Thrust Allocation Method for Solid Attitude and Divert Control Engine

A thrust allocation method for a solid attitude and divert control engine, using a single combustion chamber shared by 4 divert thrusters and 6 attitude control thrusters, is proposed. Thrust allocation for multi-valve solid rocket engines is typically under-constrained due to multiple degrees of freedom and the need for precise control. To address this, we designed a distribution strategy based on the engine's operational requirements, aiming to maximize total impulse output while prioritizing attitude control thrust synthesis. This comprehensive method optimizes thrust distribution across thrusters, ensuring the engine operates within design constraints for reliable and precise control in spacecraft and missile systems. Our approach demonstrates significant improvements over traditional methods by ensuring effective thrust utilization, minimizing propellant consumption, and maintaining high precision in attitude and divert control. This paper offers a novel solution and algorithm for thrust allocation in solid attitude and divert control engines, contributing valuable advancements to aerospace propulsion systems.