Dynamics of angular motion of spacecraft with dissipative damper


Аuthors

Morina Z. V.

Samara National Research University named after Academician S.P. Korolev, Moskovskoe shosse, 34, Samara, Russia

e-mail: morina.zv@ssau.ru

Abstract

This research paper describes a study of the dynamics of angular motion of a CubeSat-3U nanosatellite equipped with an internal dissipative damper located in its central module. The main goal of the research is to analyze and compare the effectiveness of two types of dampers - gravitational and magnetic - designed for passive stabilization of the satellite orientation by reducing its angular momentum due to dissipation of internal energy.
A gravity damper works by means of fluid-filled viscous friction between an inner spherical body and a spherical hollow. During orbital motion of the satellite, the relative motion of the damper and the satellite body results in resisting forces that gradually dissipate the kinetic energy of rotation. As a result of this process, the orientation of the satellite is aligned relative to the local vertical, which provides passive stabilization through the use of gravitational forces.
The magnetic damper, in turn, utilizes the interaction of the satellite's own magnetic dipole moment with the Earth's magnetic field. The resulting magnetic moment gradually reduces the satellite's angular velocity, equalizing its orientation along the magnetic field lines.
For comparative analysis of the dampers' performance, a mathematical model was developed that combines a kinematic and dynamic model of the satellite motion. The kinematic model describes the satellite orientation change using Euler angles, while the dynamic model is derived from the dynamic Euler equations for a solid body with members describing gravitational and magnetic moments.
The work also explores the combined use of gravity and magnetic dampers. The simulation results demonstrate that both types of dampers can provide gradual stabilization of the satellite, but their combined use accelerates the damping process.
The effectiveness of each type of damper depends on orbital parameters such as altitude and inclination. In circular equatorial orbits, the gravitational and magnetic moments operate in concert, contributing to the combined stabilizing effect. In inclined orbits, the forces acting on the dampers can interfere with damping, so choosing the optimal configuration of the dampers depends on mission-specific considerations.
The results of this work can be useful in the design of passive orientation systems for nanosatellites. The inclusion of one or both types of dampers allows to increase the reliability of the orientation systems and provide effective orientation maintenance throughout the entire life of the spacecraft. This is particularly relevant for low-budget small satellite missions, where the use of active control systems may not be feasible due to mass, energy, and complexity limitations.

Keywords:

kinetic momentum, gravitational damper, spherical damper, magnetic damper, angular motion, motion dynamics, dissipative method

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