The attitude tracking control problem of a rigid spacecraft with external disturbances is addressed using the concept of extended disturbance and the inverse optimal control method. The proposed attitude tracking control law is inverse optimal with respect to a meaningful cost functional and the associated Lyapunov function satisfies a HamiltonJacobi-Isaacs partial differential equation. Hence,...

The attitude dynamics and manoeuvre survey in this paper is performed for a mission scenario involving a penetrator-type spacecraft, a semi-rigid axisymmetric prolate spacecraft spinning around its minor axis of inertia, requested to perform a 90° spin axis reorientation manoeuvre. In contrast to most existing spacecraft only one attitude control torque is available, perpendicular to the spin a...

Abstract Model-error control synthesis is a nonlinear robust control approach that mitigates the effects of modeling errors and disturbances on a system by providing corrections to the nominal control input directly. In this paper model-error control synthesis is applied to the spacecraft attitude control problem, where the model-error vector is computed using a receding-horizon approximation. ...

In this paper, two different algorithms are presented for the estimation of spacecraft body angular rates in the absence of gyro rate data for a star tracker mission. In first approach, body angular rates are estimated with the spacecraft attitude using a dynamical model of the spacecraft. The second approach makes use of a rapid update rate of star camera to estimate the spacecraft body angula...

This paper deals with the problem of simultaneous vibration suppression and robust attitude control of orbiting spacecraft with flexible appendages. Based on integral variable structure control theory, a discontinuous attitude control law is firstly derived to achieve the desired position of the spacecraft, taking explicitly into account external disturbance and nonlinearity. To reconstruct est...

This paper investigates the design of spacecraft attitude stabilization controllers that are robust against actuator faults and external disturbances. A nominal controller is developed initially, using the adaptive backstepping technique, to stabilize asymptotically the spacecraft attitude when the actuators are fault-free. Additive faults and the partial loss of actuator effectiveness are cons...

A model reference adaptive control method is proposed for uncertain nonlinear characteristics of spacecraft attitude control system. This method combines fuzzy control methodology and nonlinear feedback linearization methodology, which made the closed-loop system stable and the state of fuzzy system track the state of reference model according to the parallel distributed compensation theory and...

A method of using magnetic torque rods to do 3axis spacecraft attitude control has been developed. The goal of this system is to achieve a nadir pointing accuracy on the order of 0.1 to 1.0 deg without the need for thrusters or wheels. The open-loop system is under-actuated because magnetic torque rods cannot torque about the local magnetic field direction. This direction moves in space as the ...

In this paper, two different algorithms are presented for the estimation of spacecraft body angular rates in the absence of gyro rate data for a star tracker mission. In first approach, body angular rates are estimated with the spacecraft attitude using a dynamical model of the spacecraft. The second approach makes use of a rapid update rate of star camera to estimate the spacecraft body angula...

A continuous feedback controller with a periodic time varying term for the attitude control of an un-deractuated rigid spacecraft is derived. The attitude is described with the Euler parameter vector. Due to the nondiierentiable nature of exponential stabilizers , sampling of some measurements is used. Global exponential convergence is indicated with analysis and simulations.