Structural flexibility in spacecraft can degrade the accuracy of the attitude control system. With this motivation in mind, we compare the performance of inertia-free attitude control laws for a spacecraft with an undamped discrete flexible mode and demonstrate robustness with respect to unmodeled spacecraft dynamics and actuator saturation. First the equations of motion are derived using Lagra...

Hardware and software architecture of a novel spacecraft Attitude Determination and Control System (ADCS) based on smartphones using Variable Speed Control Moment Gyroscope (VSCMG) as actuator is proposed here. A spacecraft ground simulator testbed for Hardware-in-the-loop (HIL) attitude estimation and control with VSCMG is also described. The sensor breakouts with independent micro-controller ...

There is a substantial amount of literature within the field of spacecraft control which deals with the separate issues of position and attitude control; comparatively little work has been carried out on the joint nonlinear problem of spacecraft position and attitude control. (R.Pongvthithum etal 2005, H.Wong etal 2001, S.M.Veres etal 2002) provide control solutions for spacecraft position cont...

Complete attitude control of a spacecraft is not possible with only one single-gimbal variable-speed control moment gyro due to the conservation of angular momentum. However, partial attitude control without violating the angular momentum conservation principle is still possible. In this paper feedback controllers using only one singlegimbal variable-speed controlmoment gyro are presented that ...

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...