CN103112583A - Pilotless helicopter with independent tail rotor dynamic system - Google Patents
Pilotless helicopter with independent tail rotor dynamic system Download PDFInfo
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- CN103112583A CN103112583A CN2012105971559A CN201210597155A CN103112583A CN 103112583 A CN103112583 A CN 103112583A CN 2012105971559 A CN2012105971559 A CN 2012105971559A CN 201210597155 A CN201210597155 A CN 201210597155A CN 103112583 A CN103112583 A CN 103112583A
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- rotor
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- pilotless
- pilotless helicopter
- electrical
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Abstract
The invention relates to a rotary wing type pilotless plane and further relates to a pilotless helicopter with an independent tail rotor dynamic system. The invention aims at solving the problem of chaotic flight direction and posture once the rotors are out of control when the rotary wing type pilotless helicopter runs in the air. The pilotless helicopter with independent tail rotor dynamic and control system comprises a body, rotary wings, a rotary wing power resource and tail rotors. The pilotless helicopter further comprises an electric motor driving the tail rotors 1, and an electric energy accumulating device 5 connected with the electric motor 2 through a rectifying and shunting device 6. The pilotless helicopter with the independent tail rotor dynamic system disclosed by the invention has the advantages that the ground operator is capable of adjusting the angle and the rotor distance of the tail rotors 1 at any time and correcting the flight direction and posture of the pilotless plane at any time so as to stabilize the flight state of the pilotless plane.
Description
Technical field
The present invention relates to the rotary wind type unmanned plane, further relate to independently pilotless helicopter of tail-rotor power system.
Background technology
In recent years, pilotless helicopter is fast-developing, of many uses, make an inspection tour, search and rescue the civil areas such as seeking, public safety, traffic monitoring, exploration exploration, industrial detection, record evidence obtaining, business are taken, specialty is taken pictures in atmosphere and environmental monitoring, security monitoring, rescue and relief work, patrol, the military domain such as electronic countermeasure, technical search and supervision, myriametric wave communication, information relay all have outstanding performance.
Rotor and the tail-rotor of traditional pilotless helicopter provide power by the same power source, are among the same system of unmanned plane power and transmission.When pilotless helicopter carried out operation aloft, the rotor of unmanned plane was in a single day out of control, and the ground controlling personnel just can't adjust rotor again, to correct direction and the attitude of unmanned plane during flying.The pilotless helicopter heading that is under the rotor runaway condition is chaotic, and the ground controlling personnel can't catch its flight path, and the powerful destructive force of the rotor in motion can cause great unpredictable danger to ground, causes very big injury.
Summary of the invention
When the object of the invention is to the operation aloft of driverless operation heligyro, rotor is in a single day out of control, causes unmanned plane during flying direction and attitude chaotic.The manipulation hand on ground by handling tail-rotor independently power and control system, is adjusted angle and the pitch of tail-rotor at once, and heading and the attitude of correcting at any time unmanned plane are to stablize the state of flight of unmanned plane.Thereby avoided wearing over the ground because rotor is out of control the unpredictable considerable damage power of coming.
Technical scheme of the present invention is as follows:
The tail-rotor power system is pilotless helicopter independently, comprising: fuselage, rotor, rotor propulsion source, tail-rotor also comprise: drive the electrical motor 2 of tail-rotor 1, the electrical energy storage device 5 that is connected with electrical motor 2 by rectification and part flow arrangement 6.
The propulsion source of mast 9 is provided by driving engine 4, driving engine 4 drives an electrical generator 7 simultaneously, the electric energy that electrical generator produces electrical motor 2 power supplies for driving tail-rotor through overcommutation and part flow arrangement 6, electrical generator 7 is guaranteeing to drive under the prerequisite of tail-rotor electrical motor 2 power consumptions, and the power storage that fecund is given birth to is at electrical energy storage device 5.
The present invention is for the advantage of prior art:
Tradition driverless operation heligyro: its rotor and tail-rotor provide power by a propulsion source jointly, within being in the same flying power of unmanned plane and driving system.
Depopulated helicopter of the present invention: within rotor and tail-rotor are placed in respectively different two power and driving system, provide power to main rotor and drive electrical generator 7 by driving engine 4 respectively to produce electric power; The electric energy that electrical generator 7 transforms is when overcommutation and part flow arrangement 6 provide power (power supply) for tail-rotor electrical motor 2, and electric energy more than needed is stored into electrical energy storage device 5 by rectification and part flow arrangement 6 again.After driving engine 4 accidents stop, provide emergency service by electrical energy storage device 5, thereby avoided going wrong because of main rotor, engine power system, make tail-rotor motor stalling, ground staff and can't continue to handle tail-rotor, make heading and attitude out of control, thereby whole heading and the attitude that can not in time correct unmanned plane.
Description of drawings
Fig. 1 is the structural representation of the embodiment of the present invention.In figure, 1 represents tail-rotor, and 2 representatives drive the tail-rotor electrical motor, and 3 represent the fuselage tail pipe, and 4 represent driving engine, and 5 represent electrical energy storage device, and 6 represent rectification and part flow arrangement, and 7 represent electrical generator, and 8 represent reducing gear, and 9 represent mast.
The specific embodiment
The tail-rotor power system is pilotless helicopter independently, comprising: fuselage, rotor, rotor propulsion source, tail-rotor also comprise: drive the electrical motor 2 of tail-rotor 1, by rectification and part flow arrangement 6 and the electrical energy storage device 5 that drives tail-rotor electrical motor 2 and be connected.The propulsion source of mast 9 is provided by driving engine 4, driving engine 4 drives electrical generator 7 simultaneously, the electric energy that electrical generator 7 produces is the power supply of tail-rotor motor through overcommutation and part flow arrangement 6, electrical generator 7 is stored in electrical energy storage device 5 with electric energy more than needed by rectification and part flow arrangement 6 guaranteeing to drive under the prerequisite of tail-rotor electrical motor 2 power consumptions.
Working process is as follows: driving engine 4 drives mast 9 rotations by reducing gear 8, a part of mechanical energy is converted into electric energy by electrical generator 7, output on driving tail-rotor electrical motor 2 through overcommutation and part flow arrangement 6, further drive tail-rotor 1 work, rectification and part flow arrangement 6 with the electrical power storage of having more than needed in electrical energy storage device 5.When aircraft operation aloft, rotor is in a single day out of control, and the manipulation hand on ground by handling tail-rotor 1 independently power and control system, is adjusted angle and the pitch of tail-rotor 1 at once, and heading and the attitude of correcting at any time unmanned plane are to stablize the state of flight of unmanned plane.
Claims (3)
1. tail-rotor power system pilotless helicopter independently, comprise: fuselage, rotor, rotor propulsion source, tail-rotor, it is characterized in that, also comprise: drive the electrical motor (2) of tail-rotor (1), the electrical energy storage device (5) that is connected with electrical motor (2) by rectification and part flow arrangement (6).
2. tail-rotor power system pilotless helicopter independently according to claim 1, it is characterized in that, the propulsion source of mast (9) is provided by driving engine (4), driving engine (4) drives electrical generator (7) simultaneously, the electric energy that electrical generator (7) produces is powered for the electrical motor (2) that drives tail-rotor through overcommutation and part flow arrangement (6), electrical generator (7) is guaranteeing to drive under the prerequisite of tail-rotor electrical motor (2) power consumption, electric energy more than needed is stored in electrical energy storage device (5) by rectification and part flow arrangement (6).
3. tail-rotor power system pilotless helicopter independently according to claim 1, is characterized in that, after driving engine (4) accident stopped, the tail-rotor propulsion source provided emergency service by electrical energy storage device (5), thereby drove the tail-rotor normal operation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210597155.9A CN103112583B (en) | 2012-12-31 | 2012-12-31 | The pilotless helicopter of tail-rotor dynamical system independence |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210597155.9A CN103112583B (en) | 2012-12-31 | 2012-12-31 | The pilotless helicopter of tail-rotor dynamical system independence |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103112583A true CN103112583A (en) | 2013-05-22 |
| CN103112583B CN103112583B (en) | 2016-10-19 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210597155.9A Active CN103112583B (en) | 2012-12-31 | 2012-12-31 | The pilotless helicopter of tail-rotor dynamical system independence |
Country Status (1)
| Country | Link |
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| CN (1) | CN103112583B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235901A (en) * | 2015-10-21 | 2016-01-13 | 青岛宏百川金属精密制品有限公司 | Independent tail rotor structure of unmanned helicopter |
| CN105966609A (en) * | 2016-05-26 | 2016-09-28 | 北京理工大学 | Hybrid power jump takeoff system of heavy type gyroplane provided with variable pitch teeterboard type rotor head |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB651391A (en) * | 1945-05-09 | 1951-04-04 | United Aircraft Corp | Improvements in or relating to rotary wing aircraft |
| US5836545A (en) * | 1994-04-25 | 1998-11-17 | Paul E. Arlton | Rotary wing model aircraft |
| CN201012292Y (en) * | 2006-01-19 | 2008-01-30 | 银辉玩具制品厂有限公司 | Helicopter |
| WO2011144690A1 (en) * | 2010-05-19 | 2011-11-24 | Eads Deutschland Gmbh | Hybrid drive for helicopters |
| CN203078755U (en) * | 2012-12-31 | 2013-07-24 | 天津曙光敬业科技有限公司 | Unmanned helicopter with independent tail rotor power system |
-
2012
- 2012-12-31 CN CN201210597155.9A patent/CN103112583B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB651391A (en) * | 1945-05-09 | 1951-04-04 | United Aircraft Corp | Improvements in or relating to rotary wing aircraft |
| US5836545A (en) * | 1994-04-25 | 1998-11-17 | Paul E. Arlton | Rotary wing model aircraft |
| CN201012292Y (en) * | 2006-01-19 | 2008-01-30 | 银辉玩具制品厂有限公司 | Helicopter |
| WO2011144690A1 (en) * | 2010-05-19 | 2011-11-24 | Eads Deutschland Gmbh | Hybrid drive for helicopters |
| CN203078755U (en) * | 2012-12-31 | 2013-07-24 | 天津曙光敬业科技有限公司 | Unmanned helicopter with independent tail rotor power system |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235901A (en) * | 2015-10-21 | 2016-01-13 | 青岛宏百川金属精密制品有限公司 | Independent tail rotor structure of unmanned helicopter |
| CN105966609A (en) * | 2016-05-26 | 2016-09-28 | 北京理工大学 | Hybrid power jump takeoff system of heavy type gyroplane provided with variable pitch teeterboard type rotor head |
| CN105966609B (en) * | 2016-05-26 | 2019-11-26 | 北京理工大学 | A kind of heavy autogyro hybrid power richochet system with variable-distance teetering rotor head |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103112583B (en) | 2016-10-19 |
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Application publication date: 20130522 Assignee: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Assignor: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd.|Zhao Runhong Contract record no.: 2017990000070 Denomination of invention: Pilotless helicopter with independent tail rotor dynamic system Granted publication date: 20161019 License type: Exclusive License Record date: 20170307 |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170418 Address after: 300000 Tianjin city Dongli District Junliangcheng Tengfei Road No. 3 floor of building B Patentee after: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. Address before: No. 300151 Tianjin road Hebei District City, Wang Chuanchang Hospital No. 62 Co-patentee before: Zhao Runhong Patentee before: TIANJIN AURORA UAV TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221008 Address after: 300457 No. 105, Building 9, Zone B3 (formerly Zone 2 of Ronghui Business Park), Binhai Zhongguancun Science and Technology Park, Tianjin Economic and Technological Development Zone, Binhai New Area, Tianjin Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |