CN109870253A - A kind of aircraft assembling process stress monitor method based on profile measurement - Google Patents
A kind of aircraft assembling process stress monitor method based on profile measurement Download PDFInfo
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- CN109870253A CN109870253A CN201910165728.2A CN201910165728A CN109870253A CN 109870253 A CN109870253 A CN 109870253A CN 201910165728 A CN201910165728 A CN 201910165728A CN 109870253 A CN109870253 A CN 109870253A
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Abstract
The aircraft assembling process stress monitor method based on profile measurement that the invention discloses a kind of, comprising: lift components A and part B into position；It establishes aircraft axes and measures the shape key point of measuring part A and part B respectively, the shape key point coordinate record after components A and part B posture adjustment is transmitted to Data Computation Unit to primary data storage unit；By the pre- pairing of components A and part B；Changeover portion skeleton and covering trial assembly are monitored shape key point course location with measuring instrument, and are sent to Data Computation Unit；Data Computation Unit compares the position degree of shape key point, and variation is more than preset threshold value, issues alarm, otherwise installs changeover portion skeleton and covering.The present invention installs changeover portion skeleton when monitoring the coordinate of shape key point, avoids because assembly is forced to generate erection stress, causes the deformation of docking site part, improve assembling quality, extends Aircraft life etc., reduce the erection stress of aircraft docking operation.
Description
Technical field
The present invention relates to aircraft manufacturings and mounting technology field, are a kind of aircraft dresses based on profile measurement specifically
With process stress monitoring method.
Background technique
Aircraft manufacturing is generally divided into multiple big components such as forebody, middle fuselage, rear body, wing.As aircraft manufacturing
One key link, an important process of aircraft components assembly be according to size coordination principle, using tooling and equipment by this
A little big component combinations are at an entirety.Traditional Large Aircraft Components assembly is guaranteed by dedicated pairing tooling, using level,
The optical instruments such as theodolite measure, and cooperate by crane with traction and carry out component attitude adjusting and dock, low efficiency is easy to produce
Stress assembly, assembling quality are poor.With the development of numeric terminal technology, the assembly of Large Aircraft Components pairing uses digitized measurement
Device measuring and detection aircraft components position and posture carry out pose adjustment to component using flexible support positioning tool, use
Survey Software, integrated control platform etc. control the entire pairing assembling process of aircraft components, improve the efficiency of component pairing assembly,
Reduce stress assembly.By taking two big component as an example, process steps can be divided into: (1) big component (A, B) is lifted into position；(2) big
Component attitude adjusting.By ground public-measurement point, aircraft axes and measuring part shape key point are established, according to shape key point
Posture adjustment is carried out, is in the two big component (A, B) of pairing or utmostly close to theoretical position；(3) fixed big components A, edge
The mobile big part B in course to close to theoretical position, carry out the pre- pairing of big component；(4) changeover portion skeleton and covering installation；(5)
Big component undercarriage.Since aircraft assembly coordination route is long, factor is more, the accumulation of part manufacturing error in addition, if entire big
Lack effective monitoring means during component pairing, easily because assembly is forced to generate erection stress, causes docking site zero
The deformation of part, makes aspect change, and seriously affects assembling quality, to impact to Aircraft life etc..
Summary of the invention
The aircraft assembling process stress monitor method based on profile measurement that the purpose of the present invention is to provide a kind of, for solving
Certainly lack the problem of monitoring be easy to cause part deformation in assembling process in the prior art.
In order to reach the goals above, the present invention is achieved through the following technical solutions:
A kind of aircraft assembling process stress monitor method based on profile measurement, comprising:
Step S100: components A and part B are lifted into position；
Step S200: setting ground public-measurement point establishes aircraft axes and measures the outer of measuring part A and part B respectively
Shape key point, according to shape key point by components A and part B posture adjustment；Choose the shape pass after the completion of components A and part B posture adjustment
Key point coordinate is transmitted to data operation together with sortie record as initial value, record to primary data storage unit
Unit；
Step S300: fixation member A, it is close to components A along course moving parts B, carry out the pre- pairing of components A and part B；
Step S400: changeover portion skeleton and covering trial assembly close shape in changeover portion skeleton and covering installation with measuring instrument
Key point process position is monitored, record shape key point course location to process data storage unit, while together with measurement rank
Segment information is sent to " Data Computation Unit " together；
Step S500: Data Computation Unit compares key point initial position and shape key point course location, if shape
The position degree variation of key point is more than preset threshold value, issues alarm, and result is sent to " data display unit ", " data
Display unit " shows warning information, otherwise enters in next step；
Step S600: changeover portion skeleton and covering installation.
Working principle:
The biggish components A of structure and part B are lifted with lifting device into position first, according to ground public-measurement point, establishes and flies
Machine coordinate, and with the shape key point of measuring instrument measuring part A and part B, then carried out according to the coordinate of shape key point
Posture adjustment, by the initial position of the shape key point after posture adjustment and sortie information preservation to primary data storage unit, then by initial
Data storage cell input data arithmetic element.Moving parts A and part B, make components A and part B be in theoretical position or
To the greatest extent close to theoretical position.Then fixation member A, along course direction moving parts B to close to theoretical position, carry out portion
The pre- pairing of part A and part B.In moving process, measuring instrument tracks the course location of shape key point, and by course location
It is sent to process data storage unit with measuring phases information, Data Computation Unit is transported to by process data storage patrilineal line of descent with only one son in each generation.Data
The initial position of shape key point is compared by arithmetic element with course location, if position degree variation is more than the threshold value of setting,
Alarm is then issued, and comparison result is sent to data display unit, operator is reminded to search reason.Survey aircraft bone at this time
Frame and components A, the amount of interference of part B, for instructing skeleton repair, if changeover portion skeleton and covering are mounted on threshold range
It is interior, then start moving parts B, it is known that eligible state.The hole location that airframe is connect with components A, part B is produced, it is outer in monitoring
Changeover portion skeleton is installed in the case of the coordinate of shape key point, avoids because assembly is forced to generate erection stress, causes docking section
The deformation of position part, improves assembling quality, extends Aircraft life etc., reduces the erection stress of aircraft docking operation.
Further, in the step S400 specifically:
Step S410: fixation member A, along course moving parts B to close to theoretical position 2mm, the skeleton of pre- pairing changeover portion,
The skeleton amount of interference with components A and part B respectively is measured, after being measured, part B exits original to far from the movement of components A direction
State；
Step S430: with the shape key point of measuring instrument measuring part A and part B, while the measuring phases letter of flag data
Breath is " pre- pairing 1 ", and sends data to process data storage unit；
Step S440: process data storage unit, which synchronizes data, is sent to Data Computation Unit, and Data Computation Unit has been calculated
Bi Hou is sent to data display unit when by fructufy.
Working principle:
When components A and part B are moved to theoretical position, the coordinate of shape key point is monitored with measuring instrument, and will acquisition
The measuring phases information of shape key point is sent to process data storage unit together.Data Computation Unit is stored from primary data
Unit and process data storage unit read data in real time, compare the initial external between course location of shape key point
Position degree variation, and calculated result is shown by data display unit.Therefore, the seat of shape key point can be monitored in real time
Mark, when shifting, can timely show, remind operator.
Further, in the step S500 specifically:
Step S510: received data are compared by Data Computation Unit with shape key point initial position, if position degree
Variation is less than the threshold value of setting, then enters step S600；Otherwise, then S520 is entered step；
Step S520: if skeleton repair amount is unsatisfactory for matching requirements, alarm, and return step S410 are issued；Otherwise, it enters step
S600。
Working principle:
If position degree variation is more than the threshold value of setting, alarm is issued, and return step S410 re-moves components A and component
The position of B.Until the course location of components A and part B and initial position within the set threshold range, then start changeover portion skeleton
It is installed with covering.
Further, in the step S600 specifically:
Step S610: the hole location that skeleton is connect with components A and part B is produced respectively；
Step S620: with the shape key point of measuring instrument measuring part A and part B, flag data measuring phases are that " skeleton is pre-
Fill drilling "；
Step S630: it is separately connected components A and part B with skeleton, changeover portion skeleton is installed.
Working principle:
Skeleton is connect with the hole location above components A, part B, carries out the installation of changeover portion skeleton, after being installed, components A and portion
Part B is separated with skeleton, components A and part B undercarriage.
Further, the measuring instrument in the step S400 uses laser tracker.
Working principle:
It is a kind of high-precision Large-scale Measuring Instruments in industrial measuring system using digitized laser tracker.It gathers
Laser interference ranging technology, detecting technique, precision machinery technology, computer and control technology, modern numerical calculation reason
By etc. various advanced technologies, to space movement target track and real-time measurement target 3 d space coordinate.It has height
Precision, high efficiency, real-time follow-up, it is quick for installation, easy to operate the features such as, be suitable for the equipped measurement of large-size workpiece.
Compared with prior art, the present invention have the following advantages that and the utility model has the advantages that
(1) present invention installs changeover portion skeleton when monitoring the coordinate of shape key point, avoids because assembly is forced to produce
Raw erection stress, causes the deformation of docking site part, improves assembling quality, extends Aircraft life etc., reduces aircraft docking
The erection stress of process.
(2) track to space movement target the 3 d space coordinate of simultaneously real-time measurement target using laser tracker,
Have the characteristics that high-precision, high efficiency, real-time follow-up, quick for installation, easy to operate, is suitable for that large-size workpiece is equipped to be surveyed
Amount.
Specific embodiment
The present invention is described in further detail below with reference to embodiment, embodiments of the present invention are not limited thereto.
Embodiment 1:
A kind of aircraft assembling process stress monitor method based on profile measurement, comprising:
Step S100: components A and part B are lifted into position；
Step S200: setting ground public-measurement point establishes aircraft axes and measures the outer of measuring part A and part B respectively
Shape key point, according to shape key point by components A and part B posture adjustment；Choose the shape pass after the completion of components A and part B posture adjustment
Key point coordinate is transmitted to data operation together with sortie record as initial value, record to primary data storage unit
Unit；
Step S300: fixation member A, it is close to components A along course moving parts B, carry out the pre- pairing of components A and part B；
Step S400: changeover portion skeleton and covering trial assembly close shape in changeover portion skeleton and covering installation with measuring instrument
Key point process position is monitored, record shape key point course location to process data storage unit, while together with measurement rank
Segment information is sent to " Data Computation Unit " together；
Step S500: Data Computation Unit compares key point initial position and shape key point course location, if shape
The position degree variation of key point is more than preset threshold value, issues alarm, and result is sent to " data display unit ", " data
Display unit " shows warning information, otherwise enters in next step；
Step S600: changeover portion skeleton and covering installation.
Working principle:
The biggish components A of structure and part B are lifted with lifting device into position first, according to ground public-measurement point, establishes and flies
Machine coordinate, and with the shape key point of measuring instrument measuring part A and part B, then carried out according to the coordinate of shape key point
Posture adjustment, by the initial position of the shape key point after posture adjustment and sortie information preservation to primary data storage unit, then by initial
Data storage cell input data arithmetic element.Moving parts A and part B, make components A and part B be in theoretical position or
To the greatest extent close to theoretical position.Then fixation member A, along course direction moving parts B to close to theoretical position, carry out portion
The pre- pairing of part A and part B.In moving process, measuring instrument tracks the course location of shape key point, and by course location
It is sent to process data storage unit with measuring phases information, Data Computation Unit is transported to by process data storage patrilineal line of descent with only one son in each generation.Data
The initial position of shape key point is compared by arithmetic element with course location, if position degree variation is more than the threshold value of setting,
Alarm is then issued, and comparison result is sent to data display unit, operator is reminded to search reason.Survey aircraft bone at this time
Frame and components A, the amount of interference of part B, for instructing skeleton repair, if changeover portion skeleton and covering are mounted on threshold range
It is interior, then start moving parts B, it is known that eligible state.The hole location that airframe is connect with components A, part B is produced, it is outer in monitoring
Changeover portion skeleton is installed in the case of the coordinate of shape key point, avoids because assembly is forced to generate erection stress, causes docking section
The deformation of position part, improves assembling quality, extends Aircraft life etc., reduces the erection stress of aircraft docking operation.
Further, in the step S400 specifically:
Step S410: fixation member A, along course moving parts B to close to theoretical position 2mm, the skeleton of pre- pairing changeover portion,
The skeleton amount of interference with components A and part B respectively is measured, after being measured, part B exits original to far from the movement of components A direction
State；
Step S430: with the shape key point of measuring instrument measuring part A and part B, while the measuring phases letter of flag data
Breath is " pre- pairing 1 ", and sends data to process data storage unit；
Step S440: process data storage unit, which synchronizes data, is sent to Data Computation Unit, and Data Computation Unit has been calculated
Bi Hou is sent to data display unit when by fructufy.
Working principle:
When components A and part B are moved to theoretical position, the coordinate of shape key point is monitored with measuring instrument, and will acquisition
The measuring phases information of shape key point is sent to process data storage unit together.Data Computation Unit is stored from primary data
Unit and process data storage unit read data in real time, compare the initial external between course location of shape key point
Position degree variation, and calculated result is shown by data display unit.Therefore, the seat of shape key point can be monitored in real time
Mark, when shifting, can timely show, remind operator.
Further, in the step S500 specifically:
Step S510: received data are compared by Data Computation Unit with shape key point initial position, if position degree
Variation is less than the threshold value of setting, then enters step S600；Otherwise, then S520 is entered step；
Step S520: if skeleton repair amount is unsatisfactory for matching requirements, alarm, and return step S410 are issued；Otherwise, it enters step
S600。
Working principle:
If position degree variation is more than the threshold value of setting, alarm is issued, and return step S410 re-moves components A and component
The position of B.Until the course location of components A and part B and initial position within the set threshold range, then start changeover portion skeleton
It is installed with covering.
Further, in the step S600 specifically:
Step S610: the hole location that skeleton is connect with components A and part B is produced respectively；
Step S620: with the shape key point of measuring instrument measuring part A and part B, flag data measuring phases are that " skeleton is pre-
Fill drilling "；
Step S630: it is separately connected components A and part B with skeleton, changeover portion skeleton is installed.
Working principle:
Skeleton is connect with the hole location above components A, part B, carries out the installation of changeover portion skeleton, after being installed, components A and portion
Part B is separated with skeleton, components A and part B undercarriage.
Further, the measuring instrument in the step S400 uses laser tracker.
Working principle:
It is a kind of high-precision Large-scale Measuring Instruments in industrial measuring system using digitized laser tracker.It gathers
Laser interference ranging technology, detecting technique, precision machinery technology, computer and control technology, modern numerical calculation reason
By etc. various advanced technologies, to space movement target track and real-time measurement target 3 d space coordinate.It has height
Precision, high efficiency, real-time follow-up, it is quick for installation, easy to operate the features such as, be suitable for the equipped measurement of large-size workpiece.
The above is only presently preferred embodiments of the present invention, not does limitation in any form to the present invention, it is all according to
According to technical spirit any simple modification to the above embodiments of the invention, equivalent variations, protection of the invention is each fallen within
Within the scope of.
Claims (5)
1. a kind of aircraft assembling process stress monitor method based on profile measurement characterized by comprising
Step S100: components A and part B are lifted into position；
Step S200: setting ground public-measurement point establishes aircraft axes and measures the outer of measuring part A and part B respectively
Shape key point, according to shape key point by components A and part B posture adjustment；Choose the shape pass after the completion of components A and part B posture adjustment
Key point coordinate is transmitted to data operation together with sortie record as initial value, record to primary data storage unit
Unit；
Step S300: fixation member A, it is close to components A along course moving parts B, carry out the pre- pairing of components A and part B；
Step S400: changeover portion skeleton and covering trial assembly close shape in changeover portion skeleton and covering installation with measuring instrument
Key point process position is monitored, record shape key point course location to process data storage unit, while together with measurement rank
Segment information is sent to " Data Computation Unit " together；
Step S500: Data Computation Unit compares key point initial position and shape key point course location, if shape
The position degree variation of key point is more than preset threshold value, issues alarm, and result is sent to " data display unit ", " data
Display unit " shows warning information, otherwise enters in next step；
Step S600: changeover portion skeleton and covering installation.
2. a kind of aircraft assembling process stress monitor method based on profile measurement according to claim 1, feature exist
In in the step S400 specifically:
Step S410: fixation member A, along course moving parts B to close to theoretical position 2mm, the skeleton of pre- pairing changeover portion,
The skeleton amount of interference with components A and part B respectively is measured, after being measured, part B exits original to far from the movement of components A direction
State；
Step S430: with the shape key point of measuring instrument measuring part A and part B, while the measuring phases letter of flag data
Breath is " pre- pairing 1 ", and sends data to process data storage unit；
Step S440: process data storage unit, which synchronizes data, is sent to Data Computation Unit, and Data Computation Unit has been calculated
Bi Hou is sent to data display unit when by fructufy.
3. a kind of aircraft assembling process stress monitor method based on profile measurement according to claim 2, feature exist
In in the step S500 specifically:
Step S510: received data are compared by Data Computation Unit with shape key point initial position, if position degree
Variation is less than the threshold value of setting, then enters step S600；Otherwise, then S520 is entered step；
Step S520: if skeleton repair amount is unsatisfactory for matching requirements, alarm, and return step S410 are issued；Otherwise, it enters step
S600。
4. a kind of aircraft assembling process stress monitor method based on profile measurement according to claim 3, feature exist
In in the step S600 specifically:
Step S610: the hole location that skeleton is connect with components A and part B is produced respectively；
Step S620: with the shape key point of measuring instrument measuring part A and part B, flag data measuring phases are that " skeleton is pre-
Fill drilling "；
Step S630: it is separately connected components A and part B with skeleton, changeover portion skeleton is installed.
5. a kind of aircraft assembling process stress monitor method based on profile measurement according to claim 3, feature exist
In the measuring instrument in the step S400 uses laser tracker.
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