Active Twist Control for a Compliant Wing Structure

Period of Performance: 06/17/2015 - 06/17/2016

$125K

Phase 1 STTR

Recipient Firm

Aurora Flight Sciences Corp.
9950 Wakeman Drive Array
Manassas, VA 20110
Firm POC
Principal Investigator

Research Institution

University of California Santa Cruz
MS: Engineering Baskin 350A 1156 High St
Santa Cruz, CA 95064
Institution POC

Abstract

Blended wing body (BWB) aircraft provide an aerodynamically superior solution over traditional tube-and-wing designs for a number of mission profiles. These platforms provide an all-lifting surface with a reduced wetted area, which lead to significant aerodynamic improvements over their conventional counterparts. However, due to their lack of a conventional tail surface with which to trim in pitch during low-speed operations, these aircraft suffer from a number of stability issues. Chief among these issues is the potentially catastrophic loss of feedback – normally a function of the tail surfaces – when the wing stalls at high angles of attack. This problem is further manifested through the large variation in stall behavior across the BWB's wingspan due to significant thickness differences between the payload-carrying centerbody and the aerodynamically efficient outer wing portions of the vehicle. Aurora Flight Sciences, in collaboration with Professor Mircea Teodorescu of the University of California at Santa Cruz, proposes an actively twisted compliant wing architecture for BWB aircraft that mitigates the stall concerns typically associated with these platforms while providing a significant increase in aerodynamic efficiency. The practical implication resulting from this novel approach is a state-of-the-art compliant wing architecture that provides active control of the twist along the span of the wing by sensing and appropriately responding to oncoming stall risks, thereby eliminating the need for outer wing washout and drastically improving the aerodynamic performance of the wing during cruise. These innovative concepts will be used to complete a preliminary design and build of the wing structure for proof-of-concept flight testing by the end of Phase I.