Research on the nose wheel rotation angle boundary of civil aircraft

Abstract Simulation is an important design tool in the engineering field. It plays a crucial role in the process of requirement analysis and confirmation in design. This paper first introduces the positioning of simulation in the design field and then establishes the models to analyze the nose wheel corner stability boundary based on mature dynamic models and the data from the engineering field. All these simulation models are built in the landing phase of an aircraft, considering the motion of an aircraft on the ground in this situation and analyzing the changes in the nose wheel steering angle under different weights. After analysis and calculation, we concluded that the higher the speed of the aircraft taxiing on the ground, the smaller the rotation angle of the nose wheels. The analysis results can be used as a reference for rotation angles in aircraft design.