The ASRTU Micro-satellite is a 12U CubeSat managed by Harbin Institute of Technology. In order to meet the needs micro-satellite mission, health management method suitable for this mission proposed attitude control system. Firstly, according main performance indicators system, configuration sensors and actuators operation mode are designed. And system-level strategy given priority design sensor...

Received Jul 5, 2014 Revised Nov 11, 2014 Accepted Nov 22, 2014 In this paper, an algorithm was presented to control the satellite attitude in orbit in order to reduce the fuel consumption and increase longevity of satellite. Because of proper operation and simplicity, fuzzy controller was used to save fuel and analyze the uncertainty and nonlinearities of satellite control system. The presente...

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

In this report, we propose a periodic state feedback control law for a class of continuous-time linear periodic systems. The proposed control law generates a sufficiently high frequency sinusoidal in the coefficient of a closed loop system, then the closed loop system is shown to be exponentially stable based on the averaging method. It is also shown that a closed loop solution is approximated ...

In this paper, we deal with the attitude control of a satellite equipped with wheels of reaction, using the static output feedback. In the first part, we set the control and its integral in the state-feedback form. Then, by using the algorithm of Kucera, we establish the necessary and sufficient conditions so that the nonlinear system which models the satellite will be stabilizable by the Stati...

Attitude determination, along with attitude control, is critical to functioning of every space mission. Here, we investigate the application of a steady-state Kalman Filter for attitude determination using attitude sensors (sun sensor and horizon sensors) and rate integrating gyros. The three-axis steady-state Kalman Filter formulation, adopted from literature, offers obvious computational adva...

Theory and simulation results have demonstrated that four, variable speed flywheels could potentially provide the energy storage and attitude control functions of existing batteries and control moment gyros on a satellite. Past modeling and control algorithms were based on the assumption of rigidity in the flywheel’s bearings and the satellite structure. This paper provides simulation results a...