CN106347633B - A kind of trailing edge flap rocker-arm motion mechanism design - Google Patents
A kind of trailing edge flap rocker-arm motion mechanism design Download PDFInfo
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- CN106347633B CN106347633B CN201610843971.1A CN201610843971A CN106347633B CN 106347633 B CN106347633 B CN 106347633B CN 201610843971 A CN201610843971 A CN 201610843971A CN 106347633 B CN106347633 B CN 106347633B
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- flap
- trailing edge
- circle
- rocker arm
- rocker
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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)
- Valve-Gear Or Valve Arrangements (AREA)
- Escalators And Moving Walkways (AREA)
Abstract
A kind of trailing edge flap rocker-arm motion mechanism design provided by the invention makees circule method using 3 points by the point and straightway using variable ginseng, design double rocker arm rotation mode schemes, realize the design of big back amount trailing edge flap movement mechanism, design method is simple, easy to operate；The problems such as motion scheme actuation form and mechanism of formation are simple, safe and reliable, are not in abrasion and clamping stagnation.A kind of trailing edge flap rocker-arm motion mechanism design disclosed by the invention, the design suitable for flap kinematics after big back amount.
Description
Technical field
The invention belongs to technical field of aircraft design, and in particular to a kind of trailing edge flap rocker-arm motion mechanism design.
Background technique
Trailing edge flap is to improve and taking off/one of landing configuration lower wing lift coefficient movable rudder face, in rear
In wing flap design process, generally according to the taking off of aircraft, landing data requirement, determine the design object of high lift device (as maximum
Lift coefficient increment), and then determine form, the flat shape etc. of high lift device, then carry out two-dimentional wing flap design, it determines outside wing flap
The location parameters such as shape and seam amount, lap, deflection angle.
The motion principle of trailing edge flap is generally according to the determining seam amount of two-dimentional wing flap design, lap, deflection angle etc.
Location parameter is designed for target position, and common trailing edge flap forms of motion has hinge type, four link type, sliding rail-pulley
Posture etc..For big back amount trailing edge flap, hinge type and four link type forms of motion are relatively difficult to guarantee trailing edge flap seam amount, again
The key parameters such as folded amount, deflection angle, cannot achieve two-dimensional design target；And four link type and sliding rail-pulley posture move rail
The selection of mark is more complex, and the problems such as clamping stagnation, abrasion easily occurs.Single big retrusive trailing edge flap motion principle scheme of seam is set at present
Timing generally requires to expend considerable time and effort, and the motion principle formed often results in movement mechanism and actuation form is multiple
Miscellaneous, movement mechanism bump height is big, the problems such as clamping stagnation abrasion easily occurs.
Summary of the invention
To be solved by this invention is that existing trailing edge flap movement mechanism bump height the technology of clamping stagnation abrasion greatly, easily occurs
Problem provides a kind of trailing edge flap rocker-arm motion mechanism design, and movement mechanism and actuation form are simple, are rotated by rocker arm
Realize flap kinematics, safe and reliable, the problems such as being not in abrasion and clamping stagnation.
In order to solve technical problem of the invention, the present invention is achieved by the following technical solutions: a kind of trailing edge flap
Rocker-arm motion mechanism design, comprising the following steps:
The two-dimensional position parameter step 1: determining trailing edge flap initial/taking off/lands, amount containing seam, lap, deflection angle
The location parameter of degree.
Step 2: being landed two-dimensional position parameter according to trailing edge flap initial/taking off/, in wing flap leading edge lower surface apart from the flap
An adjustable point is chosen respectively in the position of nose of wing X1.
Step 3: the point according to selected by second step, draws an equal length straight line perpendicular to following table surface curve respectively
Section.
Step 4: determining driving rocker arm scheme, three endpoints of three straightways determined by third step determine one
Circle determines that the center of circle of circle is the rotation center for driving rocker arm, the identified center of circle and trailing edge flap initial position straightway
The line of endpoint is to drive rocker arm scheme.
Step 5: being landed two-dimensional position parameter according to initial/taking off/, in wing flap rear lower surface apart from wing flap rear L2
Position choose an adjustable point respectively.
Step 6: the point according to selected by the 5th step, draws an equal length straight line perpendicular to following table surface curve respectively
Section.
Step 7: determining driven rocker arm scheme, three endpoints of the three articles of straightways determined by the 6th step determine one
Circle determines that the center of circle of circle is the rotation center of driven rocker arm, the identified center of circle and trailing edge flap initial position straightway
The line of endpoint is driven rocker arm scheme.
Preferably, the wing flap that the value range of X1 is 1% ~ 5% in the second step is with respect to chord length.
Preferably, the wing flap that the value range of L2 is 5% ~ 10% in the 5th step is with respect to chord length.
Preferably, drive rocker arm rotation center close to flap lower surface in the 4th step, including the position to selected point
The step of setting and the length of straightway is adjusted, minimizing wing flap bulge, realizes optimal aeroperformance.
Preferably, driven rocker arm rotation center is close to flap lower surface in the 7th step, including the position to selected point
The step of setting and the length of straightway is adjusted, minimizing wing flap bulge, realizes optimal 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 passes through the point and straight line using variable ginseng
Section makees circule method using 3 points, designs double rocker arm rotation mode schemes, realizes the design of big back amount trailing edge flap movement mechanism,
Design method is simple, easy to operate；The motion scheme actuation form and mechanism of formation are simple, safe and reliable, are not in mill
The problems such as undermining clamping stagnation.A kind of trailing edge flap rocker-arm motion mechanism design disclosed by the invention is suitable for the big back amount back of robe
The design of wing movement.
Detailed description of the invention
Fig. 1 is that trailing edge flap initial/taking off/lands 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 driving rocker arm rotation center and rocker arm scheme schematic diagram.
Fig. 4 is adjustable point and straightway at trailing edge flap rear lower surface.
Fig. 5 is driven rocker arm rotation center and rocker arm scheme schematic diagram.
Fig. 6 is the double rocker-arm motion principle figures of trailing edge flap.
Specific embodiment
With reference to the accompanying drawing, embodiment is described in detail.
Referring to attached drawing 1 to attached drawing 6, a kind of trailing edge flap rocker-arm motion mechanism design includes the following steps:
(C) two-dimensional position parameter of landing step 1: determining trailing edge flap initial (A)/takes off (B)/, amount containing seam, overlapping
The location parameter of amount, deflection angle.
Second step lands two-dimensional position parameter according to trailing edge flap initial/taking off/, 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.
Third step, the point according to selected by second step draw an equal length L1's perpendicular to following table surface curve respectively
Straightway determines three endpoints e, e1, e2.
4th step determines driving rocker arm scheme, and three endpoints e, e1, e2 by three determining straightways of third step are true
A fixed circle 1, at the beginning of determining that the center of circle O1 of circle 1 as drives the rotation center of rocker arm, identified center of circle O1 and trailing edge flap
The line of beginning position straightway endpoint e, e1, e2 are to drive rocker arm scheme.
5th step/is taken off (B)/(C) two-dimensional position parameter of landing according to initial (A), in wing flap rear lower surface apart from the flap
Wing rear L2 chooses adjustable point f, f1, a f2 in position respectively.
6th step, according to point selected by the 5th step, drawing one respectively perpendicular to lower surface length of a curve is X2's
Straightway determines three endpoints g, g1, g2.
7th step determines driven rocker arm scheme, and three endpoints g, g1, g2 by three articles of determining straightways of the 6th step are true
A fixed circle 2 determines that the center of circle O2 for justifying 2 is the rotation center of driven rocker arm, at the beginning of identified center of circle O2 and trailing edge flap
The line of beginning position straightway endpoint g, g1, g2 are driven rocker arm scheme.
Further, the value range of X1 is 1% ~ 5% wing flap with respect to chord length in the second step.
Further, the value range of L2 is 5% ~ 10% wing flap with respect to chord length in the 5th step.
Further, it drives rocker arm rotation center close as far as possible from flap lower surface in the 4th step, including passes through size
The position of X1 point of adjustment d, d1, d2 and the length L1 by adjusting straightway optimize the position of endpoint e, e1, e2, make wing flap bulge
The step of minimum, preferably suitably drives rocker arm rotation center and rocker arm scheme, realizes optimal aeroperformance.
Further, driven rocker arm rotation center is close as far as possible from flap lower surface in the 7th step, including by adjusting
The position of size L2 point of adjustment f, f1, f2 and the length X2 by adjusting straightway optimize the position of endpoint g, g1, g2, make wing flap
The step of bulge minimizes, preferably suitable driven rocker arm rotation center and rocker arm scheme, realize optimal aeroperformance.
By above method, the motion principle scheme of big back amount trailing edge flap, design method letter can be quickly determined
It is single, it is easy to operate；The problems such as motion scheme actuation form of formation is simple, safe and reliable, is not in abrasion and clamping stagnation.
One of the above enumerated are only specific embodiments of the present invention.It is clear that the invention is not restricted to which above embodiments, may be used also
With there are many similar reshapings.What those skilled in the art directly can export or associate from present disclosure
All deformations, are 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: the following steps are included:
The B/ landing C two-dimensional position parameter step 1: the determining initial A/ of trailing edge flap takes off, amount containing seam, lap, deflection angle
Location parameter；
Step 2: being taken off B/ landing C two-dimensional position parameter according to the initial A/ of trailing edge flap, in wing flap leading edge lower surface apart from wing flap
Adjustable point d, d1, a d2 are chosen respectively in the position of leading edge X1；
Step 3: the point according to selected by second step, draws an equal length straightway perpendicular to following table surface curve, really respectively
Fixed three endpoints e, e1, e2；
Step 4: determining driving rocker arm scheme, three endpoints e, e1, e2 of three straightways determined by third step determine one
A circle determines that the center of circle O1 of circle is the rotation center for driving rocker arm, identified center of circle O1 and trailing edge flap initial position
The line of straightway endpoint e, e1, e2 are to drive rocker arm scheme；
Step 5: being taken off B/ landing C two-dimensional position parameter according to initial A/, in wing flap rear lower surface apart from wing flap rear L2's
Adjustable point f, f1, a f2 are chosen respectively in position；
Step 6: the point according to selected by the 5th step, draws an equal length straightway perpendicular to following table surface curve, really respectively
Fixed three endpoints g, g1, g2；
Step 7: determining driven rocker arm scheme, by three endpoints of three articles of straightways that the 6th step determines, three endpoints are determined
G, g1, g2 determine a circle, determine that the center of circle O2 of circle is the rotation center of driven rocker arm, identified center of circle O2 and rear
The line of wing flap initial position straightway endpoint g, g1, g2 are driven rocker arm scheme.
2. a kind of trailing edge flap rocker-arm motion mechanism design as described in claim 1, it is characterised in that: in the second step
The wing flap that the value range of X1 is 1% ~ 5% is with respect to chord length.
3. a kind of trailing edge flap rocker-arm motion mechanism design as described in claim 1, it is characterised in that: in the 5th step
The wing flap that the value range of L2 is 5% ~ 10% is with respect to chord length.
4. a kind of trailing edge flap rocker-arm motion mechanism design as described in claim 1, it is characterised in that: in the 4th step
Drive rocker arm rotation center close to flap lower surface, the length including position and straightway to selected point is adjusted, makes
The step of wing flap bulge minimizes.
5. a kind of trailing edge flap rocker-arm motion mechanism design as described in claim 1, it is characterised in that: in the 7th step
Close to flap lower surface, the length including position and straightway to selected point is adjusted, makes driven rocker arm rotation center
The step of 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 |
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| 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 CN106347633A (en) | 2017-01-25 |
| CN106347633B true CN106347633B (en) | 2019-03-29 |
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| 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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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 | Priority date | Publication date | Assignee | Title |
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| US2620147A (en) * | 1950-05-31 | 1952-12-02 | Boeing Co | Airplane flap control mechanism |
| DE102009053126A1 (en) * | 2009-11-13 | 2011-05-19 | Airbus Operations Gmbh | Control system of an aircraft with a valve |
| DE102009060325A1 (en) * | 2009-12-23 | 2011-06-30 | Airbus Operations GmbH, 21129 | 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 |
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