CN106741855A - A kind of aircraft lift-rising contracting is away from device - Google Patents
A kind of aircraft lift-rising contracting is away from device Download PDFInfo
- Publication number
- CN106741855A CN106741855A CN201510825312.0A CN201510825312A CN106741855A CN 106741855 A CN106741855 A CN 106741855A CN 201510825312 A CN201510825312 A CN 201510825312A CN 106741855 A CN106741855 A CN 106741855A
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- CN
- China
- Prior art keywords
- robe
- wing
- aircraft
- away
- rising
- 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
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/26—Transmitting means without power amplification or where power amplification is irrelevant
- B64C13/28—Transmitting means without power amplification or where power amplification is irrelevant mechanical
- B64C13/30—Transmitting means without power amplification or where power amplification is irrelevant mechanical using cable, chain, or rod mechanisms
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Traffic Control Systems (AREA)
Abstract
The invention discloses a kind of contracting of aircraft lift-rising away from device, including deflector, the back of robe, back of robe guide rail, operating bar, joining beam, wing, drive device and transmission device, wing is integrally connected with airframe, the back of robe is connected by back of robe guide rail with wing, drive device is arranged on inside wing, joining beam one end is connected the other end and is connected with deflector with drive device, and transmission device is arranged on inside wing, and operating bar one end is connected the other end and is connected with the back of robe with transmission device.The present invention can simultaneously realize aircraft in takeoff phase and landing glide stage lift-rising, and liter is broken when the stage is alightinged run and increases resistance, so as to shorten the take-off and landing ground run distance of aircraft.And effect is good, low cost is easy to implement, applied widely, away from there is larger practical value.
Description
Technical field
The present invention relates to the takeoff and landing performance engineering device technique field of aircraft, more particularly to a kind of contracting of aircraft lift-rising is away from device.
Background technology
Aircraft wing is to provide lift source necessary to aircraft flight, and the wing flap on wing is to provide lift when taking off and the offer drag reduction coasting distance that lands.The wing flap of current aircraft is the simple function of putting down or its lift or resistance are realized on receiving, as technical merit is continued to develop, aeroplane performance is constantly lifted, and its every flight index request is also on the increase, and current flap configurations have been difficult to meet the contracting of aircraft lift-rising away from requiring.
The content of the invention
In order to solve the above technical problems, the invention provides a kind of contracting of aircraft lift-rising away from device, the device may be implemented in the broken liter in the stage of alightinging run and increase resistance, so as to shorten take-off and landing ground run distance while realizing taking off with landing glide stage lift-rising.
A kind of aircraft lift-rising contracting is away from device, including deflector, the back of robe, back of robe guide rail, operating bar, joining beam, wing, drive device and transmission device, wing is integrally connected with airframe, the back of robe is connected by back of robe guide rail with wing, drive device is arranged on inside wing, joining beam one end is connected the other end and is connected with deflector with drive device, and transmission device is arranged on inside wing, and operating bar one end is connected the other end and is connected with the back of robe with transmission device.
Further, drive device of the above-mentioned aircraft lift-rising contracting away from device is motor or hydraulic motor.
By above-mentioned technological means the present invention obtain Advantageous Effects be：The present invention can simultaneously realize aircraft in takeoff phase and landing glide stage lift-rising, and liter is broken when the stage is alightinged run and increases resistance, so as to shorten the take-off and landing ground run distance of aircraft.And effect is good, low cost is easy to implement, applied widely, away from there is larger practical value.
Brief description of the drawings
Fig. 1 is structural representation of the invention.
Fig. 2 is top view of the invention.
In figure：1st, deflector；2nd, the back of robe；3rd, back of robe guide rail；4th, push rod；5th, joining beam；6th, wing.
Specific embodiment
Principle of the invention and feature are described below in conjunction with accompanying drawing, example is served only for explaining invention, is not intended to limit the scope of the present invention.
A kind of aircraft lift-rising contracting is away from device, including deflector 1, the back of robe 2, back of robe guide rail 3, operating bar 4, joining beam 5, wing 6, drive device and transmission device, wing 6 is overall to be connected with airframe, the back of robe 2 is connected by back of robe guide rail 3 with wing 6, drive device is arranged on inside wing 6, the one end of joining beam 5 is connected the other end with drive device and is connected with deflector 1, and transmission device is arranged on inside wing 6, and the one end of operating bar 4 is connected the other end with transmission device and is connected with the back of robe 2.
To make the aircraft lift-rising contract away from device power diversification, its flexibility is improved, drive device is motor or hydraulic motor.
Deflector 1 can be connected by joining beam with the transmission device being fixed on wing and drive device, or the transmission device directly passed through on deflector rotating shaft position is connected with drive device, realizes the deflection up and down around deflector rotating shaft.The back of robe 2 operating bar push or pull on effect under along back of robe guide rail move, realize the deflection and movement of the back of robe 2.Operating bar 4 is connected by the transmission device being fixed on wing with drive device.The drive device refers to motor or hydraulic motor.The transmission device refers to gear, transmission rod, steering mechanism.
In the air during flight, deflector 1, the back of robe 2 are received and above fitted with wing, form baseline airfoil, and acquisition most preferably rises resistive energy.
In takeoff phase and landing glide stage, the back of robe 2 is retreated and deflected down, and deflector 1 is deflected down, and has gap between the back of robe 2, using wing lower aerofoil air-flow from gap to the ejector action of the upper surface air-flow of the back of robe 2 and the guide functions to upper surface of the airfoil air-flow, the lift-rising effect of the back of robe 2 is improved.
In the stage of alightinging run, deflector 1 is put by the lower off normal in landing glide stage and deflects upward into wing top, make to form larger space between deflector 1 and the back of robe 2 and pressure release, lift is greatly lowered and causes the ground friction resistance to increase, other deflector is upward deflected and also make the total aerodynamic drag increase of aircraft, so as to shorten ground run distance.
Fowler flap is a kind of trailing edge high lift device being widely used, and it is made up of the back of robe and the back of robe cabin that is fixed on wing retreated while deflection again, with simple structure and the characteristics of good lift-rising effect.The present invention is changed to movable deflector by by fixed back of robe cabin, take-off and landing glides the stage, under deflector partially, lift-rising effect can be further enhanced, in the stage of alightinging run, on deflector partially, big gap is formed between deflector and the back of robe makes wing lower surface pressure release subtract liter, increases wheel adhesive force, so as to increase frictional resistance, deflector is upward deflected and also make the total aerodynamic drag increase of aircraft, plays a part of deceleration device.
Above-mentioned technical proposal only embodies the optimal technical scheme of technical solution of the present invention, and those skilled in the art's some that to be made to some of which part variations embody principle of the invention, belong within protection scope of the present invention.
Claims (2)
1. a kind of aircraft lift-rising contracting is away from device, it is characterised in that：Described device includes deflector（1）, the back of robe（2）, back of robe guide rail（3）, operating bar（4）, joining beam（5）, wing（6）, drive device and transmission device, the wing（6）It is overall to be connected with airframe, the back of robe（2）By back of robe guide rail（3）With wing（6）Connection, the drive device is arranged on wing（6）Inside, the joining beam（5）One end is connected the other end and deflector with drive device（1）Connection, the transmission device is arranged on wing（6）Inside, the operating bar（4）One end is connected the other end and the back of robe with transmission device（2）Connection.
2. aircraft lift-rising contracting according to claim 1 is away from device, it is characterised in that：The drive device is motor or hydraulic motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510825312.0A CN106741855A (en) | 2015-11-24 | 2015-11-24 | A kind of aircraft lift-rising contracting is away from device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510825312.0A CN106741855A (en) | 2015-11-24 | 2015-11-24 | A kind of aircraft lift-rising contracting is away from device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741855A true CN106741855A (en) | 2017-05-31 |
Family
ID=58964623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510825312.0A Pending CN106741855A (en) | 2015-11-24 | 2015-11-24 | A kind of aircraft lift-rising contracting is away from device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741855A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2791385A (en) * | 1952-03-10 | 1957-05-07 | Lockheed Aircraft Corp | Landing drag flap and lift spoiler |
| CN101959754A (en) * | 2007-08-06 | 2011-01-26 | 空中客车营运有限公司 | High lift system for an aircraft |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| CN102114911A (en) * | 2011-01-18 | 2011-07-06 | 北京航空航天大学 | Pulley type structure high lift device for dual-arc sliding rail |
| EP2690006A2 (en) * | 2005-11-21 | 2014-01-29 | The Boeing Company | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
| CN103847956A (en) * | 2012-11-29 | 2014-06-11 | 波音公司 | Hinged Panel Operation Systems and Methods |
-
2015
- 2015-11-24 CN CN201510825312.0A patent/CN106741855A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2791385A (en) * | 1952-03-10 | 1957-05-07 | Lockheed Aircraft Corp | Landing drag flap and lift spoiler |
| EP2690006A2 (en) * | 2005-11-21 | 2014-01-29 | The Boeing Company | Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods |
| CN101959754A (en) * | 2007-08-06 | 2011-01-26 | 空中客车营运有限公司 | High lift system for an aircraft |
| CN102040002A (en) * | 2010-12-02 | 2011-05-04 | 北京航空航天大学 | Curve slide-connecting rod mechanism in high lift device of large aircraft |
| CN102114911A (en) * | 2011-01-18 | 2011-07-06 | 北京航空航天大学 | Pulley type structure high lift device for dual-arc sliding rail |
| CN103847956A (en) * | 2012-11-29 | 2014-06-11 | 波音公司 | Hinged Panel Operation Systems and Methods |
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Legal Events
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170531 |