CN106915472A - A kind of airframe docks numeric terminal layout structure and layout method with head - Google Patents
A kind of airframe docks numeric terminal layout structure and layout method with head Download PDFInfo
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- CN106915472A CN106915472A CN201710127942.XA CN201710127942A CN106915472A CN 106915472 A CN106915472 A CN 106915472A CN 201710127942 A CN201710127942 A CN 201710127942A CN 106915472 A CN106915472 A CN 106915472A
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- fuselage
- head
- posture adjustment
- positioning unit
- operating desk
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S17/00—Systems using the reflection or reradiation of electromagnetic waves other than radio waves, e.g. lidar systems
- G01S17/66—Tracking systems using electromagnetic waves other than radio waves
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- Electromagnetism (AREA)
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Automatic Assembly (AREA)
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Abstract
A kind of airframe docks numeric terminal layout structure and layout method with head, belong to aircraft manufacturing mounting technology field, its structure includes that two fuselage brackets, head are raised wages positioning unit, fuselage posture adjustment positioning unit, two laser trackers, two interface operating desks, one fuselage end operating desk, two active operation ladders and an integrated control system operating desk, two fuselage brackets are located at airframe lower section, and head posture adjustment positioning unit and fuselage posture adjustment positioning unit are respectively arranged at the lower section of the head and fuselage；Two described laser trackers are symmetricly set in the both sides in front of head, form aircraft digital measurement field, two interface operating desks are respectively arranged the end that fuselage is arranged in the fuselage end operating desk described in head and fuselage abutment joint both sides, two described active operation ladders are arranged in fuselage both sides, and described integrated control system operating desk is integrated with measuring system, posture adjusting system, process management and Database Systems and completes docking control work.
Description
Technical field
The invention belongs to aircraft manufacturing mounting technology field, especially numeric terminal is docked with head with a kind of airframe
Layout structure and layout method are relevant.
Background technology
During the entire process of aircraft manufacturing production, the assembly work of aircraft account for general 50% workload, therefore improve
The operating efficiency of aircraft assembling is improved to the efficiency of whole aircraft manufacturing production process and made great sense.At present, it is domestic
The assembling of aircraft all uses traditional assembly method substantially, and aircraft Butt Assembling is carried out using frock, and people's measurement is being passed using station
On system working stand, this not only loses time, and increased the working strength of personnel, reduces work quality and efficiency.
The content of the invention
The purpose of the present invention is to overcome prior art not enough, there is provided a kind of airframe docks numeric terminal cloth with head
Office's structure and layout method.
A kind of airframe docks numeric terminal layout structure with head, it is characterized in that, described structure includes two machines
Body bracket, head are raised wages positioning unit, fuselage posture adjustment positioning unit, two laser trackers, two interface operating desks, one
Fuselage end operating desk, two active operation ladders and an integrated control system operating desk, two fuselage brackets are located at airframe
Lower section, support and protective effect are played to fuselage, in case fuselage landing accident occurs caused by equipment fault, while increased machine
The strong point of body, makes head fuselage assembling process more stablize；
The head posture adjustment positioning unit and fuselage posture adjustment positioning unit are respectively arranged at the lower section of the head and fuselage, head
Posture adjustment positioning unit and fuselage posture adjustment positioning unit are constituted by four three axis positioners, and each three axis positioner is provided with three-dimensional
Force snesor, real-time force monitoring during ensureing to carry out head and fuselage posture adjustment；
Two described laser trackers are symmetricly set in the both sides in front of head, form aircraft digital measurement field, and every is swashed
Optical tracker system is installed by the laser tracker pedestal lifted based on king bolt, and light path can in having adapted to laser tracker measurement process
Up to property and human users' convenience, realize without dead angle measurement；
Described two interface operating desks are respectively arranged in head and fuselage abutment joint both sides, for realizing aircraft exterior interface
Operation；
Described fuselage end operating desk is arranged at the end of fuselage, is operated into interior of aircraft docking area as personnel and material
Passage；
Two described active operation ladders are arranged in fuselage both sides, one man operation can voluntarily reach relevant position as needed,
For entering fuselage interior from external fuselage and completing the measurement work of external fuselage measurement point, and coordinate with locator, prevent
Only collided with locator and damage locator；
Described integrated control system operating desk is integrated with measuring system, posture adjusting system, process management and Database Systems and completes
Docking control work, is arranged at immediately below the top view of fuselage.
As the supplement to above-mentioned technical proposal and perfect, present invention additionally comprises following technical characteristic.
Described fuselage end operating desk includes electric up-down counter and the access way of fuselage interior is passed in and out for workman, is somebody's turn to do
The top of access way sets platform, and lifting counter will need the material rising used to be transported at platform when assembling, it is to avoid
Workman carries the trouble of material up and down.
Further, the table surface height of the platform is identical with the floor level in aircraft cabin, facilitates workman to pass in and out fuselage
It is internal.
Further, anti-collision rubber bar is installed near aircraft side on the platform, it is to avoid misoperation is anticipated
Damaged when outer aircraft.
Described numeric terminal layout structure also includes an internal work being made using aluminium alloy lightweight material
Ladder, internal work ladder is positioned on the joint floor of aircraft cabin inside, primarily to being applicable internal docking area adapts to space
Height and the height differences demand of people.
Further, the surrounding of the internal work ladder is provided with anti-collision rubber, in order to avoid working stand collsion damage aircraft.
A technique bracket, machine are correspondingly arranged on respectively on the head posture adjustment positioning unit and fuselage posture adjustment positioning unit
Head and fuselage are respectively placed on each self-corresponding technique bracket, when being mainly to ensure that head and fuselage posture adjustment rigidly avoid posture adjustment
Pull phenomenon.
Described interface operating desk is divided into 2 layers of Liftable type operating desk and base, meets workman and is constructed in arbitrary height,
Using electric model, earth leakage protective, there are jerk, spacing, anticollision device, collision-prevention device.
A kind of airframe docks numeric terminal layout method with head, it is characterized in that, comprise the following steps：First
Step, System self-test is carried out by integrated control system operating desk；Second step, digitized measurement is built by two laser trackers
；3rd step, enters position to head posture adjustment positioning unit, by the corresponding technique bracket of fuselage by the corresponding technique bracket correspondence of head
Correspondence enters position to fuselage posture adjustment positioning unit；4th step, lifts position to the corresponding technique bracket of fuselage, to machine by forebody
Body realizes flexible support；5th step, is adjusted using active operation ladder measurement fuselage measurement point and by fuselage posture adjustment positioning unit
Appearance；6th step, position is lifted to the corresponding technique bracket of head by head, and flexible support is realized to head；7th step, utilizes
Active operation ladder measures head measurement point and by head posture adjustment positioning unit posture adjustment；8th step, by fuselage bracket, interface
Operating desk, fuselage end operating desk, internal work ladder enter position and complete related docking operation；9th step, by fuselage bracket, interface
Operating desk, fuselage end operating desk, internal work ladder return；Tenth step, the fuselage and head after docking are integrally transferred from, and are completed
Butt Assembling.
The present invention can reach following beneficial effect：Integrated application of the present invention includes digital coordination technology, digitlization
The various advanced technologies such as emulation technology, Digital Measuring Technique, Digital location technology, virtual five axles posture adjustment technology, set up
Advanced digitlization Butt Assembling system, improves efficiency of assembling and assembly precision.
Brief description of the drawings
Fig. 1 is front view of the invention.
Fig. 2 is top view of the invention.
Fig. 3 is left view of the invention.
Fig. 4 is right view of the invention.
Specific embodiment
Specific embodiment of the invention is described in detail below in conjunction with the accompanying drawings.
As shown in Fig. 1 ~ Fig. 4, airframe of the invention 2 docks numeric terminal layout structure, including two machines with head
Body bracket 5, head is raised wages positioning unit, the interface operating desk 8 of laser tracker 10, two of fuselage posture adjustment positioning unit 7, two
With internal work ladder, 4, two active operations ladders 3 of fuselage end operating desk and an integrated control system operating desk 6, two machines
Body bracket 5 is located at the lower section of airframe 2, and support and protective effect are played to fuselage.
Head posture adjustment positioning unit 9 and fuselage posture adjustment positioning unit 7 are respectively arranged at the lower section of the head 1 and fuselage 2,
A technique bracket, the He of head 1 are correspondingly arranged on the head posture adjustment positioning unit 9 and fuselage posture adjustment positioning unit 7 respectively
Fuselage 2 is respectively placed on each self-corresponding technique bracket, head posture adjustment positioning unit 9 and fuselage posture adjustment positioning unit 7 by
Four three axis positioners compositions, each three axis positioner is provided with three-dimensional force sensor, to ensure to carry out head 1 and fuselage 2
Real-time force monitoring during posture adjustment；
Two described laser trackers 10 are symmetricly set in the both sides in the front of head 1, form aircraft digital measurement field, every
Laser tracker 10 is installed by the pedestal of laser tracker 10 lifted based on king bolt, has adapted to the measurement process of laser tracker 10
Middle light path accessibility and human users' convenience；
Described two interface operating desks 8 are respectively arranged in head 1 and the abutment joint both sides of fuselage 2, and 8 points of interface operating desk is 2
Layer Liftable type operating desk and base, meet workman and are constructed in arbitrary height, using electric model, earth leakage protective, there is jerk, limit
Position, anticollision device, collision-prevention device, the operation for realizing aircraft exterior interface；
Described fuselage end operating desk 4 is arranged at the end of fuselage, and fuselage end operating desk 4 includes electric up-down counter and confession
Access way inside workman's turnover fuselage 2, the top of the access way sets platform, and lifting counter will need to use when assembling
Material rise be transported at platform, the table surface height of platform is identical with the floor level in aircraft cabin, facilitates workman to pass in and out
Inside fuselage 2, anti-collision rubber bar is installed near aircraft side on platform, it is to avoid damaged when misoperation or unexpected generation winged
Machine；Internal work ladder 12 is positioned on the joint floor of aircraft cabin inside, and the surrounding of the internal work ladder 12 is provided with anti-
Rubber is hit, in order to avoid working stand collsion damage aircraft, each internal work 12 plug-in battery-type electric lights of ladder are improving inside
Operation brightness, each working stand 12 is made up of two faces, and one of face possesses the body that elevating function adapts to space height and people
High Defferential demand；Two described active operation ladders 3 are arranged in the both sides of fuselage 2, are power by reliable motorized motions, using shifting
Dynamic lift truck form, single-grip control, you can relevant position is voluntarily reached with one man operation as needed, for from outside fuselage 2
Portion enters the inside of fuselage 2 and completes the measurement work of the externally measured point of fuselage 2, and coordinates with locator, prevents and locator
Collide and damage locator, and can be raised with variable raising and lowering speed control and reduction action, active operation ladder 3
Using compact design, it is allowed to rotated around the axletree of oneself, the limited space of turnover is lighter, and reliable motorized motions are liter
Drop car provides lasting power, and built-in automatic charger can be realized filling soon, for from the outside of fuselage 2 enter inside fuselage 2 with
And completing the measurement work of the externally measured point of fuselage 2, i.e., one can directly open this driver and hold target ball or T-Probe and complete
Measurement work is without as conventional conventional operation ladder needs people first to move ladder, high and low realizes measurement, and and locator again again
Hight coordinate；Described integrated control system operating desk 6 is integrated with measuring system, posture adjusting system, process management and data base set
System completes docking control work, is arranged at the side-lower of fuselage 2.
Airframe of the invention 2 docks numeric terminal layout method with head, comprises the following steps：The first step, leads to
Crossing integrated control system operating desk carries out System self-test；Second step, digitized measurement is built by two laser tracker 10；The
Three steps, position to head posture adjustment positioning unit 9 is entered by die process bracket correspondence, and the corresponding technique bracket correspondence of fuselage is entered into position extremely
Fuselage posture adjustment positioning unit 7；4th step, position is lifted to the corresponding technique bracket of fuselage by forebody 2, and fuselage 2 is realized
Flexible support；5th step, the measurement point of fuselage 2 is measured and by the posture adjustment of fuselage posture adjustment positioning unit 7 using active operation ladder 3；
6th step, position is lifted to the corresponding technique bracket 11 of head by head 1, and flexible support is realized to head 1；7th step, profit
Head measurement point is measured with active operation ladder 3 and by the posture adjustment of head posture adjustment positioning unit 9；8th step, by fuselage bracket 5,
Interface operating desk 8, fuselage end operating desk 4, internal work ladder 12 enter position and complete related docking operation；9th step, by fuselage
Bracket 5, interface operating desk 8, fuselage end operating desk 4, internal work 12 returns of ladder；Tenth step, by the He of fuselage 2 after docking
The overall distancing of head 1, completes Butt Assembling.
Claims (9)
1. a kind of airframe docks numeric terminal layout structure with head, it is characterised in that：Described structure includes two machines
Body bracket, head are raised wages positioning unit, fuselage posture adjustment positioning unit, two laser trackers, two interface operating desks, one
Fuselage end operating desk, two active operation ladders and an integrated control system operating desk, two fuselage brackets are located under airframe
Side, support and protective effect are played to fuselage, and head posture adjustment positioning unit and fuselage posture adjustment positioning unit are respectively arranged at described
The lower section of head and fuselage, head posture adjustment positioning unit and fuselage posture adjustment positioning unit are constituted by four three axis positioners, respectively
Individual three axis positioner is provided with three-dimensional force sensor, real-time force monitoring during ensureing to carry out head and fuselage posture adjustment；
Two described laser trackers are symmetricly set in the both sides in front of head, form aircraft digital measurement field, and every is swashed
Optical tracker system is installed by the laser tracker pedestal lifted based on king bolt, and light path can in having adapted to laser tracker measurement process
Up to property and human users' convenience；
Described two interface operating desks are respectively arranged in head and fuselage abutment joint both sides, for realizing aircraft exterior interface
Operation；
Described fuselage end operating desk is arranged at the end of fuselage, is operated into interior of aircraft docking area as personnel and material
Passage；
Two described active operation ladders are arranged in fuselage both sides, one man operation can voluntarily reach relevant position as needed,
For entering fuselage interior from external fuselage and completing the measurement work of external fuselage measurement point, and coordinate with locator, prevent
Only collided with locator and damage locator；
Described integrated control system operating desk is integrated with measuring system, posture adjusting system, process management and Database Systems and completes
Docking control work, is arranged at fuselage side-lower.
2. a kind of airframe docks numeric terminal layout structure with head according to claim 1, it is characterised in that：Institute
The fuselage end operating desk stated includes electric up-down counter and the access way for workman's turnover fuselage interior, the access way
Top sets platform, lifting counter will need the material used to rise to be transported at platform when will assemble, it is to avoid workman removes up and down
Transport the trouble of material.
3. a kind of airframe docks numeric terminal layout structure with head according to claim 2, it is characterised in that：Institute
The table surface height for stating platform is identical with the floor level in aircraft cabin, facilitates workman to pass in and out fuselage interior.
4. a kind of airframe docks numeric terminal layout structure with head according to claim 3, it is characterised in that：Institute
State and anti-collision rubber bar is installed near aircraft side on platform, it is to avoid misoperation occurs aircraft of being damaged during accident.
5. a kind of airframe docks numeric terminal layout structure with head according to claim 4, it is characterised in that：Institute
The numeric terminal layout structure stated also includes an internal work ladder being made using aluminium alloy lightweight material, internal work
Ladder is positioned on the joint floor of aircraft cabin inside, primarily to being applicable the body that internal docking area adapts to space height and people
High Defferential demand.
6. a kind of airframe docks numeric terminal layout structure with head according to claim 5, it is characterised in that：Institute
The surrounding for stating internal work ladder is provided with anti-collision rubber.
7. a kind of airframe docks numeric terminal layout structure with head according to claim 6, it is characterised in that：Institute
State and be correspondingly arranged on a technique bracket on head posture adjustment positioning unit and fuselage posture adjustment positioning unit respectively, head and fuselage divide
It is not positioned on each self-corresponding technique bracket, is mainly to ensure that head and fuselage posture adjustment rigidly avoid being pullled during posture adjustment now
As.
8. a kind of airframe docks numeric terminal layout structure with head according to claim 7, it is characterised in that：Institute
The interface operating desk stated is divided into 2 layers of Liftable type operating desk and base, meets workman and is constructed in arbitrary height, using electronic mould
Formula, earth leakage protective has jerk, spacing, anticollision device, collision-prevention device.
9. a kind of airframe docks numeric terminal layout method with head, it is characterised in that：Comprise the following steps：First
Step, System self-test is carried out by integrated control system operating desk；Second step, digitized measurement is built by two laser trackers
；3rd step, enters position to head posture adjustment positioning unit, by the corresponding technique bracket of fuselage by the corresponding technique bracket correspondence of head
Correspondence enters position to fuselage posture adjustment positioning unit；4th step, lifts position to the corresponding technique bracket of fuselage, to machine by forebody
Body realizes flexible support；5th step, is adjusted using active operation ladder measurement fuselage measurement point and by fuselage posture adjustment positioning unit
Appearance；6th step, position is lifted to the corresponding technique bracket of head by head, and flexible support is realized to head；7th step, utilizes
Active operation ladder measures head measurement point and by head posture adjustment positioning unit posture adjustment；8th step, by fuselage bracket, interface
Operating desk, fuselage end operating desk, internal work ladder enter position and complete related docking operation；9th step, by fuselage bracket, interface
Operating desk, fuselage end operating desk, internal work ladder return；Tenth step, the fuselage and head after docking are integrally transferred from, and are completed
Butt Assembling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710127942.XA CN106915472B (en) | 2017-03-06 | 2017-03-06 | Digital assembly layout structure and layout method for docking of airplane body and nose |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710127942.XA CN106915472B (en) | 2017-03-06 | 2017-03-06 | Digital assembly layout structure and layout method for docking of airplane body and nose |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106915472A true CN106915472A (en) | 2017-07-04 |
| CN106915472B CN106915472B (en) | 2023-05-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710127942.XA Active CN106915472B (en) | 2017-03-06 | 2017-03-06 | Digital assembly layout structure and layout method for docking of airplane body and nose |
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| Country | Link |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109541625A (en) * | 2018-11-27 | 2019-03-29 | 中国农业大学 | Plant protection drone flight parameter measurement method and system |
| CN110406693A (en) * | 2018-04-26 | 2019-11-05 | 波音公司 | Flexible rail manufacture system and method |
| CN114954995A (en) * | 2021-02-28 | 2022-08-30 | 浙江大学 | Automatic lifting support device with support force monitoring function |
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| CN1432509A (en) * | 2002-01-14 | 2003-07-30 | 奥特玛尔·法里昂 | Maintenance mount unit for aeroplane, etc. |
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| Publication number | Publication date |
|---|---|
| CN106915472B (en) | 2023-05-09 |
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