Conceptual Performance Analysis of Solid-Propellant Propulsion for Small Satellites

Abstract

This study presents a conceptual and computational framework for evaluating solid-propellant propulsion for small-satellite missions. The methodology combines the rocket thrust equation, specific impulse, total impulse, and the ideal rocket equation to examine the relationships among propulsion performance, maneuver duration, propellant requirements, and spacecraft mass ratio. A parametric analysis is conducted using representative, non-experimental propulsion parameters. The study investigates the effects of specific impulse, thrust, required velocity change, and spacecraft mass on ideal propulsion performance and maneuver characteristics. The results indicate that increasing specific impulse reduces the ideal propellant mass required for a prescribed velocity change, while increasing thrust primarily reduces the time required to deliver a given impulse. The study also discusses mission-level considerations associated with solid propulsion, including limited restart capability, thermal and structural loads, integration constraints, and safety considerations. This work provides a conceptual basis for further numerical, orbital-dynamics, thermal, structural, and higher-fidelity propulsion studies of small-satellite systems.