An output feedback control law is proposed in this paper for spacecraft attitude reorientation task. Although maneuver has been widely investigated and obtained significant results, it still challenging when considering pointing constraints lacking the information of angular velocity. Firstly, potential function introduced to tackle constraints. Then, by jointly designing sign function, anti-un...

In this paper, we consider a distributed attitude alignment problem for a team of deep space formation flying spacecraft through local information exchange. We propose control laws for three different cases. In the first case, multiple spacecraft converge to their (possibly time-varying) desired attitudes while maintaining the same attitude or given relative attitudes during formation maneuvers...

The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sliding mode control laws that ensure the exponential convergence of the attitude control system are developed. Integral sliding mode control ISMC is applied to combine the first-order sliding modewith optimal control and is used to control quaternion-based spacecraft attitudemanoeuvres with externa...

This paper presents a novel attitude determination and control solution for a three cube nanosatellite performing science operations in low Earth orbit. The spacecraft is tasked with studying the water content of Earth’s upper atmosphere by taking radiometer measurements along the 183 GHz absorption line. The radiometer must be calibrated against the cold of deep space, and this calibration nec...

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 ...