CN2440751Y - Sharp turning device for aircraft against collision - Google Patents
Sharp turning device for aircraft against collision Download PDFInfo
- Publication number
- CN2440751Y CN2440751Y CN 00244059 CN00244059U CN2440751Y CN 2440751 Y CN2440751 Y CN 2440751Y CN 00244059 CN00244059 CN 00244059 CN 00244059 U CN00244059 U CN 00244059U CN 2440751 Y CN2440751 Y CN 2440751Y
- Authority
- CN
- China
- Prior art keywords
- valve
- aircraft
- turning device
- spout
- high pressure
- 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
- 238000003915 air pollution Methods 0.000 abstract 1
- 238000011109 contamination Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
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- Actuator (AREA)
Abstract
The utility model relates to a sharp turning device for an aircraft against collision, which is composed of wings, a vertical rudder, a high-pressure air compressor, a valve, a spout, etc. When the aircraft needs sharp turn, the vertical rudder is combined, and an electric control valve is opened to complete the sharp turn. The utility model has maneuver, facility, convenience and small turning curvature radius. The air pollution is reduced.
Description
The utility model relates to the flexible sharply turning device of the aerial anticollision of aircraft.
It is to lean on the yaw rudder on wing and the vertical tail to finish that existing aircraft turns in the air.Fuselage standardized the very long radius of curvature of certain angle that will tilt just can be finished when aloft turning.Be dumb a large amount of oil plant that consumes again, cause unnecessary atmospheric contamination.
It is a kind of that the purpose of this utility model is to provide, the sharply turning device that the aerial anticollision of aircraft is flexible, the steering swivel system of incorporating aircraft into, the high pressure air that energized produces High-Pressure Compressor work, from the ejection of spout separately of front and back air receiver, utilize counter the doing of high pressure air ejection firmly to make the flexible reverses its direction of frame head and tail.Reduce the turning radius of the radian of aircraft, reduce the fuel consumption aerial contamination.
The utility model is made up of wing, vertical direction rudder, High-Pressure Compressor, gascollecting cap cylinder, electric control valve, high pressure spout.The aircraft steering swivel system is made of wing, vertical direction rudder.At the aeroplane nose afterbody gascollecting cap cylinder is installed respectively, the high pressure spout of an angle adjustable respectively is installed in the both sides of gascollecting cap cylinder, can make the aircraft vertical lift to 90 ° of angles of downward modulation.An electric control valve respectively is installed on each high pressure spout, valve with make in the cabin in about turn to knob connection, gascollecting cap cylinder is connected with High-Pressure Compressor by pipeline.The energized compressor operating is pressed into high pressure air in the gascollecting cap cylinder, and the bonding position rudder is opened and turned to knob during turning.
The utility model compared with the prior art, orphan's degree radius is little when having aerial sharply turning, maneuverability is convenient, simple to operate, reduces the fuel consumption aerial contamination.
Accompanying drawing: the utility model structural representation.
[1] gascollecting cap cylinder before and after, [2] High-Pressure Compressor, [3] high pressure spout, [4] preceding left electric control valve, [5] preceding right electric control valve, the left electric control valve in [6] back, the right electric control valve in [7] back, [8] left steering knob, [9] right steering knob, [10] wing, [11] vertical direction rudder.
Preferred embodiment of the utility model is realized by following method, wing [10], vertical direction rudder [11] is a conventional device in the aircraft, in this system, a gascollecting cap cylinder [1] respectively is installed before and after the aircraft, in air receiver [1], both sides the high pressure spout [3] of an adjustable angle respectively is installed, locate respectively to install an electric control valve [4] at spout [3], valve [5], valve [6], valve [7].Electric control valve [4], valve [7] are connected with right steering knob [9], valve [5], and valve [6] is connected with left steering knob [8], and front and back gascollecting cap cylinder [1] is connected with High-Pressure Compressor [2] through pipeline, and the pressure power switch of High-Pressure Compressor [2] is connected with power supply.Start the aero-engine power supply during operation by the power supply pressure switch combination on the High-Pressure Compressor [2], gascollecting cap cylinder [1] was interior when reaching certain pressure before and after the high pressure air that compressor operating produces was pressed into by pipeline, and pressure switch is cut off the power supply automatically.Turn to knob [8] in conjunction with rudder of aircraft [11], left steering unlatching when turning to, high pressure air is through valve [5], and valve [6] is from spout [3] ejection, and right steering is opened and turned to knob [9], and high pressure air is through valve [4], and valve [7] sprays from spout [3].
Also available aero-engine directly drives high pressure air that High-Pressure Compressor work produces through pressure clutch and is pressed into and finishes aircraft in the air receiver and turn in the air.
Claims (2)
1, the flexible sharply turning device of the aerial anticollision of a kind of aircraft, by the steering swivel system that wing, vertical direction rudder constitute, it is characterized in that in steering swivel system, being provided with gascollecting cap cylinder [1], High-Pressure Compressor [2], high pressure spout [3], electric control valve [4], valve [5], valve [6], valve [7].
2, device according to claim 1 is characterized in that high pressure spout [3] can adjust 90 ° downwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00244059 CN2440751Y (en) | 2000-08-04 | 2000-08-04 | Sharp turning device for aircraft against collision |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 00244059 CN2440751Y (en) | 2000-08-04 | 2000-08-04 | Sharp turning device for aircraft against collision |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2440751Y true CN2440751Y (en) | 2001-08-01 |
Family
ID=33603819
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 00244059 Expired - Fee Related CN2440751Y (en) | 2000-08-04 | 2000-08-04 | Sharp turning device for aircraft against collision |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2440751Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102167162A (en) * | 2011-03-10 | 2011-08-31 | 洪瑞庆 | Ultra-high pressure fluid jetting power track transferring system and method for aircraft |
-
2000
- 2000-08-04 CN CN 00244059 patent/CN2440751Y/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102167162A (en) * | 2011-03-10 | 2011-08-31 | 洪瑞庆 | Ultra-high pressure fluid jetting power track transferring system and method for aircraft |
| WO2012119468A1 (en) * | 2011-03-10 | 2012-09-13 | Hong Ruiqing | Track changing system and method using ultra-high pressure fluid jet power for aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |