Simulation And Analysis On Flight Dynamics For The Launch Vehicle’s Ascent Stage

In modern local conflicts, aerospace information integration has played an importantrole. When the existing military satellite and rocket launch base have been destroyed, smallLaunch Vehicle is urgently used to rebuild new information systems. In this paper, dynamiccharacteristics for its ascent trajectory have been researched and analysis, including rigidbody dynamics, sloshing of tanks and elastic vibration.For Launch Vehicle, the precise control system and implementing agencies are the keysubsystems to ensure complete launch mission successfully. The structural features of theexisting launch vehicle have decided the swing motor as its actuators, which generate thecontrol force and torque. With large aspect ratio and small structural stiffness， its elasticvibration showed modal characteristics of a beam, and bending vibration equation forone-dimensional beam are used to describe the elastic vibration in pitch, yaw directions. Asfor tank sloshing problem, using the mass-spring-damper models to simulate liquidsloshing, and which has been proved to be effective and correct. Considering the abovefactors, the ascent stage ballistic simulation framework has been built based on Matlab/Simulink platform, and the analysis and evaluation its results indicate the model is correct.Through theoretical analysis and simulation on the launch vehicle，which provide someused suggestions and reference for related research in the field of small Launch Vehicle.