This paper mainly focuses on the maneuver of satellite in orbit. A non-linear multi-inputs multi-outputs model has been derived from Newton-Euler equations motion. The dynamics is presented with control methodologies allowing Extended Kalman Filter (EKF) to iteratively provide improved data sets zero errors. As system distracted atmospheric swings which are random hence problem stochastic distu...

Hysteresis dampers are commonly used in Passive magnetic Attitude Control System (PACS). In PACS these rods produce a damping torque and reduce the satellite angular momentum and angular velocity. In this paper, a spin satellite was investigated which utilizes a passive magnetic damper consisting of magnetic hysteresis rods aligned with principal axis or spin axis of satellite and de-tumbling o...

High-accuracy pointing capabilities are desired for many three-axis stabilized small satellites. Momentum-based attitude control system actuators, initially developed for larger satellites. are being utilized by small satellites to meetthesc pointing requirements. This paper provides an overview of momentum devices available for small satellite applications and three-axis attitude control syste...

A control law for an Integrated Power/Attitude Control System (IPACS) for a satellite is presented in this paper. Four or more energy/momentum wheels in an arbitrary non-coplanar configuration and a set of three thrusters are used to implement the torque inputs. The energy/momentum wheels are used as attitude control actuators, as well as an energy storage mechanism, providing power to the spac...

We introduce a decentralized attitude control strategy that can dramatically reduce the usage of propellant, by taking full advantage of the physical coupling of the tether. Motivated by a controllability analysis, indicating that both spin-up and relative attitudes are fully controllable by the reaction wheels, we report the first propellant-free underactuated linear and nonlinear control resu...

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Driven by the satellite’s features such as closed-loop, limited storage space and computing capacity constraint, a fault detection scheme based on the coprime factorization and Youla parameterization is proposed for the on-orbit satellite attitude control system. Based on the SISO dynamic of the satellite in pitch direction and the MIMO one in roll/yaw direction, the residuals equal to  ˆ ( ) ...

This paper discusses the influence of aerodynamic drag torque on the dynamics of a satellite in a very low altitude orbit. The larger atmospheric density in low altitude earth orbits results in significant aerodynamic drag torques acting on the satellite. With a conventional satellite design this may result in instability. This paper shows how the instability can be avoided, and how the aerodyn...

This paper presents the theory and numerical results of utilizing four gimbaled, magnetically suspended, variable speed flywheels for simultaneous satellite attitude control and power transfer (charge, storage, and delivery). Previous variable speed control moment gyro models and control algorithms assumed that the flywheel bearings were rigid. However, high speed flywheels on spacecraft will b...