CN105651205A

CN105651205A - Enclosure frame type butting face verticality detection process for airplane part employing level meter to realize positioning and processing

Info

Publication number: CN105651205A
Application number: CN201410650202.0A
Authority: CN
Inventors: 范斌; 杨根军; 王梅; 吴军豪; 林震宇; 叶青; 姚展; 谢佰玲; 王宁
Original assignee: AVIC Shaanxi Aircraft Industry Group Corp Ltd
Current assignee: Shaanxi Aircraft Industry Co Ltd
Priority date: 2014-11-14
Filing date: 2014-11-14
Publication date: 2016-06-08
Anticipated expiration: 2034-11-14
Also published as: CN105651205B

Abstract

The invention provides an enclosure frame type butting face verticality detection process for an airplane part employing a level meter to realize positioning and processing. According to the process, large-scale reconstruction for an original precisely-processed system is not necessary, rapid construction of a digital measurement field for the precisely-processed system of traditional parts can be realized, digital measurement equipment such as a laser tracker is utilized to carry out digital detection, accuracy of evaluation on detection precision and plane verticality of an enclosure frame type butting face of a product after precise processing is improved, and thereby an artificial measurement error caused by measurement through a traditional optical measurer in the prior art can be avoided.

Description

A kind of peripheral frame formula interface measuring for verticality process for the aircraft components adopting the processing of level indicator location

Technical field

The invention belongs to aircraft assembling detection technique field, particularly to a kind of peripheral frame formula interface measuring for verticality process for the aircraft components adopting the processing of level indicator location.

Background technology

In order to eliminate the accumulated error formed in part manufacture and assembling process due to reasons such as location and deformation, adopt the method that surplus compensates namely after airfoil member assembly work completes, special process equipment is used to reprocess peripheral frame formula interface by the requirement of wing horizontal survey state, to meet exchange coordination between airfoil member and matching requirements, therefore the perpendicularity of peripheral frame formula interface requires higher.

In traditional aircraft components Finish Machining System, level indicator is adopted to determine product attitude by the method for horizontal survey with the earth for benchmark, after peripheral frame formula interface is carried out plane milling polish by special purpose machine tool in use system, adopt ruler and range quadrant to ride against and docking plane detects end face perpendicularity relative to the earth by the scale corresponding to the bubble on range quadrant. Owing to the certainty of measurement of the traditional optical such as level indicator and range quadrant measurement instrument is not high, there is the artificial collimation error when reading in result, causes that testing result is unstable, easily causes erroneous judgement and determines by mistake.

Adopt digital measuring method to be greatly improved Product checking precision when parts polish, but owing to mostly domestic air mail enterprise major part legacy device Finish Machining System is what the 80s and 90s in last century manufactured and designed, now domestic not yet introduce laser tracker, all use optical instrument detection product attitude and check frock, employing type rock is as the manufacture benchmark of fixture system, and it is not provided with the datum mark of laser measurement, it is impossible to directly apply the digitized measurement equipment such as laser tracker. Simultaneously, for in these domestic air mail enterprises still using, large number of legacy device Finish Machining System, if building digitized measurement coordinate system by increasing the method for laser measurement datum mark (OTB point) on original polish type frame basis, there will be newly constructed digitized measurement coordinate system and original inharmonious phenomenon of frock coordinate system determined by type rock, cause that measurement error is bigger.

Summary of the invention

It is an object of the invention to: the optical instrument detection method interface squareness measurement error overcoming traditional aircraft components Finish Machining System Central Plains traditional is relatively big, and directly cannot accurately build the digitized measurement field problem to use digitized measurement equipment.

Technical solution of the present invention provides a kind of peripheral frame formula interface measuring for verticality process for the aircraft components adopting the processing of level indicator location, comprises the following steps:

A, theorizes coordinate system with the ideal position of the plane of peripheral frame formula interface (1) and string plane for benchmark;

B, composes theoretical coordinate value with theoretical coordinate system for the butt hole 5 that benchmark is peripheral frame formula interface 1, and composes theoretical coordinate value for measuring the measuring basis hole 4 on flat board 2;

C, makees to measure flat board 2 by theoretical coordinate system, and described measurement flat board 2 includes the fixing hole corresponding with butt hole 5 and measuring basis hole 4;

D, installs measurement flat board 2 at parts peripheral frame formula interface 1 by maximum envelope principle, and described peripheral frame formula interface 1 is connected with fixing hole bolt by the butt hole 5 of link position with described measurement flat board 2;

E, adopting laser tracker that measuring basis hole 4 measurement measured on flat board 2 is obtained the actual coordinate value in described measuring basis hole 4, being fitted with the theoretical coordinate value in corresponding measuring basis hole 4, thus building digitized actual coordinates;

F, with digitized actual coordinates for benchmark, adopts laser tracker that the butt hole 5 of peripheral frame formula interface 1 is detected;

G, under digitized actual coordinates, peripheral frame formula interface 1 is fitted to a plane by the measurement result according to butt hole 5;

H, compares fit Plane with the airfoil chord plane in digitized actual coordinates and measures interface perpendicularity.

The invention have the advantage that without former Finish Machining System is carried out large-scale redevelopment, achieve the digitized measurement field rapid build of legacy device Finish Machining System, the digitized measurement equipment such as laser tracker are used to be digitized detection, improve the evaluation accuracy of the accuracy of detection after product peripheral frame formula interface polish and plane verticality, thus avoiding traditional optical in prior art to measure the artificial measurement error that apparatus measures is brought.

Accompanying drawing explanation

Below accompanying drawing of the present invention is illustrated:

Fig. 1 is that digital coordinate system builds schematic diagram;

Fig. 2 is laser tracker detection schematic diagram.

Detailed description of the invention

Below in conjunction with accompanying drawing and detailed description of the invention, the present invention is described in further detail:

A, sets up (X, Y, Z) theoretical coordinate system with the plane of peripheral frame formula interface 1 and string plane for benchmark;

B, with (X, Y, Z) theoretical coordinate system for benchmark, theoretical coordinate value is composed (such as a hole (Xa for interface butt hole (a, b, c ...), Ya, Za) ...), measure measuring basis hole (A, B, C ...) on flat board and compose theoretical coordinate value (such as A hole (XA, YA, ZA) ...);

C, flat board 2 is measured in digital control processing, make fixing hole and measuring basis hole (A, B, C ...) that the butt hole (a, b, c ...) with peripheral frame formula interface 1 is connected, it is ensured that measure the relative tertiary location of the fixing hole on flat board 2 and measuring basis hole (A, B, C ...);

D, installs measurement flat board 2 by maximum envelope principle on peripheral frame formula interface 1 four jiaos, adopts bolt to be connected with the fixing hole measured on flat board 2 by the butt hole (a, b, c ...) of peripheral frame formula interface 1;

E, adopt the laser tracker 3 measuring basis hole (A, B, C ...) measurement to measuring on flat board 2, according to measurement result (A hole (XA1, YA1, ZA1), B hole (XB1, YB1, ZB1) ...) measure point theoretical assignment (A hole (XA, YA with corresponding, ZA), B hole (XB, YB, ZB) ...) it is fitted, thus building digitized actual coordinates (X1, Y1, Z1);

F, with digitized actual coordinates (X1, Y1, Z1) for benchmark, adopts laser tracker 3 to use target that the butt hole (a, b, c ...) on peripheral frame formula interface 1 is detected;

G, according to butt hole (a, b, c ...) measurement result (such as a hole (Xa1, Ya1, Za1) ... c hole (Xc1 under digitized actual coordinates (X1, Y1, Z1), Yc1, Zc1) ...) interface fitted to a plane;

H, compares fit Plane with the interior airfoil chord plane of digitized actual coordinates (X1, Y1, Z1) and measures interface perpendicularity.

Claims

1. the peripheral frame formula interface measuring for verticality process for the aircraft components adopting the processing of level indicator location, it is characterised in that comprise the following steps:

B, composes theoretical coordinate value with theoretical coordinate system for the butt hole (5) that benchmark is peripheral frame formula interface (1), and composes theoretical coordinate value for measuring the measuring basis hole (4) on flat board (2);

C, makees to measure flat board (2) by theoretical coordinate system, and described measurement flat board (2) includes the fixing hole corresponding with butt hole (5) and measuring basis hole (4);

D, installing measurement flat board (2) at parts peripheral frame formula interface (1) by maximum envelope principle, described peripheral frame formula interface (1) is connected with fixing hole bolt by the butt hole (5) of link position with described measurement flat board (2);

E, laser tracker measuring basis hole (4) measurement to measuring on flat board (2) is adopted to obtain the actual coordinate value of described measuring basis hole (4), it is fitted with the theoretical coordinate value of corresponding measuring basis hole (4), thus building digitized actual coordinates;

F, with digitized actual coordinates for benchmark, adopts laser tracker that the butt hole (5) of peripheral frame formula interface (1) is detected;

G, under digitized actual coordinates, peripheral frame formula interface (1) is fitted to a plane by the measurement result according to butt hole (5);