CN105292467A - Horizontal speed-raising system of rotorcraft - Google Patents
Horizontal speed-raising system of rotorcraft Download PDFInfo
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- CN105292467A CN105292467A CN201510750558.6A CN201510750558A CN105292467A CN 105292467 A CN105292467 A CN 105292467A CN 201510750558 A CN201510750558 A CN 201510750558A CN 105292467 A CN105292467 A CN 105292467A
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- horizontal
- cyclogyro
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- rotor
- rotorcraft
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Abstract
The invention provides a horizontal speed-raising system of a rotorcraft. The system comprises a rotorcraft body (1), a horizontal speed-raising system body (2) and a retractable rotor wing (3). The rotorcraft body (1) is in a coaxial double-blade mode. The horizontal speed-raising system body (2) is composed of wings (4) and a horizontal drive propeller (5) and can increase the speed of the rotorcraft. The retractable rotor wing (3) is composed of a rotor wing blade (6) and a telescopic system (7). The diameter of the rotor wing can be changed, and the sound barrier phenomenon of the tip of the rotor wing can be reduced during high-speed flight. The system is suitable for large-area fields on one side of a road, pesticide can be sprayed on the fields as long as the road, an agricultural unmanned aerial vehicle can meet the requirement for continuous work in the aspect of endurance and pesticide carrying capacity, and meanwhile the requirements of work time aging and work area can be met at the same time.
Description
Technical field
The invention belongs to cyclogyro technical field, be specifically related to a kind of horizontal acceleration system of cyclogyro.
Background technology
Autogiro is that one exactly likes helicopter, but is all greatly better than the type of autogyro in performance and operation, can vertical lift.Its cruising speed can reach 300 kilometers per hour the soonest, and takes off without the need to runway, can realize point-to-point flight.
The speed of traditional rotor machine arrives bottleneck, rests between 300-400 kilometer/hour, then it is further difficult to improve speed, it is also proposed the speedup design of multiple cyclogyro both at home and abroad, as increased horizontal speedup screw propeller etc.But when speed is increased to a certain degree, the relative atmospheric speed of rotor wing tip close to velocity of sound, thus will cause sound barrier, resistance will increase sharply, and efficiency significantly reduces on the contrary, can not do further speed-raising.
Summary of the invention
Instant invention overcomes the deficiencies in the prior art, propose a kind of horizontal acceleration system of cyclogyro, by being equipped with the means such as horizontal acceleration system, rotor contraction, increasing the flying speed of cyclogyro, delay and reduction rotor sharp and rounded sounds barrier phenomenon.
Consider the problems referred to above of prior art, according to an aspect disclosed by the invention, the present invention by the following technical solutions:
A horizontal acceleration system for cyclogyro, comprises cyclogyro body (1), horizontal acceleration system (2) and contraction type rotor (3);
Described cyclogyro body (1), be coaxial double-oar form, upper and lower rotor shares turning cylinder, and contrarotation is to form the moment balance of cyclogyro horizontal direction;
Described horizontal acceleration system (2), two are respectively arranged before and after cyclogyro body (1) both sides, horizontal acceleration system (2) is made up of wing (4) and horizontal drive screw propeller (5), when taking off, horizontal drive screw propeller (5) rotates to axis around each wing (4) exhibition, make horizontal drive screw propeller (5) arrive vertical direction, thus auxiliary lifting is provided; After taking off, horizontal drive screw propeller (5) rotates to horizontal direction to axis around each wing (4) exhibition, progressively gathers way, and wing (4) also provides lift simultaneously;
Described contraction type rotor (3), be made up of rotor blade (6) and telescopic system (7), along with the raising of aircraft horizontal velocity, telescopic system (7) by rotor blade (6) Stepwize Shrink to rotary-wing root section, reduce rotor diameter, postpone, the sound barrier phenomenon of rotor wing tip when reducing high-speed flight, reduce air resistance simultaneously.
The invention provides the horizontal acceleration system design plan of collapsible rotor, can by speed-raising and the horizontal acceleration system scheme of cyclogyro reducing the generation of rotor wing tip sound barrier.On the basis of traditional rotor machine, increase horizontal drive screw propeller and wing, and adopt contraction type rotor, make when high-speed horizontal flight, postpone, reduce rotor wing tip sound barrier phenomenon.
Accompanying drawing explanation
Fig. 1 is the horizontal acceleration system integral structure figure of cyclogyro;
Fig. 2 is horizontal acceleration system constructional drawing;
Fig. 3 is contraction type rotor structure figure;
Fig. 4 is rotor blade and contracting mechanism exploded view.
Detailed description of the invention
Below in conjunction with embodiment, the present invention is described in further detail, but embodiments of the present invention are not limited thereto.
See accompanying drawing 1, the horizontal acceleration system of a kind of cyclogyro of the present invention, comprises cyclogyro body (1), horizontal acceleration system (2) and contraction type rotor (3).
Described cyclogyro body (1), for coaxial double-oar form, upper and lower rotor shares turning cylinder, contrarotation to form the moment balance of cyclogyro horizontal direction, the moment that such structure makes cyclogyro not need tail-rotor to come in balancing helicopter horizontal direction.
Described horizontal acceleration system (2), arranges 4 altogether, before and after cyclogyro body (1) both sides, respectively arrange two.Horizontal acceleration system (2) is made up of wing (4) and horizontal drive screw propeller (5).In cyclogyro take-off process, horizontal drive screw propeller (5) rotates to axis around each wing (4) exhibition, makes horizontal drive screw propeller (5) arrive vertical direction, thus provides auxiliary lifting.After cyclogyro takes off, horizontal drive screw propeller (5) rotates to horizontal direction to axis around each wing (4) exhibition, progressively gathers way, and wing (4) can also provide lift for cyclogyro simultaneously.Cyclogyro speed can be promoted to 400-500 kilometer/hour by horizontal acceleration system (2), makes cyclogyro high speed, smooth flight.
Described contraction type rotor (3), be made up of rotor blade (6) and telescopic system (7), along with the raising of aircraft horizontal velocity, telescopic system (7) by rotor blade (6) Stepwize Shrink to rotary-wing root section, reduce rotor diameter, postpone, the sound barrier phenomenon of rotor wing tip when reducing high-speed flight, reduce air resistance simultaneously.
Claims (1)
1. a horizontal acceleration system for cyclogyro, comprises cyclogyro body (1), horizontal acceleration system (2) and contraction type rotor (3);
Described cyclogyro body (1), be coaxial double-oar form, upper and lower rotor shares turning cylinder, and contrarotation is to form the moment balance of cyclogyro horizontal direction;
Described horizontal acceleration system (2), two are respectively arranged before and after cyclogyro body (1) both sides, horizontal acceleration system (2) is made up of wing (4) and horizontal drive screw propeller (5), when taking off, horizontal drive screw propeller (5) rotates to axis around each wing (4) exhibition, make horizontal drive screw propeller (5) arrive vertical direction, thus auxiliary lifting is provided; After taking off, horizontal drive screw propeller (5) rotates to horizontal direction to axis around each wing (4) exhibition, progressively gathers way, and wing (4) also provides lift simultaneously;
Described contraction type rotor (3), be made up of rotor blade (6) and telescopic system (7), along with the raising of aircraft horizontal velocity, telescopic system (7) by rotor blade (6) Stepwize Shrink to rotary-wing root section, reduce rotor diameter, postpone, the sound barrier phenomenon of rotor wing tip when reducing high-speed flight, reduce air resistance simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510750558.6A CN105292467A (en) | 2015-11-06 | 2015-11-06 | Horizontal speed-raising system of rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510750558.6A CN105292467A (en) | 2015-11-06 | 2015-11-06 | Horizontal speed-raising system of rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105292467A true CN105292467A (en) | 2016-02-03 |
Family
ID=55190459
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510750558.6A Pending CN105292467A (en) | 2015-11-06 | 2015-11-06 | Horizontal speed-raising system of rotorcraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105292467A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043696A (en) * | 2016-06-30 | 2016-10-26 | 天津曙光天成科技有限公司 | Flying system for unmanned aerial vehicle |
| CN107472512A (en) * | 2017-08-01 | 2017-12-15 | 西华酷农无人机产业园运营有限公司 | A kind of reinforced propeller of unmanned plane |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3768923A (en) * | 1969-09-18 | 1973-10-30 | United Aircraft Corp | Variable length blade |
| CN101384480A (en) * | 2005-12-22 | 2009-03-11 | 艾伦·J·杰贝诺 | Retractable lifting blades for aircraft |
| CN201793018U (en) * | 2010-09-16 | 2011-04-13 | 中国计量学院 | Four-rotor-winged aircraft with retractable fuselage |
| CN204250360U (en) * | 2014-11-06 | 2015-04-08 | 南京航空航天大学 | Culvert type verts aircraft |
-
2015
- 2015-11-06 CN CN201510750558.6A patent/CN105292467A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3768923A (en) * | 1969-09-18 | 1973-10-30 | United Aircraft Corp | Variable length blade |
| CN101384480A (en) * | 2005-12-22 | 2009-03-11 | 艾伦·J·杰贝诺 | Retractable lifting blades for aircraft |
| CN201793018U (en) * | 2010-09-16 | 2011-04-13 | 中国计量学院 | Four-rotor-winged aircraft with retractable fuselage |
| CN204250360U (en) * | 2014-11-06 | 2015-04-08 | 南京航空航天大学 | Culvert type verts aircraft |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043696A (en) * | 2016-06-30 | 2016-10-26 | 天津曙光天成科技有限公司 | Flying system for unmanned aerial vehicle |
| CN107472512A (en) * | 2017-08-01 | 2017-12-15 | 西华酷农无人机产业园运营有限公司 | A kind of reinforced propeller of unmanned plane |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160203 |