CN107719644A - A kind of wing flap draw off gear - Google Patents
A kind of wing flap draw off gear Download PDFInfo
- Publication number
- CN107719644A CN107719644A CN201710969569.2A CN201710969569A CN107719644A CN 107719644 A CN107719644 A CN 107719644A CN 201710969569 A CN201710969569 A CN 201710969569A CN 107719644 A CN107719644 A CN 107719644A
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- CN
- China
- Prior art keywords
- aircraft
- rotating shaft
- gear
- aircraft flap
- support
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Classifications
-
- 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
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Automation & Control Theory (AREA)
- Transmission Devices (AREA)
Abstract
A kind of aircraft flap draw off gear, including：Bearing, the pleasant flow arrangement of the bearing and the fixation trailing edge that aircraft wing can be fixedly connected to；First rotating shaft, first rotating shaft are rotatably installed on bearing；Rocking arm, one end of rocking arm are fixedly connected to first rotating shaft；Connecting rod, one end of connecting rod is pivotably connected to the other end of rocking arm, and the other end of connecting rod is provided with ball pivot；Supplemental support, supplemental support are provided with three ball pivots being triangularly arranged, and supplemental support is connected to bearing by one in three ball pivots；Two other ball pivot in three ball pivots on ball pivot and supplemental support wherein on connecting rod is used to be connected to the downside of aircraft flap.The aircraft flap draw off gear is simple in construction and easily controllable, compact-sized therefore lightweight, while ensureing that mechanism radome fairing can be with pleasant flow arrangement, effectively reduces the size of radome fairing.
Description
Technical field
The present invention relates to a kind of lift system, more specifically a kind of aircraft flap draw off gear.
Background technology
At present, common wing flap jack mainly has three kinds of forms：Simple hinge mechanism, connecting rod sliding track mechanism and four connect
Linkage.
Simple hinge mechanism is normally used for the double slotted flaps of the less single slotted flap of fowler motion or the stator wing, wing flap
Around a fixed-axis rotation.This mechanism is simple, it is light, reliable, be easily controlled, but have certain limitation simultaneously.It is primarily due to the flap
Wing movement locus is a fixed circular arc, thus take-off and landing position cannot concurrently reach it is pneumatic optimal；Secondly it is fixed
The fowler motion that hinge is allowed is smaller, and the radome fairing needed is larger, and compared with other devices, aeroperformance will have very big folding
Button.
Connecting rod sliding track mechanism is of wide application, and can realize arbitrary pneumatic design substantially.Wing flap is connected to pulley
On frame, in landing, pulley yoke is moved by connecting rod drives edge slide rail, allows wing flap to reach the lift-rising position of each design with this.According to
Track is different, and slide rail can substantially be divided into three classes：Line slide rail, circular arc and hook slide rail.Wherein, circular arc and hook
Slide rail controls the position and drift angle of wing flap by the shape of slide rail simultaneously；Line slide rail controls flap configuration by slide rail, leads to
Bar of overdriving is deflected to control the drift angle of wing flap.Connecting rod sliding track mechanism can make wing flap reach optimal design attitude, but this
Kind mechanism weight is very big, and structure is more complicated, and maintenance is also more troublesome.
Quadric chain pneumatic efficiency is higher, but structure is more complicated, and maintenance is also more troublesome.
In addition, various mechanisms in order to avoid producing interference when inside and outside wing flap is put down, will use complicated mechanism to design,
Pay the cost in many pneumatic and weight.
Therefore, this area needs wing flap jack a kind of simple in construction and easily controllable.
The content of the invention
The present invention provides a kind of aircraft flap draw off gear, and its is simple in construction and easily controllable, compact-sized therefore lightweight,
While ensureing that mechanism radome fairing can be with pleasant flow arrangement, the size of radome fairing is effectively reduced.The specifically aircraft flap
Draw off gear includes：
Bearing, the pleasant flow arrangement of the bearing simultaneously can be fixedly connected to the fixation trailing edge of aircraft wing；
First rotating shaft, the first rotating shaft are rotatably installed on the bearing；
Rocking arm, one end of the rocking arm are connected to the first rotating shaft；
Connecting rod, one end of the connecting rod are pivotably connected to the other end of the rocking arm, and the other end of the connecting rod
Provided with ball pivot；
Supplemental support, the supplemental support are provided with three ball pivots being triangularly arranged, and the auxiliary branch
Bearing member is connected to the bearing by one in three ball pivots；
Two other ball pivot in three ball pivots on ball pivot and the supplemental support on wherein described connecting rod is used
In the downside for being connected to aircraft flap.
In a preferred embodiment, the first rotating shaft is connected with gear-box and can driven by the gear-box and rotated.
In a preferred embodiment, the gear-box be installed on the bearing and with the output axis connection of motor.
In a preferred embodiment, the supplemental support is Y-shaped support, located at three balls of the supplemental support
Hinge is arranged on the end of three branches of the Y-shaped support.
In a preferred embodiment, the supplemental support is " V " shape support, located at three balls of the supplemental support
Hinge is separately positioned on the bottom apex of the " V " shape support and the end of Liang Ge branches.
In a preferred embodiment, the bearing is provided with two supportings positioned at the rocking arm and the connecting rod both sides respectively
Plate.
In a preferred embodiment, at least two be fixedly connected with the support plate are provided between described two support plates
Spaced support block.
In a preferred embodiment, the first rotating shaft is rotatably installed on described two support plates.
In a preferred embodiment, the rocking arm and the connecting rod pass through the second rotating shaft pivot parallel to the first rotating shaft
Turn connection.
In a preferred embodiment, the supplemental support is connected by being pivoted parallel to the 3rd rotating shaft of the first rotating shaft
Two support plates are connected to, and the 3rd rotating shaft is consolidated with a ball pivot in three ball pivots on the supplemental support
Fixed connection.
In a preferred embodiment, the pleasant flow arrangement of the bearing.
In a preferred embodiment, the aircraft flap jack is used for the outer wing flap for controlling aircraft.
In a preferred embodiment, the aircraft flap draw off gear is used for the interior wing flap for controlling aircraft.
In a preferred embodiment, it is in more highly swept control rudder face that the aircraft flap draw off gear, which is used to control,.
A kind of aircraft, the aircraft are provided with above-mentioned aircraft flap draw off gear.
The additional features and advantage of wing flap jack described herein will state in detailed description below, and
By below with those skilled in the art obviously or from by putting into practice embodiment described herein and by art technology
Personnel recognize that these descriptions include detailed description below, claim and accompanying drawing.
It should be appreciated that general description above and detailed description below illustrate various embodiments and be intended to provide understanding
The general introduction of the property and feature of claimed theme or framework.Various embodiments are further understood with providing including accompanying drawing
And accompanying drawing is incorporated in this specification and forms the part of this specification.Accompanying drawing shows various implementations described herein
Example, and it is used for explaining principle and the operation of claimed theme together with the description.
Brief description of the drawings
With reference to object above, technical characteristic of the invention is explicitly described in the following claims, and its advantage
It is clear that accompanying drawing has been illustrated by way of example the preferred embodiments of the present invention from detailed description referring to the drawings, and
The scope of present inventive concept is not limited.
Fig. 1 shows the stereogram of the aircraft flap draw off gear according to the present invention.
Fig. 2 shows Fig. 1 rocking arm of aircraft flap draw off gear and the diagrammatic side view of link assembly.
Fig. 3 shows the schematic isometric of the supplemental support of Fig. 1 aircraft flap draw off gear.
Fig. 4 shows the schematic diagram of the aircraft flap draw off gear installation site according to the present invention.
Fig. 5 shows the exploded view of the aircraft flap draw off gear according to the present invention.
Reference numerals list
1 supplemental support
2 the 3rd rotating shafts
3 bearings
4 connecting rods
5 rocking arms
6 first rotating shafts
7 support blocks
8 gear-boxes
9 second rotating shafts
13 support plates
One end of 41 connecting rods
The other end of 42 connecting rods
One end of 51 rocking arms
The other end of 52 rocking arms
111st, 411 ball pivot
Embodiment
Reference will now be made in detail to each embodiment of the present invention, the example of these embodiments is shown in the accompanying drawings
And it is described as follows.Although the present invention will be combined with exemplary and be described, it will be appreciated that this specification
It is not intended to limit the invention to those exemplaries.On the contrary, it is contemplated that not only cover these exemplary realities
Apply scheme, and covering can be included in it is various within the spirit and scope of the present invention being defined by the appended claims
Selection form, modification, equivalents and other embodiments.For the ease of explaining and accurately determining in the following claims
Justice, term " on ", " under ", " interior " and " outer " position for being used for the feature with reference to exemplary shown in the figure are come pair
These features are described.
The outer wing flap of aircraft the rotating shaft do not fixed when favorable current moves, is one because having the upper counterangle and angle of sweep
The compound motion put english and turned is retreated, and also has and opens up to displacement.Therefore, the motion of outer wing flap is space six-freedom motion.
When mechanism designs, it is necessary to fully take into account the complexity of motion, constraint reasonable in design, ensure the normal operations of flap kinematics.
The motion of trailing edge flap follows " equal percentage chord length " principle, due to wingpiston be about one it is trapezoidal, cause the same flap
Two actuator motion on wing rudder face is not synchronous, needs during design meticulous calculating and movement relation to analyze.On pneumatic
It is required that inside and outside flap kinematics will be carried out synchronously, but under conditions of same set of torque tube transmits power, inside and outside wing flap is real-time
Deflection identical angle can not realize in theory, can only when reaching design attitude error minimum.Therefore in installation motion
After also need to check aeroperformance, ensure aeroperformance error in scope reasonable in design.In view of these factors,
The aircraft flap draw off gear of the present invention is made.
The exemplary of the present invention is described in detail below with reference to the accompanying drawings.
The aircraft flap draw off gear 100 according to the present invention is shown in Fig. 1.The aircraft flap draw off gear 100 includes：
Bearing 3, first rotating shaft 6, Rocker arm 5, connecting rod 4 and supplemental support 1.3 pleasant flow arrangement of bearing can be simultaneously fixedly connected to
The fixation trailing edge of aircraft wing is to support the miscellaneous part of the wing flap draw off gear 100.First rotating shaft 6 is rotatably installed on branch
Seat 3, so as to which first rotating shaft 6 can rotate in bearing 3 around its own axis.
Referring further to Fig. 2 and 4, Rocker arm 5 is fixedly connected to first rotating shaft 6 with can be 6 turns with first rotating shaft in its one end 51
It is dynamic.Connecting rod 4 is pivotably connected to the other end 52 of Rocker arm 5 in its one end 41, can be relative to this so as to one end 41 of connecting rod 4
The other end 52 pivots.And the other end 42 of connecting rod 4 is provided with ball pivot 411, the ball pivot 411 is used for the downside for being linked to aircraft flap,
So as to when first rotating shaft 6 is rotated by driving, drive Rocker arm 5 to rotate, so drivening rod 4 downside of wing flap is applied thrust or
Pulling force.
Supplemental support 1 is provided with three ball pivots 111 being triangularly arranged.A ball pivot 111 in three ball pivots 111
Bearing 3 is connected to, and two other ball pivot 111 is used to be connected to the downside of aircraft flap.Due to the cloth of the auxiliary supports 1
Put, when connecting rod 4 deploys to wing flap application thrust, pass through the effect of three ball pivots 111 so that wing flap is crossed in partially lower
Have and extend to outside displacement.When the device is used for outer wing flap, the interference with interior wing flap can be effectively avoided, and can effectively subtract
Gap between small inside and outside wing flap.
Specifically, first rotating shaft 6 is connected with gear-box 8 and can driven by the gear-box 8 and rotated.Alternatively,
First rotating shaft 6 can also be the output shaft of gear-box 8.And gear-box 8 can be arranged on bearing 3 or be attached to fuselage, and with
The output axis connection of motor is with by motor-driven rotation.
Wherein auxiliary supports 1 can be configured to different forms, as long as three balls being triangularly arranged can be arranged
Hinge 111 is simultaneously easy to ball pivot 111 to be connected respectively with the downside of bearing 3 and wing flap.In the embodiment shown in fig. 3, aiding support
Part 1 is Y-shaped support, and three ball pivots 111 of supplemental support 1 are then separately positioned on the end of three branches of the Y-shaped support
Portion.Of course, it is possible to contemplate, supplemental support 1 may be alternatively formed to " V " shape support, then the three of supplemental support 1 ball pivot 111 divides
The bottom apex of the " V " shape support and the end of Liang Ge branches are not arranged on.In this case, for the ease of two ball pivots 111
Installation on the downside of to wing flap, it is preferred that the ball pivot 111 for being arranged on the bottom apex of " V " shape support is connected to bearing 3, and in addition
On the downside of the wing flap of two connections of ball pivot 111.
It is preferred that bearing 3 is provided with two support plates 13 positioned at Rocker arm 5 and the both sides of connecting rod 4 respectively.Two support plates
At least two spaced support blocks 7 being fixedly connected with support plate are provided between 13, to strengthen bearing 3.
The first rotating shaft 6 is rotatably installed on two support plates 13.
It is preferred that Rocker arm 5 and connecting rod 4 are pivotally connected by the second rotating shaft 9 parallel to first rotating shaft 6, so as to change
The rotating speed and direction that drive shaft passes over.It is also preferred that supplemental support 1 passes through the 3rd turn parallel to first rotating shaft 6
Axle 2 is pivotally attached to two support plates 13, and the 3rd rotating shaft 2 and a ball in three ball pivots 111 on supplemental support
Hinge is fixedly connected.
It is particularly suitable for use according to the aircraft flap draw off gear of one's duty invention and controls the outer wing flap of aircraft.In control aircraft
It is with the obvious advantage during outer wing flap, but the device can also be used for controlling the interior wing flap of aircraft and in more highly swept control rudder face.Fig. 4
In show the installation site of the aircraft flap draw off gear 100 on aircraft flap.
The main beneficial effect of the present invention is：
1st, due to the setting of four ball pivots, relative to conventional simple hinge, four ball pivots can make outboard flap under
There is one to extend the interference that to outside displacement, effectively prevent with inboard flap during partially, and effectively reduce medial and lateral
Gap between wing flap；
2nd, due to the setting of supplemental support, it can effectively carry three ball pivots, make compact-sized, mitigation weight；
3rd, due to the pleasant flow arrangement of bearing, can be effectively reduced while ensureing that radome fairing can be along its flow arrangement
The size of radome fairing；
4th, due to the setting of simple ball-and-socket hinge device so that wing flap draw off gear is simple in construction, and control is easy；
5th, due to deflecting, the setting of change gear box, rotating speed and direction that drive shaft passes over can effectively be changed.
Although the structure and operation principle of the present invention are illustrated above in association with preferred embodiment, this technology
Those of ordinary skill in field is it should be appreciated that above-mentioned example is intended merely to explanation, and cannot function as the limit to the present invention
System.Therefore, the present invention can be modified in the spirit of claims and modification, these modifications and variations
It will all fall within the scope of required by claims of the present invention.
Claims (15)
1. a kind of aircraft flap draw off gear, including：
Bearing (3), the pleasant flow arrangement of the bearing (3) simultaneously can be fixedly connected to the fixation trailing edge of aircraft wing；
First rotating shaft (6), the first rotating shaft (6) are rotatably installed on the bearing (3)；
Rocking arm (5), one end (51) of the rocking arm (5) are fixedly connected to the first rotating shaft (6)；
Connecting rod (4), one end (41) of the connecting rod (4) are pivotably connected to the other end (52) of the rocking arm (5), and described
The other end (42) of connecting rod (4) is provided with ball pivot (411)；
Supplemental support (1), the supplemental support (1) are provided with three ball pivots (111) being triangularly arranged, and described
Supplemental support (1) is connected to the bearing (3) by one in three ball pivots (111)；
Two other ball in three ball pivots (111) on ball pivot (411) and the supplemental support on wherein described connecting rod
Hinge (111) is used to be connected to the downside of aircraft flap.
2. aircraft flap jack according to claim 1, it is characterised in that
The first rotating shaft (6) is connected with gear-box (8) and can driven by the gear-box (8) and rotated.
3. aircraft flap jack according to claim 1, it is characterised in that
The gear-box be installed on the bearing (3) and with the output axis connection of motor.
4. aircraft flap jack according to claim 1, it is characterised in that
The supplemental support (1) is Y-shaped support, and three ball pivots (111) located at the supplemental support (1) are arranged on institute
State the end of three branches of Y-shaped support.
5. aircraft flap jack according to claim 1, it is characterised in that
The supplemental support (1) is " V " shape support, and three ball pivots (111) located at the supplemental support (1) are set respectively
In the bottom apex of the " V " shape support and the end of Liang Ge branches.
6. aircraft flap jack according to claim 1, it is characterised in that
The bearing (3) is provided with two support plates (13) positioned at the rocking arm (5) and the connecting rod (4) both sides respectively.
7. aircraft flap jack according to claim 6, it is characterised in that
At least two spaced supports being fixedly connected with the support plate are provided between described two support plates (13)
Block (7).
8. aircraft flap jack according to claim 6, it is characterised in that
The first rotating shaft (6) is rotatably installed on described two support plates (13).
9. aircraft flap jack according to claim 1, it is characterised in that
The rocking arm (5) and the connecting rod (4) are pivotally connected by the second rotating shaft (9) parallel to the first rotating shaft (6).
10. aircraft flap jack according to claim 6, it is characterised in that
The supplemental support (1) is pivotally attached to described in two by the 3rd rotating shaft (2) parallel to the first rotating shaft (6)
Support plate (13), and the 3rd rotating shaft (2) are consolidated with a ball pivot in three ball pivots (111) on the supplemental support
Fixed connection.
11. aircraft flap jack according to claim 1, it is characterised in that
The pleasant flow arrangement of the bearing (3).
12. aircraft flap jack according to claim 1, it is characterised in that
The aircraft flap draw off gear is used for the outer wing flap for controlling aircraft.
13. aircraft flap jack according to claim 1, it is characterised in that the aircraft flap draw off gear is used to control
The interior wing flap of aircraft processed.
14. aircraft flap jack according to claim 1, it is characterised in that the aircraft flap draw off gear is used to control
System is in more highly swept control rudder face.
15. a kind of aircraft, it is characterised in that the aircraft is provided with to be received according to any one of claim 1-14 aircraft flap
Put device.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710969569.2A CN107719644B (en) | 2017-10-18 | 2017-10-18 | Flap retracting device |
| PCT/CN2018/110845 WO2019076341A1 (en) | 2017-10-18 | 2018-10-18 | Flap retraction and releasing apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710969569.2A CN107719644B (en) | 2017-10-18 | 2017-10-18 | Flap retracting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107719644A true CN107719644A (en) | 2018-02-23 |
| CN107719644B CN107719644B (en) | 2021-09-10 |
Family
ID=61211811
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710969569.2A Active CN107719644B (en) | 2017-10-18 | 2017-10-18 | Flap retracting device |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN107719644B (en) |
| WO (1) | WO2019076341A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606638A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of sinking hinge type wing flap rocker supporting structure |
| WO2019076341A1 (en) * | 2017-10-18 | 2019-04-25 | 中国商用飞机有限责任公司 | Flap retraction and releasing apparatus |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20220266998A1 (en) * | 2021-02-19 | 2022-08-25 | Lilium Eaircraft Gmbh | Aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201045075Y (en) * | 2007-06-13 | 2008-04-09 | 江西洪都航空工业集团有限责任公司 | Flap double four-bar linkage motion 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 |
| EP2808250A1 (en) * | 2013-05-28 | 2014-12-03 | Airbus Operations GmbH | Aircraft flap system with aileron functionality |
| EP2851287A1 (en) * | 2013-09-24 | 2015-03-25 | The Boeing Company | Trailing edge actuator system and associated method |
| CN104816817A (en) * | 2013-09-24 | 2015-08-05 | 埃姆普里萨有限公司 | Aerodynamic surface drive mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107719644B (en) * | 2017-10-18 | 2021-09-10 | 中国商用飞机有限责任公司 | Flap retracting device |
-
2017
- 2017-10-18 CN CN201710969569.2A patent/CN107719644B/en active Active
-
2018
- 2018-10-18 WO PCT/CN2018/110845 patent/WO2019076341A1/en active Application Filing
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201045075Y (en) * | 2007-06-13 | 2008-04-09 | 江西洪都航空工业集团有限责任公司 | Flap double four-bar linkage motion 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 |
| EP2808250A1 (en) * | 2013-05-28 | 2014-12-03 | Airbus Operations GmbH | Aircraft flap system with aileron functionality |
| EP2851287A1 (en) * | 2013-09-24 | 2015-03-25 | The Boeing Company | Trailing edge actuator system and associated method |
| CN104816817A (en) * | 2013-09-24 | 2015-08-05 | 埃姆普里萨有限公司 | Aerodynamic surface drive mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019076341A1 (en) * | 2017-10-18 | 2019-04-25 | 中国商用飞机有限责任公司 | Flap retraction and releasing apparatus |
| CN109606638A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of sinking hinge type wing flap rocker supporting structure |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019076341A1 (en) | 2019-04-25 |
| CN107719644B (en) | 2021-09-10 |
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