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Variable-Fidelity Aeroservoelastic Analysis Tool for Concept Evaluation, Design and Wind-Tunnel Test Support

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX14CL59P
Agency Tracking Number: 144988
Amount: $124,896.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: A3.01
Solicitation Number: N/A
Timeline
Solicitation Year: 2014
Award Year: 2014
Award Start Date (Proposal Award Date): 2014-06-20
Award End Date (Contract End Date): 2014-12-19
Small Business Information
34 Lexington Avenue
Ewing, NJ 08618-2302
United States
DUNS: 096857313
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Glen Whitehouse
 Principal Investigator
 (609) 538-0444
 glen@continuum-dynamics.com
Business Contact
 Barbara Agans
Title: Business Official
Phone: (609) 538-0444
Email: barbara@continuum-dynamics.com
Research Institution
 Stub
Abstract

Ongoing work in advanced air-vehicles, such as ultra-light-weight truss-braced and elastically tailored concepts is beginning to provide the insight necessary to meet NASA's N+3 transport system goals. Unfortunately, contemporary analysis methods are unsuited for aeroservoelastic analysis of such configurations suffering from accessibility, usability, fidelity or resource constraints. Design tools have typically been developed using configuration dependent low-fidelity approaches that are unsuitable to reliably analyze advanced configurations. Contemporary aeromechanics solvers (i.e. viscous compressible Computational Fluid Dynamics coupled to Finite Element structural models) can analyze advanced concepts, but require significant user input to support advanced configurations, not to mention extensive computational resources. What has long been needed is an approach that bridges the middle ground to enable aeroservoelastic analysis at the "appropriate level of fidelity for the problem at hand", while reliably permitting the novel application of aeroelastic knowledge to new concepts, in addition to supporting wind-tunnel and flight tests by enabling the efficient investigation of flight dynamics, flutter, stability and control. By exploiting Continuum Dynamics Inc.'s extensive experience developing fully-coupled aeromechanics methods, we propose the development of a new rapid, reliable, variable┬ľfidelity first-principles physics-based aeroservoelastic analysis to support concept evaluation, wind-tunnel/flight testing and design.

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

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