Evaluation of a СubeSat initial angle velocity during separation via pulse-magnetic field and method of its reduction

The use of pulse-magnetic field for separation of nanosatellites under control is a new patented method. In papers only operability of the method has been shown without considering motion variables of a satellite after acting with pulse-magnetic field. It is a common knowledge that separation with the use of conventional spring adapters leads to the increase of initial angle velocity up to 10 degrees/sec. In order to decrease it systems like damping system on the basis of hysteresis bars are used. Authors show that in case of initial angle velocity of 0.5 degrees/sec the damping time is equal to 1.7 day during which a CubeSat is not able to perform the mission fully. Computational simulation results of 1U CubeSat separation with undisplaced center of mass with the use of pulse-magnetic field are shown for achieved forward velocity of 1 m/s. Simulation had been performed in software package LS-DYNA. Obtained angle velocity was 20.98 degrees/sec. Components of the angle velocity vector had been studied the proposition had been made that magnetic pressure on a conductive plate along one of the axis was inhomogeneous. Equations for distribution of the magnetic field intensity along the axis on any distance above the inductor in absence of a conductive plate had been obtained. Relative distributions of normal and tangential components of the magnetic field are shown. It had been found that distributions are symmetrical but the line of symmetry is shifted by a quarter of the winding pitch along the axis relatively to the origin of coordinates. It had been proposed that alignment of a satellite center of mass and the line of magnetic field symmetry leads to the decrease of initial angle velocity. Simulation results show that it had been decreased in 11.8 times and became 1.78 degrees/sec. Angle velocities for forward speed of 0.5, 1.5, and 2 m/s are also presented.