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High Performance Actuators for Solid Propulsion Control Systems

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0147-17-C-7215
Agency Tracking Number: B162-010-0014
Amount: $149,998.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: MDA16-010
Solicitation Number: 2016.2
Timeline
Solicitation Year: 2016
Award Year: 2017
Award Start Date (Proposal Award Date): 2016-12-19
Award End Date (Contract End Date): 2017-06-22
Small Business Information
HC64Box3115, Moab, UT, 84532
DUNS: 966515863
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 George Holling
 Technical Director
 (435) 259-5500
 George.Holling@ElectricDrivetrainTechnologies.com
Business Contact
 Fred Stone
Phone: (435) 259-5500
Email: Fred.Stone@ElectricDrivetrainTechnologies.com
Research Institution
N/A
Abstract
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)

* Information listed above is at the time of submission. *

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