Solid rocket propulsion technology for de-orbiting spacecraft

This paper presents the topic of using solid rocket propulsion for de-orbiting spacecraft, in order to fulfil space debris mitigation requirements. The benefits and disadvantages of using such means are discussed. A dedicated system can be implemented in the satellite design phase and shall be a key subsystem of platforms inserted into orbit. Uncontrolled, semi-controlled and controlled de-orbit can be completed using solid rocket motors. Their impact on the space debris environment is discussed. Specific requirements for dedicated propellants and systems are provided. While the majority of presently developed rocket systems worldwide require high burn rates, several applications, including de-orbiting, benefit from solid propellants with decreased regression rates. This allows limiting spacecraft accelerations and loads during de-orbit manoeuvres. Moreover, the requirement of minimising solid particle generation is presented. Heritage technology from the Mercury and Gemini human spaceflight programmes, where de-orbit motors were used, is shown. Historical Soviet, American and Chinese film-return-capsule solid propellant retrorockets, enabling de-orbit, are also presented. A detailed survey of current work worldwide on end-of-life disposal using solid propulsion is included. Challenges of developing dedicated systems are discussed. Finally, an outlook on solid rocket motor utilisation for space debris mitigation is provided.