Aircraft fuselage flexible and automatic attitude-adjusting method

An aircraft fuselage and flexible technology, applied in the field of automatic attitude adjustment and aircraft fuselage flexibility, can solve the problems of low adjustment accuracy, flexibility, poor versatility, and large assembly stress.

Inactive Publication Date: 2009-06-17
ZHEJIANG UNIV +1
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

This method has problems such as low adjustment accuracy and large assembly stress.
Moreover, this working method requires a large number of standard tooling and special assembly tooling for different assembly objects, which has poor flexibility and versatility, high cost, and low degree of automation.

Method used

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  • Aircraft fuselage flexible and automatic attitude-adjusting method
  • Aircraft fuselage flexible and automatic attitude-adjusting method
  • Aircraft fuselage flexible and automatic attitude-adjusting method

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Embodiment Construction

[0073] The flexible and automatic attitude adjustment method of the aircraft fuselage includes three stages: the attitude adjustment preparation stage, the fuselage attitude adjustment stage, and the attitude adjustment result evaluation and analysis stage.

[0074] The posture adjustment preparation phase includes the following steps:

[0075] 1) Using multiple three-coordinate locators to realize the spherical hinged support of the fuselage;

[0076] 2) Arrange laser tracker measurement targets at the key coordination positions of the fuselage and wing intersection holes, the fuselage and canard intersection holes, the fuselage and vertical tail intersection holes, and the fuselage and landing gear intersection holes of the aircraft;

[0077] 3) The laser tracker measures public observation points installed on a fixed platform, and directly uses the transfer function of the laser tracker to make the measurement coordinate system of the laser tracker consistent with the globa...

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Abstract

The invention discloses a method for flexibly and automatically adjusting posture of an airframe of an airplane. The method comprises: the spatial position of a target of the airframe is measured through a laser tracking instrument; a measuring result and a digital standard model are subjected to matched analysis to calculate the posture of the airframe; and finally a plurality of three-coordinate positioner units are controlled and driven to realize adjustment of the posture of the airframe. The whole posture adjusting process comprises three stages: a posture adjusting preparation stage, an airframe posture adjusting stage and a posture adjusting result evaluation and analysis stage to realize automatic and non-stress posture adjustment of the airframe. The method has the following advantages: 1, the method can realize digital posture adjustment of the airframe; 2, the airframe is supported by the plurality of the positioner units; and in the posture adjusting process, motion cooperativity of the airframe is monitored in real time to realize non-stress posture adjustment; 3, the method has good flexibility and compatibility and can meet the requirement of posture adjustment of various airplane models; and 4, the method can carry out quantitative evaluation and analysis on the posture adjusting result and obtain the position and posture of the airframe in a scene coordinate system.

Description

technical field [0001] The invention relates to a flexible and automatic attitude adjustment method for an aircraft fuselage in an aircraft digital assembly process. Background technique [0002] In the field of aircraft manufacturing, in order to achieve the best quality fuselage docking assembly and improve the aerodynamic performance of the aircraft, it is necessary to adjust the pose of large rigid body components such as the aircraft fuselage before assembly. [0003] Aircraft fuselage components are a unique object with large volume and mass, requiring high precision in pose adjustment, and the adjustment tooling is not allowed to cause damage to the fuselage surface or internal components. In the traditional frame-based manufacturing and assembly process, multiple jacks are generally used to support the fuselage, and the posture adjustment of components is realized by manual assisted positioning. This method has problems such as low adjustment accuracy and large asse...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64F5/10
Inventor 柯映林杨卫东王青李江雄方强蒋君侠秦龙刚毕运波贾叔士黄鹏俞慈君余进海郭志敏陈学良黄浦缙盖宇春刘刚
Owner ZHEJIANG UNIV
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