# Research on Prediction Method of Bolt Tightening for Aviation Components Based on Neural Network
###### Abstract  
Aviation components play an important role in national defense and aviation development. Bolt connections are widely used in the assembly of aviation components, due to their simple structure and convenient disassembly. In addition to the impact of elastic interaction, the gap between the tightened parts also makes it very difficult to obtain a uniform bolt load, to achieve the required tightness during the tightening process. However, the impact of elastic interaction can be reduced by selecting the best tightening sequence, and the optimal tightening sequence of aviation components under different gaps can be predicted by constructing a neural network surrogate model. Based on the predicted optimal sequence, the elastic interaction matrix corresponding to the sequence can be obtained. In order to obtain a uniform preload, the initial load of each bolt is calculated according to an elastic interaction matrix. This research has improved the tightness of aviation components and the real-life efficiency of tightening process planning. a +
Footnote †: journal: Medical Engineering  
-aviation component bolt tightening process. Thus, it is of great significance to study the bolt tightening technology of aviation components. In order to solve the above problems, researchers at home and abroad have launched research on the bolt tightening process. [PERSON] [2] proposed a new methodology called the tetraparametric assembly method (TAM). It was developed for a specific type of joint and calculates tightening loads using only two load steps and a small number of load measurements, thus presenting a much lower cost than the elastic interaction coefficients method. [PERSON] [3] developed a three-dimensional nonlinear finite element model for achieving a uniform clamp load in gasketed bolted joints. This model is used for both multiple- and single-pass tightening patterns. [PERSON] [4] studied an asymmetric multi-bolted connection at the preloading state. He tested two methods of bolt tightening and proposed an assembly method. [PERSON] [5] used finite element simulation and stress test experiments to study the effect of different bolt tightening sequences on the stress of a bolted workpiece. [PERSON] [6] proposed an analytical model based on the theory of circular beams on the linear elastic foundation. The elastic interaction during the tightening of bolted flange joints was simulated, to reduce the number of passes, while achieving bolt load uniformity. [PERSON] [7] built two sets of mechanical characteristic test systems to test the dynamic parameters of tangential and bending directions of a bolted flange joint interface. He studied the mechanical behavior and the change in regularities of dynamic parameters under different external excitations, bolt distributions, and tightening torques. [PERSON] [8] proposed a methodology for the optimization of the tightening sequence. The methodology provided satisfactory results with a very low computational cost. [PERSON] [9] established a mechanical model of the connection structure, and applied state-space theory and numerical calculation methods to numerically simulate an engine system with a bolted connection. Based on the TC4 single-bolt experimental system, [PERSON] [10] studied the influence of surface characteristics such as surface roughness and lubrication process parameters on the assembly process characteristics of aeroengine bolts. [PERSON] [11] analyzed the bending stiffness of bolts when an engine is tightened under different conditions. They obtained the influence of different factors on the bending stiffness of the bolts. [PERSON] [12] presented the results of the effect of different bolt tightening sequences and methods on the performance of a gasketed bolted flange joint using nonlinear finite element analysis. [PERSON] [13] presented a field experiment to study the interaction effects on clamp bolt tightening. [PERSON] [14] applied the Kriging method to investigate the influence of the tightening sequence for a solid rocket motor.