Vibration Reduction Methods and Techniques for Rotorcraft Utilizing On-Blade Active Control

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX07CA09P
Agency Tracking Number: 066243
Amount: $100,000.00
Phase: Phase I
Program: SBIR
Awards Year: 2007
Solitcitation Year: 2006
Solitcitation Topic Code: A2.10
Solitcitation Number: N/A
Small Business Information
Techno-Sciences Inc
11750 Beltsville Drive, Su 300, Beltsville, MD, 20705-3194
Duns: 061997029
Hubzone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Curt Kothera
 Principal Investigator
 (240) 790-0600
 kotherac@technosci.com
Business Contact
 Amy Hizoune
Title: Business Official
Phone: (240) 790-0609
Email: aph@technosci.com
Research Institution
N/A
Abstract
Rotor blades adapted for vibration control have the added benefit of extended blade and rotor life, as well as improved passenger comfort. Approaches that have been explored for on-blade active control or individual blade control include control surface actuation, such as trailing edge flaps, and integrated blade manipulation, such as controllable twist. For retro-fit and upgrade purposes, the advanced rotor system needs an actuation scheme with appropriate force, deflection, and bandwidth, without detrimentally increasing on-blade mass. Research in this area has been conducted with potential solutions employing various conventional active material actuator configurations, but these systems have typically suffered from inherent disadvantages. Due to these limitations, Techno-Sciences, Inc. proposes the use of pneumatic artificial muscles to actuate a trailing edge flap device for management of rotorcraft vibration. The proposed actuators are constructed of passive materials that are very mass efficient and low cost, while maintaining adequate force, stroke, and bandwidth. Oriented along the blade span and located within the airfoil contour near the blade root, the antagonistic configuration of actuators offers bi-directional flap deflection and operation under a low centrifugal field. A lightweight mechanism accompanies the actuators, running along the span, to transfer and tailor the mechanical work from the actuators to the span station of the flap. The proposed research plan will work to properly size and scale the actuators and mechanism for the desired response, and construct a prototype device that demonstrates the feasibility of the concept on the bench-top and in a rotating environment at full-scale loading.

* information listed above is at the time of submission.

Agency Micro-sites

US Flag An Official Website of the United States Government