Analysis of the possibility of using the system for small satellite de-orbiting based on an aerodynamic stabilizer, taking into account the physical features of the Earth’s upper atmosphere

Abstract

Abstract The paper presents an analysis of performance of a satellite de-orbiting system that utilizes a deployable aerodynamic stabilizer for controling the angular motion of a spacecraft in order to ensure the correct orientation of the breaking impulse. The problem of determining the shape of the stabilizer, considering its performance requirements and technological constraints has been adressed. The effectiveness of proposed design of the stabilizer for the prototype spacecraft based on the “AIST” small satellite was evaluated using two methods – calculation of aerodynamic forces generated by the rarefied gas flow using the experimental coefficients of the form and stochastic modelling using software. According to the calculations, the proposed aerodynamic system would be capable of providing sufficient stabilizing influence to satisfy the required stabilization time and permissible angle of attack deviation constraints. The range of orbits, where the aerodynamic stabilizer would remain efficient, have been determined with regards to atmospheric properties and design constraints, imposed by mass and size limitations of the system and the de-orbiting time.