CN114013679A - Adjustable connecting method for tail cone with assembly compensation - Google Patents
Adjustable connecting method for tail cone with assembly compensation Download PDFInfo
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- CN114013679A CN114013679A CN202111328954.1A CN202111328954A CN114013679A CN 114013679 A CN114013679 A CN 114013679A CN 202111328954 A CN202111328954 A CN 202111328954A CN 114013679 A CN114013679 A CN 114013679A
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- 238000000034 method Methods 0.000 title claims abstract description 23
- 210000001503 joint Anatomy 0.000 claims abstract description 39
- 230000001360 synchronised effect Effects 0.000 claims description 8
- 230000015572 biosynthetic process Effects 0.000 claims 2
- 230000005540 biological transmission Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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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
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- 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)
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Abstract
The invention belongs to the field of airplane design and provides an adjustable connecting method of a tail cone with assembly compensation. The proposal aims at the connection between the tail cone and the front section of the rear fuselage in a 5-point statically indeterminate structure form, and the assembly compensation is realized at the calibration joint through 2 eccentric bushings which are sleeved inside and outside; assembly compensation is achieved at the spare butt joint by 2 eccentric bushings rotating synchronously with the bolt. 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 assembly incongruity, improves the matching precision among the connecting pieces, and leads the load transmission among the structures to be more efficient.
Description
Technical Field
The invention belongs to the field of airplane design, and relates to an adjustable connecting method of 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 adopted for butt joint. Each group of joints comprises two parts which are respectively arranged on the front section of the rear machine body and the tail cone. Three sets of primary butt joints have been able to completely constrain the 6 degrees of freedom of the tail cone, and the spare butt joint and the calibration joint are redundant connection points designed to meet the breakage safety requirements.
The five sets of joints have an over-positioning problem during butt joint, and due to manufacturing and assembling errors, normal installation of all the joints is difficult to guarantee. The traditional solution is to use standard sample pieces for coordination, the machining and assembling precision requirements of each joint are high, and the manufacturing precision is often reduced at the expense of the load transfer capacity to a certain extent.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the adjustable connecting method of the tail cone with the assembly compensation, which has low requirement on the manufacturing precision and is easy to assemble and coordinate, so that the matching precision of redundant connecting points is improved, and the overall fatigue performance of the structure is improved.
In order to achieve the purpose, the invention adopts the following specific technical method:
a tail cone adjustable connection method with assembly compensation aims at connection between a tail cone and a front section of a rear machine body in a 5-point statically indeterminate structure mode, and assembly compensation is achieved through 2 eccentric bushings which are sleeved inside and outside at a calibration joint. The method is applied to the rear fuselage of the airplane, wherein the rear fuselage of the airplane comprises a tail cone 1 and a rear fuselage front section 2 which 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 the assembly coordination, the connection mode 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: the pin shaft 6 fixed on the front section 2 of the rear fuselage is inserted into an inner hole of a joint bearing 7 arranged on the tail cone 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 bush 9 is installed in the bearing seat 8, and can rotate relatively around the hole axis of the bearing seat 8 between the two, and after rotating to the required position, the relative position of the two can be locked, specifically: after the outer eccentric bushing 9 and the bearing seat 8 rotate to the required positions and the inner eccentric bushing 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 through an outer spline structure on a flange of the outer eccentric bushing 9 and a boss structure 23 on the bearing seat 8 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 10 rotates to a required position, the relative position of the inner eccentric bushing and the outer eccentric bushing can be locked, specifically: after the inner eccentric bushing 10 and the outer eccentric bushing 9 are rotated to a required position and the inner eccentric bushing and the outer eccentric bushing are attached to each other along the X direction, the relative positions of the inner eccentric bushing and the outer eccentric bushing are locked by the mutual matching of the outer spline structure on the flange of the inner eccentric bushing 10 and the boss structure 22 on the outer eccentric bushing 9. The eccentric amounts of the outer eccentric bushing 9 and the inner eccentric bushing 10 are the same, and the assembly compensation range is zero to the sum of the eccentric amounts of the two. The outer eccentric bush 9 and the inner eccentric bush 10 are rotationally adjusted according to the actual non-coaxial condition of the inner holes of the pin shaft 6 and the bearing seat 8, so that the pin shaft 6 and the inner hole of the joint 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 installed on the single-lug support assembly 14. The double-lug support assembly 11 and the single-lug support assembly 14 are connected through a bolt 16, an upper eccentric bushing 17, a lower eccentric bushing 18, a flat washer 19, a groove top nut 20 and a split pin 21. Specifically, the method comprises the following steps: the upper eccentric bushing 17 is a sliding bushing and is arranged in the upper flange bushing 12; the lower eccentric bush 18 is a sliding bush and is arranged in the lower flange bush 13; the bolt 16 passes through an upper eccentric bushing 17, a joint bearing 15, a lower eccentric bushing 18, a flat washer 19 and a slot top nut 20 in sequence. 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 being rotated 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 sets with different eccentricity, and the bushing sets can be selected according to actual different axial conditions of intersection 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 a groove structure at the top of the bolt 16 and a 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 through the mutual matching of the external spline structure of the upper eccentric bushing 17 and the internal spline structure on the limit plate 24, so that the position locking of the bolt 16 is realized. Retainer plate 24 is ultimately secured to binaural mount assembly 11.
The invention has the beneficial effects that:
(1) by designing the assembly compensation method, the invention solves the problem that the multipoint connection method has ultrahigh assembly and machining precision requirements on the connecting pieces, reduces the probability of assembly incongruity, improves the matching precision among the connecting pieces and ensures that 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 airplane design and other mechanical design fields as long as the connection form of the joint is similar to the connection method of the calibration joint and the spare connection joint and is an overconstrained connection point.
Drawings
FIG. 1 is a schematic diagram showing the relative position relationship between the tail cone and the front section of the rear fuselage according to the present invention.
FIG. 2 is a schematic diagram of the arrangement and freedom degree limiting method of the butt joint of the tail cone and the front section of the rear fuselage.
FIG. 3 is a horizontal cross-sectional view of the alignment joint of the present invention.
FIG. 4 is a schematic diagram of the locking of the relative positions of the inner eccentric bushing and the outer eccentric bushing of the present invention.
FIG. 5 is a schematic diagram of the locking of the relative positions of the bearing seat and the outer eccentric bushing of the present invention.
FIG. 6 is a schematic view of the connection method at the spare butt joint according to the present invention.
FIG. 7 is a schematic view of the synchronous rotation of the bolt and the upper eccentric bushing according to the present invention.
FIG. 8 is a schematic view 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 front section of the rear fuselage; 3, calibrating the joint; 4, 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 an inner eccentric bushing; 11 a binaural stand assembly; 12 an upper flange bushing; 13 a lower flange bushing; 14 a monaural mount assembly; 15 knuckle bearing on the single ear support assembly; 16 bolts; 17, an upper eccentric bushing; 18 lower eccentric bush; 19 a flat washer; 20 groove top nuts; 21 a cotter pin; 22 an upper boss structure on the outer eccentric bushing; 23, a boss structure on the bearing seat; 24 limiting plates; 25, an upper boss structure of the eccentric bushing; 26, a bolt upper plane structure; 27 lower eccentric bushing upper planar structure.
Detailed Description
The invention will be further described with reference to the accompanying drawings and technical methods.
A tail cone adjustable connection method with assembly compensation is applied to an airplane rear fuselage, wherein the airplane rear fuselage comprises a tail cone 1 and a rear fuselage front section 2 which 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 three groups of main butt joints 4 can limit 6 degrees of freedom of the tail cone 1, and in order to ensure the 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, the rear fuselage of the airplane comprises a tail cone 1 and a rear fuselage front section 2 which are connected through a group of calibration joints 3, three groups of main butt joints 4 and a group of spare butt joints 5. The connection at the three sets of primary butt joints 4 may already limit the 6 degrees of freedom of the tail cone.
As shown in fig. 3, the connection of the alignment joint of the present invention is realized by inserting the pin 6 fixed on the rear fuselage front section 2 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 bush 9 and the inner eccentric bush 10 between the bearing seat 8 and the knuckle bearing 7. 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 non-coaxial condition of the inner holes of the pin shaft 6 and the bearing seat 8, so that the pin shaft 6 and the inner hole of the joint bearing 7 are coaxial.
As shown in fig. 4, the inner eccentric bushing 10 is installed in the outer eccentric bushing 9, and they can rotate relatively around the hole axis of the outer eccentric bushing 9, and after rotating to the required position and making the two fit each other along the X direction, the relative position of the two is locked by the external spline structure on the flange of the inner eccentric bushing 10 and the boss structure 22 on the outer eccentric bushing 9 cooperating with each other.
As shown in fig. 5, the outer eccentric bushing 9 is installed in the bearing seat 8, and can rotate relatively around the axis of the hole of the bearing seat 8, and after rotating to a desired position and making the inner two fit each other along the direction X, the relative positions of the two are locked by the mutual cooperation of the external spline structure on the flange of the outer eccentric bushing 9 and the 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 fixed with 1 single ear support component 14, and the single ear support component 14 is provided with a joint bearing 15. The double-lug support assembly 11 and the single-lug support assembly 14 are connected through a bolt 16, an upper eccentric bushing 17, a lower eccentric bushing 18, a flat washer 19, a groove top nut 20 and a split pin 21. The upper eccentric bush 17 is a sliding bush and is mounted in the upper flange bush 12; the lower eccentric bush 18 is a sliding bush and is mounted in the lower flange bush 13; the bolt 16 passes through the upper eccentric bushing 17, the knuckle bearing 15, the lower eccentric bushing 18, the flat washer 19 and the slot top nut 10 in sequence. The upper eccentric bush 17 and the lower eccentric bush 18 have the same eccentric amount, and can rotate synchronously with the bolt 16. A plurality of groups of upper eccentric bushing 17 and lower eccentric bushing 18 bushing sets with different eccentric amounts are designed, during assembly, the upper eccentric bushing 17 and the lower eccentric bushing 18 are selected according to actual different-axis conditions of intersection holes of the double-lug support assembly 11 and the single-lug support assembly 14, and the adjusting bolt 16, the upper eccentric bushing 17 and the lower eccentric bushing 18 are rotated to ensure assembly coordination.
As shown in fig. 7, the synchronous rotation of the bolt 16 and the upper eccentric bushing 17 is achieved by the groove structure on the bolt 16 cooperating with 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 a flat structure 26 on the bolt 16 and a flat structure 27 on the lower eccentric bushing 18.
As shown in fig. 9, the position of the upper eccentric bushing 17 is locked by the internal spline structure of the retainer plate 24 and the external spline structure of the upper eccentric bushing 17, so that the position of the bolt 16 is locked. Retainer plate 24 is ultimately secured to binaural mount assembly 11.
The above-mentioned embodiments only express the embodiments of the present invention, but not should be understood as the limitation of the scope of the invention patent, it should be noted that, for those skilled in the art, many variations and modifications can be made without departing from the concept of the present invention, and these all fall into the protection scope of the present invention.
Claims (5)
1. A tail cone adjustable connection method with assembly compensation is applied to an airplane rear fuselage, wherein the airplane rear fuselage comprises a tail cone (1) and a rear fuselage front section (2) which 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) needs to have the assembly compensation function;
the connection mode of the calibration joint (3) is as follows: the device 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 joint bearing (7); outer eccentric bush (9) are installed in bearing frame (8), can rotate relatively around the hole axis of bearing frame (8) between the two, and after rotating to required position, the relative position of the two can lock, and is specific: the relative positions of the outer eccentric bushing (9) and the bearing seat (8) are locked by the mutual matching of an outer spline structure on the flange of the outer eccentric bushing (9) and a boss structure (23) on the bearing seat (8); the inner eccentric bushing (10) is arranged in the outer eccentric bushing (9), the inner eccentric bushing and the outer eccentric bushing can rotate relatively around the axis of a hole of the outer eccentric bushing (9), and after the inner eccentric bushing and the outer eccentric bushing are rotated to a required position, the relative positions of the inner eccentric bushing and the outer eccentric bushing can be locked, specifically: the relative positions of the inner eccentric bushing (10) and the outer eccentric bushing (9) are locked by the mutual matching of an outer spline structure on the flange of the inner eccentric bushing (10) and a boss structure (22) on the outer eccentric bushing (9); the eccentric amounts of the outer eccentric bushing (9) and the inner eccentric bushing (10) are the same, 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 non-coaxial condition of the inner holes of the pin shaft (6) and the bearing seat (8), so that the pin shaft (6) and the inner hole of the joint bearing (7) are coaxial;
the spare butt joint (5) is connected in the following mode: 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 installed 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 installed on the single-lug support assembly (14); the double-lug support assembly (11) and the single-lug support assembly (14) are connected through a bolt (16), an upper eccentric bushing (17), a lower eccentric bushing (18), a flat washer (19) and a groove top nut (20); specifically, the method comprises the following steps: 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 penetrates 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 being rotated 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 tail cone connecting method with the assembly compensation function is characterized in that a plurality of groups of upper eccentric bushing (17) and lower eccentric bushing (18) bushing sets with different eccentric amounts can be designed, and the upper eccentric bushing and the lower eccentric bushing are selected according to actual different axial conditions of intersection holes of a double-lug support assembly (11) and a single-lug support assembly (14) during assembly.
3. A tailcone adjustable connection method with assembly compensation as claimed in 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 attachment with assembly compensation as claimed in claim 1, wherein the synchronous rotation of the bolt (16) and the lower eccentric bushing (18) is achieved by the cooperation of a bottom planar formation (26) of the bolt (16) and a planar formation (27) of the inner surface of the lower eccentric bushing (18).
5. The adjustable tail cone connecting method with assembly compensation is characterized in that the position locking of the upper eccentric bushing (17) is realized through 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; and 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 |
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| 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 true CN114013679A (en) | 2022-02-08 |
| CN114013679B CN114013679B (en) | 2024-01-26 |
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| Application Number | Title | Priority Date | Filing Date |
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|---|---|---|---|---|
| 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 |
| 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 |
| US20190024530A1 (en) * | 2017-07-18 | 2019-01-24 | United Technologies Corporation | Variable-pitch vane assembly |
| CN209274928U (en) * | 2018-11-07 | 2019-08-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of receiving axial load docking structure of the unilateral side with slide bushing |
| 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 |
-
2021
- 2021-11-10 CN CN202111328954.1A patent/CN114013679B/en active Active
Patent Citations (8)
| 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 |
| 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 |
| US20190024530A1 (en) * | 2017-07-18 | 2019-01-24 | United Technologies Corporation | Variable-pitch vane assembly |
| CN209274928U (en) * | 2018-11-07 | 2019-08-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of receiving axial load docking structure of the unilateral side with slide bushing |
| 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 |
| 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 |
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| CN114013679B (en) | 2024-01-26 |
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