TY - GEN
T1 - RLV (Reusable Launch Vehicle) reentry nonlinear controller design
AU - Xu, Zhi
AU - Tang, Shuo
PY - 2010
Y1 - 2010
N2 - 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.
AB - 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.
KW - Nonlinear control
KW - Reentry
KW - Reusable Launch Vehicle
UR - http://www.scopus.com/inward/record.url?scp=78649985252&partnerID=8YFLogxK
U2 - 10.1109/CMCE.2010.5610293
DO - 10.1109/CMCE.2010.5610293
M3 - 会议稿件
AN - SCOPUS:78649985252
SN - 9781424479566
T3 - 2010 International Conference on Computer, Mechatronics, Control and Electronic Engineering, CMCE 2010
SP - 380
EP - 383
BT - 2010 International Conference on Computer, Mechatronics, Control and Electronic Engineering, CMCE 2010
T2 - 2010 International Conference on Computer, Mechatronics, Control and Electronic Engineering, CMCE 2010
Y2 - 24 August 2010 through 26 August 2010
ER -