CN108791815A - It is a kind of to prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea - Google Patents
It is a kind of to prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea Download PDFInfo
- Publication number
- CN108791815A CN108791815A CN201810658621.7A CN201810658621A CN108791815A CN 108791815 A CN108791815 A CN 108791815A CN 201810658621 A CN201810658621 A CN 201810658621A CN 108791815 A CN108791815 A CN 108791815A
- Authority
- CN
- China
- Prior art keywords
- plate
- wing
- flatland
- stretch
- control
- 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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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea is prevented the invention discloses a kind of, the device is located at the position of aircraft wing droope snoot, the device includes plate windward, leeward plate, lift aerofoil, leeward plate is flexibly connected the lower section for being located at wing one end with the formation certain angle of plate windward and wing is affixed, lift aerofoil be located at wing the other end lower section and wing it is affixed, the apparatus structure is simple, can avoid nose heave tail light when aircraft is out of control, stretch of flatland in a hilly area sea is hit, serious air crash is avoided.
Description
Technical field
It is specifically a kind of to prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea the present invention relates to vehicle technology field.
Background technology
Currently, aircraft, in the air in flight course, aircraft engine goes wrong or encounters other accidents or meets bad weather
When, it is out of control to be easy to cause aircraft, causes light after weight before aircraft, lift not rise head, and it is extra large to hit a stretch of flatland in a hilly area, causes air crash.
Invention content
Prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the device from can fly the purpose of the present invention is to provide a kind of
It avoids nose heave tail light when machine is out of control, hits stretch of flatland in a hilly area sea, avoid serious air crash.
Realizing the technical solution of the object of the invention is：
It is a kind of that the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the device is prevented to be located at the position of aircraft wing droope snoot, the dress
It sets including plate windward, leeward plate, lift aerofoil, leeward plate is flexibly connected with the formation certain angle of plate windward and is located under wing one end
Side it is affixed with wing, lift aerofoil be located at wing the other end lower section and wing it is affixed.
The angle of the plate windward and wing is 20-30 °.
The angle of the lift aerofoil and wing is 30-45 °.
The vertical height of the plate windward and leeward plate is 20-30cm.
The leeward plate controls leeward plate and the windward angle between plate by air pump, and air pump is the prior art, described
Air pump is connect with two pistons respectively, and two pistons are connect by connecting rod with leeward plate, living by air pump control by two pistons
Controls connecting rod is filled in, and then controls the locking and expansion of leeward plate.
Plate windward, leeward plate and the lift aerofoil, is manufactured using high temperature resistant, anti-freeze composite material.
It is provided by the invention it is a kind of preventing the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the apparatus structure is simple, Ke Yi
It avoids nose heave tail light when aircraft is out of control, hits stretch of flatland in a hilly area sea, avoid serious air crash.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram preventing the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea；
Fig. 2 is a kind of schematic diagram when preventing the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea leeward plate opening；
Fig. 3 preventing the schematic diagram of the Aircraft Air device installation out of control for hitting stretch of flatland in a hilly area sea aboard to be a kind of；
In figure, 1. lift 2. wings 3. of aerofoil, 4. leeward plate of plate, 5. piston, 6. air pump, 7. connecting rod windward.
Specific implementation mode
The present invention is further elaborated with reference to the accompanying drawings and examples, but is not limitation of the invention.
Embodiment：
：
It is a kind of that the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the device is prevented to be located at the position of aircraft wing droope snoot, instead of
The wing flap of aircraft, the device include that plate 3, leeward plate 4, lift aerofoil 1, leeward plate 4 form certain angle with plate 3 windward and live windward
Dynamic connect is located at that the lower section of 2 one end of wing is affixed with wing 2, and lift aerofoil 1 is located at the lower section of the other end of wing 2 and wing 2 is consolidated
It connects.
The angle of the plate windward 3 and wing 2 is 25 °.
The angle of the lift aerofoil 1 and wing 3 is 35 °.
The vertical height of the plate windward 3 and leeward plate 4 is 30cm.
Plate windward 3, leeward plate 4 and the lift aerofoil 1, is manufactured using high temperature resistant, anti-freeze composite material.
The leeward plate 4 is controlled the angle between leeward plate 4 and windward plate 3 by air pump 6, the air pump 6 respectively with
Two piston-cylinders 5 connect, and two piston-cylinders 5 are connect by connecting rod 7 with leeward plate 4, are controlled by two pistons by air pump 6
Cylinder 5,5 controls connecting rod 7 of piston-cylinder, and then the locking and expansion of leeward plate 4 are controlled, air pump 6 and piston-cylinder 5 are existing skill
Art.In use, right angle setting piston-cylinder, one end of connecting rod connects leeward plate, and small end connects piston-cylinder, normal flight
When, leeward plate is locked connecting rod lower end by piston-cylinder, and leeward plate is in up-side down triangle with plate windward, when aircraft is out of control, piston
Cylinder charge is opened leeward plate by connecting rod, and leeward plate is the straight angle with plate windward, after lifting that aircraft is flat and flying, piston-cylinder fortune
It is dynamic that leeward plate and plate windward are formed by up-side down triangle by connecting rod, become normal condition, lands a plane safely.
The present invention operation principle be：When aircraft normal flight, the angle between plate 3 and leeward plate 4 is obtuse angle, gas windward
After stream flows through plate 3 windward, rise suddenly along leeward plate 4, to aircraft with lifting force；It, will plate 3 windward by piston 5 when aircraft is out of control
Angle between leeward plate 4 is adjusted to the straight angle, and plate 3 and leeward plate 4 and 2 wing chord of wing are in 25 degree windward, and air-flow is to plate windward
Reaction lifting force is generated, plane nose is lifted, compels to be down to other safer places, avoids serious air crash.
Air pump 6 is on wingbar, and 6 tracheae of air pump inflates position at the connecting rod of piston-cylinder lower end, and gas up fills, lock piston
Tight leeward plate, makes leeward plate and the obtuse-angulate up-side down triangle of plate shape windward.
Claims (5)
1. a kind of prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the device to be located at the position of aircraft wing droope snoot,
It is characterized in that, which includes that plate, leeward plate, lift aerofoil, leeward plate are flexibly connected with the formation certain angle of plate windward and set windward
It is affixed in the lower section of wing one end and wing, lift aerofoil be located at wing the other end lower section and wing it is affixed.
2. a kind of the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea is prevented according to claim 1, which is characterized in that described
The angle of plate and rotor beam is 20-30 ° windward.
3. it is according to claim 1 it is a kind of prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the lift aerofoil and rotation
The angle of spar is 30-45 °.
4. it is according to claim 1 it is a kind of prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the leeward plate hangs down
Straight height is 30cm.
5. it is according to claim 1 it is a kind of preventing the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea, the leeward plate is by gas
Pump controls leeward plate and the windward angle between plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810658621.7A CN108791815A (en) | 2018-06-25 | 2018-06-25 | It is a kind of to prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810658621.7A CN108791815A (en) | 2018-06-25 | 2018-06-25 | It is a kind of to prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108791815A true CN108791815A (en) | 2018-11-13 |
Family
ID=64085070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810658621.7A Pending CN108791815A (en) | 2018-06-25 | 2018-06-25 | It is a kind of to prevent the Aircraft Air device out of control for hitting stretch of flatland in a hilly area sea |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108791815A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1267989B (en) * | 1964-11-12 | 1968-05-09 | Boeing Co | Aircraft wing with improved characteristics of stalling at cruising speed |
| GB9122225D0 (en) * | 1991-10-19 | 1991-12-04 | British Aerospace | An aircraft wing leading edge arrangement |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| CN101466597A (en) * | 2006-06-14 | 2009-06-24 | 波音公司 | Link mechanisms for gapped rigid Krueger flaps, and associated systems and methods |
| CN103863556A (en) * | 2014-02-25 | 2014-06-18 | 李竟儒 | Device for preventing out-of-control aircraft in air from mountain collision and ocean crash |
-
2018
- 2018-06-25 CN CN201810658621.7A patent/CN108791815A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1267989B (en) * | 1964-11-12 | 1968-05-09 | Boeing Co | Aircraft wing with improved characteristics of stalling at cruising speed |
| GB9122225D0 (en) * | 1991-10-19 | 1991-12-04 | British Aerospace | An aircraft wing leading edge arrangement |
| WO2007117260A2 (en) * | 2005-07-27 | 2007-10-18 | University Of Southern California | Aircraft with belly flaps |
| CN101466597A (en) * | 2006-06-14 | 2009-06-24 | 波音公司 | Link mechanisms for gapped rigid Krueger flaps, and associated systems and methods |
| CN103863556A (en) * | 2014-02-25 | 2014-06-18 | 李竟儒 | Device for preventing out-of-control aircraft in air from mountain collision and ocean crash |
| CN104590549A (en) * | 2014-02-25 | 2015-05-06 | 李竟儒 | Device capable of preventing aircraft out of control from colliding mountains and flying toward oceans in air |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181113 |