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Rotary Electromechanical Actuator for Next-Generation Thin-Wing Aircraft Flight Control

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-13-M-2387
Agency Tracking Number: F131-168-0700
Amount: $149,568.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF131-168
Solicitation Number: 2013.1
Timeline
Solicitation Year: 2013
Award Year: 2013
Award Start Date (Proposal Award Date): 2013-06-26
Award End Date (Contract End Date): 2014-04-27
Small Business Information
20252 Bancroft Circle
Huntington Beach, CA -
United States
DUNS: 114746279
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 James Hynes
 Principal Investigator
 (877) 575-0053
 jim.hynes@continentalctrls.com
Business Contact
 Lore Hynes
Title: Contract Administrator
Phone: (877) 575-0053
Email: lore.hynes@continentalctrls.com
Research Institution
N/A
Abstract

ABSTRACT: We propose to develop a 5 inch direct hinge line aileron actuator based on our 2 inch highly integrated EM boat ride control actuator. By exploiting the natural physical scaling laws we can create an even more efficient larger motor which operates on 270VDC. The optimization of EM actuator parameters starts with straightforward math and requirements definition but becomes complicated by soft constraints like speed vs life and application specific details of the cost function. The BLDC motor we propose to build and test has significantly better metrics than any comparable motor currently available. Working with prime contractor feedback we will develop concepts for redundancy and failsafe disconnects. Though a primary focus is the innovative motor, we will study the feasibility of a wide range of coupling alternatives including a variable reduction ratio hybrid valveless hydraulic transmission. BENEFIT: A lightweight EM aileron actuator will will have both military and commercial aircraft applications as more electric aircraft are developed and wing profiles become smaller.

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

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