CN108082449A - A kind of large aircraft control surface suspension structure - Google Patents
A kind of large aircraft control surface suspension structure Download PDFInfo
- Publication number
- CN108082449A CN108082449A CN201711051823.7A CN201711051823A CN108082449A CN 108082449 A CN108082449 A CN 108082449A CN 201711051823 A CN201711051823 A CN 201711051823A CN 108082449 A CN108082449 A CN 108082449A
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- China
- Prior art keywords
- load
- rudder face
- carrying construction
- bearing
- control surface
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
- B64C9/02—Mounting or supporting thereof
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vehicle Body Suspensions (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The present invention provides a kind of large aircraft control surface suspension structure, is made of hinge linear load load-carrying construction (1) and aerodynamic loading load-carrying construction (2)；Hinge linear load load-carrying construction (1) independent bearing that hinge linear load is made up of stabilization (4) interior box beam (11) and its internal longitudinal joints (12) of the bolt axle (13) of interior installation, rudder face (3)；Aerodynamic loading load-carrying construction (2) independent bearing that aerodynamic loading is made up of the stabilization (4) interior suspension arm (21) and the rudder face (3) interior suspension joint (22).The present invention avoids rudder face forepart big opening, improves rudder face pneumatic efficiency by the way that hinge linear load load-carrying construction (1) is arranged at rudder face root and stabilization rear lower；Box beam (11) is directly connected with empennage banjo fixing butt jointing, and power transmission is simply direct, light-weight；The gap combined and rationally set by bushing and bearing discharges different degree of freedom so that it works between each structure non-interference, reliable operation.
Description
Technical field
The present invention relates to a kind of aircraft suspended structure more particularly to a kind of large aircraft control surface suspension structures.
Background technology
Large aircraft control surface suspension structure is in addition to rudder face aerodynamic loading to be born, it is necessary to can bear rudder face along hinge lines
36Wg inertial loads.Existing large aircraft rudder face hinge linear load load-carrying construction is hanged using brace combination rudder face mostly
Arm bears rudder face hinge linear load.This structure in order to avoid when rudder face rotates with brace collision, it is necessary in rudder face leading edge
Larger opening is set, seriously reduces rudder face pneumatic efficiency；Brace is will be in hinge lines load transmission to the stabilization back rest
When, power transmission efficiency is low, and construction weight cost is high.
The content of the invention
The defects of to solve existing large aircraft control surface suspension structure and deficiency, the technical problems to be solved by the invention are
There is provided a kind of rudder face opening is smaller, power transmission directly, weight cost is small and the control surface suspension structure design of reliable operation.
Existing in the prior art in order to solve the problems, such as, the technical solution adopted by the present invention is：A kind of large aircraft rudder face hangs
Hanging hang structure is made of hinge linear load load-carrying construction 1 and aerodynamic loading load-carrying construction 2；The hinge linear load load-carrying construction 1 by
The box beam 11 being arranged on stabilization 4 and its interior bolt axle 13 and the longitudinal joints 12 being arranged in rudder face 3 pass through bolt
Connection composition, to carry rudder face hinge linear load；The aerodynamic loading load-carrying construction 2 is by being arranged in the stabilization 4
Composition is bolted in suspension arm 21 and the suspension joint 22 being arranged in the rudder face 3, is pneumatically carried to carry rudder face
Lotus；The box beam 11 includes vertical clapboard 111, lower end rib 112, upper end rib 113, diaphragm plate 114 and box-like beam splice 115, leads to
The box-like beam splice 115 is crossed to be connected with the bolt axle 13.
As a kind of improvement of large aircraft control surface suspension structure of the present invention, the stabilization box-like beam splice 115 is installed
There is customization bearing 131, the customization bearing 131 can bear larger axial load and with aligning rotating function so that described
The ball centre of sphere can relatively it turn on 3 directions in the customization bearing 131 between bolt axle 13 and the box-like beam splice 115
It is dynamic.
As a further improvement, 131 inner ring upper and lower end face of the customization bearing is pressed with convex shoulder bushing 132, for preventing
Bolt axle 13 is stated to collide with neighbouring structure when rotating.
As a further improvement, bolt mounting holes are " track type " hole in the longitudinal joints 12, it is equipped with " track type "
Slide bushing 121, " track type " slide bushing 121 is than the 12 soft strip shape of longitudinal joints " hole is smaller so that it is described
Between " track type " slide bushing 121 and the bolt axle 13 and the longitudinal joints 12, can in the rudder face plane of symmetry normal direction
It is opposite on direction to slide.
As a further improvement, between being provided between 12 auricle of 13 auricle of bolt axle and the longitudinal joints centainly
Gap so that, can be along bolt hole between the bolt axle 13 and " track type " slide bushing 121 and the longitudinal joints 12
Axial direction is opposite to be slided.
As a further improvement, being provided with oiling groove in the bolt axle 13, pressure pump nozzle 133 is installed, is described fixed
Bearing 131 processed provides lubrication.
As a kind of improvement of large aircraft control surface suspension structure of the present invention, oscillating bearing is pressed on the suspension arm 21
211 so that between the suspension arm 21 and the suspension joint 22 can in the oscillating bearing 211 the ball centre of sphere at 3
It is relatively rotated on direction.
As a further improvement, the suspension arm 21 and 22 auricle of the suspension joint are vertically disposed with certain interval,
And the 211 inner ring upper and lower end face of oscillating bearing is pressed with slide bushing 23 so that the suspension arm 21 and the suspension joint
It can be slided between 22 along hinge lines direction is opposite.
As a further improvement, abrasion resistant convex shoulder piece set 221 is pressed on the suspension joint 22 so that the slide bushing 23
It is installed between bolt and abrasion resistant convex shoulder piece set 221, to protect the auricle hole of the suspension joint 22 and provide repairing
Surplus.
Compared with the prior art, a kind of the advantages of large aircraft control surface suspension structure of the invention, is：Rudder face leading edge is not required to
Big opening is wanted, avoids the reduction of rudder face pneumatic efficiency；11 structure of box beam is directly connected to empennage banjo fixing butt jointing, power transmission
It is simple direct, save weight；The aerodynamic loading load-carrying construction 2 and the hinge linear load load-carrying construction 1 by bushing and
The gap width that bearing is combined and rationally set discharges corresponding translation or rotational freedom so that works between it and does not do mutually
It relates to, respective definite functions and reliable operation.
Description of the drawings
Fig. 1 is a kind of large aircraft control surface suspension structure arrangement schematic diagram of the present invention, in figure：
1 is hinge linear load load-carrying construction；2 be aerodynamic loading load-carrying construction；
3 be rudder face；4 be stabilization；
A-A is connected section view for suspension arm with suspension joint.
Fig. 2 is the detailed in enlarged drawing, figure of hinge linear load load-carrying construction 1 in Fig. 1：
11 be box beam；111 be vertical clapboard；
112 be lower end rib；113 be upper end rib；
114 be diaphragm plate；115 be box-like beam splice；
12 be longitudinal joints；13 be bolt axle；
B-B is longitudinal joints and bolt axis connection sectional view.
Fig. 3 is that A-A suspension arms are connected sectional view with suspension joint in Fig. 1, in figure：
21 be suspension arm；211 be oscillating bearing；
22 be suspension joint；221 be abrasionproof convex shoulder bushing；
23 be slide bushing；24 be connection bolt；
25 be self-locking nut；
Fig. 4 is B-B longitudinal joints and bolt axis connection sectional view in Fig. 2, in figure：
121 be " track type " bushing；131 be customization bearing；
132 be bushing；133 be pressure pump nozzle；
134 be self-locking nut；C-C connects sectional view for longitudinal joints.
Fig. 5 is that C-C longitudinal joints connects sectional view in Fig. 4, in figure：
122 be connection bolt；123 be attaching nut.
Specific embodiment
In conjunction with a kind of specific embodiment of large aircraft control surface suspension structure of the description of the drawings present invention.
Refering to Figure 1, a kind of large aircraft control surface suspension structure of the present invention is used between rudder face 3 and stabilization 4
Connection；Hinge linear load load-carrying construction 1 is used to bear inertial load of the rudder face along hinge lines；Aerodynamic loading load-carrying construction 2 is used for
Bear rudder face aerodynamic loading.
It please refers to Fig.1 with shown in Fig. 2, the hinge linear load load-carrying construction 1 includes directly connecting with 4 back rest of stabilization
The box beam 11 that connects, the longitudinal joints 12 in the rudder face 3, bolt axle 13；The box beam 11 includes being located at aerofoil profile pair
Vertical clapboard 111, lower end rib 112, upper end rib 113, diaphragm plate 114 and box-like beam splice 115 in title face.
Further referring to shown in Fig. 2 and Fig. 4, the box-like beam splice 115 and the bolt axle 13 pass through self-locking nut
134 fix, and are equipped with customization bearing 131, to discharge the rotational freedom being connected on 3 directions herein.
It is preferred that when the bolt axle 13 and the customization bearing 131 connect, convex shoulder bushing 132 is provided with, to prevent
When the bolt axle 13 moves, collide with surrounding structure.
More preferably, in order to which the lubrication of the customization bearing 131 needs, it is provided with oiling groove in the bolt axle 13 and is equipped with
Pressure pump nozzle 133.
It refers to shown in Fig. 4 and Fig. 5, the bolt axle 13 and the longitudinal joints 12 are by connecting bolt 122 and self-locking
Nut 123 connects.
It is preferred that being provided with " track type " hole in the longitudinal joints 12, and " track type " slide bushing 121, institute are installed
It is more smaller than " track type " hole in the longitudinal joints 12 to state " track type " slide bushing 121 so that " track type " slides
It, can be relatively sliding in normal orientation in the rudder face plane of symmetry between bushing 121 and the bolt axle 13 and the longitudinal joints 12
It is dynamic.
Further referring to Fig. 5,13 auricle of bolt axle and 12 auricle of the longitudinal joints and described " track type "
The sum of 121 width of slide bushing is more than the 12 ears width of longitudinal joints so that bolt axle 13 and the longitudinal joints 12 it
Between, it can be slided along bolt hole axial direction is opposite.
It please refers to Fig.1 with shown in Fig. 3, the aerodynamic loading load-carrying construction 2 includes the suspension branch being located in the stabilization 4
Arm 21, the suspension joint 22 in the rudder face 3, the suspension arm 21 and the suspension joint 22 are by connecting bolt 24
It is connected with self-locking nut 25.
It is preferred that 21 internal pressure of suspension arm has oscillating bearing 211 so that the suspension arm 21 and suspension joint 22
Between can be relatively rotated around the ball centre of sphere in the oscillating bearing 211 in 3 direction degree of freedom.
More preferably, certain interval, and the pass are provided between 22 auricle of the suspension arm 21 and the suspension joint
211 inner ring upper and lower end face of bearings is pressed with slide bushing 23 so that can edge between the suspension arm 21 and suspension joint 22
Hinge lines direction is opposite to be slided.
More preferably, abrasion resistant convex shoulder piece set 221 is pressed on the suspension joint 22, to protect 22 auricle of suspension joint
Surplus is repaired in hole and offer.
Embodiment described above only expresses the several embodiments of the present invention, and description is more specific and detailed, but simultaneously
Cannot the limitation to the scope of the claims of the present invention therefore be interpreted as.It should be pointed out that for those of ordinary skill in the art
For, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to the guarantor of the present invention
Protect scope.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.
Claims (4)
1. a kind of large aircraft control surface suspension structure, it is characterised in that：It is held by hinge linear load load-carrying construction (1) and aerodynamic loading
Power structure (2) forms；Hinge linear load is by being located at the bolt axle (13) of stabilization (4) box beam (11) and its inside and being located at
Hinge linear load load-carrying construction (1) independent bearing that the internal longitudinal joints (12) of rudder face (3) is formed；Aerodynamic loading passes through position
In the pneumatic load that the suspension arm (21) in the stabilization (4) and the suspension joint (22) in the rudder face (3) form
Lotus load-carrying construction (2) independent bearing.
2. a kind of large aircraft control surface suspension structure according to claim 1, it is characterised in that：In the box beam (11)
Bolt axle (13) is connected by screw bolts with longitudinal joints (12), and the longitudinal joints (12) is provided with " track type " hole and is equipped with
" track type " bushing (121), to discharge junction along bolt axial direction translational degree of freedom and along the aircraft plane of symmetry normal direction translation from
By spending.
3. a kind of large aircraft control surface suspension structure according to claim 1, it is characterised in that：The bolt axle (13) is logical
It crosses box-like beam splice (115) to be fixed on box beam (11), and customization bearing is installed on the box-like beam splice (115)
(131), the customization bearing (131) can bear larger axial load and with aligning rotating function, to bear rudder face hinge
Chain linear load and the rotational freedom for discharging 3 directions in junction.
4. a kind of large aircraft control surface suspension structure according to claim 3, it is characterised in that：The customization bearing
(131) with bolt axle (13) assemble when, it is described customization bearing (131) inner ring both ends be equipped with convex shoulder bushing (132) with to avoid
During rotation, bolt axle (13) collides with neighbouring structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711051823.7A CN108082449B (en) | 2018-03-06 | 2018-03-06 | Large aircraft control surface suspension structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711051823.7A CN108082449B (en) | 2018-03-06 | 2018-03-06 | Large aircraft control surface suspension structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108082449A true CN108082449A (en) | 2018-05-29 |
| CN108082449B CN108082449B (en) | 2022-06-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711051823.7A Active CN108082449B (en) | 2018-03-06 | 2018-03-06 | Large aircraft control surface suspension structure |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109080814A (en) * | 2018-09-30 | 2018-12-25 | 西安爱生技术集团公司 | A kind of full-height foam core unmanned plane lifting rudder face shaft installing mechanism |
| CN109703744A (en) * | 2019-02-20 | 2019-05-03 | 西安爱生技术集团公司 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
| CN112373687A (en) * | 2020-11-17 | 2021-02-19 | 中航通飞华南飞机工业有限公司 | Large-scale seaplane rudder face suspension structure |
| CN114104264A (en) * | 2021-12-17 | 2022-03-01 | 江西洪都航空工业集团有限责任公司 | Control surface mounting structure |
| WO2024087990A1 (en) * | 2022-10-25 | 2024-05-02 | 峰飞航空科技(昆山)有限公司 | Aircraft and control surface hinge structure thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109080814A (en) * | 2018-09-30 | 2018-12-25 | 西安爱生技术集团公司 | A kind of full-height foam core unmanned plane lifting rudder face shaft installing mechanism |
| CN109703744A (en) * | 2019-02-20 | 2019-05-03 | 西安爱生技术集团公司 | A kind of unmanned plane aileron rudder face fast assembly and disassembly mechanism and assembly and disassembly methods |
| CN112373687A (en) * | 2020-11-17 | 2021-02-19 | 中航通飞华南飞机工业有限公司 | Large-scale seaplane rudder face suspension structure |
| CN114104264A (en) * | 2021-12-17 | 2022-03-01 | 江西洪都航空工业集团有限责任公司 | Control surface mounting structure |
| WO2024087990A1 (en) * | 2022-10-25 | 2024-05-02 | 峰飞航空科技(昆山)有限公司 | Aircraft and control surface hinge structure thereof |
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| Publication number | Publication date |
|---|---|
| CN108082449B (en) | 2022-06-10 |
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Effective date of registration: 20220428 Address after: 519040 building 201, 999 Jinhai Middle Road, Jinwan District, Zhuhai City, Guangdong Province Applicant after: SOUTH CHINA AIRCRAFT INDUSTRY CO., LTD. OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. Address before: 519040 AVIC Tongfei industrial base, aviation industrial park, Jinwan District, Zhuhai City, Guangdong Province Applicant before: R&D INSTITUTE OF CHINA AVIATION INDUSTRY GENERAL AIRCRAFT Co.,Ltd. |
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