High Performance Actuators for Solid Propulsion Control Systems

The US Missile Defense Agency is seeking to develop innovative architectures and/or high temperature electronics for increasing the temperature capability of actuators used with proportionally controlled valves/thrusters. Solid propellant exhaust gases are commonly 2,000-4,000F while the actuator to valve/thruster interface commonly must be limited to less than 200-300F. This relatively low temperature limit at the actuator interface is often a driving design factor in many propulsion control systems. Successful development of higher temperature capable actuators has the potential to increase the operation times of future SPCS and offer propulsion vendors increased system design flexibility. These desired improvements for actuators can potentially be achieved through; innovative architectures, the design of high temperature electronic controls, or enhanced materials. During Phase I we will review and apply the latest state-of-the-art materials, actuator design topologies, bearing materials and high temperature power electronics to design an actuator that can operate ambient temperatures in excess of 400/450 F (minimum/target). Using thermal and magnetic finite element analysis we will validate the design. During the Phase I Option we will expand the design and include failure and vibration analysis. Upon successful validation we will then generate a complete print package to prepare for Phase II. Approved for Public Release | 16-MDA-8917 (15 November 16)