Robust Adaptive Attitude Control of Crew Exploration Vehicles (CEVs) with Guaranteed Performance

High precision attitude control is vital to achieve safe and reliable operation of crew exploration vehicles (CEVs) such as docking (with service module) and landing (on the moon or earth). This work investigates a robust adaptive approach to adjusting CEV's orientation through the driving forces produced by various RCS engines mounted on the vehicle. By using the structural properties of the capsule vehicle and the 4-parameter (quaternion) orientation representation, a set of control algorithms are developed to ensure adaptive and robust attitude tracking of CEV. The proposed control scheme explicitly addresses 1) uncertain aerodynamics due to unpredictable disturbances; 2) time-varying and uncertain mass property of the vehicle due to fuel consumption, payload release, and/or modules separation; and 3) guaranteed tracking performance under varying operation conditions. It is shown that the developed control scheme does not demand detail vehicle system parameters/dynamics and asymptotic orientation tracking is achieved. Furthermore, tracking performance index is guaranteed bounded and there is no need to redesign or reprogram the control scheme under varying flight/operation conditions. Both theoretic analysis and simulation studies confirm the effectiveness of the proposed method.

[1]  T. Kane Solution of Kinematical Differential Equations for a Rigid Body , 1973 .

[2]  G. Meyer,et al.  DESIGN AND GLOBAL ANALYSIS OF SPACECRAFT ATTITUDE CONTROL SYSTEMS , 1971 .

[3]  Y. B. Shtessel,et al.  Reusable launch vehicle trajectory control in sliding modes , 1997, Proceedings of the 1997 American Control Conference (Cat. No.97CH36041).

[4]  Haim Weiss,et al.  Quarternion feedback regulator for spacecraft eigenaxis rotations , 1989 .

[5]  Roberto Alonso,et al.  Robust optimal solution to the attitude/force control problem , 2000, IEEE Trans. Aerosp. Electron. Syst..

[6]  Suresh M. Joshi,et al.  Passivity-based control of nonlinear flexible multibody systems , 1995 .

[7]  Yuri B. Shtessel,et al.  On-Line Computation of a Local Attainable Moment Set for Reusable Launch Vehicles , 2002 .

[8]  R. S. Sanchez Pena,et al.  Thruster design for position/attitude control of spacecraft , 2002 .

[9]  Ping Lu Entry Guidance and Trajectory Control for Reusable Launch Vehicle , 1997 .

[10]  B. Ickes A new method for performing digital control system attitude computations using quaternions , 1970 .

[11]  A. C. Robinson,et al.  ON THE USE OF QUATERNIONS IN SIMULATION OF RIGID-BODY MOTION , 1958 .

[12]  J. Wen,et al.  Robust attitude stabilization of spacecraft using nonlinear quaternion feedback , 1995, IEEE Trans. Autom. Control..

[13]  J. Wen,et al.  The attitude control problem , 1991 .

[14]  Bin Li,et al.  Neuro-Robust Reentry Path Control of Reusable Launch Vehicles , 2006 .

[15]  Y. D. Song Guaranteed Performance Control of Nonlinear Systems with Application to Flexible Space Structure , 1995 .

[16]  Bong Wie,et al.  Quaternion feedback for spacecraft large angle maneuvers , 1985 .

[17]  E. J. Haug,et al.  Computer aided kinematics and dynamics of mechanical systems. Vol. 1: basic methods , 1989 .

[18]  X.H. Liao,et al.  Neuro-variable structure flight control of reusable launch vehicles , 2005, Proceedings of the Thirty-Seventh Southeastern Symposium on System Theory, 2005. SSST '05..

[19]  Zhihua Qu Robust control of nonlinear systems by estimating time variant uncertainties , 2002, IEEE Trans. Autom. Control..