CN107088743B - Automatic installation method and installation device for airplane duck wings - Google Patents
Automatic installation method and installation device for airplane duck wings Download PDFInfo
- Publication number
- CN107088743B CN107088743B CN201710446271.3A CN201710446271A CN107088743B CN 107088743 B CN107088743 B CN 107088743B CN 201710446271 A CN201710446271 A CN 201710446271A CN 107088743 B CN107088743 B CN 107088743B
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- duck wing
- shaft
- installation
- inner rings
- supporting sleeve
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- 241000272525 Anas platyrhynchos Species 0.000 title claims abstract description 52
- 238000000034 method Methods 0.000 title claims abstract description 41
- 238000009434 installation Methods 0.000 title claims abstract description 30
- 230000008569 process Effects 0.000 claims abstract description 29
- 230000007246 mechanism Effects 0.000 claims abstract description 10
- 210000001503 joint Anatomy 0.000 claims description 18
- 238000006073 displacement reaction Methods 0.000 claims description 6
- 238000005452 bending Methods 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 238000003032 molecular docking Methods 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
- Automatic Assembly (AREA)
Abstract
The invention discloses an automatic installation method and an installation device for an airplane duck wing, and belongs to the technical field of docking installation of airplane duck wings. The installation method of the invention is as follows: the method comprises the steps of supporting inner rings of two universal bearings by using a fixing mechanism capable of stretching in the axial direction to fix the directions of the two inner rings, loading a process shaft with the same diameter as that of a large duck wing shaft into the two universal bearings to pre-calibrate the axial positions of the two universal bearings, presetting theoretical axial position parameters according to the axial positions of the process shaft by using a plurality of annularly arranged distance sensors, extracting the process shaft, then installing the large duck wing shaft, sensing the attitude parameters of the large duck wing shaft in real time through the distance sensors in the assembling process of the large duck wing shaft, and controlling an installation tool to automatically adjust the installation attitude of the large duck wing shaft after comparing the real-time attitude parameters with the theoretical axial position parameters by using a control system.
Description
Technical Field
The invention belongs to the technical field of airplane duck wing butt joint installation, and particularly relates to an airplane duck wing automatic installation method and an airplane duck wing automatic installation device.
Background
The butt joint process of the airplane body with the duck wings is that a shaft is matched with the bearings, one shaft needs to pass through the two bearings arranged at a certain distance, the bearings are universal bearings, and the inner rings of the bearings can move freely, so that great problems are brought to assembly. Particularly, in the automatic assembly process, the inner ring can freely move, the axis direction of the bearing is not fixed, the axis direction of the corresponding duck wing large shaft cannot be determined, and automatic butt joint cannot be realized. The traditional duck wing butt joint is accomplished through the manual work, utilizes to hang and lifts the duck wing, and the big axle of duck wing passes a bearing earlier, because the actual axis of big axle does not have coaxial line with the axis of theoretical installation, needs to make big axle and second universal bearing coaxial through manual adjustment axle and bearing, passes the second bearing, accomplishes the butt joint of duck wing. The manual assembly needs 5-6 people to participate in each time, the assembly efficiency is low, the occupied amount of the personnel is large, and the automatic butt joint of the duck wings is realized, and the premise is that the axis of the bearing is fixed.
Disclosure of Invention
Aiming at the defects existing in the installation of the existing aircraft duck wings, the invention aims to provide an automatic installation method and an installation device for the aircraft duck wings.
For this purpose, the invention adopts the following technical scheme: an automatic installation method of an aircraft duck wing is characterized by comprising the following steps: the method comprises the steps of supporting inner rings of two universal bearings by using a fixing mechanism capable of stretching in the axial direction to fix the directions of the two inner rings, loading a process shaft with the same diameter as that of a large duck wing shaft into the two universal bearings to pre-calibrate the axial positions of the two universal bearings, presetting theoretical axial position parameters according to the axial positions of the process shaft by using a plurality of annularly arranged distance sensors, extracting the process shaft, then installing the large duck wing shaft, sensing the attitude parameters of the large duck wing shaft in real time through the distance sensors in the assembling process of the large duck wing shaft, and controlling an installation tool to automatically adjust the installation attitude of the large duck wing shaft after comparing the real-time attitude parameters with the theoretical axial position parameters by using a control system.
The automatic installation device for the airplane duck wings is characterized by comprising a fixing mechanism and a distance sensor, wherein the fixing mechanism comprises an air cylinder and a supporting sleeve, piston rods are arranged at two ends of the air cylinder, the outer end parts of the piston rods are connected with the supporting sleeve, the supporting sleeve comprises two semicircular supporting sleeve pieces, the two supporting sleeve pieces can be turned over at the end parts through hinge movable connection, the two supporting sleeve pieces are butted to form a through hole, the central lines of the through holes of the two supporting sleeve pieces are positioned on the same straight line, and a process shaft penetrates through the two through holes; the end faces formed by butt joint of the two support sleeve sheets are matched with the end faces of the inner rings of the universal bearing, the cylinder drives the support sleeve to move towards the two ends, so that the end faces of the inner rings of the universal bearing, the outer rings of which are fixed, are matched with the end faces of the two butt joint support sleeve sheets, the two inner rings are fixed, and a plurality of distance sensors are distributed along the circumferential direction of each support sleeve.
The invention also comprises the following technical characteristics as supplement and improvement of the technical scheme.
The two cylinders are symmetrically arranged along the center line of the through hole of the supporting sleeve, so that the stability of the displacement of the supporting sleeve driven by the cylinders can be improved.
The outer end part of the piston rod is fixedly connected with the outer peripheral surface of the supporting sleeve through bending.
The outer ring of the universal bearing is limited and fixed through the base, and the base is provided with a step hole matched with the outer ring, so that the displacement of the outer ring in the axial direction is limited.
The invention has the following beneficial effects: by utilizing the mounting device provided by the invention, the directions of the inner rings of the two bearings can be fixed, so that the real-time monitoring and adjustment of the butt joint of the duck wings are realized, the two bearings are coaxial, the conditions for automatic butt joint are provided, and the successful completion of the butt joint is ensured. Through the distance sensor that is close to every support cover department and sets up, can confirm that the axis position of two bearings of technology axle demarcation, in the assembly process, the sensor can show the deviation of duck wing major axis and theoretical axis in real time to feed back the deviation data to docking equipment, thereby adjust the gesture of duck wing major axis. The invention can improve the utilization rate of personnel, reduce the labor intensity and improve the working efficiency.
Drawings
Fig. 1 is a schematic top view of the present invention.
Fig. 2 is a schematic diagram of a front view structure of the present invention.
Description of the embodiments
The following detailed description of specific embodiments of the invention refers to the accompanying drawings.
According to the automatic installation method of the airplane and the duck wing, the fixing mechanism which can stretch in the axial direction is used for supporting the inner rings of the two universal bearings to fix the directions of the two inner rings, a process shaft with the same diameter as the large axis of the duck wing is installed in the two universal bearings to conduct axis position pre-calibration of the two universal bearings, a plurality of distance sensors which are arranged in an annular mode are used for presetting theoretical axis position parameters according to the axis position of the process shaft, the large axis of the duck wing is installed after the process shaft is extracted, the attitude parameters of the large axis of the duck wing are sensed in real time through the distance sensors in the assembling process of the large axis of the duck wing, and the installation tool is controlled to automatically adjust the installation attitude of the large axis of the duck wing after the real-time attitude parameters and the theoretical axis position parameters are compared by the control system.
As shown in fig. 1-2, the automatic airplane duck wing mounting device comprises a fixing mechanism and a distance sensor, wherein the fixing mechanism comprises an air cylinder 2 and a supporting sleeve, piston rods are arranged at two ends of the air cylinder 2, the outer end parts of the piston rods are connected with the supporting sleeve, the supporting sleeve comprises two semicircular supporting sleeve pieces 1, the two supporting sleeve pieces 1 can be turned over at the end parts by being movably connected with a hinge 3, the two supporting sleeve pieces 1 are butted to form a through hole, the central lines of the through holes of the two supporting sleeve pieces are positioned on the same straight line, and a process shaft 6 penetrates through the two through holes; the end faces formed by butt joint of the two support sleeve sheets 1 are matched with the end faces of the inner rings of the universal bearings 5, the cylinder 2 drives the support sleeve to move towards two ends, so that the end faces of the inner rings of the universal bearings 5 with the outer rings fixed are matched with the end faces of the two butt joint support sleeve sheets 1, the directions of the two inner rings are fixed, and a plurality of distance sensors 4 are distributed along the circumferential direction of each support sleeve.
Preferably, two cylinders 2 are arranged, and the two cylinders 2 are symmetrically arranged along the center line of the through hole of the support sleeve, so that the stability of the displacement of the support sleeve driven by the cylinders can be improved.
Further preferably, the outer end of the piston rod is fixedly connected with the outer circumferential surface of the support sleeve through bending.
Further, the outer ring of the universal bearing 5 is limited and fixed through a base, and a step hole matched with the outer ring is formed in the base, so that the displacement of the outer ring in the axial direction is limited.
In the use process of the invention, firstly, a supporting sleeve device is placed between two universal bearings 5, and the position is adjusted to enable the outer side of the supporting sleeve 1 of the device to be matched and correspond to the inner ring of the bearing; then air is introduced into the air cylinder 2, the supporting sleeve 1 is stressed to prop up the two sides, the supporting sleeve 1 props up the inner ring of the universal bearing 5, so that the inner ring is fixed, and meanwhile, the device is also fixed between the two universal bearings 5 due to friction force; then, a process shaft 6 is inserted between the two universal bearings 5, the process shaft 6 simulates the state of the installed duck wings, the installation position of the process shaft is sensed by the two groups of distance sensors 4 to determine the position parameters of the theoretical axis, and the operation steps for determining the position parameters of the theoretical axis are as follows: the deviation between one circle center and the theoretical circle center on the axis of the process shaft 6 is displayed through a group of distance sensors, the deviation between the axis of the large axis of the duck wing and the theoretical axis can be displayed in real time through the cooperation of the two circles of distance sensors 4, deviation data are fed back to the butt joint equipment, the axis posture of the process shaft 6 is adjusted, the position of the axis is calibrated, then the process shaft 6 is dismantled, the duck wing is in butt joint, after the butt joint is completed, gas in the cylinder 2 is pumped out, the supporting sleeve 1 is retracted, and the airplane duck wing installation device is turned over along the hinge 3 to be opened for dismantling.
The foregoing has shown and described the basic principles and main features of the present invention and the advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (5)
1. An automatic installation method of an aircraft duck wing is characterized by comprising the following steps: the method comprises the steps of supporting inner rings of two universal bearings by using a fixing mechanism capable of stretching in the axial direction to fix the directions of the two inner rings, loading a process shaft with the same diameter as that of a large duck wing shaft into the two universal bearings to pre-calibrate the axial positions of the two universal bearings, presetting theoretical axial position parameters according to the axial positions of the process shaft by using a plurality of annularly arranged distance sensors, extracting the process shaft, then installing the large duck wing shaft, sensing the attitude parameters of the large duck wing shaft in real time through the distance sensors in the assembling process of the large duck wing shaft, and controlling an installation tool to automatically adjust the installation attitude of the large duck wing shaft after comparing the real-time attitude parameters with the theoretical axial position parameters by using a control system.
2. An automatic installation device of aircraft duck wing, its characterized in that: the automatic mounting device comprises a fixing mechanism and a distance sensor, wherein the fixing mechanism comprises an air cylinder (2) and supporting sleeves, piston rods are arranged at two ends of the air cylinder (2), the outer ends of the piston rods are connected with the supporting sleeves, each supporting sleeve comprises two semicircular supporting sleeve pieces (1), the two supporting sleeve pieces (1) can be turned over at the ends through movable connection of a hinge (3), the two supporting sleeve pieces (1) are butted to form a through hole, the central lines of the through holes of the two supporting sleeves are positioned on the same straight line, and a process shaft (6) penetrates through the two through holes; the end faces formed by butt joint of the two support sleeve sheets (1) are matched with the end faces of the inner rings of the universal bearings (5), the support sleeve is driven by the air cylinder (2) to move towards two ends, so that the end faces of the inner rings of the universal bearings (5) with the outer rings fixed are matched with the end faces of the two butt joint support sleeve sheets (1), the two inner rings are fixed in directions, and a plurality of distance sensors (4) are distributed along the circumferential direction of each support sleeve.
3. An aircraft duck wing automatic mounting device as recited in claim 2, wherein: the two cylinders (2) are symmetrically arranged along the center line of the through hole of the supporting sleeve, so that the stability of the displacement of the supporting sleeve driven by the cylinders can be improved.
4. An aircraft duck wing automatic mounting device as recited in claim 3, wherein: the outer end part of the piston rod is fixedly connected with the outer peripheral surface of the supporting sleeve through bending.
5. An aircraft duck wing automatic mounting device as recited in claim 2, 3 or 4, wherein: the outer ring of the universal bearing (5) is limited and fixed through a base, and a step hole matched with the outer ring is formed in the base, so that the displacement of the outer ring in the axial direction is limited.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710446271.3A CN107088743B (en) | 2017-06-14 | 2017-06-14 | Automatic installation method and installation device for airplane duck wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710446271.3A CN107088743B (en) | 2017-06-14 | 2017-06-14 | Automatic installation method and installation device for airplane duck wings |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107088743A CN107088743A (en) | 2017-08-25 |
| CN107088743B true CN107088743B (en) | 2023-12-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710446271.3A Active CN107088743B (en) | 2017-06-14 | 2017-06-14 | Automatic installation method and installation device for airplane duck wings |
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| Country | Link |
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| CN (1) | CN107088743B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022166066A1 (en) * | 2021-02-04 | 2022-08-11 | 武汉工程大学 | Accurate adjustment and positioning assembly system and method for aircraft canard wings |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002213565A (en) * | 2001-01-22 | 2002-07-31 | Ckd Corp | Conveyance positioning device |
| CN1991592A (en) * | 2005-12-27 | 2007-07-04 | 优志旺电机株式会社 | Object stage device |
| US7263765B1 (en) * | 2004-05-17 | 2007-09-04 | Smith Thomas F | Marine bearing alignment and insertion tool |
| CN101745905A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Multi-degree of freedom adjustable assembling platform used for butt joint of aircraft wings |
| CN102745337A (en) * | 2012-06-19 | 2012-10-24 | 中国民航大学 | Large-scale aircraft trailing edge flap mandril assembly vehicle and mounting method thereof |
| KR101359471B1 (en) * | 2013-02-25 | 2014-02-11 | 주식회사 코렘 | System for disassembling wheel assembly and method thereof |
| US8661684B1 (en) * | 2010-01-21 | 2014-03-04 | The Boeing Company | High rate pulsing wing assembly line |
| CN103879567A (en) * | 2014-02-28 | 2014-06-25 | 成都飞机工业（集团）有限责任公司 | Self-adaptive skin rolling supporting structure |
| CN106541254A (en) * | 2015-09-23 | 2017-03-29 | 中航商用航空发动机有限责任公司 | Butt-joint mounting device |
| CN206223130U (en) * | 2016-11-23 | 2017-06-06 | 华南理工大学 | A kind of device of real-time measurement rotating shaft spatial pose |
-
2017
- 2017-06-14 CN CN201710446271.3A patent/CN107088743B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2002213565A (en) * | 2001-01-22 | 2002-07-31 | Ckd Corp | Conveyance positioning device |
| US7263765B1 (en) * | 2004-05-17 | 2007-09-04 | Smith Thomas F | Marine bearing alignment and insertion tool |
| CN1991592A (en) * | 2005-12-27 | 2007-07-04 | 优志旺电机株式会社 | Object stage device |
| US8661684B1 (en) * | 2010-01-21 | 2014-03-04 | The Boeing Company | High rate pulsing wing assembly line |
| CN101745905A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Multi-degree of freedom adjustable assembling platform used for butt joint of aircraft wings |
| CN102745337A (en) * | 2012-06-19 | 2012-10-24 | 中国民航大学 | Large-scale aircraft trailing edge flap mandril assembly vehicle and mounting method thereof |
| KR101359471B1 (en) * | 2013-02-25 | 2014-02-11 | 주식회사 코렘 | System for disassembling wheel assembly and method thereof |
| CN103879567A (en) * | 2014-02-28 | 2014-06-25 | 成都飞机工业（集团）有限责任公司 | Self-adaptive skin rolling supporting structure |
| CN106541254A (en) * | 2015-09-23 | 2017-03-29 | 中航商用航空发动机有限责任公司 | Butt-joint mounting device |
| CN206223130U (en) * | 2016-11-23 | 2017-06-06 | 华南理工大学 | A kind of device of real-time measurement rotating shaft spatial pose |
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| Publication number | Publication date |
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| CN107088743A (en) | 2017-08-25 |
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