CN204264442U - Rotor is in conjunction with fixed wing aircraft - Google Patents
Rotor is in conjunction with fixed wing aircraft Download PDFInfo
- Publication number
- CN204264442U CN204264442U CN201420484265.9U CN201420484265U CN204264442U CN 204264442 U CN204264442 U CN 204264442U CN 201420484265 U CN201420484265 U CN 201420484265U CN 204264442 U CN204264442 U CN 204264442U
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- CN
- China
- Prior art keywords
- pinna
- accessory pinna
- wing
- fixed
- rotor
- 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.)
- Expired - Fee Related
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Abstract
The utility model relates to a kind of rotor in conjunction with fixed wing aircraft.Runway is wanted in takeoff and landing, and helicopter cruising speed is slow, efficiency is low.Rotor is in conjunction with fixed wing aircraft, and its structure is equivalent to helicopter and adds the fixed-wing and cruise system that emplane.Fixed-wing is combined by wing frame and serial accessory pinna, and accessory pinna imbricate arrangement in order, the trailing edge of last accessory pinna is always in the below of a rear accessory pinna leading edge.Accessory pinna structure is as the remex of birds, and pinna rachis is eccentric shaft, pinna rachis and aircraft long axis normal.Accessory pinna can with landing, to cruise and automatic open-close.Rotor in conjunction with fixed wing aircraft, can as aircraft high speed, efficiently cruise, again can without the need to runway as helicopter, can landing everywhere.
Description
Technical field
The utility model relates to a kind of aviation machine, particularly relates to a kind of rotor in conjunction with fixed wing aircraft.
Background technology
The mankind have developed aircraft, helicopter, and aircraft cruising speed is fast, efficiency is high, but runway is wanted in landing, and helicopter landing is without the need to runway, but cruising speed is slow, efficiency is low.
Summary of the invention
Want runway and slow, the inefficient deficiency of helicopter cruising speed to overcome existing takeoff and landing, the utility model provides a kind of rotor in conjunction with fixed wing aircraft, landing without the need to runway, can cruise by high-speed and high-efficiency again as aircraft as helicopter.
Rotor is in conjunction with fixed wing aircraft, and its structure is equivalent to helicopter and adds the fixed-wing and cruise system that emplane.Fixed-wing is combined by wing frame and serial accessory pinna, and accessory pinna imbricate arrangement in order, the trailing edge of last accessory pinna is always in the below of a rear accessory pinna leading edge.Accessory pinna structure is as the remex of birds, and pinna rachis is eccentric shaft, and or not the center of accessory pinna, but be partial to the front side of accessory pinna, the accessory pinna part namely on front side of pinna rachis is narrower, and the accessory pinna part on rear side of pinna rachis is wider.Pinna rachis is vertical with aircraft long axis direction, thus make accessory pinna can with landing, to cruise and automatic open-close.
The utility model solves the technical scheme that its technical matters adopts: rotor, in conjunction with fixed wing aircraft, adds the fixed-wing of boarding a plane by helicopter and cruise system forms.Fixed-wing is combined by wing frame and serial accessory pinna, and accessory pinna presses the arrangement of tandem imbricate, and the trailing edge of last accessory pinna is always in the below of a rear accessory pinna leading edge.Accessory pinna structure is as the remex of birds, and pinna rachis is eccentric shaft, and pinna rachis is vertical with aircraft long axis direction.During landing, rotor promotes air and forms downward air-flow, rotate around pinna rachis downwards on rear side of downward air propels accessory pinna, maximum to 90 °, accessory pinna is opened, like this, just reduce rotor and promote the downdraft of air formation to the application force area of fixed-wing, reduce rotor and promote the downdraft of air formation to the application force of fixed-wing, namely reduce downward drag effect, and the lift effect relatively added upwards, ensure the lifting of aircraft highly effective and safe.When cruising, accessory pinna by pull back spring work in order to, and relative to the effect of aircraft slipstream, go up spinning reduction backward to horizontality on rear side of accessory pinna, serial accessory pinna is closed.The lower surface of each accessory pinna is plane (or concave surface), and upper surface is convex surface, and the radian of its projection is different and different with its position in the sequence, makes whole fixed-wing be aerofoil profile, can provide lift under cruising condition.When cruising, rotor quits work, and rotor is subject to airflow function auto-folder, to reduce the interference to air-flow.
The beneficial effects of the utility model are, rotor in conjunction with fixed wing aircraft, can as aircraft high speed, efficiently cruise, again can without the need to runway as helicopter, can landing everywhere.The helicopter of ratio and aircraft, have higher practicality and safe reliability.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the utility model is described further.
Fig. 1 is the structural representation of the utility model case fixed-wing leading edge accessory pinna I
Fig. 2 is the structural representation of the utility model case fixed-wing near the accessory pinna II of leading edge
Fig. 3 is the structural representation of the utility model case fixed-wing near the accessory pinna III of trailing edge
Fig. 4 is the structural representation of the utility model case fixed-wing trailing edge accessory pinna IV
Fig. 5 is the structural representation that the utility model case fixes thriving frame.
Fig. 6 is the schematic cross section of the fixed-wing that the utility model case wing frame and accessory pinna are combined into.
Detailed description of the invention
Rotor, in conjunction with fixed wing aircraft, adds the fixed-wing of boarding a plane by helicopter and cruise system forms.Fixed-wing is made up of wing frame and serial accessory pinna.
Seeing Fig. 1, Fig. 2, Fig. 3, Fig. 4, is the serial accessory pinna of four different radians: accessory pinna I, accessory pinna II, accessory pinna III, accessory pinna IV, and accessory pinna has the pinna rachis hole 1 passed for pinna rachis.
See Fig. 5, form the wing frame of fixed-wing, have the pinna rachis 2 of fixing accessory pinna.
See Fig. 6, fixed-wing is by the serial accessory pinna of four different radians, accessory pinna I 101, accessory pinna II 102, accessory pinna III 103, accessory pinna IV 104, be fixed on wing frame by pinna rachis 2 and combine, the trailing edge of last accessory pinna is always close to the below of a rear accessory pinna leading edge, pinna rachis and aircraft long axis normal, arrange pull back spring between accessory pinna pinna rachis hole 1 and pinna rachis 2.
Claims (3)
1. a rotor is in conjunction with fixed wing aircraft, it is characterized in that: its structure adds the fixed-wing of boarding a plane by helicopter and cruise system combines, fixed-wing is combined by wing frame and serial accessory pinna, accessory pinna imbricate arrangement in order, the trailing edge of last accessory pinna is always close to below, pinna rachis and the aircraft long axis normal of a rear accessory pinna leading edge.
2. rotor as claimed in claim 1 is in conjunction with fixed wing aircraft, it is characterized in that: accessory pinna structure is as the remex of birds, and pinna rachis is eccentric shaft, not at the center of accessory pinna, but be partial to the front side of accessory pinna, the accessory pinna part namely on front side of pinna rachis is narrower, and the accessory pinna part on rear side of pinna rachis is wider.
3. rotor as claimed in claim 1 is in conjunction with fixed wing aircraft, it is characterized in that: the lower surface of each accessory pinna be plane or concave surface, and upper surface is convex surface, and the radian of its projection is different with its position difference in the sequence, makes whole fixed-wing be aerofoil profile.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420484265.9U CN204264442U (en) | 2014-08-27 | 2014-08-27 | Rotor is in conjunction with fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420484265.9U CN204264442U (en) | 2014-08-27 | 2014-08-27 | Rotor is in conjunction with fixed wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204264442U true CN204264442U (en) | 2015-04-15 |
Family
ID=52799325
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420484265.9U Expired - Fee Related CN204264442U (en) | 2014-08-27 | 2014-08-27 | Rotor is in conjunction with fixed wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204264442U (en) |
-
2014
- 2014-08-27 CN CN201420484265.9U patent/CN204264442U/en not_active Expired - Fee Related
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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: 20150415 Termination date: 20180827 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |