We consider the problem of attitude stabilization for a low Earth orbit satellite having only electromagnetic actuation. Such is not fully actuated, as control torque cross-product magnetic moment due to magnetorquers and geomagnetic field. The aim this work study whether oscillating controls can be designed such that actuated via alone achieve full three-axis irrespective position satellite. T...

Abstract Existing sounding rocket flight is probably disturbed by external factors, of which attitude lack automatic control function and trajectory not stable, thus the project designed a canard adjustable posture scheme based on PID algorithm, can effectively solve stability path anti-interference problem with high efficiency.

In this paper, a new field oriented control scheme with maximum torque for permanent magnet hysteresis synchronous (PMHS) motor has been presented. Vector control method provides significant improvement to the dynamic performance of ac motors but in this method d- axis current is controlled such as the ratio of motor torque to motor current is a maximum, then the dynamic performance will be ver...

The HAUSAT-2 is a 30kg class nanosatellite which is stabilized by 3-axis active control method. Its main mission objectives are to provide studying the scope of activity and ecology of animals using Animal Tracking System (ATS) and collecting the space information data of mission orbit from Electric Plasma Probe (EPP) as a space science payload. 2-axes sun sensors, 3-axes magnetometer, and star...

In this paper, we analyze dynamics of a DGVSCMG(Double-Gimbal VariableSpeed Control Moment Gyro) and develop an easy-to-use LPV (Linear ParameterVarying) model, in which we deal with 3-axis attitude control of a spacecraft equipped with a DGVSCMG. Although it is hard to consider overall stability and control performance of attitude control at the same time with conventional methods, this paper ...

In this paper an observer-controller structure for attitude synchronization of a satellite formation is presented. The design applies methods from mechanical synchronization to design a nonlinear observer and controller for satellites actuated by means of reaction wheels and magnetic torquers. In this approach one satellite is defined as the leader of the formation, while the rest are defined a...