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Computation method for attitude of aircraft fuselage based on laser tracking instrument

A laser tracker, aircraft fuselage technology, used in instruments, optical devices, measurement devices, etc.

Inactive Publication Date: 2009-02-11
ZHEJIANG UNIV +1
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  • Description
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Problems solved by technology

The results obtained by matching calculations using the above methods often cannot meet these constraints

Method used

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  • Computation method for attitude of aircraft fuselage based on laser tracking instrument
  • Computation method for attitude of aircraft fuselage based on laser tracking instrument
  • Computation method for attitude of aircraft fuselage based on laser tracking instrument

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Experimental program
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Effect test

Embodiment

[0075] 1) In the measurement space, arrange 6 public observation points (2), all public observation points can be measured by the laser tracker A (1) and the laser tracker B (6); the fuselage parts are placed on the POGO column ( 5) on;

[0076] 2) Use the laser tracker A (1) to measure the three-dimensional coordinates of the public observation point (2), and establish an on-site reference coordinate system according to the needs of the site. Get the theoretical value of public observation point (2),

[0077] 3) According to the digital model of the fuselage, the coordinate values ​​of each measuring point (3) on the fuselage (4) are used as the theoretical values ​​of the measuring points of the aircraft fuselage when calculating the design zero attitude of the aircraft fuselage.

[0078] 4) Laser tracker A (1) and laser tracker B (6) measure the public observation point (2), and obtain the measurement value of the public observation point (2). According to the theoretical...

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Abstract

The invention discloses an aircraft body attitude calculation method which is based on laser trackers. The attitude calculation method adopts a plurality of laser trackers to measure measurement points which are arranged on the measured aircraft body and used for expressing the aircraft attitude, and the current attitude of the aircraft part is calculated through the measurement values the theoretical values under the ideal designed attitude of the measurement points. The attitude calculation method takes into account the constraints to part of the measurement points, uses a least square error expression as a target function, utilizes a multi-target optimization model to combine the constraints and point matching, utilizes the Newton method to solve the optimization problem and obtains the aircraft body best attitude which is in line with the conditions of the constraints. The attitude calculation method adopts the advanced laser measurement technology to improve the precision of the measurement of the aircraft attitude; the attitude calculation method uses a plurality of points to carry out the attitude assessment and improves the accuracy of the attitude calculation by distributing errors to various points through the optimization function; and the attitude assessment takes into account the constraints of the measurement points and increases the flexibility of the attitude calculation by regulating the errors through the manual adjustment of weight value.

Description

technical field [0001] The invention relates to the technical field of aviation manufacturing, in particular to a method for calculating the attitude of an aircraft fuselage based on a laser tracker. Background technique [0002] As a large-scale and high-precision measurement tool, the laser tracker is playing an increasingly important role in the digital assembly of large aircraft components. The invention patent (Application No. 99109623) applied by Tsinghua University discloses a target spatial position and attitude laser measurement and tracking system composed of a target mirror group, a tracking station group, and a computer control and data acquisition and processing system. The system can realize the measurement of target space coordinates, velocity, acceleration and full attitude. However, in order to obtain the position and attitude of the target in this method, the target measurement points can only take 3 points. And it is necessary to pre-calibrate the positi...

Claims

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Application Information

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IPC IPC(8): G01B11/00
Inventor 柯映林杨卫东李江雄俞慈君王青秦龙刚毕运波贾叔仕余进海陈学良
Owner ZHEJIANG UNIV
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