Attitude control of nanosatellite with single thruster using relative displacements of movable unit

Abstract

The attitude dynamics of a nanosatellite (NS) with one movable unit changing its angular position relative to a main body of the nanosatellite is considered. This relative movability of the unit can be implemented with the help of flexible rods of variable length connecting the unit with the main body. Change of the relative position of the movable unit shifts the center of mass of the entire mechanical system. The NS has a single jet engine rigidly mounted into the NS main body. The shift of the mass center creates an arm of the jet-engine thrust and a corresponding control torque. Schemes to control the attitude dynamics of the satellite using the movability of its unit are developed, using both the torque from the engine and inertia change.

Synthesis of dynamics of nanosatellites with variable inertial-mass parameters

“…Such passive stabilization systems can be part of attitude control systems using movable modules to reorient the nanosatellite in the direction of the axis of its greatest moment of inertia, as well as perform more complex angular maneuvers, for example [1][2][3]. As can be seen from the above calculations (Fig.…”

A prescribed time attitude control method based on thrust vector control (TVC) nozzle for solid propulsion satellite

“…Liang et al 6 proposed an attitude disturbance suppression method based on spin stabilization, but the nutation characteristics brought by spin and the additional despiralization actuators are not conducive to space mission execution of micro-satellites. Doroshin et al 7 proposed to use the mass moment technology to eliminate the thrust misalignment torque. The sliding of the mass block will intensify the dynamic uncertainties, which will bring additional disturbances to the micro-satellites.…”