CN102602540A - Solar electric helicopter - Google Patents
Solar electric helicopter Download PDFInfo
- Publication number
- CN102602540A CN102602540A CN2011104414074A CN201110441407A CN102602540A CN 102602540 A CN102602540 A CN 102602540A CN 2011104414074 A CN2011104414074 A CN 2011104414074A CN 201110441407 A CN201110441407 A CN 201110441407A CN 102602540 A CN102602540 A CN 102602540A
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- helicopter
- solar power
- screw propeller
- frame
- battery pack
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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 helicopter using solar energy and storage batteries, which comprises a body, a frame, a solar panel and a storage battery set. The frame is fixed on the body. The solar panel is disposed on the upper surface of the storage battery set which is mounted on the body and/or the frame. A propeller is fixed on the frame. A cab is hinged to the body through rotary shafts. A controller for controlling rotation of the propeller and the cab is disposed in the cab. A landing support for stabilizing the helicopter in landing is connected with the frame. The helicopter is powered by electric energy only, using the solar panel to generate power supplied to electric equipment in the helicopter in real time can meet the double requirements of environmental friendliness and energy conservation and greatly improved flying capacity, and the helicopter is low in manufacturing process requirements, simple and accurate in operation, convenient in management, low in maintenance, environment-friendly, energy-saving, high in flying capacity, long in airborne period, high in reliability, high in energy conservation rate, widely applicable to civil fields of practical flying training, aerial surveillance.
Description
Technical field
The present invention is a kind of electronic autogyro, and particularly a kind of electronic autogyro that has solar panels and battery pack belongs to the renovation technique of the electronic helicopter that uses solar power.
Background technology
At aviation field, the energy of use is single at present, and great majority are main fuel with petroleum fuel extractive matter (aircraft gasoline, aviation kerosene or aviation diesel oil etc.) all, and using combustion engine is main propelling unit.But,, be unfavorable for energy conservation and environment protection because there are pollutions such as flue dust, noise, profit in traditional combustion engine.The heliotechnics development so far, and is quite ripe, uses heliotechnics to become inexorable trend; But because heliotechnics receives the meteorological conditions restriction; Under night and rainy weather, can't normally use, so, need to use the energy in other sources to carry out effectively additional.And other energy recharge forms like wind energy, then because of reasons such as waste of power can't compensate, also are not suitable on aerocraft, using.
Summary of the invention
The objective of the invention is to consider the problems referred to above and a kind of electronic helicopter of use solar power that can satisfy environmental protection and energy saving simultaneously and significantly improve the double requirements of boat power is provided.The present invention is reasonable in design, and is convenient and practical.
Technical scheme of the present invention is: the autogyro of use solar power of the present invention and storage battery; Include body, framework, solar panels, battery pack; Wherein frame fixation is on body, the solar panels that are used to absorb solar power be placed on battery pack above, battery pack is installed on body and/or the framework; Screw propeller is fixed on the framework; The crew module is contained on the body through rotating shaft hinge, and the controller that is used to control screw propeller and crew module's rotation is placed in the crew module, keeps fuselage pulsation-free landing support to be connected with framework when being used for helicopter landing.
Above-mentioned crew module is fixed on the adapter shaft, and adapter shaft is connected with rotating shaft, and the rotating shaft hinge is contained on the body.
Above-mentioned screw propeller is controlled rotating speed separately through controller.
Above-mentioned body upper is provided with some solar panels and battery pack, and some battery packs connect in parallel, or connects with series connected mode.
Above-mentioned screw propeller is 4, and 4 screw propellers are all controlled rotating speed separately through controller.
Above-mentioned crew module is that 360 ° of rotations can be done in the axle center with the rotating shaft.
The electricpropulsion installation that above-mentioned screw propeller uses is DC motor.
The present invention is owing to adopt to use solar panels and battery pack, and solar panels are installed on the body, supplies power with the solar power and the mode of battery pack cooperation, can satisfy environmental protection and energy saving simultaneously and significantly improve the double requirements of boat power.The electricpropulsion installation that the present invention supplies power and is provided with to screw propeller with the mode that solar power and battery pack cooperate, electricpropulsion installation is connected to screw propeller and produces lift, promotes to take off; In addition, the present invention realizes different rotating speed through 4 screw propellers of controller control, and identical and when reaching enough rotating speed when 4 propeller speed, helicopter takes off vertically; Identical and when reaching corresponding rotating speeds when 4 propeller speed, helicopter in hover or decline are when needs during to certain side flight; Improve rightabout propeller speed, the lift of this side is improved, then helicopter flies to opposite side; And the crew module is rotated by controller control, turns to the working direction of flight, but crew module's rotation automatic guidance; Also can manually be controlled by chaufeur, the all-electric aircraft of use solar panels provided by the invention and battery pack has following characteristics:
1) utilization of the present invention and storage regenerative resource help alleviating the pressure of energy-saving and emission-reduction.
2) the present invention does not rotate fuselage, only rotates crew module's angle and realizes control.Be different from the design of conventional helicopters.
3) the present invention adopts ripe relatively battery technology; Can under the condition that solar panels can't be worked fully, produce enough electric energy and be supplied in electricpropulsion installation promotion screw propeller, thereby realize electric energy is stored and satisfies the needs of all-weather flight task.
4) the present invention is in the solar panels normal operation, and can provide the moving propelling unit of sufficient electrical energy power supply to use the time, the accumulators group of charging automatically reaches the environmental protection purpose.
6) the present invention can be carried out the reasonable disposition of power supply by the controller of driving compartment, makes electricpropulsion installation be in optimum Working constantly.
The present invention is that a kind of design is ingenious, function admirable, the electronic helicopter of convenient and practical use solar power.
Description of drawings
Fig. 1 is a birds-eye view of the present invention.
Fig. 2 is a lateral plan of the present invention.
The specific embodiment
Embodiment:
Structural representation of the present invention is as shown in Figure 1; The present invention uses the autogyro of solar power and storage battery, includes body 1, framework 2, solar panels 3, battery pack 4, and its middle frame 2 is fixed on the body 1; The solar panels 3 that are used to absorb solar power be placed on battery pack 4 above; Battery pack 4 is installed on body 1 and/or the framework 2, and screw propeller 10 is fixed on the framework 2, and crew module 7 is contained on the body 1 through rotating shaft 5 hinges; The controller 8 that is used to control screw propeller 10 and crew module's 7 rotation is placed in the crew module 7, keeps fuselage pulsation-free landing support 9 to be connected with framework 2 when being used for helicopter landing.In the present embodiment, solar panels 3 and battery pack 4 are installed on the body 1.
Above-mentioned crew module 7 is fixed on the adapter shaft 6, and adapter shaft 6 is connected with rotating shaft 5, and rotating shaft 5 hinges are contained on the body 1.In the present embodiment, above-mentioned crew module 7 is that 360 ° of rotations can be done in the axle center with rotating shaft 5.
In the present embodiment, above-mentioned screw propeller 10 is controlled rotating speed separately through controller 8.
Above-mentioned body 1 top is provided with some solar panels 3 and battery pack 4, and some battery packs 4 connect according to the electric power of screw propeller 10 employed electricpropulsion installation demands in parallel, or connect with series connected mode.In the present embodiment, some battery packs 4 connect with series connected mode according to the electric power of screw propeller 10 employed electricpropulsion installation demands.
In the present embodiment, above-mentioned screw propeller 10 is 4, and 4 screw propellers 10 all pass through controller 8 control rotating speed separately.
In the present embodiment, the electricpropulsion installation that above-mentioned screw propeller 10 uses is DC motor.
Aircraft of the present invention is owing to adopt to use solar panels and battery pack, and solar panels are installed on the body, supplies power with the solar power and the mode of battery pack cooperation, can satisfy environmental protection and energy saving simultaneously and significantly put forward the double requirements of endurance.The electricpropulsion installation that the present invention supplies power and is provided with to screw propeller with the mode that solar power and battery pack cooperate, electricpropulsion installation is connected to screw propeller and produces lift, promotes to take off.
Principle of work of the present invention is following: realize different rotating speed through 4 screw propellers of controller control, identical and when reaching enough rotating speed when 4 propeller speed, helicopter takes off vertically; Identical and when reaching corresponding rotating speeds when 4 propeller speed, helicopter in hover or decline are when needs during to certain side flight; Improve rightabout propeller speed, the lift of this side is improved, then helicopter flies to opposite side; And the crew module is rotated by controller control; Turn to the working direction of flight, but crew module's rotation automatic guidance can manually be controlled also by chaufeur.The present invention has simple to operate accurate, convenient management, and environmental protection and energy saving, boat power is high, and reliability is high, and the advantage that energy transformation ratio is high can be widely used in flight driving practical operation and train many civil areas such as aerial monitoring.
Claims (7)
1. autogyro that uses solar power and storage battery; Include body (1), framework (2), solar panels (3), battery pack (4); Its middle frame (2) is fixed on the body (1); The solar panels (3) that are used to absorb solar power are placed on above the battery pack (4); Battery pack (4) is installed on body (1) and/or the framework (2), and screw propeller (10) is fixed on the framework (2), and crew module (7) is contained on the body (1) through rotating shaft (5) hinge; The controller (8) that is used to control screw propeller (10) and crew module's (7) rotation is placed in the crew module (7), keeps fuselage pulsation-free landing support (9) to be connected with framework (2) when being used for helicopter landing.
2. the electronic helicopter of use solar power according to claim 1 is characterized in that above-mentioned crew module (7) is fixed on the adapter shaft (6), and adapter shaft (6) is connected with rotating shaft (5), and rotating shaft (5) hinge is contained on the body (1).
3. the electronic helicopter of use solar power according to claim 1 is characterized in that above-mentioned screw propeller (10) controls rotating speed separately through controller (8).
4. the electronic helicopter of use solar power according to claim 1; It is characterized in that above-mentioned body (1) top is provided with some solar panels (3) and battery pack (4); Some battery packs (4) connect in parallel, or connect with series connected mode.
5. according to the electronic helicopter of each described use solar power of claim 1 to 4, it is characterized in that above-mentioned screw propeller (10) is 4,4 screw propellers (10) all pass through controller (8) and control rotating speed separately.
6. the electronic helicopter of use solar power according to claim 5 is characterized in that above-mentioned crew module (7) is that 360 ° of rotations can be done in the axle center with rotating shaft (5).
7. the electronic helicopter of use solar power according to claim 6 is characterized in that the electricpropulsion installation that above-mentioned screw propeller (10) uses is DC motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104414074A CN102602540A (en) | 2011-12-26 | 2011-12-26 | Solar electric helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104414074A CN102602540A (en) | 2011-12-26 | 2011-12-26 | Solar electric helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102602540A true CN102602540A (en) | 2012-07-25 |
Family
ID=46520444
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011104414074A Pending CN102602540A (en) | 2011-12-26 | 2011-12-26 | Solar electric helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102602540A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103754361A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
| CN103770942A (en) * | 2014-02-28 | 2014-05-07 | 戴维 | Long-endurance solar aircraft capable of vertically taking off and landing |
| GB2514340A (en) * | 2013-05-20 | 2014-11-26 | Michael Lee Burdett | An unmanned aerial power plant drone |
| CN104309801A (en) * | 2014-09-26 | 2015-01-28 | 金陵科技学院 | Rotary wing type unmanned plane with spherical solar collector at central section and landing seat thereof |
| CN104608914A (en) * | 2014-12-12 | 2015-05-13 | 宁波高新区甬晶微电子有限公司 | Intelligent multipurpose rescue unmanned aircraft |
| US10266264B2 (en) | 2016-12-05 | 2019-04-23 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| CN112977787A (en) * | 2021-03-11 | 2021-06-18 | 北京航天发射技术研究所 | Flexible fuselage wing aircraft |
| CN112977786A (en) * | 2021-03-11 | 2021-06-18 | 北京航天发射技术研究所 | Flexible tubular fuselage wing-group aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6308912B1 (en) * | 1997-10-21 | 2001-10-30 | Natural Colour Kari Kirjavainen Oy | Rotorcraft |
| DE20120758U1 (en) * | 2001-12-26 | 2002-08-01 | Jahns, Christian, Dipl.-Ing., 42659 Solingen | Construction for helicopter control by changing the rotor speed and protecting the rotor against contact |
| JP2002347698A (en) * | 2001-05-23 | 2002-12-04 | Ishigaki Foods Co Ltd | Vertical takeoff and landing aircraft |
| CN102020019A (en) * | 2010-12-03 | 2011-04-20 | 华南师范大学 | Small-sized electric airplane using hybrid energy |
-
2011
- 2011-12-26 CN CN2011104414074A patent/CN102602540A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6308912B1 (en) * | 1997-10-21 | 2001-10-30 | Natural Colour Kari Kirjavainen Oy | Rotorcraft |
| JP2002347698A (en) * | 2001-05-23 | 2002-12-04 | Ishigaki Foods Co Ltd | Vertical takeoff and landing aircraft |
| DE20120758U1 (en) * | 2001-12-26 | 2002-08-01 | Jahns, Christian, Dipl.-Ing., 42659 Solingen | Construction for helicopter control by changing the rotor speed and protecting the rotor against contact |
| CN102020019A (en) * | 2010-12-03 | 2011-04-20 | 华南师范大学 | Small-sized electric airplane using hybrid energy |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2514340A (en) * | 2013-05-20 | 2014-11-26 | Michael Lee Burdett | An unmanned aerial power plant drone |
| CN103754361A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
| CN103770942A (en) * | 2014-02-28 | 2014-05-07 | 戴维 | Long-endurance solar aircraft capable of vertically taking off and landing |
| CN104309801A (en) * | 2014-09-26 | 2015-01-28 | 金陵科技学院 | Rotary wing type unmanned plane with spherical solar collector at central section and landing seat thereof |
| CN104309801B (en) * | 2014-09-26 | 2016-02-03 | 金陵科技学院 | A kind of middle part is rotary wind type unmanned plane and the landing seat thereof of spherical solar catcher |
| CN104608914A (en) * | 2014-12-12 | 2015-05-13 | 宁波高新区甬晶微电子有限公司 | Intelligent multipurpose rescue unmanned aircraft |
| US10266264B2 (en) | 2016-12-05 | 2019-04-23 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US10407171B2 (en) | 2016-12-05 | 2019-09-10 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US10906643B2 (en) | 2016-12-05 | 2021-02-02 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| US11498677B2 (en) | 2016-12-05 | 2022-11-15 | Autel Robotics Co., Ltd. | Unmanned aerial vehicle |
| CN112977787A (en) * | 2021-03-11 | 2021-06-18 | 北京航天发射技术研究所 | Flexible fuselage wing aircraft |
| CN112977786A (en) * | 2021-03-11 | 2021-06-18 | 北京航天发射技术研究所 | Flexible tubular fuselage wing-group aircraft |
| CN112977786B (en) * | 2021-03-11 | 2023-02-21 | 北京航天发射技术研究所 | Flexible tubular fuselage wing-group aircraft |
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Application publication date: 20120725 |