Simulation design and control experiment of Folding quadrotor UAV

To shorten the flight time and reduce the probability of being intercepted when the flight reaches the specified area, the overall design of a spring-foldable rotorcraft is presented. Virtual modeling analysis and motion simulation were carried out by using 3D modeling and simulation software. The parameters of the torsion spring folding mechanism are designed and calculated in detail by the mathematical model. On this basis, the control algorithm of the folded rotorcraft is studied to meet the attitude control requirements of the aircraft. Further through the actual flight test, multiple experimental data show that. The control system can meet the flight requirements of folding aircraft. Furthermore, the rationality of the design and the feasibility of the control algorithm is verified.