CN106347633A - Design method of trailing edge flap rocking-arm type motion - Google Patents
Design method of trailing edge flap rocking-arm type motion Download PDFInfo
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- CN106347633A CN106347633A CN201610843971.1A CN201610843971A CN106347633A CN 106347633 A CN106347633 A CN 106347633A CN 201610843971 A CN201610843971 A CN 201610843971A CN 106347633 A CN106347633 A CN 106347633A
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- trailing edge
- flap
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- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Escalators And Moving Walkways (AREA)
- Valve-Gear Or Valve Arrangements (AREA)
Abstract
The invention provides a design method of trailing edge flap rocking-arm type motion. A point and a straight line segment with variable parameters are used; a three-point circle making method is adopted to design a double-rocking-arm rotation way scheme; and the design of a trailing edge flap motion mechanism with a large retreating amount is realized. The design method is simple and easy in operation; a formed motion scheme has a simple actuation form and a simple structure and is safe and reliable in work, and the problems of abrasion, clamping stagnation and the like can be avoided. The design method of the trailing edge flap rocking-arm type motion is suitable for designing the trailing edge flap type motion with the large retreating amount.
Description
Technical field
The invention belongs to technical field of aircraft design is and in particular to a kind of trailing edge flap rocker-arm motion mechanism design.
Background technology
Trailing edge flap is to take off/one of landing configuration lower wing lift coefficient movable rudder face for improving, in trailing edge
In wing flap design process, it is typically based on the taking off of aircraft, landing data requires, the design object determining high lift device is (as maximum
Lift coefficient increment), and then determine the form of high lift device, flat shape etc., then carry out two-dimentional wing flap design, determine outside wing flap
The location parameters such as Xing Jifeng road amount, lap, deflection angle.
The motion principle of trailing edge flap designs the seam road amount determining, lap, deflection angle etc. generally according to two-dimentional wing flap
Location parameter is designed for target location, and conventional trailing edge flap forms of motion has hinge type, four link type, slide rail-pulley
Posture etc..For big back amount trailing edge flap, hinge type and four link type forms of motion are relatively difficult to ensure card trailing edge flap seam road amount, weight
The folded key parameter such as amount, deflection angle is it is impossible to realize two-dimensional design target；And four link type and slide rail-pulley posture motion rail
The selection of mark is more complicated, and the problems such as clamping stagnation, abrasion easily.The big retrusive trailing edge flap motion principle scheme of single seam sets at present
Timing, generally requires to expend considerable time and effort, and the motion principle being formed often results in motion and start form is multiple
Miscellaneous, motion bump height is big, easily clamping stagnation the problems such as wear and tear.
Content of the invention
To be solved by this invention is that existing trailing edge flap motion bump height the technology that clamping stagnation weares and teares greatly, easily
Problem, is provided a kind of trailing edge flap rocker-arm motion mechanism design, its motion and start form simple, is rotated by rocking arm
Realize flap kinematics, safe and reliable, be not in abrasion and the problems such as clamping stagnation.
In order to solve the technical problem of the present invention, the present invention is achieved by the following technical solutions: a kind of trailing edge flap
Rocker-arm motion mechanism design, comprises the following steps:
The first step: determine trailing edge flap initial/two-dimensional position parameter of taking off/land, the road containing seam amount, lap, deflection angle
Location parameter.
Second step: according to trailing edge flap initial/two-dimensional position parameter of taking off/land, in wing flap leading edge lower surface apart from the flap
The position of nose of wing x1 chooses an adjustable point respectively.
3rd step: the point according to selected by second step, draw an equal length straight line perpendicular to following table surface curve respectively
Section.
4th step: determine and drive rocking arm scheme, three end points of the three articles of straightways being determined by the 3rd step determine one
Circle, is determined that the center of circle of circle is the center of rotation of driving rocking arm, determined by the center of circle and trailing edge flap initial position straightway
The line of end points is and drives rocking arm scheme.
5th step: according to initial/two-dimensional position parameter of taking off/land, in wing flap trailing edge lower surface apart from wing flap trailing edge l2
Position choose an adjustable point respectively.
6th step: the point according to selected by the 5th step, draw an equal length straight line perpendicular to following table surface curve respectively
Section.
7th step: determine from motion rocker arm scheme, three end points of the three articles of straightways being determined by the 6th step determine one
Circle, the center of circle being determined circle as from the center of rotation of motion rocker arm, determined by the center of circle and trailing edge flap initial position straightway
The line of end points is from motion rocker arm scheme.
Preferably, in described second step x1 span be 1% ~ 5% wing flap relative to chord length.
Preferably, in described 5th step l2 span be 5% ~ 10% wing flap relative to chord length.
Preferably, drive rocking arm center of rotation in described 4th step near flap lower surface, including the position to selected point
Put and the length of straightway is adjusted, make the step that wing flap bulge minimizes, realize optimum aeroperformance.
Preferably, in described 7th step from motion rocker arm center of rotation near flap lower surface, including the position to selected point
Put and the length of straightway is adjusted, make the step that wing flap bulge minimizes, realize optimum aeroperformance.
Compared with prior art, the beneficial effect that the present invention obtains is:
A kind of trailing edge flap rocker-arm motion mechanism design disclosed by the invention, by using point and the straightway of variable ginseng, adopts
Make circule method with 3 points, the double rocking arm rotation mode scheme of design, realize the design of big back amount trailing edge flap motion, design side
Method is simple, easy to operate；The motion scheme start form being formed and mechanism are simple, safe and reliable, are not in abrasion and card
Stagnant the problems such as.A kind of trailing edge flap rocker-arm motion mechanism design disclosed by the invention is it is adaptable to flap kinematics after big back amount
Design.
Brief description
Fig. 1 be trailing edge flap initial/take off/land two-dimensional position schematic diagram.
Fig. 2 is adjustable point and straightway schematic diagram at trailing edge flap leading edge lower surface.
Fig. 3 is to drive rocking arm center of rotation and rocking arm scheme schematic diagram.
Fig. 4 is adjustable point and straightway at trailing edge flap trailing edge lower surface.
Fig. 5 is from motion rocker arm center of rotation and rocking arm scheme schematic diagram.
Fig. 6 is the double rocker-arm motion principle figure of trailing edge flap.
Specific embodiments
Below in conjunction with the accompanying drawings, embodiment is described in detail.
Referring to accompanying drawing 1 to accompanying drawing 6, a kind of trailing edge flap rocker-arm motion mechanism design, comprise the steps:
The first step: determine initial (a)/(c) two-dimensional position parameter of taking off (b)/lands of trailing edge flap, the amount of the road containing seam, lap, inclined
The location parameter of gyration.
Second step, according to trailing edge flap initial/two-dimensional position parameter of taking off/land, in wing flap leading edge lower surface apart from the flap
The position of nose of wing x1, defines one adjustable point d, d1, d2 respectively.
3rd step, the point according to selected by second step, draw one respectively perpendicular to the equal length l1's of following table surface curve
Straightway, determines three end points e, e1, e2.
4th step, determines and drives rocking arm scheme, three end points e, e1, e2 of the three articles of straightways determining by the 3rd step are true
A fixed circle 1, is determined that the center of circle o1 of circle 1 is the center of rotation of driving rocking arm, determined by the beginning of center of circle o1 and trailing edge flap
The line of beginning position straightway end points e, e1, e2 is and drives rocking arm scheme.
5th step, according to initial (a)/(c) two-dimensional position parameter of taking off (b)/land, in wing flap trailing edge lower surface apart from the flap
Wing trailing edge l2 chooses adjustable point f, f1, a f2 in position respectively.
6th step, the point according to selected by the 5th step, drawing one respectively perpendicular to lower surface length of a curve is x2's
Straightway, determines three end points g, g1, g2.
7th step, determines from motion rocker arm scheme, three end points g, g1, g2 of the three articles of straightways determining by the 6th step are true
A fixed circle 2, is determined that the center of circle o2 of circle 2 is the center of rotation from motion rocker arm, determined by the beginning of center of circle o2 and trailing edge flap
The line of beginning position straightway end points g, g1, g2 is from motion rocker arm scheme.
Further, in described second step, the span of x1 is 1% ~ 5% wing flap relative to chord length.
Further, in described 5th step, the span of l2 is 5% ~ 10% wing flap relative to chord length.
Further, in described 4th step drive rocking arm center of rotation from flap lower surface try one's best close to, including by size
X1 point of adjustment d, d1, the position of d2 and the position optimizing end points e, e1, e2 by length l1 adjusting straightway, make wing flap bulge
The step minimizing, preferably suitably drives rocking arm center of rotation and rocking arm scheme, realizes optimum aeroperformance.
Further, in described 7th step close to motion rocker arm center of rotation is tried one's best from flap lower surface, including by adjustment
Size l2 point of adjustment f, f1, the position of f2 and the position optimizing end points g, g1, g2 by length x2 adjusting straightway, make wing flap
The step that bulge minimizes, preferably suitably from motion rocker arm center of rotation and rocking arm scheme, realizes optimum aeroperformance.
By above method, can quickly determine the motion principle scheme of big back amount trailing edge flap, method for designing letter
Single, easy to operate；The motion scheme start form being formed is simple, safe and reliable, the problems such as be not in abrasion and clamping stagnation.
Listed above is only one of specific embodiment of the present invention.It is clear that the invention is not restricted to above example, also may be used
There to be many similar reshapings.Those of ordinary skill in the art can directly derive from present disclosure or associate
All deformation, are all considered as invention which is intended to be protected.
Claims (5)
1. a kind of trailing edge flap rocker-arm motion mechanism design it is characterised in that: comprise the following steps:
The first step: determine trailing edge flap initial/two-dimensional position parameter of taking off/land, the road containing seam amount, lap, deflection angle
Location parameter；
Second step: according to trailing edge flap initial/two-dimensional position parameter of taking off/land, in wing flap leading edge lower surface before wing flap
The position of edge x1 chooses an adjustable point respectively；
3rd step: the point according to selected by second step, draw an equal length straightway perpendicular to following table surface curve respectively；
4th step: determine and drive rocking arm scheme, three end points of the three articles of straightways being determined by the 3rd step determine a circle, institute
Determine that the center of circle of circle is the center of rotation driving rocking arm, determined by the center of circle and trailing edge flap initial position straightway end points
Line is and drives rocking arm scheme；
5th step: according to initial/two-dimensional position parameter of taking off/land, in wing flap trailing edge lower surface apart from the position of wing flap trailing edge l2
Put one adjustable point of selection respectively；
6th step: the point according to selected by the 5th step, draw an equal length straightway perpendicular to following table surface curve respectively；
7th step: determine from motion rocker arm scheme, three end points of the three articles of straightways being determined by the 6th step determine a circle, institute
Determine that the center of circle of circle is from the center of rotation of motion rocker arm, determined by the center of circle and trailing edge flap initial position straightway end points
Line is from motion rocker arm scheme.
2. as claimed in claim 1 a kind of trailing edge flap rocker-arm motion mechanism design it is characterised in that: in described second step
The wing flap for 1% ~ 5% for the span of x1 is relative to chord length.
3. as claimed in claim 1 a kind of trailing edge flap rocker-arm motion mechanism design it is characterised in that: in described 5th step
The wing flap for 5% ~ 10% for the span of l2 is relative to chord length.
4. as claimed in claim 1 a kind of trailing edge flap rocker-arm motion mechanism design it is characterised in that: in described 4th step
Drive rocking arm center of rotation near flap lower surface, be adjusted including to the selected position of point and the length of straightway, make
The step that wing flap bulge minimizes.
5. as claimed in claim 1 a kind of trailing edge flap rocker-arm motion mechanism design it is characterised in that: in described 7th step
From motion rocker arm center of rotation near flap lower surface, it is adjusted including to the selected position of point and the length of straightway, makes
The step that wing flap bulge minimizes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610843971.1A CN106347633B (en) | 2016-09-23 | 2016-09-23 | A kind of trailing edge flap rocker-arm motion mechanism design |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610843971.1A CN106347633B (en) | 2016-09-23 | 2016-09-23 | A kind of trailing edge flap rocker-arm motion mechanism design |
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| Publication Number | Publication Date |
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| CN106347633A true CN106347633A (en) | 2017-01-25 |
| CN106347633B CN106347633B (en) | 2019-03-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610843971.1A Active CN106347633B (en) | 2016-09-23 | 2016-09-23 | A kind of trailing edge flap rocker-arm motion mechanism design |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600389A (en) * | 2017-09-04 | 2018-01-19 | 江西洪都航空工业集团有限责任公司 | A kind of slide guide posture trailing edge flap movement technique |
| CN114228977A (en) * | 2021-11-23 | 2022-03-25 | 北京航空航天大学 | Movement form of trailing edge flap with large deviation degree along airflow |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2620147A (en) * | 1950-05-31 | 1952-12-02 | Boeing Co | Airplane flap control mechanism |
| CN102642615A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane high lift device with single slotted flaps |
| CN102781775A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | A high lift system for an aircraft |
| CN102791574A (en) * | 2009-11-13 | 2012-11-21 | 空中客车运作有限责任公司 | Flap adjusting system of an aircraft with a regulating flap |
-
2016
- 2016-09-23 CN CN201610843971.1A patent/CN106347633B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2620147A (en) * | 1950-05-31 | 1952-12-02 | Boeing Co | Airplane flap control mechanism |
| CN102791574A (en) * | 2009-11-13 | 2012-11-21 | 空中客车运作有限责任公司 | Flap adjusting system of an aircraft with a regulating flap |
| CN102781775A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | A high lift system for an aircraft |
| CN102642615A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane high lift device with single slotted flaps |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107600389A (en) * | 2017-09-04 | 2018-01-19 | 江西洪都航空工业集团有限责任公司 | A kind of slide guide posture trailing edge flap movement technique |
| CN107600389B (en) * | 2017-09-04 | 2020-05-08 | 江西洪都航空工业集团有限责任公司 | Method for moving trailing edge flap of guide sliding frame |
| CN114228977A (en) * | 2021-11-23 | 2022-03-25 | 北京航空航天大学 | Movement form of trailing edge flap with large deviation degree along airflow |
| CN114228977B (en) * | 2021-11-23 | 2023-06-13 | 北京航空航天大学 | Method for designing motion form of downstream large-deflection trailing edge flap |
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| Publication number | Publication date |
|---|---|
| CN106347633B (en) | 2019-03-29 |
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