CN203255356U - Annular-wing aircraft - Google Patents
Annular-wing aircraft Download PDFInfo
- Publication number
- CN203255356U CN203255356U CN 201320087861 CN201320087861U CN203255356U CN 203255356 U CN203255356 U CN 203255356U CN 201320087861 CN201320087861 CN 201320087861 CN 201320087861 U CN201320087861 U CN 201320087861U CN 203255356 U CN203255356 U CN 203255356U
- Authority
- CN
- China
- Prior art keywords
- wing
- aircraft
- annular
- annular arrangement
- air
- 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
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model relates to an aircraft which can take off and land vertically and which caused no impact to a landing ground during taking off and landing. According to the annular-wing aircraft, an engine is arranged in the inner circle of the annular wing. An air inlet of the engine is connected with an air inlet pipe on the lower part of the annular wing. An air outlet of the engine is connected with a shunt cap on the upper part of the annular wing. The engine absorbs air from the air inlet pipe; the air is jet from the seam between the shunt cap and the inner circle of the annular wing; airflow pressure below the annular wing is larger than that above; with the great pressure difference, the annular-wing aircraft takes off; and the flight actions of the annular-wing aircraft are controlled by an adjusting wing on the outer circle of the annular-wing aircraft. An aircraft parachute is arranged in the shunt cap.
Description
Affiliated technical field
But the utility model relates to a kind of vertical takeoff and landing, can not give the aircraft of the impulsive force in landing ground when landing. with the aircraft parachute.
Background technology
At present, but the aircraft of known vertical takeoff and landing can give landing ground an impulsive force when landing, can cause certain harm to the personage on landing ground. there is not the aircraft parachute, and can the fast-descending fatal crass when aircraft aloft breaks down.
Summary of the invention
In order to overcome existing aircraft to the impulsive force in landing ground, the utility model provides a kind of aircraft, and this aircraft can not only vertical takeoff and landing, and can not give landing ground an impulsive force. also with the aircraft parachute.
The technical scheme that its technical matters that solves the utility model adopts is: straight wing is become the annular arrangement wing, annular arrangement wing inner circle is equipped with driving engine, engine inlet port links to each other with the air inlet pipe of ring air foil bottom, the driving engine air extractor duct links to each other with the shunting cap on annular arrangement wing top, driving engine is from the air inlet pipe air amount of annular arrangement wing bottom, pressure increased after air accelerated via driving engine, the air that pressure increases sprays from the slit of shunting cap and annular arrangement wing inner circle, final one continual air stream that forms, air-flow also can drive by viscous force the air movement of annular arrangement wing top simultaneously, according to Bernoulli's theorem, air-flow velocity is faster, the pressure that fluid produces is just less, the air-flow velocity of annular arrangement upper surface of the airfoil is just greater than the air-flow velocity of lower surface, so annular arrangement wing below stream pressure is just greater than the pressure of top air-flow, huge difference of pressure is by annular arrangement wing aircraft takeoff, then control the action of annular arrangement wing aircraft flight by the adjusting wing of annular arrangement wing cylindrical. annular arrangement wing aircraft is equipped with gyroscope, in the situation of not sending instruction, such as wind, if the direction of aircraft is inclined to one side, gyroscope can be experienced this skew, automatically send instruction to the adjusting wing of annular arrangement wing cylindrical, repair the direction of aircraft, guarantee that aircraft is all the time towards a direction.Operator's compartment and annular arrangement wing bottom, main cabin. the aircraft parachute is inner at shunting cap.
The beneficial effects of the utility model are, can vertical takeoff and landing, and can not give landing ground an impulsive force. can eject parachute aloft when aircraft breaks down and prevent the fatal crass.
Description of drawings
Fig. 1 is the utility model front elevation.
Fig. 2 is the I-I cutaway view of Fig. 1.
Fig. 3 is birds-eye view.
1. annular arrangement wings among the figure, 2. driving engine, 3. shunting cap, 4. the adjusting wing, 5. air inlet pipe, 6. operator's compartment and main cabin .7. wheel undercarriage.
The specific embodiment:
In Fig. 2, driving engine (2) can be selected jet engine or cyclone accelerator, driving engine (2) admission port links to each other with air inlet pipe (5), air inlet pipe (5) is overhead too not near in order to avoid the inspiration foreign matter. and air inlet pipe (5) has four or eight to be evenly distributed below annular arrangement wing (1). and driving engine (2) air extractor duct links to each other with shunting cap (3), regulating the wing (4) is by control the action of annular arrangement wing aircraft flight along middle shaft rotation. regulate the wing (4) axis and link to each other with annular arrangement wing (1), the adjusting wing (4) has eight or 16 or 32 to be evenly distributed at annular arrangement wing (1) cylindrical.
Claims (3)
1. the aircraft that wing is annular arrangement has driving engine in annular arrangement wing inner circle, it is characterized in that, engine inlet port links to each other with the air inlet pipe of ring air foil bottom, and the driving engine air extractor duct links to each other with the shunting cap on annular arrangement wing top.
2. aircraft according to claim 1 is characterized in that: regulating the wing is by controlling the action of annular arrangement wing aircraft flight along middle shaft rotation, regulating wing axis and link to each other with the annular arrangement wing.
3. aircraft according to claim 1 is characterized in that: the aircraft parachute is inner at shunting cap.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320087861 CN203255356U (en) | 2013-02-17 | 2013-02-17 | Annular-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320087861 CN203255356U (en) | 2013-02-17 | 2013-02-17 | Annular-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203255356U true CN203255356U (en) | 2013-10-30 |
Family
ID=49467944
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320087861 Expired - Fee Related CN203255356U (en) | 2013-02-17 | 2013-02-17 | Annular-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203255356U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108609183A (en) * | 2016-12-11 | 2018-10-02 | 梁韵琳 | Aerial spray |
-
2013
- 2013-02-17 CN CN 201320087861 patent/CN203255356U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108609183A (en) * | 2016-12-11 | 2018-10-02 | 梁韵琳 | Aerial spray |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101857085B (en) | Aircraft | |
| CN105083551B (en) | One kind can tiltrotor and its control method | |
| CN103935517B (en) | Aircraft | |
| CN205971844U (en) | Fixed wing aircraft vertical take -off auxiliary system | |
| CN109319110A (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN106864744A (en) | A kind of co-axial rotor variant vertically taking off and landing flyer | |
| CN103419933A (en) | Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices | |
| CN102837819A (en) | Wing surface increased flow short distance takeoff and landing carrier-based airplane | |
| WO2011041991A2 (en) | Aircraft using ducted fan for lift | |
| CN103057703A (en) | Dual-rotor coaxial helicopter with wing-shaped rotors | |
| CN101143622A (en) | Wingless air vehicle capable of vertical take-off and landing and its realizing method | |
| CN106114852A (en) | A kind of cross-arranging type dual-culvert vertical take-off and landing Spacecraft Attitude Control | |
| CN203255356U (en) | Annular-wing aircraft | |
| CN106081097A (en) | A kind of jet changement of aircraft | |
| CN103419935A (en) | Vertical take-off and landing aircraft in saucer-shaped arrangement and based on novel high-lift device | |
| CN105197234B (en) | A kind of compound aircraft with empennage | |
| CN202670093U (en) | Autogiro capable of taking off and landing vertically | |
| CN209225395U (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN105539816A (en) | Wing structure and propeller blade structure | |
| CN102785777A (en) | Hang glider device with cross-flow fan | |
| CN202481307U (en) | Four-propeller aircraft taking off and landing vertically | |
| CN206734629U (en) | A kind of disk aircraft | |
| RU121488U1 (en) | AIRCRAFT | |
| RU112153U1 (en) | AIRCRAFT | |
| CN105270622B (en) | A kind of compound wing aircraft in the band upper counterangle |
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: 20131030 Termination date: 20150217 |
|
| EXPY | Termination of patent right or utility model |