High Fidelity Helicopter Lag Damper Model for Comprehensive Rotor Analysis

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-11-C-0421
Agency Tracking Number: N11A-010-0266
Amount: $80,000.00
Phase: Phase I
Program: STTR
Awards Year: 2011
Solitcitation Year: 2011
Solitcitation Topic Code: N11A-T010
Solitcitation Number: 2011.A
Small Business Information
Advanced Rotorcraft Technology, Inc.
635 Vaqueros Avenue, Sunnyvale, CA, -
Duns: 149732315
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Hossein Saberi
 Vice President of Enginee
 (408) 523-5100
 saberi@flightlab.com
Business Contact
 Donna Carrig
Title: Vice President of Finance
Phone: (408) 523-5100
Email: donna@flightlab.com
Research Institution
 Pennsylvania State University
 Debbie Mottin
 233B Hammond Building
Pennsylvania State University
University Park, PA, 16802-
 (814) 865-1966
 Nonprofit college or university
Abstract
This research is dedicated to developing high fidelity lag damper models to significantly improve the accuracy of the analysis of the rotor lead-lag damper forces over a wide range of blade lead-lag motion amplitudes, temperatures, and frequencies in support of aircraft design and engineering applications. The model development will emphasize the dampers with various configurations (e.g., linear stroke and snubber) and various materials (e.g., elastomeric materials, fluidic materials, and various combinations of these two materials). Semi-active dampers with feedback control will also be modeled. The developed damper model will be suited for modern comprehensive rotorcraft analysis systems formulated using multi-body and finite element methodology. In Phase~I of this SBIR, ART will team with Penn State University and the work will focus on the development of the time domain elastomeric damper, the time domain fluid-elastomeric damper, and the magnetorheological fluid-elastomeric damper. The Phase~I efforts will also focus on integration of the lag damper models in a comprehensive rotorcraft analysis system. In addition, Phase~I will demonstrate the feasibility, accuracy, and capability of the models via stability and loads analyses of a rotorcraft in both ground resonance and forward flight.

* information listed above is at the time of submission.

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