CN114013679B - Adjustable connection method for tail cone with assembly compensation - Google Patents
Adjustable connection method for tail cone with assembly compensation Download PDFInfo
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- CN114013679B CN114013679B CN202111328954.1A CN202111328954A CN114013679B CN 114013679 B CN114013679 B CN 114013679B CN 202111328954 A CN202111328954 A CN 202111328954A CN 114013679 B CN114013679 B CN 114013679B
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 210000001503 joint Anatomy 0.000 claims abstract description 39
- 230000001360 synchronised effect Effects 0.000 claims description 8
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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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
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
Abstract
The invention belongs to the field of aircraft design, and provides an adjustable connection method for a tail cone with assembly compensation. The scheme aims at the connection between the tail cone and the front section of the rear machine body in a 5-point hyperstatic structure mode, and assembly compensation is realized at a calibration joint through 2 eccentric bushings sleeved inside and outside; assembly compensation is achieved at the backup butt joint by 2 eccentric bushings rotating synchronously with the bolts. The invention has simple and compact structure and mature process, can solve the problem that the multipoint connection scheme has ultrahigh assembly and processing precision requirements on the connecting pieces, reduces the probability of inconsistent assembly, improves the matching precision among the connecting pieces, and ensures that the load transmission among the structures is more efficient.
Description
Technical Field
The invention belongs to the field of aircraft design, and relates to an adjustable connection method for a tail cone with an assembly compensation function.
Background
In aircraft design, the tail cone and the aft fuselage forward section are typically manufactured separately and then butt assembled. In order to improve the assembly efficiency, three groups of main butt joints, one group of standby butt joints and one group of calibration joints are often adopted for butt joint. Each group of the joint comprises two parts which are respectively arranged on the front section and the tail cone of the rear machine body. The three groups of main butt joints can completely limit 6 degrees of freedom of the tail cone, and the standby butt joints and the calibration joints are redundant connection points designed for meeting the damage safety requirements.
The five sets of joints have the over-positioning problem during butt joint, and due to manufacturing and assembly errors, normal installation of all the joints is difficult to ensure. The traditional solution is to coordinate by adopting standard sample pieces, the processing and assembling precision requirements of each joint are high, and the manufacturing precision is often required to be reduced to a certain extent at the expense of the load carrying capacity.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the tail cone adjustable connection method with the assembly compensation.
In order to achieve the above purpose, the specific technical method adopted by the invention is as follows:
an adjustable connection method of a tail cone with assembly compensation aims at connecting the tail cone with the front section of a rear machine body in a 5-point hyperstatic structure mode, and the assembly compensation is realized at a calibration joint through 2 eccentric bushings which are sleeved inside and outside. The connection method is applied to an aircraft rear fuselage, wherein the aircraft rear fuselage comprises a tail cone 1 and a rear fuselage front section 2, the tail cone 1 and the rear fuselage front section 2 are connected through a group of calibration joints 3, three groups of main butt joints 4 and a group of standby butt joints 5, the connection at the positions of the traditional three groups of main butt joints 4 can limit 6 degrees of freedom of the tail cone 1, and in order to ensure assembly coordination, the connection mode at the positions of the calibration joints 3 and the standby butt joints 5 needs to have an assembly compensation function.
The connection mode of the calibration joint 3 is as follows: by inserting a pin 6 fixed on the front section 2 of the rear fuselage into the inner bore of a knuckle bearing 7 mounted on the tailcone 1. In order to realize assembly compensation, an outer eccentric bushing 9 and an inner eccentric bushing 10 are added between a bearing seat 8 fixed on the tail cone 1 and the knuckle bearing 7, namely, the assembly compensation is realized by adding an inner eccentric bushing and an outer eccentric bushing 2 between the bearing seat 8 and the knuckle bearing 7. The outer eccentric bushing 9 is installed in the bearing seat 8, and can rotate relatively around the hole axis of the bearing seat 8, and after the outer eccentric bushing rotates to a required position, the relative position of the outer eccentric bushing 9 and the bearing seat can be locked, and the outer eccentric bushing is specifically: after the outer eccentric bushing 9 and the bearing seat 8 rotate to the required positions and the inner eccentric bushing 9 and the bearing seat 8 are mutually attached along the X direction, the relative positions of the outer eccentric bushing 9 and the bearing seat 8 are mutually matched with the boss structure 23 on the bearing seat 8 through the outer spline structure on the flange of the outer eccentric bushing 9 to realize locking. The inner eccentric bushing 10 is installed in the outer eccentric bushing 9, and can rotate relatively around the hole axis of the outer eccentric bushing 9, and after the inner eccentric bushing rotates to a required position, the relative position of the inner eccentric bushing and the outer eccentric bushing can be locked, and the inner eccentric bushing can be locked: after the inner eccentric bushing 10 and the outer eccentric bushing 9 rotate to the required positions and are mutually attached along the X direction, the relative positions of the inner eccentric bushing 10 and the outer eccentric bushing 9 are mutually matched with the boss structure 22 on the outer eccentric bushing 9 through the outer spline structure on the flange of the inner eccentric bushing 10 to realize locking. The eccentric amount of the outer eccentric bushing 9 is the same as that of the inner eccentric bushing 10, and the assembly compensation range is zero to the sum of the eccentric amounts of the outer eccentric bushing and the inner eccentric bushing. The outer eccentric bush 9 and the inner eccentric bush 10 are rotationally adjusted according to the actual different coaxial conditions of the pin shaft 6 and the inner hole of the bearing seat 8, so that the pin shaft 6 and the inner hole of the knuckle bearing 7 are coaxial.
The connection mode of the spare butt joint 5 is as follows: a double-lug support assembly 11 is fixed on the rear fuselage front section 2, and an upper flange bushing 12 and a lower flange bushing 13 are mounted on the double-lug support assembly 11; the tailcone 1 is fixedly provided with a single-lug support assembly 14, and the single-lug support assembly 14 is provided with a joint bearing 15. The double-lug support assembly 11 and the single-lug support assembly 14 are connected through bolts 16, an upper eccentric bushing 17, a lower eccentric bushing 18, a flat washer 19, a groove top nut 20 and cotter pins 21. Specific: the upper eccentric bushing 17 is a sliding bushing and is arranged in the upper flange bushing 12; the lower eccentric bushing 18 is a sliding bushing and is arranged in the lower flange bushing 13; the bolt 16 sequentially passes through an upper eccentric bushing 17, a knuckle bearing 15, a lower eccentric bushing 18, a flat washer 19 and a groove top nut 20. The eccentric amounts of the upper eccentric bushing 17 and the lower eccentric bushing 18 are the same, and the upper eccentric bushing and the lower eccentric bushing can synchronously rotate with the bolt 16. The bolt 16 can be locked after rotating to a required position, and the assembly coordination is ensured by rotating the adjusting bolt 16, the upper eccentric bushing 17 and the lower eccentric bushing 18.
Furthermore, the invention can design a plurality of groups of upper eccentric bushing 17 and lower eccentric bushing 18 bushing groups with different eccentric amounts, and the upper eccentric bushing 17 and the lower eccentric bushing 18 bushing groups are selected according to the actual different coaxial conditions of the intersection point holes of the double-lug support assembly 11 and the single-lug support assembly 14 during assembly.
Further, the synchronous rotation of the bolt 16 and the upper eccentric bushing 17 is realized by the mutual cooperation of the groove structure at the top of the bolt 16 and the boss structure 25 on the upper eccentric bushing 17.
Further, the synchronous rotation of the bolt 16 and the lower eccentric bushing 18 is achieved by the cooperation of the bottom planar structure 26 of the bolt 16 and the planar structure 27 of the inner surface of the lower eccentric bushing 18.
Further, the position locking of the upper eccentric bushing 17 is realized by the mutual matching of the external spline structure of the upper eccentric bushing 17 and the internal spline structure on the limiting plate 24, so that the position locking of the bolt 16 is realized. The limiting plate 24 is finally fixed to the binaural holder assembly 11.
The invention has the beneficial effects that:
(1) According to the invention, the problem that the multipoint connection method has ultrahigh assembly and machining precision requirements on the connecting pieces is solved by designing the assembly compensation method, the assembly uncoordinated probability is reduced, the matching precision among the connecting pieces is improved, and the load transmission among the structures is more efficient.
(2) The invention has simple and compact structure and mature process.
(3) The application range is wide. The invention is applicable to the field of aircraft design and other mechanical design as long as the joint connection mode is similar to that of a calibration joint and a standby connection joint and is an over-constraint connection point.
Drawings
FIG. 1 is a schematic view of the relative positional relationship between the tail cone and the front section of the rear fuselage of the present invention.
FIG. 2 is a schematic view of the arrangement of the butt joint of the tail cone and the front section of the rear fuselage and the method for limiting the degree of freedom according to the present invention.
FIG. 3 is a horizontal cross-sectional view of the calibration joint of the present invention.
FIG. 4 is a schematic diagram of the relative position locking of the inner eccentric bushing and the outer eccentric bushing of the present invention.
Fig. 5 is a schematic diagram of the relative position locking of the bearing housing and the outer eccentric bushing of the present invention.
FIG. 6 is a schematic diagram of a method of connecting a spare butt joint according to the present invention.
Fig. 7 is a schematic diagram of the synchronous rotation of the bolt and the upper eccentric bushing of the present invention.
Fig. 8 is a schematic diagram of the synchronous rotation of the bolt and the lower eccentric bushing of the present invention.
Fig. 9 is a schematic diagram of the bolt position locking of the present invention.
In the figure: 1, a tail cone; 2 a rear fuselage front section; 3, calibrating the joint; 4, a main butt joint; 5, a spare butt joint; 6, a pin shaft; 7, a joint bearing is arranged on the bearing seat; 8 bearing seats; 9 an outer eccentric bushing; 10 inner eccentric bushing; a binaural support assembly; 12 upper flange bushing; 13 a lower flange bushing; 14 a single ear mount assembly; 15 a joint bearing on the single-lug support assembly; 16 bolts; 17 an eccentric bushing; 18 lower eccentric bushings; 19 plain washers; a 20 groove top nut; 21 cotter pin; 22 an upper boss structure of the outer eccentric bushing; 23, a boss structure on the bearing seat; 24 limiting plates; an upper boss structure of the upper eccentric bushing 25; 26 a planar structure on the bolt; 27 lower eccentric bushing upper planar structure.
Detailed Description
The invention is further described below with reference to the drawings and technical methods.
The invention discloses an adjustable connection method of a tail cone with assembly compensation, which is applied to an aircraft rear fuselage, wherein the aircraft rear fuselage comprises the tail cone 1 and a rear fuselage front section 2, the tail cone 1 and the rear fuselage front section 2 are connected through a group of calibration joints 3, three groups of main butt joints 4 and a group of standby butt joints 5, the connection of the traditional three groups of main butt joints 4 can limit 6 degrees of freedom of the tail cone 1, and in order to ensure assembly coordination, the connection mode of the calibration joints 3 and the standby butt joints 5 needs to have the assembly compensation function.
As shown in fig. 1 and 2, an aircraft rear fuselage comprises a tail cone 1 and a rear fuselage front section 2, which are connected by a set of calibration joints 3, three sets of main butt joints 4 and a set of spare butt joints 5. The connection at the three sets of main butt joints 4 may already limit 6 degrees of freedom of the tailcone.
As shown in fig. 3, the connection at the calibration joint of the present invention is realized by inserting the pin shaft 6 fixed on the front section 2 of the rear fuselage into the inner hole of the knuckle bearing 7 mounted on the tail cone, and the assembly compensation is realized by adding the outer eccentric bushing 9 and the inner eccentric bushing 10 between the bearing seat 8 and the knuckle bearing 7. The eccentric amount of the outer eccentric bush 9 is the same as that of the inner eccentric bush 10, and the assembly compensation range is zero to the sum of the eccentric amounts of the outer eccentric bush and the inner eccentric bush. The outer eccentric bush 9 and the inner eccentric bush 10 are rotationally adjusted according to the actual different coaxial conditions of the pin shaft 6 and the inner hole of the bearing seat 8, so that the pin shaft 6 and the inner hole of the knuckle bearing 7 are coaxial.
As shown in fig. 4, the inner eccentric bush 10 is mounted in the outer eccentric bush 9, and can rotate relatively around the hole axis of the outer eccentric bush 9 to a required position, and after the inner eccentric bush 10 and the outer eccentric bush are mutually attached along the X direction, the relative positions of the inner eccentric bush 10 and the outer eccentric bush 9 are mutually matched and locked through an external spline structure on the flange of the inner eccentric bush 10 and a boss structure 22 on the outer eccentric bush 9.
As shown in fig. 5, the outer eccentric bush 9 is installed in the bearing seat 8, and can rotate relatively around the hole axis of the bearing seat 8 to a required position, and after the inner eccentric bush 9 and the bearing seat 8 are mutually attached in the X direction, the relative positions of the outer eccentric bush 9 and the bearing seat 8 are mutually matched and locked through an outer spline structure on the flange of the outer eccentric bush 9 and a boss structure 23 on the bearing seat 8.
As shown in fig. 6, at the spare butt joint, 1 binaural support assembly 11 is fixed on the front section of the rear fuselage, and an upper flange bushing 12 and a lower flange bushing 13 are mounted on the binaural support assembly 11; the tail cone is fixedly provided with 1 single-lug support assembly 14, and the single-lug support assembly 14 is provided with a joint bearing 15. The binaural mount assembly 11, the monaural mount assembly 14 are connected by bolts 16, upper eccentric bushings 17, lower eccentric bushings 18, flat washers 19, channel top nuts 20, cotter pins 21. The upper eccentric bushing 17 is a sliding bushing installed in the upper flange bushing 12; the lower eccentric bushing 18 is a sliding bushing, installed in the lower flange bushing 13; the bolts 16 pass through the upper eccentric bushing 17, the knuckle bearing 15, the lower eccentric bushing 18, the flat washer 19, and the groove top nut 10 in order. The upper eccentric bushing 17 and the lower eccentric bushing 18 have the same eccentric amount, and can rotate synchronously with the bolt 16. And a plurality of groups of upper eccentric bushing 17 and lower eccentric bushing 18 bushing groups with different eccentric amounts are designed, and the adjustment bolts 16, the upper eccentric bushing 17 and the lower eccentric bushing 18 are rotated according to the actual different coaxial conditions of the intersection point holes of the double-lug support assembly 11 and the single-lug support assembly 14 when in assembly, so that the assembly coordination is ensured.
As shown in fig. 7, the synchronous rotation of the bolt 16 and the upper eccentric bushing 17 is achieved by the cooperation of the groove structure on the bolt 16 and the boss structure 25 on the upper eccentric bushing 17.
As shown in fig. 8, the synchronous rotation of the bolt 16 and the lower eccentric bushing 18 is achieved by the cooperation of the flat surface structure 26 on the bolt 16 and the flat surface structure 27 on the lower eccentric bushing 18.
As shown in fig. 9, the position locking of the upper eccentric bushing 17 is achieved by the cooperation of the internal spline structure on the limiting plate 24 and the external spline structure of the upper eccentric bushing 17, thereby achieving the position locking of the bolt 16. The limiting plate 24 is finally fixed to the binaural holder assembly 11.
The examples described above represent only embodiments of the invention and are not to be understood as limiting the scope of the patent of the invention, it being pointed out that several variants and modifications may be made by those skilled in the art without departing from the concept of the invention, which fall within the scope of protection of the invention.
Claims (5)
1. An adjustable connection method of a tail cone with assembly compensation is applied to an aircraft rear fuselage, wherein the aircraft rear fuselage comprises a tail cone (1) and a rear fuselage front section (2), and the tail cone and the rear fuselage are connected through a group of calibration joints (3), three groups of main butt joints (4) and a group of standby butt joints (5), and is characterized in that the connection mode of the calibration joints (3) and the standby butt joints (5) is required to have the assembly compensation function;
the connection mode of the calibration joint (3) is as follows: is realized by inserting a pin shaft (6) fixed on the front section (2) of the rear machine body into an inner hole of a joint bearing (7) arranged on the tail cone (1); the assembly compensation is realized by adding an inner eccentric bushing and an outer eccentric bushing between the bearing seat (8) and the knuckle bearing (7); the outer eccentric bushing (9) is arranged in the bearing seat (8), the outer eccentric bushing and the bearing seat can rotate relatively around the hole axis of the bearing seat (8), and after the outer eccentric bushing and the bearing seat rotate to the required position, the relative position of the outer eccentric bushing and the bearing seat can be locked, and the outer eccentric bushing can be specifically: the relative positions of the outer eccentric bushing (9) and the bearing seat (8) are mutually matched with a boss structure (23) on the bearing seat (8) through an outer spline structure on a flange of the outer eccentric bushing (9) to realize locking; the inner eccentric bushing (10) is arranged in the outer eccentric bushing (9), the inner eccentric bushing and the outer eccentric bushing can relatively rotate around the hole axis of the outer eccentric bushing (9), and after the inner eccentric bushing and the outer eccentric bushing rotate to the required positions, the relative positions of the inner eccentric bushing and the outer eccentric bushing can be locked, and the inner eccentric bushing can be specifically: the relative positions of the inner eccentric bushing (10) and the outer eccentric bushing (9) are mutually matched with a boss structure (22) on the outer eccentric bushing (9) through an external spline structure on a flange of the inner eccentric bushing (10) to realize locking; the eccentric amount of the outer eccentric bushing (9) is the same as that of the inner eccentric bushing (10), and the assembly compensation range is zero to the sum of the eccentric amounts of the outer eccentric bushing and the inner eccentric bushing; the outer eccentric bushing (9) and the inner eccentric bushing (10) are rotationally adjusted according to the actual different coaxiality of the pin shaft (6) and the inner hole of the bearing seat (8), so that the pin shaft (6) and the inner hole of the knuckle bearing (7) are coaxial;
the connection mode of the spare butt joint (5) is as follows: a double-lug support assembly (11) is fixed on the front section (2) of the rear machine body, and an upper flange bushing (12) and a lower flange bushing (13) are arranged on the double-lug support assembly (11); a single-lug support assembly (14) is fixed on the tail cone (1), and a joint bearing (15) is arranged on the single-lug support assembly (14); the double-lug support assembly (11) and the single-lug support assembly (14) are connected through bolts (16), an upper eccentric bushing (17), a lower eccentric bushing (18), a flat washer (19) and a groove top nut (20); specific: the upper eccentric bushing (17) is a sliding bushing and is arranged in the upper flange bushing (12); the lower eccentric bushing (18) is a sliding bushing and is arranged in the lower flange bushing (13); the bolt (16) sequentially passes through the upper eccentric bushing (17), the knuckle bearing (15), the lower eccentric bushing (18), the flat washer (19) and the groove top nut (20); the eccentric amounts of the upper eccentric bushing (17) and the lower eccentric bushing (18) are the same, and the upper eccentric bushing and the lower eccentric bushing can synchronously rotate with the bolt (16); the bolt (16) can be locked after rotating to a required position, and the assembly coordination is ensured by rotating the adjusting bolt (16), the upper eccentric bushing (17) and the lower eccentric bushing (18).
2. The adjustable connecting method of the tail cone with assembly compensation according to claim 1, wherein a plurality of groups of upper eccentric bushings (17) and lower eccentric bushings (18) with different eccentric amounts can be designed, and the assembly is selected according to the actual different axial conditions of intersection holes of the double-lug support assembly (11) and the single-lug support assembly (14).
3. The adjustable connection method of a tailcone with assembly compensation according to claim 1, characterized in that the synchronous rotation of the bolt (16) and the upper eccentric bushing (17) is achieved by the cooperation of a groove structure at the top of the bolt (16) and a boss structure (25) on the upper eccentric bushing (17).
4. A tailcone adjustable connection method with assembly compensation according to claim 1, characterized in that the synchronous rotation of the bolt (16) and the lower eccentric bushing (18) is achieved by the co-operation of the bottom planar structure (26) of the bolt (16) and the planar structure (27) of the inner surface of the lower eccentric bushing (18).
5. The adjustable connection method of the tail cone with assembly compensation according to claim 1, characterized in that the position locking of the upper eccentric bushing (17) is realized by the mutual cooperation of an external spline structure of the upper eccentric bushing (17) and an internal spline structure on the limiting plate (24), thereby realizing the position locking of the bolt (16); the limiting plate (24) is finally fixed on the double-lug support assembly (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111328954.1A CN114013679B (en) | 2021-11-10 | 2021-11-10 | Adjustable connection method for tail cone with assembly compensation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111328954.1A CN114013679B (en) | 2021-11-10 | 2021-11-10 | Adjustable connection method for tail cone with assembly compensation |
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| Publication Number | Publication Date |
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| CN114013679A CN114013679A (en) | 2022-02-08 |
| CN114013679B true CN114013679B (en) | 2024-01-26 |
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| CN202111328954.1A Active CN114013679B (en) | 2021-11-10 | 2021-11-10 | Adjustable connection method for tail cone with assembly compensation |
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| CN102417028A (en) * | 2010-09-24 | 2012-04-18 | 空中客车西班牙运营有限责任公司 | Rear fuselage of an aircraft |
| CN203345196U (en) * | 2013-01-05 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Airplane body structure of airplane |
| CN106672197A (en) * | 2016-12-26 | 2017-05-17 | 中国航空工业集团公司西安飞机设计研究所 | Cargo hold floor longitudinal beam and blocking wall connecting structure |
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| CN111059140A (en) * | 2019-12-25 | 2020-04-24 | 中国航空工业集团公司西安飞机设计研究所 | Clamping stagnation prevention hinge structure |
| CN211001802U (en) * | 2019-11-28 | 2020-07-14 | 上海航空工业(集团)有限公司 | Eccentric bushing adjusting mechanism capable of achieving linear adjustment of track |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10815818B2 (en) * | 2017-07-18 | 2020-10-27 | Raytheon Technologies Corporation | Variable-pitch vane assembly |
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2021
- 2021-11-10 CN CN202111328954.1A patent/CN114013679B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1818405A (en) * | 2004-12-16 | 2006-08-16 | 斯奈克玛公司 | Connection device of adjustable length between two parts |
| CN102417028A (en) * | 2010-09-24 | 2012-04-18 | 空中客车西班牙运营有限责任公司 | Rear fuselage of an aircraft |
| CN203345196U (en) * | 2013-01-05 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Airplane body structure of airplane |
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| CN211001802U (en) * | 2019-11-28 | 2020-07-14 | 上海航空工业(集团)有限公司 | Eccentric bushing adjusting mechanism capable of achieving linear adjustment of track |
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| CN114013679A (en) | 2022-02-08 |
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