control unit.
3. according to claim 1 in conjunction with the miniature solar power reconnaisance flight vehicle of Coanda effect, it is characterized in that, described balance control unit comprises gyroscope, the arduino pro mini chip being with self-balancing program, amplifier and four hollow-cup motors, gyroscope signal send arduino pro mini chip, and arduino pro mini chip exports control signal controls symmetrical four hollow-cup motors placed rotating speed by amplifier.
4. according to claim 1 in conjunction with the miniature solar power reconnaisance flight vehicle of Coanda effect, it is characterized in that, described solar panel adopts frivolous flexible solar panel.
5. according to claim 1 in conjunction with the miniature solar power reconnaisance flight vehicle of Coanda effect, it is characterized in that, also comprise camera and image biography system, camera collection image passes system by image and graphicinformation is sent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510398999.4A CN105015785B (en) | 2015-07-08 | 2015-07-08 | Micro solar reconnaissance flight vehicle incorporated with Coanda effect |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510398999.4A CN105015785B (en) | 2015-07-08 | 2015-07-08 | Micro solar reconnaissance flight vehicle incorporated with Coanda effect |
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| Publication Number | Publication Date |
|---|---|
| CN105015785A true CN105015785A (en) | 2015-11-04 |
| CN105015785B CN105015785B (en) | 2017-03-22 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5803199A (en) * | 1994-05-02 | 1998-09-08 | Hybricraft, Inc. | Lift augmented ground effect platform |
| CN101003302A (en) * | 2007-01-02 | 2007-07-25 | 杨旭 | An aviation aircraft |
| CN101913428A (en) * | 2010-07-26 | 2010-12-15 | 李进朋 | Flying disk |
| CN102548842A (en) * | 2009-07-06 | 2012-07-04 | 艾希尔有限公司 | Craft and method for assembling craft with controlled spin |
| CN202783780U (en) * | 2012-07-13 | 2013-03-13 | 哈尔滨飞机工业集团有限责任公司 | Annular blown flap ducted aerial vehicle |
| CN103803051A (en) * | 2012-11-07 | 2014-05-21 | 康镭 | Solar energy disc-shaped unmanned aircraft with high thrust-weight ratio |
| CN104670504A (en) * | 2015-02-13 | 2015-06-03 | 吉林大学 | Oil/light/electricity multi-power-source fixed wing aircraft |
| CN204776038U (en) * | 2015-07-08 | 2015-11-18 | 上海理工大学 | Miniature solar energy reconnaisance flight vehicle that combines ke enda effect |
-
2015
- 2015-07-08 CN CN201510398999.4A patent/CN105015785B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5803199A (en) * | 1994-05-02 | 1998-09-08 | Hybricraft, Inc. | Lift augmented ground effect platform |
| CN101003302A (en) * | 2007-01-02 | 2007-07-25 | 杨旭 | An aviation aircraft |
| CN102548842A (en) * | 2009-07-06 | 2012-07-04 | 艾希尔有限公司 | Craft and method for assembling craft with controlled spin |
| CN101913428A (en) * | 2010-07-26 | 2010-12-15 | 李进朋 | Flying disk |
| CN202783780U (en) * | 2012-07-13 | 2013-03-13 | 哈尔滨飞机工业集团有限责任公司 | Annular blown flap ducted aerial vehicle |
| CN103803051A (en) * | 2012-11-07 | 2014-05-21 | 康镭 | Solar energy disc-shaped unmanned aircraft with high thrust-weight ratio |
| CN104670504A (en) * | 2015-02-13 | 2015-06-03 | 吉林大学 | Oil/light/electricity multi-power-source fixed wing aircraft |
| CN204776038U (en) * | 2015-07-08 | 2015-11-18 | 上海理工大学 | Miniature solar energy reconnaisance flight vehicle that combines ke enda effect |
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| Publication number | Publication date |
|---|---|
| CN105015785B (en) | 2017-03-22 |
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Granted publication date: 20170322 Termination date: 20190708 |