SBIR-STTR Award

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)

The Missile Defense Agency seek solid propellant, propulsion control systems with longer operation times, increased performance, and reduced size, weight, power, and cost.Solid propellant exhaust gases are commonly 2,000-4,000F.Proportionally controlled actuators that are capable of enduring higher temperatures while aiming to maintain performance and/or reduce SWaP-C will improve the robustness of future SPCS architectures.During Phase I, we have identified different actuator design options and we build, tested and performed a preliminary design and mechanical analysis of a novel actuator. This design can operate at 500C and save the MDA up to $2m/yr based on data supplied by one of its prime contractors: Aerojet/Rocketdyne.During Phase II, we will produce two or more fully functioning actuators for performance and environmental testing.The design and the testing will be performed with partner companies: Aerojet/Rocketdyne, Honeywell, GHSP and others who will assist with design input, testing and test facilities, application knowledge and know-how and the supply of advanced materials.This design will become a production intent unit for the MDA upon completion of all testing required for production models to be built in Phase III and we will also use these samples to demonstrate to our commercial customer base.Approved for Public Release | 18-MDA-9522 (23 Feb 18)