CN104260875A - Collision-resistant structure of agricultural plant protection unmanned aerial vehicle - Google Patents
Collision-resistant structure of agricultural plant protection unmanned aerial vehicle Download PDFInfo
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- CN104260875A CN104260875A CN201410479198.6A CN201410479198A CN104260875A CN 104260875 A CN104260875 A CN 104260875A CN 201410479198 A CN201410479198 A CN 201410479198A CN 104260875 A CN104260875 A CN 104260875A
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- resistant structure
- plant protection
- wing shell
- unmanned plane
- agricultural plant
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Abstract
The invention discloses a collision-resistant structure of an agricultural plant protection unmanned aerial vehicle. The collision-resistant structure comprises a wing shell and a hybrid power system arranged in the wing shell, wherein the hybrid power system comprises a main rotor and multiple auxiliary rotors; the main rotor is arranged in the middle of the wing shell; the multiple auxiliary rotors are uniformly distributed at several corners of the wing shell; and finned plates with adjustable directions are arranged below the main rotor. According to the mode, the collision-resistant structure disclosed by the invention has the advantages that the collision resistance of the unmanned aerial vehicle can be improved, and the unmanned aerial vehicle has the excellent wind resistance and the good control ability.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, particularly relate to a kind of agricultural plant protection unmanned plane impact resistant structure.
Background technology
Plant protection unmanned plane is a kind of for touching the agricultural unmanned plane spilling agricultural chemicals.Plant protection unmanned plane during flying circumstance complication, especially in middle part and eastern region, it is densely populated, has the obstacles such as a large amount of trees, house, pedestrian, various electric pole and electric wire tower in field.Plant protection unmanned plane flies and is easy to crash in field.Current various aircrafts such as fixed wing aircraft, once encounter obstacle, will crash; Helicopter and many cyclogyros, once encounter obstacle, wing will fracture, and causes air crash, once meet pedestrian, the rotor flown in circles equally can injure pedestrian to blade.
Summary of the invention
The technical matters that the present invention mainly solves is to provide a kind of agricultural plant protection unmanned plane impact resistant structure, can improve the impact resistant ability of unmanned plane, ensures that unmanned plane has excellent wind resistance and good road-holding property.
For solving the problems of the technologies described above, the technical scheme that the present invention adopts is: provide a kind of agricultural plant protection unmanned plane impact resistant structure, comprise: wing shell and the hybrid power system be arranged in described wing shell, described hybrid power system comprises main rotor and some secondary rotors, described main rotor is arranged on the centre of described wing shell, some described secondary rotors are evenly distributed on several angles of described wing shell, and the below of described main rotor is provided with the fin plate in adjustable direction.
In a preferred embodiment of the present invention, described wing shell structure triangular in shape, described secondary rotor has three, is arranged on respectively on three angles of described shell.
In a preferred embodiment of the present invention, described wing shell is flexible gas-filled casing, is the aerodynamic shape consisted of skeleton and lacing wire welding balloon forming process.
In a preferred embodiment of the present invention, described wing canning material adopts the Water Cube materials for wall etfe film.
In a preferred embodiment of the present invention, described main rotor is petrol power main rotor, for providing vertical takeoff and landing and hovering power; Described secondary rotor is electronic secondary rotor, for ensureing organism balance, turning and hovering steering operation.
In a preferred embodiment of the present invention, described electronic secondary rotor adopts aviation brushless motor to control.
The invention has the beneficial effects as follows: by the hybrid power system adopting petrol power main rotor and electronic secondary rotor to form, and the asymmetric dynamic structure of main rotor and secondary rotor composition is embedded in soft inflatable wing shell completely, the impact resistant ability of unmanned plane can be improved on the one hand, ensure that unmanned plane has excellent wind resistance and good road-holding property on the other hand.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of agricultural plant protection unmanned plane of the present invention impact resistant structure one preferred embodiment;
Fig. 2 is the birds-eye view shown in Fig. 1;
Fig. 3 is the upward view shown in Fig. 1;
In accompanying drawing, the mark of each parts is as follows: 1, wing shell, and 2, secondary rotor, 3, main rotor, 4, fin plate.
Detailed description of the invention
Below in conjunction with accompanying drawing, preferred embodiment of the present invention is described in detail, can be easier to make advantages and features of the invention be readily appreciated by one skilled in the art, thus more explicit defining is made to protection scope of the present invention.
Refer to Fig. 1-Fig. 3, the embodiment of the present invention comprises:
A kind of agricultural plant protection unmanned plane impact resistant structure, comprise: wing shell 1 and the hybrid power system be arranged in described wing shell 1, described wing shell 1 structure triangular in shape, described hybrid power system comprises main rotor 3 and secondary rotor 2, described main rotor 3 is arranged on the centre of described wing shell 1, described secondary rotor 3 has three, be arranged on three angles of described wing shell 1 respectively, and the below of described main rotor 3 is provided with the fin plate 4 in adjustable direction, powerful Gasoline engine main rotor 3 is utilized to coordinate the adjustment fin plate 4 installed thereunder, flexible adjustment air flow line, improve the dynamical stability control ability of unmanned plane, overcome the airflow resistance that wind-force acts on wing shell 1 formation, realize smooth flight, when landing and hovering, described fin plate 4 forms lift vertically downward, when forward direction flies, described fin plate 4 is formed slopely to back pressure.
Described wing shell 1 is flexible gas-filled casing, is the aerodynamic shape consisted of skeleton and lacing wire welding balloon forming process, has higher Dent resistance and flexibility, can ensure can not damage urban facilities and aircraft when surprisingly colliding in-flight.
The material of described wing shell 1 adopts the Water Cube materials for wall etfe film, has high strength, high fire performance.
Described main rotor 3 is petrol power main rotor, adopt Gasoline engine, 120cc twin-tub four stroke aeronautical engine, coordinate the positive and negative blade pair of 35 inch, maximum 50 kg thrusts can be provided, form the main lift system of aircraft, for providing vertical takeoff and landing and hovering power, it adopts petrol power to ensure power and the flight time requirement of unmanned plane.1 liter of fuel oil can ensure unmanned plane hovering flight 45 minutes, cruising flight 2 hours.
Described secondary rotor 2 is electronic secondary rotor, three described secondary rotors 2 form auxiliary balance system, for ensureing organism balance, turn and hovering steering operation, it adopts aviation brushless motor W5010 200KV, instantaneous thrust 2 kg, propulsion source is controlled as auxiliary balance, function admirable, the requirement of dynamical equilibrium power change can be met, 20AH 24V lithium ion battery is adopted to power, 2 hours flight demands can be met, in addition, owing to not being main lift system, thrust requirements is low, only in hovering, balance and flight attitude is kept when vertical takeoff and landing and turning, cruising flight motor does not work substantially, service conditions redundancy is larger, electrical machinery life can be ensured, greatly can reduce the maintenance cost of unmanned plane.
Our experiments show that, wing shell area 3m
2, take-off weight 20kg, is less than 3.5m/S with the parachute pattern speed of falling, and coordinates flexible gas-filled casing, and at height 60 meters of various attitude drops, in 100 repeated fall experiments, unmanned plane serviceability rate 100% is 0 to the damage rate of bottom surface simulation dummy and automobile.
Dirigible and aircraft combine by the present invention; with the air bag of softness as wing shell; fuel power main rotor and the secondary rotor of electrodynamic balance are protected; the shell encountering obstacle softness awing can absorb collision energy, ensure unmanned plane safety; the rotor of High Rotation Speed is embedded in inside soft wing shell 1 on the other hand; can not hurt pedestrian, be the high course of new aircraft of a kind of safety.Adopt powerful main rotor 3 to coordinate fin plate 4 and secondary rotor 2, ensure that huge inflatable wing shell 1 is when being subject to windage, can keep balance and stability to fly, ensure that unmanned plane has excellent wind resistance and good road-holding property.
Agricultural plant protection unmanned plane provided by the invention relies on power rotor to provide lift, inflatable wing shell for protection; From traditional power airship and mix the flying method of lift dirigible and mode is completely different, be the safe Helicopter Technology of a kind of height completely newly.
Present invention is disclosed a kind of agricultural plant protection unmanned plane impact resistant structure, by the hybrid power system adopting petrol power main rotor and electronic secondary rotor to form, and the asymmetric dynamic structure of main rotor and secondary rotor composition is embedded in soft inflatable wing shell completely, the impact resistant ability of unmanned plane can be improved on the one hand, ensure that unmanned plane has excellent wind resistance and good road-holding property on the other hand.
The foregoing is only embodiments of the invention; not thereby the scope of the claims of the present invention is limited; every utilize specification sheets of the present invention and accompanying drawing content to do equivalent structure or equivalent flow process conversion; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present invention.
Claims (6)
1. an agricultural plant protection unmanned plane impact resistant structure, it is characterized in that, comprise: wing shell and the hybrid power system be arranged in described wing shell, described hybrid power system comprises main rotor and some secondary rotors, described main rotor is arranged on the centre of described wing shell, some described secondary rotors are evenly distributed on several angles of described wing shell, and the below of described main rotor is provided with the fin plate in adjustable direction.
2. agricultural plant protection unmanned plane impact resistant structure according to claim 1, is characterized in that, described wing shell structure triangular in shape, and described secondary rotor has three, is arranged on respectively on three angles of described wing shell.
3. agricultural plant protection unmanned plane impact resistant structure according to claim 1, it is characterized in that, described wing shell is flexible gas-filled casing, is the aerodynamic shape consisted of skeleton and lacing wire welding balloon forming process.
4. agricultural plant protection unmanned plane impact resistant structure according to claim 3, it is characterized in that, described wing canning material adopts the Water Cube materials for wall etfe film.
5. agricultural plant protection unmanned plane impact resistant structure according to claim 1, it is characterized in that, described main rotor is petrol power main rotor, for providing vertical takeoff and landing and hovering power; Described secondary rotor is electronic secondary rotor, for ensureing organism balance, turning and hovering steering operation.
6. agricultural plant protection unmanned plane impact resistant structure according to claim 5, is characterized in that, described electronic secondary rotor adopts aviation brushless motor to control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410479198.6A CN104260875B (en) | 2014-09-19 | 2014-09-19 | The resistance to crash feature of agricultural plant protection unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201410479198.6A CN104260875B (en) | 2014-09-19 | 2014-09-19 | The resistance to crash feature of agricultural plant protection unmanned plane |
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| Publication Number | Publication Date |
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| CN104260875A true CN104260875A (en) | 2015-01-07 |
| CN104260875B CN104260875B (en) | 2016-05-04 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104663099A (en) * | 2015-01-22 | 2015-06-03 | 湖南金骏农业科技有限公司 | Fertilizer apparatus and plant protection airplane including same |
| CN104859859A (en) * | 2015-05-18 | 2015-08-26 | 深圳供电局有限公司 | Aerodynamic optimization hybrid multirotor |
| CN105035328A (en) * | 2015-08-19 | 2015-11-11 | 张旭超 | Hybrid-power flight vehicle |
| CN105480418A (en) * | 2015-12-17 | 2016-04-13 | 北京猎鹰无人机科技有限公司 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
| WO2017004826A1 (en) * | 2015-07-09 | 2017-01-12 | 华南农业大学 | Anti-fall and anti-drift unmanned aerial vehicle |
| CN107352034A (en) * | 2017-06-14 | 2017-11-17 | 广州越城丰茂农林科技有限公司 | New golden-pomelo yellow twig Control Technology |
| CN109153445A (en) * | 2016-02-17 | 2019-01-04 | 雅顿技术有限公司 | Multi-rotor aerocraft with different purposes propellers |
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| CN202011472U (en) * | 2011-02-28 | 2011-10-19 | 南昌航空大学 | Tilting duct unmanned aerial vehicle |
| CN102765470A (en) * | 2011-05-05 | 2012-11-07 | 张丙炎 | Soft structured airplane |
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| CN1517270A (en) * | 2003-01-15 | 2004-08-04 | 董国宝 | Air cushion type gliding aircraft |
| CN1725600A (en) * | 2004-07-22 | 2006-01-25 | 三菱电机株式会社 | Brushless motor |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104663099A (en) * | 2015-01-22 | 2015-06-03 | 湖南金骏农业科技有限公司 | Fertilizer apparatus and plant protection airplane including same |
| CN104663099B (en) * | 2015-01-22 | 2017-01-18 | 湖南金骏农业科技有限公司 | Fertilizer apparatus and plant protection airplane including same |
| CN104859859A (en) * | 2015-05-18 | 2015-08-26 | 深圳供电局有限公司 | Aerodynamic optimization hybrid multirotor |
| WO2017004826A1 (en) * | 2015-07-09 | 2017-01-12 | 华南农业大学 | Anti-fall and anti-drift unmanned aerial vehicle |
| US10858098B2 (en) | 2015-07-09 | 2020-12-08 | South China Agricultural University | Falling-resistant and anti-drifting unmanned aerial vehicle |
| CN105035328A (en) * | 2015-08-19 | 2015-11-11 | 张旭超 | Hybrid-power flight vehicle |
| CN105480418A (en) * | 2015-12-17 | 2016-04-13 | 北京猎鹰无人机科技有限公司 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
| CN109153445A (en) * | 2016-02-17 | 2019-01-04 | 雅顿技术有限公司 | Multi-rotor aerocraft with different purposes propellers |
| US11807356B2 (en) | 2016-02-17 | 2023-11-07 | SIA InDrones | Multicopter with different purpose propellers |
| CN107352034A (en) * | 2017-06-14 | 2017-11-17 | 广州越城丰茂农林科技有限公司 | New golden-pomelo yellow twig Control Technology |
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| Publication number | Publication date |
|---|---|
| CN104260875B (en) | 2016-05-04 |
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Effective date of registration: 20160829 Address after: 215021 No. 75, Song Bei Road, Suzhou Industrial Park, Jiangsu Patentee after: Best flying technology (Suzhou) Co., Ltd. Address before: 215500 Changshu City, Jiangsu province high tech Industrial Development Zone, Southeast Avenue, No. 1, building 68, No. Patentee before: SUZHOU TIANYI AVIATION TECHNOLOGY CO., LTD. |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160504 Termination date: 20190919 |
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| CF01 | Termination of patent right due to non-payment of annual fee |