Air Force and NASA studies have shown that up to 20% can be saved in launch vehicle operation and support costs by replacing hydraulic and pneumatic systems with electrically driven systems. However, current electro-mechanical actuation technology lacks the power density to be a viable replacement. The objective of this effort is to demonstrate the feasibility of a lightweight, high torque, electro-mechanical actuation (EMA) system attractive for service in reusable launch vehicle applications. The proposed system is based on a planar, permanent magnet machine structure that utilizes a novel armature design. This system is expected to provide 5 to 8 times greater power density than current, state-of-the-art EMA technology.If this project succeeds, a small, power dense EMA technology will exist that is able to compete with hydrualic and pnuematic actuation technology. Commercial aviation and aerospace are likely markets for this technology, as similar cost saving should be realized. High power, low weight actuators and motors are also of great interest to industrial manufacturers, particularly those now using hydraulic or pneumatic servo systems
