Research On Control Method For Moving Mass Reentry Vehicle

As the contiuous deeping of astronautical technology, traditional spacecrafts,due to their small load, heavy heat insulations and high cost, could no longer meetthe requirements of further tasks. While the inflatable reentry spacecraft, with theoutstanding advantage of smaller size, lighter quality and larger loads, needs to bestudied about their theoretic value. This paper has researched the kinematic model,attitude dynamics analysis and control law design of inflatable reentry variablecentroid spacecraft, with following details：1. This paper take inflatable reentry spacecraft as the research object, thesystem of which been divided into two parts: the hull and the slider. By usingslider’s movement and thruster’s thrust as the control variable in equation, system’skinematic model has been built, based on the angular momentum theorem andmomentum theorem.2. Based on the established system kinematics mode, this paper discussedvarious factors which effecting the system’s attitude motion and dynamic quality.Also, in order to further simplify the model’s analysis, system’s characteristicparameter has been optimized.3. According to the prior analysis of the system’s attitude kinematics model,this paper educed system’s attitude kine matics model after the optimization oflayout parameters, and obtained the system’s control model by using linearizationmethod.Further on, by observing the characteristics of three channels, feedforwardand feedback methods is used to control the pitch channel, and slid ing modelcontroller is used to control the roll channel and maintain yaw channel’s stability.