| UAV is widely used in military and civil fields due to its advantages of low cost and various functions,and the launching system is the most important prerequisite guarantee for the normal operation of UAV.Single rocket-launched unmanned aerial vehicles(UAVs)of a certain model are selected in this paper for studying the launch stage,so as to improve safety and stability amid takeoff.Dynamic analysis and finite element simulation were conducted to study from the ignition to the complete detachment of the UAV from the launcher.Simulation results are then compared with the actual attitude parameters obtained from experimental launching for verification.And parameters relevant to safe launching are analyzed and optimized.The overall plan of zero-length launch of UAVs is developed based on the general conditions of the UAV launch system,and a three-dimensional model of the UAV launch system is established using CATIA and optimized for dynamic analysis and finite element simulation.A mathematical model is established to reflect the launch dynamics of the UAV,and the law of motions during its launch and the equation of motion for its detachment are figured out through coupling of multidisciplinary data such as pneumatics and structure,to support the dynamic analysis of controlled takeoff.ABAQUS is used to establish a finite element simulation model of the UAV launch system for the study of the motion characteristics of the UAV during launch and the impacts on the UAV of its motions relative to the launcher.Therefore,the launcher structure is optimized and the stability of the UAV during its launch improved.Parameter values are obtained from launching tests and relevant conclusions are made.Through comparison with these experimental values,the finite element simulation results are verified and the model architecture is optimized.The research results in this paper can provide a theoretical basis for the design of the rocket launch design for UAVs. |
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