Attitude stabilization of nanosatellite with movable module on retractable beams

Attitude stabilization of nanosatellites with a movable module on retractable beams is considered. The movable module is attached to the rigid case of the satellite by retractable beams with variable length. This scheme allows to fulfill attitude control with the help of retractable beams’ length changing that changes the local position of the mass center and creates corresponding arm of the constant jet-engine’s force. The movable module, firstly, can represent the functional element (telescope, radiometer etc.), and, secondly, it plays the role of a simple actuator of the attitude control system.

The mathematical model is constructed, and the control law is developed using the feedback principle at forming the relative position angle in proportion to the angular velocity components of the main body (p, q, r):

δ=k1·p+k2·q+k3·r

where k1, k2, k3 – are constant feedback factors.

This type of attitude control corresponds to the integral controller, which compensates the spurious angular displacements and stabilizes the attitude position of the nanosatellite. The numerical results are obtained for the angular motion parameters. The applicability of suggested stabilizing scheme is shown.

The work is supported by the Russian Foundation for Basic Research (19-08-00571 А) and by the Ministry of Science and Higher Education of the Russian Federation in the framework of the State Assignments to higher education institutions and research organizations in the field of scientific activity - the project # 9.1616.2017/ПЧ (9.1616.2017/4.6).