CN102923301A - Rotor composite propeller of helicopter - Google Patents
Rotor composite propeller of helicopter Download PDFInfo
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- CN102923301A CN102923301A CN2012104456211A CN201210445621A CN102923301A CN 102923301 A CN102923301 A CN 102923301A CN 2012104456211 A CN2012104456211 A CN 2012104456211A CN 201210445621 A CN201210445621 A CN 201210445621A CN 102923301 A CN102923301 A CN 102923301A
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- propeller
- main screw
- main
- rotor
- shaft
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Abstract
The invention discloses a rotor composite propeller of a helicopter. The propeller comprises a main propeller shaft, at least two main propeller arms, rotor blades and a rotor shaft, wherein the main propeller shaft is connected with a power shaft of the helicopter and supplies power for the whole propeller; one ends of the main propeller arms are fixed on the main propeller shaft and the rotor shaft is installed at the other ends of the main propeller arms; and the rotor blades are fixed on the rotor shaft and can rotate freely. The propeller has the advantages of vertical taking off and landing, hovering, good maneuverability, and capability of gliding landing in a rotorcraft mode when the main propeller shuts down due to faults and improving flying stability and security, and the like.
Description
Technical field
The present invention relates to the aircraft field, particularly a kind of compound heligyro screw propeller.
Background technology
Autogyro has the advantages such as vertical takeoff and landing, hovering, is used widely, but hinders for some reason when shutting down at main screw, can not carry out stalled glide, exists certain dangerously, and energy consumption is large during normal flight.The advantages such as cyclogyro has can glide, flight stability and low energy consumption, but take off distance is long, and maneuvering performance is relatively poor.Integrate the advantage of above two kinds of aircraft propellers, can greatly promote the maneuvering performance of aircraft.
Summary of the invention
The object of the invention is to overcome the shortcoming that exists in the prior art, provide a kind of maneuvering performance good, simple in structure compound heligyro screw propeller.
Purpose of the present invention is achieved through the following technical solutions:
A kind of compound heligyro screw propeller comprises main screw axle 1, the main screw arm 2 more than 2 or 2, rotor blade 3 and rotor shaft 4; Main screw axle 1 is connected with the helicopter dynamical axis, for whole screw propeller provides power; One end of main screw arm 2 is fixed on the main screw axle 1, and the other end is equipped with rotor shaft 4; Rotor blade 3 is fixed on the rotor shaft 4, and can rotate freely.
Preferred 2,3 or 4 of the quantity of described main screw arm 2, spatially symmetrical.
The hand of rotation of the plane of rotation of described rotor blade 3 and main screw arm 2 is an angle, and angular range is less than 60 degree greater than 0 degree.The number of blade of described rotor blade 3 is more than 2 or 2.
Principle of work of the present invention is: main screw axle 1 is connected with the helicopter dynamical axis, for whole screw propeller provides power; Rotor shaft 4 is unpowered, and when main screw arm 2 was pressed the certain speed rotation by 1 drive of main screw axle, rotor blade 3 rotated under the wind-power effect, and produces lift.
The present invention compared with prior art has following advantage and effect:
1, main screw axle of the present invention has improved the engine application scope than producing larger lift under the low-speed conditions, is conducive to reduce loss and life-saving, is particularly suitable for flying under the low-altitude low-speed.
2, the present invention is applied on the helicopter, and the main screw axle stops operating when flight, can provide lift by rotor blade, continues to glide and land, and has improved the flight reliability of helicopter.
3, the main screw arm outer of on-line velocity maximum of the present invention produces effective lift, has alleviated the screw propeller overall weight.
Description of drawings
Fig. 1 is embodiment 1(4 main shaft screw propeller arm) structural representation.
Fig. 2 is embodiment 2(2 main shaft screw propeller arm) structural representation.
Fig. 3 is embodiment 3(3 main shaft screw propeller arm) structural representation.
Fig. 4 is three kinds of rotor blade structural representations.
Wherein: 1, main screw axle; 2, main screw arm; 3, rotor blade; 4, rotor shaft.
The specific embodiment
Below in conjunction with embodiment the present invention is done further detailed description, but embodiments of the present invention are not limited to this.
As shown in Figure 1, compound heligyro screw propeller comprises main screw axle 1,4 main screw arms 2, rotor blade 3 and rotor shaft 4; Main screw axle 1 is connected with the helicopter dynamical axis, for whole screw propeller provides power; 4 main screw arms 2 are spatially symmetrical, and an end of main screw arm 2 is fixed on the main screw axle 1, and the other end is equipped with rotor shaft 4; Rotor blade 3 is fixed on the rotor shaft 4.
When the dynamic main screw axle 1 of tool drives 2 rotation of main screw arm, the rotor blade 3 of 4 main screw arm 2 terminals is promoted rotation by air resistance, rotor shaft 4 is unpowered axle, makes rotor blade 3 plane of rotations and main screw arm 2 working direction be a fixed angle of altitude, produces lift.
The aircraft Normal Take-Off And Landing is similar to general helicopter when hovering.When flying instrument has forward thrust or forward coasting flight and when landing, even main screw arm 2 stops operating, on 4 rotor blades 3, also can produce certain lift, this moment, offline mode was identical with cyclogyro.
As shown in Figure 4, the number of blade of rotor blade 3 can be 2,3 or 4.
As shown in Figure 2, compound heligyro screw propeller comprises main screw axle 1,2 main screw arms 2, rotor blade 3 and rotor shaft 4.2 main screw arms 2 are spatially symmetrical, and other is identical with embodiment 1.
As shown in Figure 3, compound heligyro screw propeller comprises main screw axle 1,3 main screw arms 2, rotor blade 3 and rotor shaft 4.3 main screw arms 2 are spatially symmetrical, and other is identical with embodiment 1.
Claims (4)
1. a compound heligyro screw propeller is characterized in that: comprise main screw axle, main screw arm, rotor blade and rotor shaft more than 2 or 2; The main screw axle is connected with the helicopter dynamical axis, for whole screw propeller provides power; One end of main screw arm is fixed on the main screw axle, and the other end is equipped with rotor shaft; Rotor blade is fixed on the rotor shaft, and can rotate freely.
2. compound heligyro screw propeller according to claim 1, it is characterized in that: the quantity of described main screw arm is 2,3 or 4, and is spatially symmetrical.
3. compound heligyro screw propeller according to claim 1, it is characterized in that: the hand of rotation of the plane of rotation of described rotor blade and main screw arm is an angle, and angular range is less than 60 degree greater than 0 degree.
4. compound heligyro screw propeller according to claim 1, it is characterized in that: the number of blade of described rotor blade is more than 2 or 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104456211A CN102923301A (en) | 2012-11-09 | 2012-11-09 | Rotor composite propeller of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012104456211A CN102923301A (en) | 2012-11-09 | 2012-11-09 | Rotor composite propeller of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102923301A true CN102923301A (en) | 2013-02-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012104456211A Pending CN102923301A (en) | 2012-11-09 | 2012-11-09 | Rotor composite propeller of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102923301A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107539465A (en) * | 2016-06-27 | 2018-01-05 | 权明勇 | A kind of wing structure around the rotation of aircraft central principal axis |
| CN109348705A (en) * | 2016-06-15 | 2019-02-15 | 小鹰公司 | Self-adjusting system for flying vehicles control |
| CN110001948A (en) * | 2019-04-30 | 2019-07-12 | 南京涵铭置智能科技有限公司 | A kind of double blades shooting unmanned plane and its application method |
| CN110997485A (en) * | 2017-08-04 | 2020-04-10 | 意造科技私人有限公司 | Single arm fault redundancy for multi-rotor aircraft with minimal rotor/propellers |
Citations (10)
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| US6467726B1 (en) * | 1999-06-29 | 2002-10-22 | Rokuro Hosoda | Aircraft and torque transmission |
| CN1843847A (en) * | 2006-05-18 | 2006-10-11 | 战强 | Multi-rotor aerocraft |
| CN101027214A (en) * | 2004-09-23 | 2007-08-29 | 托克及蒂尔德有限公司 | Rotorcraft |
| CN101391651A (en) * | 2008-11-17 | 2009-03-25 | 西安智澜科技发展有限公司 | Foldable Y shaped three axis two-layer six rotorcraft |
| KR100929260B1 (en) * | 2009-04-28 | 2009-12-01 | 주식회사 업앤온 | Device and method for launching quadrocopter |
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| CN101905744A (en) * | 2009-06-04 | 2010-12-08 | 尤洛考普特公司 | Control hybrid helicopter provided driftage degree methods and hybrid helicopter provided |
| CN102180267A (en) * | 2011-04-22 | 2011-09-14 | 南京航空航天大学 | Umbrella-shaped foldable multi-rotor aircraft |
| CN202244078U (en) * | 2011-07-29 | 2012-05-30 | 深圳市大疆创新科技有限公司 | Multi-rotary-wing unmanned aircraft |
| KR20120060590A (en) * | 2010-12-02 | 2012-06-12 | 충남대학교산학협력단 | Quadro-Copter with traveling ground |
-
2012
- 2012-11-09 CN CN2012104456211A patent/CN102923301A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6467726B1 (en) * | 1999-06-29 | 2002-10-22 | Rokuro Hosoda | Aircraft and torque transmission |
| CN101027214A (en) * | 2004-09-23 | 2007-08-29 | 托克及蒂尔德有限公司 | Rotorcraft |
| CN1843847A (en) * | 2006-05-18 | 2006-10-11 | 战强 | Multi-rotor aerocraft |
| CN101391651A (en) * | 2008-11-17 | 2009-03-25 | 西安智澜科技发展有限公司 | Foldable Y shaped three axis two-layer six rotorcraft |
| CN201367115Y (en) * | 2008-11-17 | 2009-12-23 | 西安智澜科技发展有限公司 | Foldable four-axis multi-rotor wing aerocraft |
| KR100929260B1 (en) * | 2009-04-28 | 2009-12-01 | 주식회사 업앤온 | Device and method for launching quadrocopter |
| CN101905744A (en) * | 2009-06-04 | 2010-12-08 | 尤洛考普特公司 | Control hybrid helicopter provided driftage degree methods and hybrid helicopter provided |
| KR20120060590A (en) * | 2010-12-02 | 2012-06-12 | 충남대학교산학협력단 | Quadro-Copter with traveling ground |
| CN102180267A (en) * | 2011-04-22 | 2011-09-14 | 南京航空航天大学 | Umbrella-shaped foldable multi-rotor aircraft |
| CN202244078U (en) * | 2011-07-29 | 2012-05-30 | 深圳市大疆创新科技有限公司 | Multi-rotary-wing unmanned aircraft |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109348705A (en) * | 2016-06-15 | 2019-02-15 | 小鹰公司 | Self-adjusting system for flying vehicles control |
| CN107539465A (en) * | 2016-06-27 | 2018-01-05 | 权明勇 | A kind of wing structure around the rotation of aircraft central principal axis |
| CN110997485A (en) * | 2017-08-04 | 2020-04-10 | 意造科技私人有限公司 | Single arm fault redundancy for multi-rotor aircraft with minimal rotor/propellers |
| CN110997485B (en) * | 2017-08-04 | 2023-08-29 | 意造科技私人有限公司 | Single-arm fault redundancy for multi-rotor aircraft with minimal rotor/propeller |
| CN110001948A (en) * | 2019-04-30 | 2019-07-12 | 南京涵铭置智能科技有限公司 | A kind of double blades shooting unmanned plane and its application method |
| CN110001948B (en) * | 2019-04-30 | 2021-02-12 | 南京涵铭置智能科技有限公司 | Double-blade shooting unmanned aerial vehicle and using method thereof |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130213 |