Abstract:

A new technique named mass moment attitude control is proposed, on the issue that the attitude is not stable when a CubeSat is carrying out a fast orbit maneuver using the solid rocket motor. At first, the whole 8 freedom degrees dynamic equations are derived and deeply analyzed to clarify how it works. Then the additional disturbance torque and systematic coupling with the mass block moving are studied utilizing the simulation. Finally, the above conclusions provide a guideline for designing the actuator layout parameters. The proposed double symmetrical actuators turn out a little disturbance torque and a weak systematic coupling. Simulation results indicate that the attitude control system has a good maneuverability.