Speaker
Description
An overview of the current status of Pre-Qualification of Aluminium-Free Solid Propellant is given in this presentation. Advantages of solid propulsion for satellite de-orbit are shown and proposed mission scenarios are the source of requirements of the system, motor and propellant itself. The first step in development of Solid Rocket Motor for deorbitation was made with elaboration of a dedicated propellant composition. Specific demand for low burn rate and typical aim for high performance required an extensive trade-off. Basing on a literature review, suitable methods of reducing linear regression rate were defined. The optimal composition selection, basing on initial laboratory test results is presented. Safety assessment results are given as a vital part of the pre-qualification process. Long in-orbit storability concerns were shown and analysed. Results of initial tests are given, including radiation impact. Final verification is done via SRM hot firings with reduced burn duration. An important part of the project is dedicated to the preliminary Solid Rocket Motor for deorbitation design since propellant performance can be analysed only with respect to the motor. Concept of a Thrust Vector Control is given. Finally, system level aspects and integration with the spacecraft is proposed as an outline for future development.
