One of the simplest and most popular methods to design a model-based controller for nonlinear dynamic system is apply linear control theories linearized model system. For linearization, first-order Taylor series expansion straightforward widely used method. Although related linearization method fairly simple, unfortunately, it causes an error in model, especially highly systems. Different strat...

In this paper, a quaternion-based finite-time sliding mode attitude controller is designed for a spacecraft performing high-thrust orbital maneuvers, with cold gas thrusters as its actuators. The proposed controller results are compared with those of a quaternion feedback controller developed for the linearized spacecraft dynamics, in terms of settling time, steady-state error, number of thrust...

Predictive control technique is applied to the three-axis attitude control of spacecraft. The principal idea of predictive control is to construct a priori reference trajectory and build control command so that the actual system follows the reference trajectory. In the case of this study, the controlled variables are the quaternion attitude parameters and angular rates of spacecraft body axes. ...

The attitude dynamics of a spacecraft with a variable speed control moment gyroscope (CMG), in the presence of conservative external inputs, are derived using variational principles. A complete dynamics model, that relaxes some of the assumptions made in prior literature on control moment gyroscopes, is obtained. These dynamics equations show the complex nonlinear coupling between the internal ...

One of the main control challenges of National Aeronautics and Space Administration’s proposed Asteroid Redirect Mission (ARM) is to stabilize and control the attitude of the spacecraft-asteroid combination in the presence of large uncertainty in the physical model of a captured asteroid. We present a new robust nonlinear tracking control law that guarantees global exponential convergence of th...

In this paper we present a PID+ backstepping controller, as a solution to the problem of coordinated attitude control in spacecraft formations. The control scheme is based on quaternions and modified Rodriguez parameters as attitude representation of the relative attitude error. Utilizing the invertibility of the modified Rodriguez parameter kinematic differential equation, a globally exponenti...

A three dimensional reorientation problem for an underactuated multi-body spacecraft is studied. Formulae for approximating the change in orientation of the base body of the spacecraft, induced by appropriately constructed small amplitude periodic joint motions, are derived. These formulae are used to construct joint motions that cause a desired reorientation maneuver to be performed within a p...

This paper presents the development of a control system design to keep the spacecraft attitude at a prescribed sun vector. A bounded controller is proposed which utilizes the measured sun vector and spacecraft spin rates, and the control gains are model independent and can be tuned for individual axis. An adaptive control scheme is developed for control parameters to ensure closed-loop performa...