VFS Website
  • VIEW CART
  • CUSTOMER SUPPORT
  • MY STORE ACCOUNT
  • CONTACT US
  • STORE HOME
  • 5Prime
  • Forum Proceedings
  • Workshops
  • Technical Meetings
  • Vertiflite
  • Books, CDs & Gifts


Unable to log in or get member pricing? Having trouble changing your password?

Please review our Frequently Asked Questions for complete information on these and other common situations.
 

Vertical Flight Library & Store

CHECKOUT

0 Item(s) In Cart Total: $0.00


Advancement of the SNUF Blade Design through Flap Configuration Parametric Study and Optimization Framework

WonJong Eun, Seoul National University; JiSoo Sim, Korea Aerospace Industries; SangWoo Lee, SangJoon Shin, Seoul National University

May 8, 2017

  • Your Path :
  • Home
  • > Advancement of the SNUF Blade Design through Flap Configuration Parametric Study and Optimization Framework

Advancement of the SNUF Blade Design through Flap Configuration Parametric Study and Optimization Framework

  • Presented at Forum 73
  • 12 pages
  • SKU # : 73-2017-0143
  • Your Price : $30.00
  • Join or log in to receive the member price of $15.00!


VFS member?
Don't add this to your cart just yet!
Be sure to log in first to receive the member price of $15.00!

 
Add To Cart

Add to Wish List

Reward Value:
(60) Member Points

Advancement of the SNUF Blade Design through Flap Configuration Parametric Study and Optimization Framework

Authors / Details: WonJong Eun, Seoul National University; JiSoo Sim, Korea Aerospace Industries; SangWoo Lee, SangJoon Shin, Seoul National University

Abstract
This paper focused on improving a small-scaled prototype of a helicopter rotor blade with a flap-driving mechanism termed as the Seoul National University Flap (SNUF). The design of SNUF included realizing vibratory load reduction. First, a multibody structural dynamics analysis was performed to determine the influence of the flap dimension and location within the rotor blade with respect to hub vibratory load reduction. This process selected a specific blade configuration that maximized vibration reduction capability. Then, a numerical optimization technique was applied to improve the cross-sectional design of the SNUF blade. The design optimization procedure established improved blade sectional design with desired first torsional frequency and reduced blade weight while satisfying sufficient structural integrity. Three-dimensional nonlinear static structural analysis was also performed for the optimized SNUF design. Von Mises stress distribution on the blade and components were predicted by considering external aerodynamic loads, centrifugal loads due to rotation, and contact among the internal components. Future studies will include fabricating the prototype blade based on the optimized design and performing a whirl tower test.

Recently Viewed Items

  • Advancement of the SNUF Blade Design through Flap Configuration Parametric Study and Optimization Framework

    Member Price :
    $15.00
    Your Price :
    $30.00

Popular Products

  • Master Card
  • Visa
  • American Express
  • Customer Support
  • Contact Us
  • Privacy and Security Policies
  • Refund Policies

Copyright © 2022 The Vertical Flight Society. All rights reserved.