RLV(Reusable Launch Vehicle) Reentry Nonlinear Controller Design
Re-entry of Reusable Launch Vehicle(RLV) is the most challenging flight phase, which has a large of flight range, highly mobile, multi-border constraints (surface temperature constraints, normal overload constraints and dynamic pressure boundary constraints, etc.), complex actuators (air control surfaces and reaction control system) and other characteristics, so classical control system design is very difficult to meet the control requirements. In this paper, feedback linearization controller is designed based on the full rotational equations of motion rather than on a conventional model derived from time-scale separation. RLV six degrees of freedom dynamic nonlinear model is linearized by output feedback linearization theory, then classical PID control theory is applied to complete control system design and apply Matlab/simulink to complete the re-entry trajectory 6DOF model and the simulation results demonstrate that the controller be able to better track the guidance parameters and meet the controller design requirements.
component reusable launch vehicle Reentry Nonlinear Control
XU Zhi TANG Shuo
College of Astronautics Northwestern Polytecnical University Xian, China
国际会议
长春
英文
380-383
2010-08-24（万方平台首次上网日期，不代表论文的发表时间）