Deorbiting Strategies: Comparison between Electrostatic Plasma Brake and Conventional Propulsion

Abstract

Space debris is a growing concern, pushing worldwide space users to commit more strongly to deorbiting unused platforms at the end of life. Recent advances in the area of the Electric Solar Wind Sail propulsion have introduced the concept of electrostatic plasma brake, mostly aimed for deorbiting small satellites weighing up to 100 kg. The operating principle is to produce drag with a negatively charged long thin tether in the ionospheric plasma environment. A relatively simple design of the deorbit module consists of a highvoltage power supply, space debris resistant tether and a tip mass. The tether is deployed using gravity gradient force. This paper will focus on the applicability of the electrostatic plasma brake concept for deorbiting larger class satellites where the electrostatic plasma brake could provide a propellantless alternative to the solid and electric propulsion deorbiting modules. Dierent low Earth orbit mission scenarios for satellite classes weighing up to 1000 kg are studied in detail from a mission analysis point of view. Optimal deorbit module parameters are proposed for these generic satellite classes and the results are compared with existing deorbiting solutions.