CN1208003A - Swing wing type helicopter - Google Patents
Swing wing type helicopter Download PDFInfo
- Publication number
- CN1208003A CN1208003A CN 97115709 CN97115709A CN1208003A CN 1208003 A CN1208003 A CN 1208003A CN 97115709 CN97115709 CN 97115709 CN 97115709 A CN97115709 A CN 97115709A CN 1208003 A CN1208003 A CN 1208003A
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- CN
- China
- Prior art keywords
- wing
- wings
- airplane
- resistance
- swing
- 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
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- 230000001174 ascending effect Effects 0.000 abstract 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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Abstract
The invention discloses a novel swing wing type helicopter which mainly comprises a helicopter body and wings. The wing can swing up and down, thereby obtaining upward and forward power and being capable of vertically ascending, descending and flying forwards. The wing can be provided with an air guide sheet, when the wing swings upwards, the air guide sheet opens the airflow channel to reduce the resistance, and when the wing swings downwards, the air guide sheet closes the airflow channel to increase the resistance, so that the airplane obtains an upward lifting force. The wings can be segmented, all the segments are connected through a shaft, the wings can be bent around the shaft, when the wings swing upwards, the wings are bent, the length of the wings is shortened, the air resistance is reduced, otherwise, the air resistance is increased, and the airplane obtains upward lifting force. The airplane has high efficiency and good safety, and even if the engine fails, the airplane cannot fall down quickly, and the wings on the two sides can enable the airplane to fall down slowly. It has wide application.
Description
The present invention relates to a kind of later-model Wing oscillating helicopter.This aircraft mainly is made up of fuselage and the wing that can swing.It obtains lifting force flight by the wing pendulum, is applicable to the aviation industry.
Existing autogyro development is very fast, constantly enlarges purposes and scope, no matter be military or civilian, is all bringing into play great role.Existing autogyro still has the place of many deficiencies, and low as flight efficiency, safety is still not high enough.
The purpose of this invention is to provide a kind of later-model autogyro, its oil consumption is less, and flight efficiency is higher, and safety is better living, is applicable to the aviation industry.
Task of the present invention is achieved in that this aircraft mainly is made up of fuselage and wing, and wing swings up and down, and obtains lifting force and aloft flies.The airguide sheet is arranged on this wing, and when wing was upwards swung, the airguide sheet was opened gas channel, has reduced resistance; When wing during to lower swing, airguide sheet closed gas flow passage has increased the application force of wing to air, and the air counteraction makes aircraft obtain the lifting force that makes progress.Wing can be to become piece continuously, also can be merogenesis.When wing is a merogenesis, wing is divided into more than two sections or two sections.Connect by axle between each section wing, wing can be transferred around axle.When wing was upwards swung, wing was transferred, and had shortened the length of wing, had reduced the application force area of wing to air, had reduced resistance.When wing during to lower swing, wing changes straight elongation, has increased wing to the application force area to air, has increased the resistance of air, makes aircraft obtain lifting force.The flight efficiency of this aircraft is higher, be because wing when lower swing, the bearing surface of wing and be subjected to force direction near vertical, and the propeller of existing autogyro follows its rotation direction face to have only a little inclination angle, its lifting force that makes progress is a component.It is high that this aircraft safety changes, and is that when stopping to start when the driving engine et out of order, aircraft descends downwards because the area of its wing is big, and wing must open elongation, and guide piece is also closed air by-pass passage, therefore is subjected to the very big resistance of air.And the propeller area of existing autogyro is very little, and is little to the resistance of air, driving engine et out of order and when shutting down, will falling very soon.Because this aircraft flight rate height, safety is higher, therefore uses this aircraft to be significant.
Provide some scheme drawings below, and further discuss the characteristics of this aircraft in conjunction with these scheme drawings.
This figure is the front-view schematic diagram of this aircraft.
Referring to this scheme drawing, fuselage (1) and wing (2) are main portion, have formed this aircraft.Along fulcrum M, wing (2) is when upwards swinging, and airguide sheet (3) is stressed downwards, has opened air by-pass passage.When it during to lower swing, airguide sheet (3) is stressed has upwards closed air by-pass passage, makes wing (2) be subjected to very big application force.Wing (2) can also be transferred, and wing (2) is when upwards swinging, and the outer end wing has shortened wing because of being subjected to downward power along some O turnover downwards, also just reduces the resistance of air.When wing (2) during to lower swing, the outer end wing changes directly because of being subjected to power upwards, has increased the application force area and the application force of wing (2).Because wing (2) is subjected to the power near vertical direction, this improves the flight efficiency of aircraft.This aircraft is when et out of order, and wing (2) area is big, is subjected to bigger resistance when aircraft is descended, and aircraft can be glided descend more slowly, has improved safe life greatly.
Swing obtains lifting force flight to this aircraft by wing, and its flight efficiency is higher, because the bigger wing of area is improved the safety of aircraft.Use this aircraft, important meaning is all arranged in directions such as aviation, tourisms.
Claims (2)
1, a kind of Wing oscillating helicopter, it mainly is made up of fuselage (1) and wing (2).It is characterized in that: wing (2) can be swung, and it has airguide sheet (3), and when it was upwards swung, airguide sheet (3) was opened air by-pass passage; When it during to lower swing, airguide sheet (3) closed gas flow passage.
2, by the described aircraft of claim 1, it is characterized in that: the outer end wing (4) of wing (2) can be transferred along fulcrum O.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97115709 CN1208003A (en) | 1997-08-08 | 1997-08-08 | Swing wing type helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 97115709 CN1208003A (en) | 1997-08-08 | 1997-08-08 | Swing wing type helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1208003A true CN1208003A (en) | 1999-02-17 |
Family
ID=5173388
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 97115709 Pending CN1208003A (en) | 1997-08-08 | 1997-08-08 | Swing wing type helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1208003A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100348605C (en) * | 2003-06-06 | 2007-11-14 | 因德纳有限公司 | Colchicoside analogues |
-
1997
- 1997-08-08 CN CN 97115709 patent/CN1208003A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100348605C (en) * | 2003-06-06 | 2007-11-14 | 因德纳有限公司 | Colchicoside analogues |
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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 |