Experimental and Numerical Analysis of In-Orbit Launch Dynamics of Micro-Spacecraft Based on Solid Thruster

Abstract

Deorbiter systems based on micro-spacecraft presents a promising approach for the active removal of space debris. Stable in-orbit deployment is a prerequisite for the successful completion of the entire mission. To investigate the reliability and launch dynamics of in-orbit launch systems for micro-spacecraft, this study developed a ground-based test system using the drop-tower method and employed a high-precision measurement system to capture the dynamic response of the micro-spacecraft during launch. A numerical model of the micro-spacecraft’s in-orbit launch dynamics was developed employing multi-body dynamics. This model accounts for thrust eccentricity, motion coupling between the micro-spacecraft and the satellite platform, contact collisions during launch, and other perturbation factors. The accuracy of the numerical model was validated by comparing the simulation results with those from ground tests. Based on this, Monte Carlo simulations were conducted to analyze and discuss the factors influencing the separation angular velocity of the micro-spacecraft. The results indicate that, for specific structural and parameter configurations, controlling the eccentricity angle of the solid-propellant thruster and the clearance between the micro-spacecraft and the separation mechanism within certain limits can effectively reduce the micro-spacecraft’s separation angular velocity.