CN204507261U - A kind of coaxial many in the same way helighros - Google Patents
A kind of coaxial many in the same way helighros Download PDFInfo
- Publication number
- CN204507261U CN204507261U CN201420695990.0U CN201420695990U CN204507261U CN 204507261 U CN204507261 U CN 204507261U CN 201420695990 U CN201420695990 U CN 201420695990U CN 204507261 U CN204507261 U CN 204507261U
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- rotor
- helighros
- rotating shaft
- same way
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Abstract
The utility model relates to autogyro technical field, and be specifically related to a kind of coaxial many in the same way helighros, it comprises aircraft body, and described aircraft body comprises a body, is provided with driving engine in this body, and this driving engine is connected with driving device; Described body is provided with main rotor, and this main rotor is connected with driving device; Described body afterbody is provided with tail-rotor; Described main rotor comprises a steering wheel, this steering wheel is arranged a tilting disc, this tilting disc is arranged a rotating shaft, this rotating shaft is provided with from top to bottom rotor two and rotor one; The rotor head structure that it adopts is simple, and blade length is short, and helicopter overall dimensions is less, reduce cost, its several secondary rotor rotating Vortex, avoids between adjacent rotor and mutually collides, even if wherein a pair breaks down, aircraft also can safety traffic, adds the advantages such as the safety of system.
Description
[technical field]
The utility model relates to autogyro technical field, is specifically related to a kind of coaxial many in the same way helighros.
[background technology]
Helicopter is the aerocraft being produced lift and horizontal direction propulsive force by rotor wing rotation, and compared with fixed wing aircraft, helicopter can realize up-and-down movement in vertical direction, hovering.Mainly comprise single-rotor helicopter and twin-rotor helicopter etc.
Single-rotor helicopter generally adopts tail-rotor to rotate and offsets the reactive torque that main rotor rotates generation.Its major defect is that tail-rotor must be positioned at beyond main oar scope, increases the space that helicopter takies.If use the main oar compared with small scale, the main rotor of many blades need be selected, increase complexity and the cost of lifting airscrew head.
Coaxial double-rotor helicopter is that two secondary rotors are arranged in same rotor shaft one on the other, at regular intervals between rotor.Common double heligyro generally adopts the rotor of two contrarotations, and rotor is cancelled out each other, and it rotates the reactive torque produced.Its major defect is that transmission and steering unit are complicated, and rotor wing rotation plane may cause blade to collide because intersecting up and down.
[utility model content]
The purpose of this utility model is defect for prior art and deficiency, there is provided a kind of structure simple, the coaxial many in the same way helighros of one reasonable in design, easy to use, the rotor head structure that it adopts is simple, blade length is short, helicopter overall dimensions is less, reduces cost, its several secondary rotor rotating Vortex, avoid between adjacent rotor and mutually collide, even if wherein a pair breaks down, aircraft also can safety traffic, adds the advantages such as the safety of system.
The coaxial many in the same way helighros of one described in the utility model, it comprises aircraft body, and described aircraft body comprises a body, is provided with driving engine in this body, and this driving engine is connected with driving device; Described body is provided with main rotor, and this main rotor is connected with driving device; Described body afterbody is provided with tail-rotor; Described main rotor comprises a steering wheel, this steering wheel is arranged a tilting disc, this tilting disc is arranged a rotating shaft, this rotating shaft is provided with from top to bottom rotor two and rotor one.
Further, described rotor two and rotor one are by blade and rotor head composition, and this rotor head is connected in rotating shaft, and blade is clipped in the oar folder of rotor head.
After adopting said structure, the utility model beneficial effect is: the coaxial many in the same way helighros of one described in the utility model, the rotor head structure that it adopts is simple, and blade length is short, and helicopter overall dimensions is less, reduce cost, its several secondary rotor rotating Vortex, avoids between adjacent rotor and mutually collides, even if wherein a pair breaks down, aircraft also can safety traffic, adds the advantages such as the safety of system.
[accompanying drawing explanation]
Accompanying drawing described herein is used to provide to further understanding of the present utility model, forms a application's part, but does not form improper restriction of the present utility model, in the accompanying drawings:
Fig. 1 is the utility model structural representation;
Fig. 2 is the structural representation of main rotor of the present utility model.
Description of reference numerals:
1, driving engine; 2, driving device; 3, main rotor; 31, rotor two; 32, rotor one; 33, rotating shaft; 34, tilting disc; 35, steering wheel; 4, tail-rotor.
[detailed description of the invention]
The utility model is described in detail, illustrative examples wherein and illustrate and be only used for explaining the utility model below in conjunction with accompanying drawing and specific embodiment, but not as to restriction of the present utility model.
As shown in Figure 1 and Figure 2, the coaxial many in the same way helighros of the one described in this detailed description of the invention, it comprises aircraft body, and described aircraft body comprises a body, is provided with driving engine 1 in this body, and this driving engine 1 is connected with driving device 2; Described body is provided with main rotor 3, this main rotor 3 is connected with driving device 2; Described body afterbody is provided with tail-rotor 4; Described main rotor 3 comprises a steering wheel 35, this steering wheel 35 is arranged a tilting disc 34, this tilting disc 34 is arranged a rotating shaft 33, this rotating shaft 33 is provided with from top to bottom rotor 2 31 and rotor 1.
Described rotor 2 31 and rotor 1 are by blade and rotor head composition, and this rotor head is connected in rotating shaft, and blade is clipped in the oar folder of rotor head.
In the utility model, the autogyro of the design can be manned or depopulated helicopter; It is primarily of body, driving engine, driving device, main rotor, tail-rotor five main portions; Power is delivered to main rotor and tail-rotor by driving device from driving engine; Main rotor forms (if figure is two rotors by two or more rotors, then rotor one as shown in Figure 1 and rotor two), rotor comprises blade and rotor head, and rotor head is connected on main shaft, can rotate with main axis, blade is clipped in the oar folder of rotor head; The lift that helicopter is produced by rotor wing rotation and flying.
In the utility model, be connected by some pull bars, bulb bearing between rotor head with tilting disc top (rotating part), tilting disc bottom (fixed part) is connected with steering wheel by some pull bars, bulb bearing, toggle, steering wheel can adopt three steering wheels or four steering wheels or tilting disc to have the form of a displacement restriction, angle and the position of tilting disc is changed by steering wheel, realize the feathering of rotor thus realize the change in helicopter lift direction, reaching the object of change of flight state; Main rotor rotates the reactive torque produced and passes through tail-rotor partial balancing.The design and other single-rotor helicopter principle of work similar, tail-rotor reaches the object controlling helicopter horizontal course simultaneously.
In the utility model, Fig. 1 is embodiment, and this embodiment is the configuration of two rotors.If the helicopter of two or more rotor, by main rotor main shaft, multiple rotor is installed.
The coaxial many in the same way helighros of one described in the utility model, the rotor head structure that it adopts is simple, blade length is short, helicopter overall dimensions is less, reduces cost, its several secondary rotor rotating Vortex, avoid between adjacent rotor and mutually collide, even if wherein a pair breaks down, aircraft also can safety traffic, adds the advantages such as the safety of system.
The above is only better embodiment of the present utility model, therefore all equivalences done according to structure, feature and the principle described in the utility model patent claim change or modify, and are included in the utility model patent claim.
Claims (2)
1. coaxial many in the same way helighros, it comprises aircraft body, and described aircraft body comprises a body, is provided with driving engine (1) in this body, and this driving engine (1) is connected with driving device (2); Described body is provided with main rotor (3), this main rotor (3) is connected with driving device (2); Described body afterbody is provided with tail-rotor (4); It is characterized in that: described main rotor (3) comprises a steering wheel (35), this steering wheel (35) is arranged a tilting disc (34), this tilting disc (34) is arranged a rotating shaft (33), this rotating shaft (33) is provided with from top to bottom rotor two (31) and rotor one (32).
2. the coaxial many in the same way helighros of one according to claim 1, it is characterized in that: described rotor two (31) and rotor one (32) are by blade and rotor head composition, this rotor head is connected in rotating shaft, and blade is clipped in the oar folder of rotor head.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420695990.0U CN204507261U (en) | 2014-11-20 | 2014-11-20 | A kind of coaxial many in the same way helighros |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420695990.0U CN204507261U (en) | 2014-11-20 | 2014-11-20 | A kind of coaxial many in the same way helighros |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204507261U true CN204507261U (en) | 2015-07-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420695990.0U Expired - Fee Related CN204507261U (en) | 2014-11-20 | 2014-11-20 | A kind of coaxial many in the same way helighros |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204507261U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105730684A (en) * | 2016-01-29 | 2016-07-06 | 安徽工程大学 | Multi-rotor gunship helicopter |
| CN105882955A (en) * | 2014-11-20 | 2016-08-24 | 北京万户空天科技有限公司 | Coaxial and equidirectional multi-rotor-wing helicopter |
| CN107140198A (en) * | 2017-06-21 | 2017-09-08 | 中电科芜湖钻石飞机制造有限公司 | Double coaxial tilting rotor wing unmanned aerial vehicle nacelle structures |
| CN107215458A (en) * | 2017-06-21 | 2017-09-29 | 中电科芜湖钻石飞机制造有限公司 | Electronic double coaxial tiltrotor aircrafts |
| CN107963208A (en) * | 2017-11-27 | 2018-04-27 | 江苏翔云航空设备零部件有限公司 | The application method of coaxal helicopter head, coaxal helicopter and coaxal helicopter |
-
2014
- 2014-11-20 CN CN201420695990.0U patent/CN204507261U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105882955A (en) * | 2014-11-20 | 2016-08-24 | 北京万户空天科技有限公司 | Coaxial and equidirectional multi-rotor-wing helicopter |
| CN105730684A (en) * | 2016-01-29 | 2016-07-06 | 安徽工程大学 | Multi-rotor gunship helicopter |
| CN105730684B (en) * | 2016-01-29 | 2018-02-02 | 安徽工程大学 | A kind of more rotor armed helicopters |
| CN107140198A (en) * | 2017-06-21 | 2017-09-08 | 中电科芜湖钻石飞机制造有限公司 | Double coaxial tilting rotor wing unmanned aerial vehicle nacelle structures |
| CN107215458A (en) * | 2017-06-21 | 2017-09-29 | 中电科芜湖钻石飞机制造有限公司 | Electronic double coaxial tiltrotor aircrafts |
| CN107215458B (en) * | 2017-06-21 | 2023-12-08 | 中电科芜湖钻石飞机制造有限公司 | Electric double coaxial tilting rotor craft |
| CN107140198B (en) * | 2017-06-21 | 2023-12-08 | 中电科芜湖钻石飞机制造有限公司 | Nacelle structure of double coaxial tilting rotor unmanned aerial vehicle |
| CN107963208A (en) * | 2017-11-27 | 2018-04-27 | 江苏翔云航空设备零部件有限公司 | The application method of coaxal helicopter head, coaxal helicopter and coaxal helicopter |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150729 Termination date: 20151120 |
|
| EXPY | Termination of patent right or utility model |