CN109515737B - Aircraft wing surface leveling device - Google Patents
Aircraft wing surface leveling device Download PDFInfo
- Publication number
- CN109515737B CN109515737B CN201810223566.9A CN201810223566A CN109515737B CN 109515737 B CN109515737 B CN 109515737B CN 201810223566 A CN201810223566 A CN 201810223566A CN 109515737 B CN109515737 B CN 109515737B
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- CN
- China
- Prior art keywords
- aileron
- arm
- rocker arm
- connecting rod
- hinged
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
The invention discloses an aircraft wing surface balancing device, which comprises an electric mechanism (1), a first connecting rod (2), a double-arm rocker arm (3), an aileron suspension support arm (4), a second connecting rod (5), a double-arm rocker arm (6), a rocker arm (7), a pull rod (8), a third connecting rod (9), an aileron girder (10) and an aileron adjustment sheet (11); when the aileron deflects, the aileron tab (follow-up compensation sheet) operating mechanism is driven to move to operate the aileron tab (follow-up compensation sheet) to follow in the direction opposite to the aileron deflection direction. When the hydraulic source of the non-reversible booster of one side aileron is in failure, the 'aileron adjusting/adjusting sheet' change-over switch on the central control platform is set to the 'adjusting sheet' position, and the aileron adjusting sheet is deflected by an electric mechanism to relieve the disc force. The invention has the beneficial effects that: the servo motor has the functions of an adjusting sheet and a follow-up compensation sheet.
Description
Technical Field
The invention belongs to the field of airplane trim design, and particularly relates to an airplane wing surface leveling device.
Background
The adjusting sheet operation system is an operation system independent of the main flight operation, and the operation adjusting sheet deflects to reduce or counteract the operation force when the driver operates the main operation surface and reduce the fatigue of long-time flight. The follow-up compensation piece does not need special operation of a driver, is connected with the main control line system, deflects reversely along with the deflection of the main rudder/airfoil surface and reduces the operation force of the driver. The existing adjusting sheet has the defects that the follow-up compensation function is not realized, and the operation burden of a driver is increased.
Disclosure of Invention
The purpose of the invention is as follows: the invention overcomes the defects in the prior art and provides an aircraft wing surface leveling device.
The technical scheme is as follows: in order to solve the technical problems, the invention is realized by the following technical scheme:
an aircraft wing trim device comprises an electric mechanism 1, a first connecting rod 2, a first double-arm rocker arm 3, a flap suspension support arm 4, a second connecting rod 5, a second double-arm rocker arm 6, a rocker arm 7, a pull rod 8, a third connecting rod 9, a flap girder 10 and a flap adjusting sheet 11;
the electric mechanism 1 is installed on an aileron girder 10, an actuating cylinder of the electric mechanism 1 is fixedly connected with one end of a first connecting rod 2, the other end of the first connecting rod 2 is hinged with one support arm of a first double-arm rocker arm 3 installed on the aileron girder 10, an upper lug of a rocker arm 7 is hinged on a support of the aileron girder 10, a middle hole of the rocker arm 7 is hinged with a second double-arm rocker arm 6, a lower lug of the rocker arm 7 is hinged with one end of a third connecting rod 9, the other end of the third connecting rod 9 is hinged with the other support arm of the first double-arm rocker arm 3, an upper arm of the second double-arm rocker arm 6 is hinged with one end of a second connecting rod 5, the other end of the second connecting rod 5 is hinged with a support seat installed on an aileron suspension support arm 4, a lower arm of the second double-arm rocker arm 6 is hinged with one end of a pull rod 8, and the other end of the lug 8 is hinged with an aileron adjustment sheet 11.
Advantageous technical effects
The invention has the beneficial effects that: the trimming mechanism has the trimming function of the trimming sheet and the function of the follow-up compensation sheet.
Drawings
Figure 1 is a block diagram of a flap tab/follower compensator deflecting mechanism,
FIG. 2 is a flap tab operating switch and neutral indicator light;
wherein: 1. the structure comprises an electric mechanism, 2, a first connecting rod, 3, a first double-arm rocker arm, 4, an aileron support arm, 5, a second connecting rod, 6, a second double-arm rocker arm, 7, a rocker arm, 8, a pull rod, 9, a third connecting rod, 10, an aileron crossbeam and 11 aileron adjustment plates.
Detailed Description
The invention is described in further detail below with reference to the following detailed description and accompanying drawings:
referring to fig. 1, the present embodiment provides an aircraft wing trim apparatus, which includes an electric mechanism 1, a first link 2, a first double-arm rocker arm 3, a flap suspension arm 4, a second link 5, a second double-arm rocker arm 6, a rocker arm 7, a pull rod 8, a third link 9, a flap girder 10, and a flap trim tab 11;
the electric mechanism 1 is installed on an aileron girder 10, an actuating cylinder of the electric mechanism 1 is fixedly connected with one end of a first connecting rod 2, the other end of the first connecting rod 2 is hinged with one support arm of a first double-arm rocker arm 3 installed on the aileron girder 10, an upper lug of a rocker arm 7 is hinged on a support of the aileron girder 10, a middle hole of the rocker arm 7 is hinged with a second double-arm rocker arm 6, a lower lug of the rocker arm 7 is hinged with one end of a third connecting rod 9, the other end of the third connecting rod 9 is hinged with the other support arm of the first double-arm rocker arm 3, an upper arm of the second double-arm rocker arm 6 is hinged with one end of a second connecting rod 5, the other end of the second connecting rod 5 is hinged with a support seat installed on an aileron suspension support arm 4, a lower arm of the second double-arm rocker arm 6 is hinged with one end of a pull rod 8, and the other end of the lug 8 is hinged with an aileron adjustment sheet 11.
The flap tab and the follower shim are identical in construction but operate on different principles. When the aircraft wing trim tab is used as the trim tab, the control switch is manually pulled to operate the deflection of the trim tab 11, so as to balance or eliminate the force applied to the steering wheel by the aircraft in a flying state. When the flap is used as a follow-up compensation piece, the flap deflects along with the flap automatically towards the direction opposite to the deflection direction of the flap so as to reduce the operating force on the steering wheel.
When the aileron deflects, the aileron tab (follow-up compensation sheet) operating mechanism is driven to move to operate the aileron tab (follow-up compensation sheet) to follow in the direction opposite to the aileron deflection direction. When the hydraulic source of the non-reversible booster of one side aileron is in failure, the 'aileron adjusting/adjusting sheet' change-over switch on the central control platform is set to the 'adjusting sheet' position, and the aileron adjusting sheet is deflected by an electric mechanism to relieve the disc force.
The flap adjusting sheet is installed on the outer side of the left and right inner flaps and driven by the electric mechanism 1. An adjusting sheet electric mechanism 1 is arranged in front of an aileron crossbeam 10, and a telescopic connecting rod of the electric mechanism 1 controls the adjusting sheet through a rocker arm and a pull rod. The aileron follow-up compensation plate is characterized in that the deflection direction of the aileron follow-up compensation plate is always opposite to the deflection direction of the aileron due to the action of the connecting rod, the rocker arm and the pull rod, so that the function of reducing the steering force of the steering wheel is achieved. The follow-up compensation piece is linked with the aileron. The follower compensator deflects in the opposite direction to the flap deflection as long as the flap deflects, regardless of the presence or absence of a load on the flap.
a. The flap adjusting sheet is driven by an electric mechanism 1, and 2 operating switches of the electric mechanism 1 are respectively arranged on the side close to a left driver and a right driver on a central control platform. The operating switch is pulled leftwards, the left aileron adjusting sheet deflects downwards, and the right aileron adjusting sheet deflects upwards; by actuating the actuating switch to the right, the flap tab is correspondingly deflected in the opposite direction. The left and right operation switches are interlocked, and when the operation switch on the left driver side is pulled, the operation circuit on the right driver side is automatically cut off.
b. When the adjusting plate is used as an adjusting plate, a driver pulls the operating switch to enable the electric mechanism 1 to work, the rocker arm 7 is driven to deflect around the mounting shaft through the first connecting rod 2, the first double-arm rocker arm 3 and the third connecting rod 9, the second double-arm rocker arm 6 is driven to move through the pin, and the upper arm of the second double-arm rocker arm 6 is connected with the support seat arranged on the aileron suspension support arm 4 through the second connecting rod 5. The upper arm of the second rocker arm 6 is thus deflected not only together with the rocker arm 7, but also about a pin fixed to the rocker arm 7, the second rocker arm 6 being deflected by a tab via a tie 8.
c. When the auxiliary wing follow-up compensation piece is used, a driver operates the auxiliary wing to deflect, the position of the auxiliary wing girder 10 relative to the auxiliary wing suspension arm 4 is changed, and the rotating shafts of the second double-arm rocker arm 6 and the rocker arm 7 are coaxial with the auxiliary wing rotating shaft. Since the electric mechanism 1 is not operated, the position of the second rocker arm 6 relative to the aileron suspension arm 4 is unchanged, but relative to the aileron girder, i.e. the aileron follower compensator controlled by the second rocker arm 6 is unchanged relative to the aileron suspension arm, but has an angle of deflection in the opposite direction relative to the moving aileron.
d. The control of the flap tab 11 by the flap tab electric mechanism 1 is a pulse control mode, namely when the time for pressing the switch once by a driver exceeds 2s, the trim electric mechanism 1 operates the flap tab 11 to deflect a stroke of 1.5 degrees at most, and if the switch needs to be released to deflect a larger stroke, the switch is pressed again; within a pulse stroke (1.5 DEG), the deflection is carried out at a deflection speed of 0.75 DEG/s to 1 DEG/s. The maximum upward and downward deflection angle of the flap tab 11 is 6 ° ± 1 °. The flap tab 11 is biased to the maximum angle by pressing the switch at least 4 times, and the end switch in the electric mechanism 1 controls the limit deflection angle of the flap tab 11. When the auxiliary wing is used as a follow-up compensation piece to work, the auxiliary wing deflects upwards and downwards by 15.6 degrees when fully deflected.
e) A flap tab neutral signal lamp is provided near the central console flap operating switch, and when the flap tab 11 is at the neutral position, the white signal lamp is on, and when the flap tab 11 is deviated from the neutral position, the white signal lamp is off. There is a tab 11 position display table on EICAS that can display the angle of the tab 11.
Claims (1)
1. An aircraft wing trim device comprises an electric mechanism (1), a first connecting rod (2), a first double-arm rocker arm (3), a aileron suspension support arm (4), a second connecting rod (5), a second double-arm rocker arm (6), a rocker arm (7), a pull rod (8), a third connecting rod (9), an aileron crossbeam (10) and an aileron trim tab (11); the method is characterized in that: the electric mechanism (1) is installed on an aileron girder (10), an actuating cylinder of the electric mechanism (1) is fixedly connected with one end of a first connecting rod (2), the other end of the first connecting rod (2) is hinged with one supporting arm of a first double-arm rocker arm (3) installed on the aileron girder (10), an upper lug of the rocker arm (7) is hinged on a support of the aileron girder (10), a middle hole of the rocker arm (7) is hinged with a second double-arm rocker arm (6), a lower lug of the rocker arm (7) is hinged with one end of a third connecting rod (9), the other end of the third connecting rod (9) is hinged with the other end of the first double-arm rocker arm (3), an upper arm of the second double-arm rocker arm (6) is hinged with one end of a second connecting rod (5), the other end of the second connecting rod (5) is hinged with a supporting seat installed on the aileron suspension supporting arm (4), a lower arm of the second double-arm rocker arm (6) is hinged with one end of a pull rod (8), and the other end of the pull rod (8) is hinged with a lug of an aileron adjusting plate (11);
when the aircraft wing trim tab is used as a trim tab, a control switch needs to be manually pulled to operate the deflection of the trim tab (11) of the aileron, so that the force of the aircraft on a steering wheel in a flying state is balanced or eliminated; when the flap is used as a follow-up compensation piece, the flap deflects along with the flap automatically towards the direction opposite to the deflection direction of the flap so as to reduce the operating force on the steering wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810223566.9A CN109515737B (en) | 2018-03-16 | 2018-03-16 | Aircraft wing surface leveling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810223566.9A CN109515737B (en) | 2018-03-16 | 2018-03-16 | Aircraft wing surface leveling device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109515737A CN109515737A (en) | 2019-03-26 |
| CN109515737B true CN109515737B (en) | 2022-04-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810223566.9A Active CN109515737B (en) | 2018-03-16 | 2018-03-16 | Aircraft wing surface leveling device |
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| Country | Link |
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| CN (1) | CN109515737B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110239737B (en) * | 2019-05-29 | 2022-08-23 | 陕西飞机工业（集团）有限公司 | Method for calculating flap adjustment amount of multi-engine turboprop aircraft during yawing and sideslip |
| 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 |
Family Cites Families (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB527549A (en) * | 1938-05-07 | 1940-10-10 | Ettore Bugatti | Improvements in or relating to actuating and controlling movable parts of aircraft |
| GB542944A (en) * | 1940-08-02 | 1942-02-03 | Dehavilland Aircraft | Improvements in or relating to actuating mechanism for aircraft controls |
| GB687682A (en) * | 1950-01-04 | 1953-02-18 | Svenska Aeroplan Ab | A combined trim and balance tab, intended especially for aircraft |
| GB763506A (en) * | 1953-06-30 | 1956-12-12 | Bendix Aviat Corp | Monitoring apparatus for automatic pilot systems |
| FR2226317B1 (en) * | 1973-07-30 | 1976-06-18 | Morin B | |
| CA1212100A (en) * | 1982-01-28 | 1986-09-30 | James E. Hampton | Method of installing, levelling and securing a subsea template |
| FR2571021B1 (en) * | 1984-10-02 | 1986-12-05 | Aerospatiale | DEVICE FOR AUTOMATICALLY CONTROLLING AN AERODYNAMIC COMPENSATOR ASSOCIATED WITH AN AERODYNAMIC SURFACE FOR CONTROLLING AN AIRCRAFT |
| GB2467945B (en) * | 2009-02-20 | 2014-03-05 | Westland Helicopters | Device which is subject to fluid flow |
| CN201597752U (en) * | 2010-02-08 | 2010-10-06 | 哈尔滨飞机工业集团有限责任公司 | Follower of aircraft elevator tab |
| CN103043209B (en) * | 2012-12-11 | 2016-04-20 | 江西洪都航空工业集团有限责任公司 | A kind of agricultural aircraft agriculture aircraft elevator |
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| Publication number | Publication date |
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| CN109515737A (en) | 2019-03-26 |
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