基于“N-2-1”定位的飞机壁板多源多序装配偏差传递建模方法研究

Aircraft panel is an important component to ensure the aerodynamic shape of the aircraft, there are complex factors influencing the panel assembly variation under multiple assembly processes, and the panel is easy to deform during the assembly process, the assembly precision of the panel can directly affect the quality of the following subassembly and final assembly of the aircraft, so in order to ensure the assembly precision of the aircraft, it is very important to achieve the accurate analysis of the assembly variation of the panel. According to the “N-2-1” positioning scheme of the panel, this research investigates the evolution rule of the contact force distribution of the skin during the positioning and clamping process, and the mechanism of its effect on the skin deformation, then further investigates the relationship among the skin clamping sequence, contact force distribution and skin deformation, to establish the method of positioning error analysis of the skin; the research investigates the evolution rule of the contact force distribution of the panel during the multiple riveting assembly process based on contact force modeling, then further investigates the relationship among the stringer riveting sequence, contact force distribution and panel deformation, to establish the method of assembly variation analysis of the panel under multiple assembly forces; the research investigates an assembly variation propagation model of the panel with multiple variation sources under multiple assembly processes based on state space modeling, to disclose the coupling effect of the assembly deformation, fixture variation and manufacturing variation on the assembly variation of the panel during assembly process, and express the evolution, propagation and accumulation rule of the assembly variation during multiple assembly processes. This research will provide the theoretical and technical support to achieve the assembly variation analysis of the aircraft panel more accurately, and control the propagation and accumulation of the assembly variation, to further improve the quality of the aircraft assembly.

飞机壁板作为飞机气动外形重要结构件，装配过程具有偏差因素复杂、工序多、易变形的特点，其装配精度直接影响后续飞机部装和总装装配质量，实现壁板装配偏差准确分析对于保证飞机装配精度具有重要意义。本项目针对壁板“N-2-1”定位，研究蒙皮装夹过程中接触力分布演变规律及其对蒙皮变形影响机理，研究蒙皮夹紧顺序、接触力分布及蒙皮变形之间影响关系，建立蒙皮定位偏差分析方法；基于接触力建模研究壁板多工序铆接装配过程中接触力分布演变规律，研究长桁铆接顺序、接触力分布及壁板变形之间影响关系，建立多种装配力作用下壁板装配偏差分析方法；基于状态空间建模研究壁板多源多序装配偏差传递模型，揭示装配变形、夹具偏差、零件制造偏差等多种偏差源对壁板装配偏差的耦合作用机制，表达装配偏差在多工序装配下的演变、传递与累积规律。本研究为更加准确地实现飞机壁板装配偏差分析，控制偏差传递与累积，进一步提高飞机装配质量提供理论与技术支持。

飞机壁板作为飞机气动外形重要结构件，装配过程具有偏差因素复杂、工序多、易变形的特点，其装配精度直接影响后续飞机部装和总装装配质量，实现壁板装配偏差准确分析对于保证飞机装配精度具有重要意义。.本项目针对壁板“N-2-1”定位，研究蒙皮装夹过程中接触力分布演变规律及其对蒙皮变形影响机理，研究蒙皮夹紧顺序、接触力分布及蒙皮变形之间影响关系，建立蒙皮定位偏差分析方法；基于接触力建模研究壁板多工序铆接装配过程中接触力分布演变规律，研究长桁铆接顺序、接触力分布及壁板变形之间影响关系，建立多种装配力作用下壁板装配偏差分析方法；基于状态空间建模研究壁板多源多序装配偏差传递模型，揭示装配变形、夹具偏差、零件制造偏差等多种偏差源对壁板装配偏差的耦合作用机制，表达装配偏差在多工序装配下的演变、传递与累积规律。.项目研究结果说明，飞机壁板在“N-2-1”定位模式下，在蒙皮多阶段装夹过程以及壁板多工序铆接装配过程中，壁板蒙皮与分布在不同位置的多个夹具元件之间的接触力会不断演变，且随不同的蒙皮装夹顺序及壁板铆接顺序演变规律不同，从而对壁板变形产生不同的影响，并导致不同的壁板装配偏差累积。通过在考虑接触力影响与不考虑接触力影响的情况下壁板关键特征点的法向装配偏差对比分析，进一步证明了“N-2-1”定位模式下壁板蒙皮与夹具元件之间接触力对壁板装配偏差的影响不可忽略，从而为更加准确地实现飞机壁板装配偏差分析提供了新的手段。.该项目研究具有明确的科学意义和应用前景，其不仅为飞机壁板装配偏差分析提供了新的理论和方法，为更加准确地实现飞机壁板装配偏差分析，进一步提高飞机装配质量提供了有力技术保障，同时，该研究也为其他类型柔性薄壁件装配偏差分析提供了理论和方法借鉴。