CN101157385A - Helicopter - Google Patents
Helicopter Download PDFInfo
- Publication number
- CN101157385A CN101157385A CNA2007101874582A CN200710187458A CN101157385A CN 101157385 A CN101157385 A CN 101157385A CN A2007101874582 A CNA2007101874582 A CN A2007101874582A CN 200710187458 A CN200710187458 A CN 200710187458A CN 101157385 A CN101157385 A CN 101157385A
- Authority
- CN
- China
- Prior art keywords
- helicopter
- flabellum
- driving engine
- engine
- puffer
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 241000883990 Flabellum Species 0.000 claims description 19
- 239000000872 buffer Substances 0.000 claims description 8
- 230000001174 ascending effect Effects 0.000 abstract 1
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 4
- 230000003042 antagnostic effect Effects 0.000 description 2
- 230000009191 jumping Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
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Abstract
The invention discloses a helicopter comprising a helicopter body, blades, and an engine. The helicopter is characterized in that the engine is arranged on a movable shaft arranged in the middle part of the helicopter body, upper strung blades and lower strung blades are respectively arranged at the two ends of the rotary shaft of the engine. Compared with the prior art, the invention has the advantages that the making is simple, the operation is flexible, the resistance is reduced, a pilot can parachute jump to flee for the life, and the ascending power can be increased.
Description
Technical field:
The invention belongs to helicopter, especially a kind of high-effect helicopter.
Background technology:
At present, the individual layer wing or the reverse double-deck wing of helicopter employing.The helicopter of individual layer wing, span area is big, and antagonistic force is also big simultaneously, if the driving engine et out of order of adjustment crashes easily.The aviator is difficult to the parachute jumping escape.Because wing is positioned at body upper, when wing produces lift, the fuselage area consumption lift.
Summary of the invention:
The object of the present invention is to provide a kind of can parachute helicopter of escape, raising lift of simple, flexible operation, minimizing resistance, aviator of making.
Technical solution of the present invention is as follows:
1, a kind of helicopter comprises by body, flabellum, driving engine, it is characterized in that, on the movable axis of described body middle part driving engine is installed, and described engine shaft two ends are installed the string flabellum respectively and gone here and there flabellum down.
2, as technical scheme 1 described helicopter, wherein, described body tail end is installed puffer, and puffer is equipped with little flabellum.
3, as technical scheme 1 described helicopter, wherein, described body is provided with frame.
The present invention compared with prior art has and makes simply, and flexible operation reduces resistance, aviator's escape of can parachuting, the advantage of raising lift.
Description of drawings:
Fig. 1 is an integral structure front view of the present invention.
Fig. 2 is an integral structure birds-eye view of the present invention.
Among Fig. 1～Fig. 2, little flabellum (1), puffer (2), body (3), on go here and there flabellum (4), go here and there flabellum (5), frame (6), movable axis (7), driving engine (8) down.
The specific embodiment:
Most preferred embodiment of the present invention is such, with reference to Fig. 1～shown in Figure 3, a kind of helicopter, comprise by body, flabellum, driving engine, wherein, described body (3) middle part movable axis (7) is upward installed driving engine (8), and described driving engine (8) rotating shaft two ends are installed string flabellum (4) respectively and gone here and there flabellum (5) down; Described body (3) tail end is installed puffer (2), and puffer (2) is equipped with little flabellum (1); Described body (3) is provided with frame (6).
Principle of work of the present invention: when driving engine (8) rotated, string flabellum (4) produced lift with string flabellum (5) rotation down drives in, when needing forward-reverse, regulated with movable axis (7), about needing during activity, by body (3) adjusting movable axis (7).Drive little flabellum (1) rotation by puffer (2), regulate the antagonistic force of helicopter lift.As when having an accident, flabellum can not injure the aviator of parachute jumping.
Claims (3)
1. a helicopter comprises by body, flabellum, driving engine, it is characterized in that, described body (3) middle part movable axis (7) is upward installed driving engine (8), and described driving engine (8) rotating shaft two ends are installed string flabellum (4) respectively and gone here and there flabellum (5) down.
2. according to the described helicopter of claim 1, it is characterized in that described body (3) tail end is installed puffer (2), puffer (2) is equipped with little flabellum (1).
3. according to the described helicopter of claim 1, it is characterized in that described body (3) is provided with frame (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101874582A CN101157385A (en) | 2007-11-27 | 2007-11-27 | Helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101874582A CN101157385A (en) | 2007-11-27 | 2007-11-27 | Helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101157385A true CN101157385A (en) | 2008-04-09 |
Family
ID=39305646
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007101874582A Pending CN101157385A (en) | 2007-11-27 | 2007-11-27 | Helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101157385A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104401489A (en) * | 2014-11-25 | 2015-03-11 | 武汉天降科技有限公司 | Helicopter aeroplane propeller brake device |
| JP2018140772A (en) * | 2017-02-27 | 2018-09-13 | エアバス ヘリコプターズ ドイチェランド ゲーエムベーハー | Thrust generating unit having at least two rotor assemblies and a shroud |
| CN111806703A (en) * | 2020-03-28 | 2020-10-23 | 赫文波 | Cloud computing type emergency state identification platform |
-
2007
- 2007-11-27 CN CNA2007101874582A patent/CN101157385A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104401489A (en) * | 2014-11-25 | 2015-03-11 | 武汉天降科技有限公司 | Helicopter aeroplane propeller brake device |
| CN104401489B (en) * | 2014-11-25 | 2016-06-08 | 武汉天降科技有限公司 | A kind of helicopter propeller brake |
| JP2018140772A (en) * | 2017-02-27 | 2018-09-13 | エアバス ヘリコプターズ ドイチェランド ゲーエムベーハー | Thrust generating unit having at least two rotor assemblies and a shroud |
| US11220325B2 (en) | 2017-02-27 | 2022-01-11 | Airbus Helicopters Deutschland GmbH | Thrust producing unit with at least two rotor assemblies and a shrouding |
| CN111806703A (en) * | 2020-03-28 | 2020-10-23 | 赫文波 | Cloud computing type emergency state identification platform |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| 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: 20080409 |