Orbital lifetime predictions of Low Earth Orbit satellites and the effect of a DeOrbitSail

[摘要] ENGLISH ABSTRACT: Throughout its lifetime in space, a spacecraft is exposed to risk of collision with orbitaldebris or operational satellites. This risk is especially high within the Low Earth Orbit(LEO) region where the highest density of space debris is accumulated.This study investigates orbital decay of some LEO micro-satellites and accelerating orbitdecay by using a deorbitsail. The Semi-Analytical Liu Theory (SALT) and the SatelliteToolkit was employed to determine the mean elements and expressions for the time ratesof change. Test cases of observed decayed satellites (Iridium-85 and Starshine-1) are usedto evaluate the predicted theory. Results for the test cases indicated that the theoryttedobservational data well within acceptable limits.Orbit decay progress of the SUNSAT micro-satellite was analysed using relevant orbitalparameters derived from historic Two Line Element (TLE) sets and comparing with decayand lifetime prediction models. The study also explored the deorbit date and time for a1U CubeSat (ZACUBE-01).A proposed orbital debris solution or technology known as deorbitsail was also investigatedto gain insight in sail technology to reduce the orbit life of spacecraft with regards to de-orbiting using aerodynamic drag. The deorbitsail technique signi cantly increases thee ective cross-sectional area of a satellite, subsequently increasing atmospheric drag andaccelerating orbit decay. The concept proposed in this work introduces a very usefultechnique of orbit decay as well as deorbiting of spacecraft.

[发布机构] Stellenbosch University