Abstract
A landing simulation of the twin-engine lateral force plate UAV was performed. Roll angle. At a constant pitch angle, the turning radius and turning center were controlled by PID control, and the descent rate was reduced depending on the altitude to attempt landing. The aircraft landed while making a stable turning flight, but the center of turning could not be maintained due to the influence of wind disturbance. It is considered that this is because the steering angle of the vertical steering blade was insufficient. In the future, we will conduct actual machine experiments based on this simulation result.
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