High Fidelity Helicopter Lag Damper Model for Comprehensive Rotor Analysis

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$80,000.00
Award Year:
2011
Program:
STTR
Phase:
Phase I
Contract:
N68335-11-C-0421
Award Id:
n/a
Agency Tracking Number:
N11A-010-0266
Solicitation Year:
2011
Solicitation Topic Code:
N11A-T010
Solicitation Number:
2011.A
Small Business Information
635 Vaqueros Avenue, Sunnyvale, CA, -
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
149732315
Principal Investigator:
Hossein Saberi
Vice President of Enginee
(408) 523-5100
saberi@flightlab.com
Business Contact:
Donna Carrig
Vice President of Finance
(408) 523-5100
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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