Nonlinear H^|^infin; Control of Six DOF Rigid Body Spacecraft
نویسندگان
چکیده
منابع مشابه
Nonlinear H∞ Robust Control for Six DOF equations of motion of Rigid Body with Mass Uncertainty
This paper derives the analytic solution of nonlinear H∞ robust controller for a system with mass and moments of inertia uncertainties and investigates the implementation using control surface inverse algorithm. A special Lyapunov function with mass and moments of inertia uncertainties is introduced to solve the associated Hamilton-Jacobi partial differential inequality (HJPDI). The HJPDI is so...
متن کاملS0me Remarks on Nonlinear Feedback Control of a Rigid Spacecraft
This paper is dealing with the control of a rigid spacecraft. The nonlinear feedback controls, derived by using the approaches that have been recently developed, based on the port controlled hamiltonian (PCH) structure, are compared to the one derived by the methods based on the eigenstructure proposed by the author in previous work. The aim is to emphasize that, using the second approach appea...
متن کاملNonlinear Attitude Control for a Rigid Spacecraft by Feedback Linearization
Attitude control law design for spacecraft large angle maneuvers is investigated in this paper. The feedback linearization technique is applied to the design of a nonlinear tracking control law. The output function to be tracked is the quaternion attitude parameter. The designed control law turns out to be a combination of attitude and attitude rate tracking command. The attitude-only output fu...
متن کاملAalborg Universitet Quaternion Feedback Control for Rigid - body Spacecraft
This paper addresses three-axis attitude control for a Danish spacecraft, R mer. The algorithm proposed is based on an approximation of the exact feedback linearisation for quaternionic attitude representation. The proposed attitude controller is tested in a simulation study. The environmental disturbances correspond to those expected for the R mer mission. The pros and cons of the algorithm ar...
متن کاملAttitude stabilization of a rigid spacecraft using two control torques: A nonlinear control approach based on the spacecraft attitude dynamics
-The attitude stabilization problem of a rigid spacecraft using control torques supplied by gas jet actuators about only two of its principal axes is considered. If the uncontrolled principal axis of the spacecraft is not an axis of symmetry, then the complete spacecraft dynamics are small time locally controllable. However, the spacecraft cannot be asymptotically stabilized to any equilibrium ...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Transactions of the Society of Instrument and Control Engineers
سال: 2005
ISSN: 0453-4654
DOI: 10.9746/sicetr1965.41.193