大型飞机翼身保形对接控制系统设计

发布时间：2019-06-26 17:53

【摘要】：保证飞机气动外形并消除装配应力是飞机装配追求的目标。某大型飞机采用多个三坐标数控定位器对机翼和机身分别进行支撑和调姿,通过机身中段开口处的四个接头与机翼中央翼盒处四个接头对接实现翼身对接装配。机身中段大开口结构降低了机身段整体刚度,在三坐标数控定位器支撑下,包括起落架在内的机身重力载荷使得翼身对接区产生变形,导致较大装配应力产生。本文针对该调姿对接系统提出力位混合控制方法,在保证机身段气动外形的前提下,通过各三坐标数控定位器的协同运动,对翼身对接区实施变形校正措施,实现翼身保形对接,减小翼身对接区装配应力。主要研究内容如下：首先,介绍国内外飞机大部件调姿系统的研究发展现状,总结变形校正理论技术以及飞机大部件保形装配的发展,并从并联机构学的角度综述调姿系统控制方法。其次阐述某大型飞机翼身调姿对接系统的调姿过程和系统组成,基于SynqNet现场总线技术设计多个三坐标数控定位器的协同运动控制系统。对翼身对接装配工艺和翼身对接区的机身大开口特殊结构进行详细分析,提出翼身对接装配中存在的变形问题及变形校正思路。然后设计实现翼身保形对接的力位混合控制系统。提出力位混合控制系统结构,应用螺旋理论和椭球法,选定参与机身调姿的6个三坐标数控定位器的位置控制轴和力控制轴组合。位置控制轴根据设定的调姿路径运动,实现机身调姿定位。力控制轴根据由正交试验和偏最小二乘回归反解得到的接触力作力伺服运动,对机身大开口处进行变形校正。接着采用计算机仿真技术研究调姿机构力位混合控制方法的变形校正效果。应用ABAQUS软件建立机身有限元简化模型,对采用力位混合控制的机身调姿系统进行有限元仿真。仿真结果表明翼身对接区的8个测点中有7个测点的变形得到了明显改善,证明了力位混合控制方法的变形校正效果。之后通过实际系统实验验证力位混合控制方法的变形校正效果。设计满足实际装配需要的定位器单轴控制系统,分别设计单轴控制系统的位置和力控制器。设计一维变形校正实验,采用力位混合控制方法对试件一维变形进行校正,实验结果表明力位混合控制方法对试件的变形校正效果优于位置控制方法。最后对本文的研究工作进行总结,并对未来研究工作进行展望。
[Abstract]:It is the goal of aircraft assembly to ensure the pneumatic shape of aircraft and eliminate the assembly stress. A large aircraft uses multiple three-coordinate NC locators to support and adjust the wing and fuselage respectively, and the wing body docking assembly is realized by docking the four joints at the middle opening of the fuselage with the four joints at the central wing box of the fuselage. The large opening structure in the middle part of the fuselage reduces the overall stiffness of the fuselage segment. Under the support of the three-coordinate NC locator, the gravity load of the fuselage, including the landing gear, causes the deformation of the opposite area of the wing body, resulting in a large assembly stress. In this paper, a force-level hybrid control method is proposed for the attitude adjustment and docking system. On the premise of ensuring the pneumatic shape of the fuselage section, through the cooperative motion of each three-coordinate NC locator, the deformation correction measures are carried out on the alignment area of the wing body, so as to realize the conformal docking of the wing body and reduce the assembly stress of the wing body alignment area. The main research contents are as follows: firstly, the research and development status of aircraft large component attitude adjustment system at home and abroad is introduced, the theory and technology of deformation correction and the development of aircraft large component conformal assembly are summarized, and the control methods of attitude adjustment system are summarized from the point of view of parallel mechanism. Secondly, the attitude adjustment process and system composition of a large aircraft wing pose adjustment and docking system are described. Based on SynqNet field bus technology, the cooperative motion control system of three coordinate NC locators is designed. The assembly technology of wing body docking and the special structure of fuselage with large opening in wing body docking area are analyzed in detail, and the deformation problems and deformation correction ideas in wing body docking assembly are put forward. Then the force level hybrid control system of wing shape-keeping docking is designed and realized. The structure of force level hybrid control system is put forward. The position control axis and force control axis combination of six three coordinate NC locators involved in fuselage attitude adjustment are selected by using spiral theory and ellipsoid method. The position control axis moves according to the set attitude adjustment path to realize the fuselage attitude adjustment and positioning. According to the contact force servo motion obtained by orthogonal test and partial least square regression inverse solution, the force control shaft corrects the deformation at the large opening of the fuselage. Then the deformation correction effect of the hybrid control method of attitude adjustment mechanism is studied by using computer simulation technology. The finite element simplified model of fuselage is established by using ABAQUS software, and the finite element simulation of fuselage attitude adjustment system with hybrid force and position control is carried out. The simulation results show that the deformation of 7 of the 8 measuring points in the opposite region of the wing body is obviously improved, and the deformation correction effect of the hybrid force and position control method is proved. Then the deformation correction effect of the force level hybrid control method is verified by the actual system experiment. The single axis control system of locator is designed to meet the needs of actual assembly, and the position and force controllers of single axis control system are designed respectively. The one-dimensional deformation correction experiment is designed, and the force-level hybrid control method is used to correct the one-dimensional deformation of the specimen. The experimental results show that the force-level hybrid control method is superior to the position control method in the deformation correction effect of the specimen. Finally, the research work of this paper is summarized, and the future research work is prospected.
【学位授予单位】：浙江大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V262.4

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