Feasibility study on Multiphysics H2-O2 combustion model for space debris removal system – NIRCSAT-X

Abstract

Space debris is a growing problem for low earth orbit (LEO) and geosynchronous orbit (GEO). The risk of space debris currently affects human activities in Space and is controlled by the collision avoidance alert. However, the risk is growing, which increases future space mission costs to avoid or shield against space debris impact.The project has evolved over four years, culminating in Meng/BEng graduation projects. At the heart of our innovation is utilising the naturally high temperatures in the exosphere and stratosphere, which can soar to 1200 °C. This environment is ideal for initiating a chemical reaction within a pressurised chamber containing a mix of H2-O2 gases, generating heat sufficient to ablate common space debris materials such as titanium, aluminium, and composites. We have crafted an initial satellite design and performed Multiphysics simulations using COMSOL to validate our concept. The project now seeks investment to enhance four critical areas: the satellite's mechanical design to ensure safe operation within a debris field, the development of a dynamic control system for debris collection and satellite navigation, the management of H2 and O2 tank refilling, and the creation of a mechanism for the safe release of ablated materials back into Space.

Keywords

• Space debris
• Finite element
• Thermal plasma
• LEO
• Thermal desktop
• Multiphysics