CN114162343B - External field 0 frame replacement, installation and positioning method - Google Patents
External field 0 frame replacement, installation and positioning method Download PDFInfo
- Publication number
- CN114162343B CN114162343B CN202111528208.7A CN202111528208A CN114162343B CN 114162343 B CN114162343 B CN 114162343B CN 202111528208 A CN202111528208 A CN 202111528208A CN 114162343 B CN114162343 B CN 114162343B
- Authority
- CN
- China
- Prior art keywords
- frame
- datum
- aircraft
- measuring
- point
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
- B64F5/40—Maintaining or repairing aircraft
Abstract
The invention provides a method for replacing, installing and positioning an external field 0 frame, which comprises the following steps: the invention aims to provide a method for replacing, installing and positioning an external field 0 frame, which ensures the whole standard of the machine body repair and the correct installation of system equipment on the premise that no special process equipment is positioned at the external field 0 frame, and ensures the consistency and the correctness of the fault plane in the external field repair by applying the method for replacing, installing and positioning the external field 0 frame, thereby avoiding the fault plane transportation and returning to the factory for maintenance.
Description
Technical Field
The invention relates to the field of aircraft outfield maintenance, in particular to a method for replacing, installing and positioning an outfield 0 frame.
Background
In the process of repairing an external field of an aircraft, the replacement of the 0 frame is an important link of the repair work of the aircraft, and the correctness of the position of the 0 frame relative to the aircraft body after the replacement determines the correctness of the installation positions of the radome (containing the finished product in the radome) and the finished product in the front equipment cabin, so that the normal use performance of the finished product of the front equipment cabin is affected. The position of the 0 frame on the airplane is a front-connection radome rear-connection equipment cabin, the installation in the factory is performed in a 0-14 frame assembly type frame for positioning assembly, and the 0-14 frame assembly type frame is of a fixed frame structure and cannot be used for the installation work of the external field. Because the 0 frame can not be assembled and positioned by adopting an assembly type frame in the replacement of the outfield aircraft, the risk of uncoordinated with the reference of the aircraft body exists, the accuracy of the 0 frame installation can not be ensured, and the reliability and the safety of the aircraft can be directly influenced. According to the position of the 0 frame and the structural characteristics analysis of the 0 frame, the installation process equipment for the external field cannot ensure that the 0 frame is correctly positioned on the airplane.
Disclosure of Invention
In order to solve the technical problems, the invention provides a method for replacing, installing and positioning an external field 0 frame, which is different from a process method in a factory, wherein a numerical control machining method is used for adding a mark of a positioning reference to a part manufacturing process on a newly manufactured 0 frame, a measuring reference point is prefabricated, process coordination of the 0 frame and a front frame is finished in advance, and when the 0 frame is replaced, the 0 frame is accurately measured and positioned by using a method of measuring and coordinating the horizontal reference line and a symmetrical axis of the frame by using an airplane level, so that the accuracy of the 0 frame of the airplane after the replacement in the external field can be ensured.
The technical scheme of the invention is as follows:
the external field 0 frame replacement, installation and positioning method is characterized by comprising the following steps of:
s1: prefabricating measuring datum points on the 0 frame, manufacturing 0 frame horizontal measuring points on the left side and the right side of the 0 frame outer edge by taking an airplane horizontal datum line and a 0 frame axis as datum, and manufacturing 0 frame upper measuring datum points and 0 frame lower measuring datum points on the upper part and the lower part of the 0 frame outer edge by taking intersection points of an airplane symmetrical axis and the 0 frame axis as datum intermediate positions;
s2: the method comprises the steps of leveling an airplane, checking that the airplane has no pilot, no store, no fuel oil and good equipment installation before the airplane is leveled, supporting a frame 1 of the airplane body by using a jack, supporting frames 2 and 8 of the airplane body by using a bracket, enabling the airplane wheel to leave the ground, leveling the front airplane body axis measuring point and the rear airplane body axis measuring point to horizontal positions, leveling the left and right of the airplane according to the left wing level measuring point and the right wing level measuring point, ensuring that the left wing level measuring point and the right wing level measuring point are level, and ensuring that the error is +/-0.5 mm;
s3: preparing a repairing and measuring datum point of the airframe, taking a 0-frame horizontal measuring point as a datum, additionally finding out the positions of the repairing and measuring datum points at the two sides and the lower part of the airframe 0-6 and marking the positions;
and S4, replacing the 0 frame, wherein in the process of replacing the 0 frame, the attitude of the aircraft is adjusted according to the restoration measurement datum point, the front point of the axis datum of the aircraft body and the rear point of the axis datum of the aircraft body, and the 0 frame installation work is carried out by taking the horizontal measurement points of the left frame and the right frame as the datum.
The invention has the advantages that:
the method ensures the whole standard of the repair of the airplane body and the correct installation of the system equipment on the premise that no special process equipment is used for positioning the 0 frame in the external field, and the application of the external field 0 frame replacement installation positioning method not only avoids the repair of the failed airplane in the transportation factory, but also ensures the compliance and the correctness of the repair of the failed airplane in the external field.
Drawings
The invention is described in further detail below with reference to the accompanying drawings.
FIG. 1 is a schematic view showing the distribution of 0 frame horizontal measuring points at 0 frame positions according to the present invention;
FIG. 2 is a schematic view showing the relative position distribution of each measuring point of the frame 0 relative to the aircraft fuselage according to the present invention;
FIG. 3 is a schematic view of the structure of the 0 frame relative to the radome of the present invention;
the figure shows: 1-0 frame horizontal measuring point, 2-0 frame upper measuring datum point, 3-0 frame lower measuring datum point, 4-front fuselage axis measuring point, 5-rear fuselage axis measuring point, 6-wing horizontal measuring point left point, 7-wing horizontal measuring point right point, 8-repair measuring datum point, 9-fuselage axis datum front point and 10-fuselage axis datum rear point.
Detailed Description
Further advantages and effects of the present invention will become apparent to those skilled in the art from the disclosure of the present invention, which is described by the following specific examples. The described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be understood that the structures, proportions, sizes, etc. shown in the drawings are for illustration purposes only and should not be construed as limiting the invention to the extent that it can be practiced, since modifications, changes in the proportions, or adjustments of the sizes, which are otherwise, used in the practice of the invention, are included in the spirit and scope of the invention which is otherwise, without departing from the spirit or scope thereof. Also, the terms such as "upper", "lower", "left", "right", "middle", etc. are used herein for convenience of description, but are not to be construed as limiting the scope of the invention, and the relative changes or modifications are not to be construed as essential to the scope of the invention.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "connected," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
The external field 0 frame replacement installation positioning method of the invention as shown in fig. 1-3 comprises the following steps:
s1: the method comprises the steps of (1) prefabricating a measuring datum point on a 0 frame, manufacturing 0 frame horizontal measuring points 1 on the left side and the right side of the outer edge of the 0 frame by taking an airplane horizontal datum line and a 0 frame axis as references, and manufacturing 0 frame upper measuring datum points 2 and 0 frame lower measuring datum points 3 on the upper part and the lower part of the outer edge of the 0 frame by taking intersection points of the airplane symmetrical axis and the 0 frame axis as reference intermediate positions;
s2: the aircraft is leveled, before the aircraft level measurement, the aircraft is checked to be free of drivers, free of stores, free of fuel oil and good in equipment installation, the frame 1 of the aircraft body is supported by a jack, the frames 2 and 8 of the aircraft body are supported by a bracket, so that the aircraft wheels are separated from the ground, the front aircraft body axis measuring point 4 and the rear aircraft body axis measuring point 5 are leveled to horizontal positions, the aircraft is leveled left and right according to the wing level measuring point left point 6 and the wing level measuring point right point 7, the wing level measuring point left point 6 and the wing level measuring point right point 7 are guaranteed to be level, and the error is +/-0.5 mm;
s3: taking a 0-frame horizontal measuring point 1 as a reference, additionally finding out the positions of the repairing measuring reference points 8 at the two sides and the lower part of the 0-6 frame of the airframe, and marking;
s4, 0 frame replacement, wherein in the 0 frame replacement process, the aircraft posture is adjusted according to the restoration measurement datum point 8, the front airframe axis datum point 9 and the rear airframe axis datum point 10 serving as references, and 0 frame installation work is carried out according to the left and right 0 frame horizontal measurement points 1 serving as references
Other aspects of the invention are not specifically described and are well known to those skilled in the art.
It should be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The protection scope of the present invention is not limited to the technical solutions disclosed in the specific embodiments, and any modification, equivalent replacement, improvement, etc. made to the above embodiments according to the technical substance of the present invention falls within the protection scope of the present invention.
Claims (1)
1. The external field 0 frame replacement, installation and positioning method is characterized by comprising the following steps of:
s1: prefabricating measuring datum points on a 0 frame, manufacturing 0 frame horizontal measuring points (1) on the left side and the right side of the outer edge of the 0 frame by taking an airplane horizontal datum line and a 0 frame axis as references, and manufacturing 0 frame upper measuring datum points (2) and 0 frame lower measuring datum points (3) on the upper part and the lower part of the outer edge of the 0 frame by taking intersection points of an airplane symmetrical axis and the 0 frame axis as reference intermediate positions;
s2: the aircraft is leveled, before the aircraft level measurement, the aircraft is checked to be free of drivers, free of stores, free of fuel oil and good in equipment installation, the frame 1 of the aircraft body is supported by a jack, the frames 2 and 8 of the aircraft body are supported by a bracket, so that the aircraft wheels are separated from the ground, the front aircraft body axis measuring point (4) and the rear aircraft body axis measuring point (5) are leveled to horizontal positions, the aircraft is leveled left and right according to the left wing level measuring point (6) and the right wing level measuring point (7), the left wing level measuring point (6) and the right wing level measuring point (7) are guaranteed to be level, and the error is +/-0.5 mm;
s3: preparing a repairing and measuring datum point of the airframe, taking the horizontal measuring point (1) as a datum, additionally finding out the positions of the repairing and measuring datum points (8) at the two sides and the lower part of the airframe 0-6 and marking;
and S4, 0 frame replacement, wherein in the 0 frame replacement process, the attitude of the aircraft is adjusted according to the restoration measurement datum point (8), the front airframe axis datum point (9) and the rear airframe axis datum point (10), and the 0 frame installation work is carried out according to the left and right 0 frame horizontal measurement points (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111528208.7A CN114162343B (en) | 2021-12-15 | 2021-12-15 | External field 0 frame replacement, installation and positioning method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111528208.7A CN114162343B (en) | 2021-12-15 | 2021-12-15 | External field 0 frame replacement, installation and positioning method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114162343A CN114162343A (en) | 2022-03-11 |
| CN114162343B true CN114162343B (en) | 2023-05-23 |
Family
ID=80486474
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111528208.7A Active CN114162343B (en) | 2021-12-15 | 2021-12-15 | External field 0 frame replacement, installation and positioning method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114162343B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101850850A (en) * | 2010-03-30 | 2010-10-06 | 浙江大学 | Layout method of central airframe digital assembly of big plane |
| CN101865653A (en) * | 2010-03-30 | 2010-10-20 | 浙江大学 | Method for measuring precision of 1# frame of plane general assembly |
| CN103303491A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Abutting technological equipment of airplane large components and abutting method thereof |
| CN203485894U (en) * | 2013-09-13 | 2014-03-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle special for external field repairing of engine |
| US9273990B1 (en) * | 2011-09-11 | 2016-03-01 | The Boeing Company | Aircraft repair fixture |
| CN110514408A (en) * | 2019-08-02 | 2019-11-29 | 西安飞机工业（集团）有限责任公司 | A kind of airborne photoelectric detecting devices zero correction method |
| CN111942612A (en) * | 2020-05-11 | 2020-11-17 | 中国南方航空股份有限公司 | Interchangeability detection process for maintenance of airplane radome |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102013110684A1 (en) * | 2013-09-26 | 2015-03-26 | Airbus Operations Gmbh | Method for assembling an aircraft fuselage and hull production station |
| US10525524B2 (en) * | 2014-07-09 | 2020-01-07 | The Boeing Company | Dual-interface coupler |
| US10501208B2 (en) * | 2017-06-30 | 2019-12-10 | The Boeing Company | Gantry system and method for processing an aircraft |
-
2021
- 2021-12-15 CN CN202111528208.7A patent/CN114162343B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101850850A (en) * | 2010-03-30 | 2010-10-06 | 浙江大学 | Layout method of central airframe digital assembly of big plane |
| CN101865653A (en) * | 2010-03-30 | 2010-10-20 | 浙江大学 | Method for measuring precision of 1# frame of plane general assembly |
| US9273990B1 (en) * | 2011-09-11 | 2016-03-01 | The Boeing Company | Aircraft repair fixture |
| CN103303491A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Abutting technological equipment of airplane large components and abutting method thereof |
| CN203485894U (en) * | 2013-09-13 | 2014-03-19 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle special for external field repairing of engine |
| CN110514408A (en) * | 2019-08-02 | 2019-11-29 | 西安飞机工业（集团）有限责任公司 | A kind of airborne photoelectric detecting devices zero correction method |
| CN111942612A (en) * | 2020-05-11 | 2020-11-17 | 中国南方航空股份有限公司 | Interchangeability detection process for maintenance of airplane radome |
Non-Patent Citations (2)
| Title |
|---|
| 某型飞机零号框损伤修复技术研究;谢大叶;邹仕军;王石;;航空制造技术(第05期);64-67 * |
| 浅谈TB200飞机零号框加强改装施工及日常维护要求;龙小辉;;科技创新导报(04);71-72 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114162343A (en) | 2022-03-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2843736C (en) | Aircraft gross weight and center of gravity validator | |
| US4848137A (en) | Automated shim manufacturing system | |
| CN104198113B (en) | Double-end calibration device and calibration method | |
| CN114162343B (en) | External field 0 frame replacement, installation and positioning method | |
| US20140007397A1 (en) | System and method for rigging a control surface of an aircraft | |
| CN110775293B (en) | Method for establishing measuring reference coordinate system of lower station of aircraft nose component frame | |
| CN109823568A (en) | A kind of aircraft blade torque automatic measurement system | |
| CN111561874A (en) | Digital measurement system and method for airplane structure deformation measurement and damage classification | |
| CN102155901B (en) | Device and method for detecting assembly stations of vehicle body sidewalls | |
| CN111422374B (en) | Coordination and compensation method suitable for welded part and machine body structure | |
| CN103963992B (en) | Aircraft iron bird testing stand undercarriage and the installation method of hatch door | |
| CN206065630U (en) | A kind of robot arc stud welding TCP correcting mechanisms of pair of guide colume type | |
| CN101031776B (en) | Method and device for measuring the orientation of an aircraft nose landing gear | |
| CN218751451U (en) | Wing main part assembly fixture | |
| CN113581489B (en) | Static balance moment adjusting device and method for airplane control surface | |
| CN112683306A (en) | Be used for unmanned aerial vehicle to be used to lead position appearance precision adjustment installation device | |
| US11679457B2 (en) | Assembling device | |
| CN110409313B (en) | High-speed railway pier unmanned aerial vehicle loading and lofting system and lofting method thereof | |
| CN109506908B (en) | Tail end load loading device for fatigue test of tail section test piece | |
| CN109084932B (en) | Method and system for adjusting calibration coordinate system of six-dimensional force/torque sensor | |
| CN111026030A (en) | Hole position double correction method for numerical control machine tool | |
| CN113670331B (en) | Method for installing standby magnetic compass of airplane | |
| CN106319792B (en) | Machine head positioning mechanism and mounting method | |
| CN218973360U (en) | Unmanned aerial vehicle rudder face zero position measuring device | |
| US10606243B2 (en) | Assembly tool production |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |