CN105667766B - A kind of method of adjustment of double slit retrusive wing flap - Google Patents
A kind of method of adjustment of double slit retrusive wing flap Download PDFInfo
- Publication number
- CN105667766B CN105667766B CN201610104760.6A CN201610104760A CN105667766B CN 105667766 B CN105667766 B CN 105667766B CN 201610104760 A CN201610104760 A CN 201610104760A CN 105667766 B CN105667766 B CN 105667766B
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- wing flap
- flap
- adjustment
- joint
- wing
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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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/30—Wing lift efficiency
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
- Transmission Devices (AREA)
Abstract
The present invention relates to a kind of method of adjustment of double slit retrusive wing flap, technique adjustment especially suitable for medium-sized medium range transporter wing flap, tolerance, the error accumulation such as left and right wing span, chord length, theoretical profile during aircraft manufacturing, it is inconsistent to directly affect left and right airfoil lift, easily cause aircraft yaw, the airplane crash problem such as gun off the runway during landing.Skill problem is adjusted to capture double slit retrusive wing flap, improves one of the medium-sized medium range transporter production efficiency in China, the breakthrough bottleneck for solving the heavy medium range transporter development of puzzlement China.Reduce the quantity of flight safety hidden danger, enhance China's aircraft international competitiveness, open and seize international market for China's Special Aircraft and done time in technological reserve.Cultivation and training substantial amounts of outstanding aeronautical manufacture and the mounting technology talent in technical scheme and the process of argumentation simultaneously.
Description
Technical field
The invention belongs to the technology in aeronautical manufacture mounting technology, is related to a kind of adjustment side of double slit retrusive wing flap
Method, especially suitable for the technique adjustment of medium-sized medium range transporter wing flap, the technology can be applied to double slit retrusive structure
All aircrafts of wing flap.
Background technology
China has proceeded by the imitated work processed of the carry out aircrafts of AN-12, in the past 70-eighties of eighties of last century
Decades in, China have accumulated substantial amounts of technology experience, successively develop 10 Multiple Types from copying to development
High, precision and frontier weapon equipment platform, ancestral is served using certain aircraft platform of new medium-sized medium range transporter as carrier aircraft platform in recent years
The national defence of state, and core force is responsible in the Defence business such as Homeland air defense, distant early warning, for the traffic guidance of motherland, far
The Defence business such as journey early warning are made that prominent achievement.
Certain new medium-sized medium range transporter is successfully developed for the early warning plane of carrier aircraft platform, has expanded the medium-sized intermediate range transport in China
Machine domestic and international market space, the military technology block headed by the U.S. is also broken, the barrier of " arms embargo to China " is not attacked
From broken.Although China in imitated and development work, have accumulated substantial amounts of technology experience and advanced technologies manufacture assembling skill
Art knowledge, but some large assemblies, part assembling in still have technical bottleneck, these bottleneck problems seriously constrain me
The production efficiency of the medium-sized medium range transporter of state, cause the medium-sized medium range transporter in China situation that supply falls short of demand, double slit retrusive
Wing flap adjustment technology is one of Pinch technology for restricting the medium-sized medium range transporter production efficiency in China and development remodeling.
According to internal authority department statistics, 85% airplane crash occurred in the takeoff and landing stage, and the event in takeoff and landing stage
Barrier rate causes airplane crash probability of happening to be about 30%.In order to improve aircraft safety performance, takeoff and landing accident probability, China pair are reduced
Medium-sized medium range transporter landing process is studied.Found in research process, the manufacturing process of the medium-sized medium range transporter in China
With use analog quantity transmission as the other aircrafts in China, analog quantity transmission can not be avoided to cause high tolerance, big error accumulation to be asked
Topic.These tolerances, error accumulation cause aircraft or so airfoil lift inconsistent, and be easily caused that the takeoff and landing stage guns off the runway flies
Act event.
The content of the invention
Goal of the invention：
The present invention proposes a kind of simple, easy to adjust, the safe technique adjustment method of method, can be fast and effectively
Solves each middle manufacture assembling difference, caused aircraft or so airfoil lift difference problem.When reducing takeoff and landing, left and right lift is answered
Difference, the accident probability for causing aircraft to deviate or gun off the runway.
This adjustment technology scheme includes, the uneven adjustment of the adjustment of left and right wing flap and unilateral wing flap length both ends.
A kind of method of adjustment of double slit retrusive wing flap, hydraulic motor 1 are that flap drive-rod 4 provides driving force, and wing flap passes
Lever 4 is connected by cross joint 11, universal knot 10 and connecting bolt 12 with spline gear shaft 8, spline gear shaft 8 by umbrella tooth and
Leading screw is connected with jack 6, and jack 6 is connected by leading screw with wing flap joint 9, and wing flap joint 9 is connected with wing flap；Rotation
Leading screw can drive the stretching motion of jack 6, and drive wing flap joint 9 to be synchronized with the movement, and wing flap joint 9 is connected with wing flap, from
And realize flap expander and move；
Set-up procedure includes herein below：
Step 1, left and right airfoil lift difference is calculated, calculate left and right wing flap adjustment direction and adjustment amount；
Step 2, disconnect spline gear shaft 8 and the connection of flap drive-rod 4, otating drive rod 4 to calculating adjustment amount；
Step 3, recover spline gear shaft 8 and the annexation of drive link 4.
Further, described disconnection is realized by extracting the connecting bolt 12 of cross joint 11 and universal knot 10 in step 2.
Further, annexation is recovered by inserting the connecting bolt 12 of cross joint 11 and universal knot 10 in step 3.
Beneficial effect
1st, manpower and materials are saved.Before the adjustment technology is not applied, there is driftage in aircraft, left and right airfoil lift differs
It during cause, can only as former state use, can only be decomposed when serious, change aircraft wing and solved.Aircraft is used quality to be present as former state
Hidden danger, decompose, change aircraft wing and need to waste substantial amounts of manpower and materials and financial resources, at the same Special Aircraft to China and in
The type medium range transporter production cycle brings influence, and causes immeasurable loss.The present invention can be solved quickly after proposing
Aircraft yaw and lift inconsistence problems.Reduce and decompose, change the huge loss that wing is brought, while solve and produce again
Manpower financial capacity's material resources waste problem caused by manufacturing aircraft wing.
2nd, the fast and effective other technique manufacturing issues of compensation.The program can apply solve engine pulling force misalignment of axe,
Wing shape deviation, span deviation, chord length deviation, wing deviation of weight etc., caused aircraft or so airfoil lift difference problem.
3rd, efficiency of assembling is improved, increases company's output value, improves the international competitiveness of medium-sized medium range transporter and Special Aircraft
And occupation rate of market.Supply falls short of demand for the medium-sized intermediate range transport in China and Special Aircraft at present, due to such assembling process technique
Bottleneck seriously constrains the throughput rate of China's aircraft, causes the medium-sized medium range transporter in China and Special Aircraft world occupation rate
It is extremely low.As such technology bottleneck problem is addressed, the increase company output value will be greatly improved, improves test manufacture occupation rate
And international competitiveness.
4th, the aero-manufacturing technology backbone talent has been cultivated.Youth is mainly enabled in the design and the process of argumentation of this programme
Technician, during conceptual design and study, technical staff has known medium-sized medium range transporter wing flap and middle outer wing system
Make, assemble, adjustment technology, having expanded the scope of one's knowledge of young worker, the time has been done for the aeronautical technology talents reserve in China.
Brief description of the drawings
Fig. 1 is flap control system schematic；
Fig. 2 is drive link and spline gear shaft connection diagram；
Fig. 3 is the structural representation of wing flap junction portion；
Wherein, 1- hydraulic motors, 2- supports, 3-XDG-23A limit switches mechanism, 4- flap drive-rods, 5- supports, 6- are received
The universal knot of laying mechanism, 7- jacks fixed support, 8- spline gear shafts, 9- wing flaps joint, 10-, 11- cross joints, 12- spiral shells
Bolt.
Double slit retrusive wing flap drives flap drive-rod 4 to rotate by hydraulic motor 1, and flap drive-rod 4 is by the kinetic energy of rotation
Jack 6 is passed to by spline gear shaft 8, rotary motion is converted to wing flap by umbrella tooth, leading screw etc. and connect by jack 6
First 9 stretching motion, so as to realize that the wing flap being screwed onto on wing flap joint 9 does stretching motion.
Embodiment
A kind of method of adjustment of double slit retrusive wing flap is provided, hydraulic motor 1 is that flap drive-rod 4 provides driving force, the flap
Wing drive link 4 is connected by cross joint 11, universal knot 10 and connecting bolt 12 with spline gear shaft 8, and spline gear shaft 8 passes through umbrella
Tooth and leading screw are connected with jack 6, and jack 6 is connected by leading screw with wing flap joint 9, and wing flap joint 9 is connected with wing flap；
Rotating threaded shaft can drive the stretching motion of jack 6, and drive wing flap joint 9 to be synchronized with the movement, and wing flap joint 9 connects with wing flap
Connect, so as to realize that flap expander moves；
Set-up procedure includes herein below：
Step 1, left and right airfoil lift difference is calculated, calculate left and right wing flap adjustment direction and adjustment amount；
Step 2, disconnect spline gear shaft 8 and the connection of flap drive-rod 4, otating drive rod 4 to calculating adjustment amount；
Step 3, recover spline gear shaft 8 and the annexation of drive link 4.
Further, described disconnection is realized by extracting the connecting bolt 12 of cross joint 11 and universal knot 10 in step 2.
Further, annexation is recovered by inserting the connecting bolt 12 of cross joint 11 and universal knot 10 in step 3.
Claims (3)
1. a kind of method of adjustment of double slit retrusive wing flap, hydraulic motor (1) is that flap drive-rod (4) provides driving force, wing flap
Drive link (4) is connected by cross joint (11), universal knot (10) and bolt (12) with spline gear shaft (8), spline gear shaft (8)
It is connected by umbrella tooth and leading screw with jack (6), jack (6) is connected by leading screw with wing flap joint (9), wing flap joint
(9) it is connected with wing flap；Rotating threaded shaft can drive jack (6) stretching motion, and drive wing flap joint (9) to be synchronized with the movement,
Wing flap joint (9) is connected with wing flap, so as to realize that flap expander moves；
Set-up procedure includes herein below：
Step 1, left and right airfoil lift difference is calculated, calculate left and right wing flap adjustment direction and adjustment amount；
Step 2, spline gear shaft (8) and the connection of flap drive-rod (4) are disconnected, swivel flap drive link (4) to calculating adjusts
Amount；
Step 3, recover spline gear shaft (8) and the annexation of flap drive-rod (4).
A kind of 2. method of adjustment of double slit retrusive wing flap according to claim 1, it is characterised in that：Pass through in step 2
The bolt (12) for extracting cross joint (11) and universal knot (10) realizes disconnection relation.
A kind of 3. method of adjustment of double slit retrusive wing flap according to claim 1, it is characterised in that：Pass through in step 3
Insertion cross joint (11) and the bolt (12) of universal knot (10) realize annexation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610104760.6A CN105667766B (en) | 2016-02-25 | 2016-02-25 | A kind of method of adjustment of double slit retrusive wing flap |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610104760.6A CN105667766B (en) | 2016-02-25 | 2016-02-25 | A kind of method of adjustment of double slit retrusive wing flap |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105667766A CN105667766A (en) | 2016-06-15 |
| CN105667766B true CN105667766B (en) | 2017-12-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610104760.6A Active CN105667766B (en) | 2016-02-25 | 2016-02-25 | A kind of method of adjustment of double slit retrusive wing flap |
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| CN (1) | CN105667766B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3478574B1 (en) * | 2016-06-29 | 2020-11-18 | Bombardier Inc. | Methods and systems for deploying adjacent trailing edge flaps |
| CN107538195A (en) * | 2017-09-26 | 2018-01-05 | 陕西飞机工业（集团）有限公司 | A kind of overlength wing assembly coordination length method |
| CN111731469B (en) * | 2019-04-12 | 2022-04-26 | 北京京东乾石科技有限公司 | Airfoil surface linkage device and aircraft |
| CN110239739B (en) * | 2019-05-29 | 2022-08-23 | 陕西飞机工业（集团）有限公司 | Method for calculating aileron adjustment amount during yaw and sideslip of multi-turboprop aircraft |
| CN110239733B (en) * | 2019-05-29 | 2022-09-20 | 陕西飞机工业（集团）有限公司 | Method for calculating flap adjustment amount during yawing and sideslip of airplane |
| CN111846201B (en) * | 2020-07-24 | 2022-01-28 | 中国电子科技集团公司第三十八研究所 | Flap synchronous drive control link mechanism |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0230061A1 (en) * | 1986-01-24 | 1987-07-29 | The Boeing Company | Trailing edge flaps |
| US6382566B1 (en) * | 1998-12-29 | 2002-05-07 | The Boeing Company | Method and apparatus for detecting skew and asymmetry of an airplane flap |
| CN102501984A (en) * | 2011-10-19 | 2012-06-20 | 无锡市海航电液伺服系统有限公司 | Flap loading device capable of calculating axial force for loading flap lead screw |
| CN105035308A (en) * | 2015-06-23 | 2015-11-11 | 中国航空工业集团公司西安飞机设计研究所 | Design method of flap driving mechanism and flap driving mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6464176B2 (en) * | 2000-07-26 | 2002-10-15 | Honda Giken Kogyo Kabushiki Kaisha | Flap operating device |
-
2016
- 2016-02-25 CN CN201610104760.6A patent/CN105667766B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0230061A1 (en) * | 1986-01-24 | 1987-07-29 | The Boeing Company | Trailing edge flaps |
| US6382566B1 (en) * | 1998-12-29 | 2002-05-07 | The Boeing Company | Method and apparatus for detecting skew and asymmetry of an airplane flap |
| CN102501984A (en) * | 2011-10-19 | 2012-06-20 | 无锡市海航电液伺服系统有限公司 | Flap loading device capable of calculating axial force for loading flap lead screw |
| CN105035308A (en) * | 2015-06-23 | 2015-11-11 | 中国航空工业集团公司西安飞机设计研究所 | Design method of flap driving mechanism and flap driving mechanism |
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| Publication number | Publication date |
|---|---|
| CN105667766A (en) | 2016-06-15 |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |
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