CN108082449B - Large aircraft control surface suspension structure - Google Patents
Large aircraft control surface suspension structure Download PDFInfo
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- CN108082449B CN108082449B CN201711051823.7A CN201711051823A CN108082449B CN 108082449 B CN108082449 B CN 108082449B CN 201711051823 A CN201711051823 A CN 201711051823A CN 108082449 B CN108082449 B CN 108082449B
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- joint
- suspension
- control surface
- hinge line
- bearing
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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
Abstract
The invention provides a large airplane control surface suspension structure which consists of a hinge line load bearing structure (1) and a pneumatic load bearing structure (2); the hinge line load is independently loaded through a hinge line load bearing structure (1) consisting of a box-shaped beam (11) in the stabilizer (4), a bolt shaft (13) arranged in the stabilizer and an axial joint (12) in the control surface (3); the pneumatic load is independently borne by a pneumatic load bearing structure (2) consisting of the stabilizing surface (4) inner suspension support arm (21) and the control surface (3) inner suspension joint (22). According to the invention, the hinge line load bearing structure (1) is arranged at the root part of the control surface and the rear lower part of the stabilizing surface, so that a large opening at the front part of the control surface is avoided, and the pneumatic efficiency of the control surface is improved; the box beam (11) is directly connected with the tail fin butt joint, so that the force transmission is simple and direct, and the weight is light; different degrees of freedom are released through the combination of the bushing and the bearing and the reasonably arranged gap, so that the structures do not interfere with each other in work, and the work is reliable.
Description
Technical Field
The invention relates to an aircraft suspension structure, in particular to a large aircraft control surface suspension structure.
Background
The large aircraft rudder surface suspension structure must be capable of bearing 36Wg inertial load of the rudder surface along the hinge line in addition to bearing aerodynamic load of the rudder surface. Most of the existing large airplane control surface hinge line load bearing structures utilize a diagonal draw bar to combine with a control surface cantilever to bear the control surface hinge line load. In order to avoid collision between the control surface and the diagonal draw bar during rotation, a large opening needs to be formed in the front edge of the control surface, so that the aerodynamic efficiency of the control surface is seriously reduced; when the diagonal draw bar transmits the load of the hinge line to the rear beam of the stabilizing surface, the force transmission efficiency is low, and the structural weight cost is high.
Disclosure of Invention
In order to overcome the defects and shortcomings of the existing large-scale airplane control surface suspension structure, the invention aims to solve the technical problem of providing a control surface suspension structure design which is small in control surface opening, direct in force transmission, low in weight cost and reliable in work.
In order to solve the problems in the prior art, the technical scheme adopted by the invention is as follows: a large-scale aircraft rudder surface suspension structure comprises a hinge line load bearing structure 1 and a pneumatic load bearing structure 2; the hinge line load bearing structure 1 is formed by connecting a box beam 11 arranged on the stabilizer 4, a bolt shaft 13 in the box beam and an axial joint 12 arranged in the control surface 3 through bolts and is used for bearing the hinge line load of the control surface; the pneumatic load bearing structure 2 is formed by connecting a suspension support arm 21 arranged in the stabilizing surface 4 and a suspension joint 22 arranged in the control surface 3 through bolts and is used for bearing the pneumatic load of the control surface; the box beam 11 comprises a vertical partition plate 111, a lower end rib 112, an upper end rib 113, a transverse partition plate 114 and a box beam joint 115, and is connected with the bolt shaft 13 through the box beam joint 115.
As an improvement of the large aircraft rudder surface suspension structure of the present invention, the box-shaped beam joint 115 of the stabilizer is provided with a customized bearing 131, and the customized bearing 131 can bear a large axial load and has a self-aligning rotation function, so that the bolt shaft 13 and the box-shaped beam joint 115 can relatively rotate around the spherical center of the customized bearing 131 in 3 directions.
As a further improvement, shoulder bushes 132 are pressed on the upper and lower end faces of the inner ring of the custom bearing 131 to prevent the bolt shaft 13 from colliding with nearby structures during rotation.
As a further improvement, the bolt mounting hole on the axial joint 12 is a "racetrack" hole, and a "racetrack" sliding bush 121 is mounted on the "racetrack" sliding bush 121, and the "racetrack" sliding bush 121 is slightly smaller than the racetrack "hole on the axial joint 12, so that the" racetrack "sliding bush 121 and the bolt shaft 13 can slide relatively in the normal direction in the control plane symmetry plane between the axial joint 12 and the bolt shaft 13.
As a further improvement, a gap is provided between the lug of the bolt shaft 13 and the lug of the axial joint 12, so that the bolt shaft 13 and the "race track" sliding bush 121 can slide relatively in the axial direction of the bolt hole with respect to the axial joint 12.
As a further improvement, the bolt shaft 13 is provided with a grease groove, and a pressure grease nipple 133 is mounted to provide lubrication for the custom bearing 131.
As an improvement of the large aircraft rudder surface suspension structure, a joint bearing 211 is pressed on the suspension arm 21, so that the suspension arm 21 and the suspension joint 22 can rotate relatively around the spherical center in the joint bearing 211 in 3 directions.
As a further improvement, a certain gap is arranged above and below the lug of the suspension arm 21 and the suspension joint 22, and a sliding bush 23 is pressed on the upper and lower end surfaces of the inner ring of the knuckle bearing 211, so that the suspension arm 21 and the suspension joint 22 can relatively slide along the hinge line direction.
As a further improvement, wear shoulder bushing 221 is pressed onto suspension joint 22 such that sliding bushing 23 fits between the bolt and wear shoulder bushing 221 to protect the tab hole of suspension joint 22 and provide a repair margin.
Compared with the prior art, the large airplane control surface suspension structure has the advantages that: the front edge of the control surface does not need a large opening, so that the reduction of the aerodynamic efficiency of the control surface is avoided; the box-shaped beam 11 structure is directly connected with the tail fin butt joint, so that force transmission is simple and direct, and weight is saved; the pneumatic load bearing structure 2 and the hinge line load bearing structure 1 release corresponding translational or rotational freedom degrees through the combination of the bushing and the bearing and a reasonably set gap value, so that the pneumatic load bearing structure and the hinge line load bearing structure do not interfere with each other in work, and have clear functions and reliable work.
Drawings
Fig. 1 is a schematic layout of a large aircraft control surface suspension structure, in which:
1 is a hinge line load bearing structure; 2 is a pneumatic load bearing structure;
3 is a control surface; 4, a stabilizing face;
A-A is the connection section of the suspension support arm and the suspension joint.
Fig. 2 is an enlarged detailed view of the hinge line load-bearing structure 1 in fig. 1, wherein:
11 is a box beam; 111 is a vertical clapboard;
112 is a lower end rib; 113 is an upper end rib;
114 is a diaphragm plate; 115 is a box beam joint;
12 is an axial joint; 13 is a bolt shaft;
B-B is a sectional view of the connection of the axial joint and the bolt shaft.
FIG. 3 is a cross-sectional view of the A-A suspension arm and suspension joint of FIG. 1, wherein:
21 is a suspension arm; 211 is a joint bearing;
22 is a suspension joint; 221 is an anti-abrasion shoulder bush;
23 is a sliding bush; 24 is a connecting bolt;
25 is a self-locking nut;
FIG. 4 is a sectional view of the connection between the axial joint B-B and the bolt shaft in FIG. 2, wherein:
121 is a "race track" bushing; 131 is a custom bearing;
132 is a bushing; 133 is a pressure grease nipple;
134 is a self-locking nut; C-C is a connecting sectional view of the axial joint.
FIG. 5 is a cross-sectional view of the C-C axial joint connection of FIG. 4, wherein:
122 is a connecting bolt; 123 is a coupling nut.
Detailed Description
The invention relates to a large airplane control surface suspension structure, which is a specific embodiment of the large airplane control surface suspension structure.
Referring to fig. 1, the large aircraft control surface suspension structure is used for connecting a control surface 3 and a stabilizing surface 4; the hinge line load bearing structure 1 is used for bearing the inertial load of the control surface along the hinge line; the pneumatic load bearing structure 2 is used for bearing the pneumatic load of the control surface.
Referring to fig. 1 and 2, the hinge line load bearing structure 1 includes a box beam 11 directly connected to the rear beam of the stabilizer 4, an axial joint 12 located in the control surface 3, and a bolt shaft 13; the box beam 11 comprises a vertical partition 111, a lower end rib 112, an upper end rib 113, a transverse partition 114 and a box beam joint 115, which are located in the symmetry plane of the airfoil.
Referring further to fig. 2 and 4, the box beam joint 115 and the bolt shaft 13 are secured by a self-locking nut 134 and fitted with a custom bearing 131 to release the rotational freedom of the connection thereto in 3 directions.
Preferably, shoulder bushings 132 are provided to prevent the bolt shaft 13 from colliding with surrounding structures during movement when the bolt shaft 13 and the custom bearing 131 are coupled.
Preferably, the bolt shaft 13 is provided with a grease groove and a pressure grease nipple 133 for lubrication of the custom bearing 131.
Referring to fig. 4 and 5, the bolt shaft 13 and the axial joint 12 are connected by a connecting bolt 122 and a self-locking nut 123.
Preferably, the axial joint 12 is provided with a "racetrack" hole, and a "racetrack" sliding bush 121 is installed, and the "racetrack" sliding bush 121 is slightly smaller than the "racetrack" hole on the axial joint 12, so that the "racetrack" sliding bush 121 and the bolt shaft 13 can slide relatively in the normal direction in the control plane symmetry plane between the axial joint 12 and the bolt shaft.
With further reference to fig. 5, the sum of the widths of the tabs of the bolt shaft 13 and the axial joint 12 and the "race track" sliding bush 121 is greater than the width of the tabs of the axial joint 12, so that the bolt shaft 13 and the axial joint 12 can slide relative to each other in the axial direction of the bolt hole.
Referring to fig. 1 and 3, the pneumatic load bearing structure 2 includes a suspension arm 21 located in the stabilizing surface 4, and a suspension joint 22 located in the control surface 3, and the suspension arm 21 and the suspension joint 22 are connected by a connecting bolt 24 and a self-locking nut 25.
Preferably, the suspension arm 21 presses the joint bearing 211 so that the suspension arm 21 and the suspension joint 22 can rotate relative to each other in 3 degrees of freedom about the spherical center of the joint bearing 211.
Preferably, a certain gap is provided between the suspension arm 21 and the lug of the suspension joint 22, and a sliding bush 23 is pressed on the upper and lower end surfaces of the inner ring of the knuckle bearing 211, so that the suspension arm 21 and the suspension joint 22 can relatively slide along the hinge line direction.
Preferably, a wear shoulder bushing 221 is pressed into suspension joint 22 to protect lug holes of suspension joint 22 and provide a repair margin.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (4)
1. The utility model provides a large-scale aircraft rudder face suspended structure which characterized in that: the hinge line load bearing structure consists of a hinge line load bearing structure (1) and a pneumatic load bearing structure (2); the hinge line load is independently borne by a hinge line load bearing structure (1) consisting of a box-shaped beam (11) positioned on the stabilizer (4), a bolt shaft (13) arranged in the box-shaped beam and an axial joint (12) arranged in the control surface (3); the pneumatic load is independently borne by a pneumatic load bearing structure (2) consisting of a suspension support arm (21) positioned in the stabilizer (4) and a suspension joint (22) positioned in the control surface (3); a joint bearing (211) is pressed on the suspension arm (21), so that the suspension arm (21) and the suspension joint (22) can relatively rotate around the spherical center in the joint bearing (211) in 3 directions; and a certain gap is formed between the suspension support arm (21) and the lug of the suspension joint (22) from top to bottom, and a sliding bush (23) is pressed on the upper end surface and the lower end surface of the inner ring of the joint bearing (211), so that the suspension support arm (21) and the suspension joint (22) can relatively slide along the direction of a hinge line.
2. The large aircraft control surface suspension structure according to claim 1, characterized in that: the box-shaped beam (11) is characterized in that a bolt shaft (13) is connected with an axial joint (12) through bolts, the axial joint (12) is provided with a runway-shaped hole and a runway-shaped lining (121) for releasing the axial translational freedom degree of the joint along the bolts and the normal translational freedom degree along the plane of symmetry.
3. The large aircraft control surface suspension structure according to claim 1, characterized in that: the bolt shaft (13) is fixed on the box-shaped beam (11) through a box-shaped beam joint (115), a customized bearing (131) is installed on the box-shaped beam joint (115), and the customized bearing (131) can bear large axial load and has a self-aligning rotation function so as to bear the load of a hinge line of a control surface and release the rotation freedom degree of 3 directions of a joint.
4. Large aircraft rudder surface suspension structure according to claim 3, characterized in that: when the custom bearing (131) is assembled with the bolt shaft (13), shoulder bushes (132) are arranged at two ends of an inner ring of the custom bearing (131) to avoid collision of the bolt shaft (13) with nearby structures during rotation.
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 |
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| Publication Number | Publication Date |
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| CN108082449A CN108082449A (en) | 2018-05-29 |
| CN108082449B true CN108082449B (en) | 2022-06-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201711051823.7A Active CN108082449B (en) | 2018-03-06 | 2018-03-06 | Large aircraft control surface suspension structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN112373687B (en) * | 2020-11-17 | 2022-11-01 | 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 |
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| SE513583C2 (en) * | 1999-12-20 | 2000-10-02 | Saab Ab | Device at a rudder for an air or watercraft |
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| US7731125B2 (en) * | 2008-03-06 | 2010-06-08 | Abe Karem | Compact stowage of transport aircraft |
| GB0810460D0 (en) * | 2008-06-09 | 2008-07-09 | Airbus Uk Ltd | Support assembly |
| ES2382062B1 (en) * | 2008-12-04 | 2013-04-26 | Airbus Operations, S.L. | STABILIZING AND DIRECTIONAL AIRCRAFT CONTROL SURFACE |
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| US9308988B2 (en) * | 2013-01-16 | 2016-04-12 | Otto Aviation Group | Aircraft main landing gear and method of operating the same |
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2018
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| CN108082449A (en) | 2018-05-29 |
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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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