A Solid-Motor Retro Kit for Controlled Deorbit of Medium Satellites: Rocket-Equation Sizing

This paper presents a computed design study of a civilian orbital-safety system based on chemical retro-propulsion lowering perigee into the upper atmosphere. It is a computed study of a civilian orbital-safety system, with no targeting application and no weapon application. Status: SIMULATED, NOT MEASURED. Under the stated assumptions the sizing gives a circular speed m per s of 7.46e+03, a transfer apogee speed m per s of 7.27e+03, and a required delta v m per s of 188. Further computed quantities include propellant kg of 28.8; kit mass kg with structure of 32.2; kit fraction percent of 7.16; transfer half period min of 46.8. The design is sized end to end from the stated assumptions in the deposited computation, so every headline number can be reproduced, challenged and revised. Where the approach performs poorly, that result is reported at the same size as the favourable results: the limitations section names the conditions under which this design should not be chosen. The contribution is a complete, auditable sizing for one operating principle, intended to be compared like-for-like with sizings built on other principles for the same task.