CN102616372A - Improvement plan for design of helicopter - Google Patents
Improvement plan for design of helicopter Download PDFInfo
- Publication number
- CN102616372A CN102616372A CN2012100425125A CN201210042512A CN102616372A CN 102616372 A CN102616372 A CN 102616372A CN 2012100425125 A CN2012100425125 A CN 2012100425125A CN 201210042512 A CN201210042512 A CN 201210042512A CN 102616372 A CN102616372 A CN 102616372A
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- China
- Prior art keywords
- helicopter
- design
- improvement plan
- rotor
- pole
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- 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.)
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Abstract
The invention relates to an improvement plan for the design of a helicopter. Struts of rotor wings of an original helicopter are lengthened, the gravity center of the helicopter is lowered, and accordingly flight stability of the helicopter is improved.
Description
Technical field
The improvement project of patent helicopter design of the present invention relates to a kind of structural design scheme of civil and military helicopter.
Background technology
Since century, the military design engineer and the amateurs of various countries on the problem of development helicopter, have ignored a very basic safety problem more than one, thereby cause the miserable situation of many helicopter accidents.The reason of searching to the bottom just is design engineers, and they have seemingly forgotten it has been the people that lives on earth themselves! They place the center of gravity that is difficult to the helicopter of stabilized flight aloft on the high position, and are born with regard to very easily overturning so stability in-flight, is met strong wind or misoperation slightly with regard to extreme difference, and the fatal crass.
Summary of the invention
The improvement project of patent helicopter design of the present invention is with improving safety and stable a kind of new departure of classifying main objective as and taking.Its way is, with center of gravity suitably reduce, in the hope of improving its stability.After center of gravity reduces, can't have a strong impact on rising, falling and flying speed and steering capability and the characteristic of climbing of helicopter.And people also never require it can do the stunt of the action of rolling aloft to helicopter, so can not change the range of use of helicopter.
In order to let it can get into hangar easily and to be suitable for long-distance transport, can its pole B be made the structure that can stretch, this just can lower the actual height of whole helicopter easily.For example, the pole B1 of rotor processed slide up and down, (sliding sleeve E of outside cover) after helicopter stopped, the rotor automatic lowering was to extreme lower position; In case but after rotor turns over,, lean on antagonistic force downwards, the rotor arrival tip position that promptly rises because wind-force blows.
Description of drawings
Fig. 1: the lateral plan that is original design-calculated helicopter
A---rotor
B---pole
C---rudder slurry
D---driver's seat
Fig. 2: the lateral plan that is the helicopter after the improvement
The B1-lengthening bar
E---sliding sleeve
The specific embodiment
1, can existing helicopter pole lengthening B1 be added a telescopic sliding sleeve E.
Claims (2)
1. the improvement project of patent helicopter design of the present invention is characterized in that center of gravity is lower.
2. according to claim 1, the pole that helicopter is driven rotor is extended.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100425125A CN102616372A (en) | 2012-02-22 | 2012-02-22 | Improvement plan for design of helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012100425125A CN102616372A (en) | 2012-02-22 | 2012-02-22 | Improvement plan for design of helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102616372A true CN102616372A (en) | 2012-08-01 |
Family
ID=46556681
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012100425125A Pending CN102616372A (en) | 2012-02-22 | 2012-02-22 | Improvement plan for design of helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102616372A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107826243A (en) * | 2017-09-27 | 2018-03-23 | 中国民航大学 | A kind of combined type aircraft |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2428475A (en) * | 1945-04-05 | 1947-10-07 | Swaab Maurice | Helicopter having means for adjusting the center of gravity and the lift rotor axis thereof |
| JPH0321593A (en) * | 1989-06-20 | 1991-01-30 | Joji Harada | Flying device of helicopter and adjusting device for center of gravity of the machine |
| CN101365624A (en) * | 2005-08-24 | 2009-02-11 | 莫尔纳里公司 | Ground air water craft |
-
2012
- 2012-02-22 CN CN2012100425125A patent/CN102616372A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2428475A (en) * | 1945-04-05 | 1947-10-07 | Swaab Maurice | Helicopter having means for adjusting the center of gravity and the lift rotor axis thereof |
| JPH0321593A (en) * | 1989-06-20 | 1991-01-30 | Joji Harada | Flying device of helicopter and adjusting device for center of gravity of the machine |
| CN101365624A (en) * | 2005-08-24 | 2009-02-11 | 莫尔纳里公司 | Ground air water craft |
Non-Patent Citations (1)
| Title |
|---|
| 高正等: "《直升机飞行动力学》", 30 April 2003, 科学出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107826243A (en) * | 2017-09-27 | 2018-03-23 | 中国民航大学 | A kind of combined type aircraft |
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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: 20120801 |