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


Damage Behaviour of Rotorcraft End Plate under High Velocity Bird Impact

R. Vijaya Kumar, D. Thenarasu, R. Ravindranath, D.B. Chalwade, Rotary Wing R&D Centre, Hindustan Aeronautics Limited

May 17, 2016

  • Your Path :
  • Home
  • > Damage Behaviour of Rotorcraft End Plate under High Velocity Bird Impact

Damage Behaviour of Rotorcraft End Plate under High Velocity Bird Impact

  • Presented at Forum 72 - Best Paper for this session
  • 8 pages
  • SKU # : 72-2016-058

  • 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

Damage Behaviour of Rotorcraft End Plate under High Velocity Bird Impact

Authors / Details: R. Vijaya Kumar, D. Thenarasu, R. Ravindranath and D.B. Chalwade, Rotary Wing R&D Centre, Hindustan Aeronautics Limited

Abstract
The finite element model is developed for simulating the bird strike test of rotorcraft End plate using the bird numerical modeling techniques. The main design goal is the satisfactory impact resistance of the composite structures in the case of bird strike. The design concept is based on the absorption of the major portion of the bird kinetic energy by the composite skins, in order to protect the inner honeycomb core from damage, thus preserving the End plate functionality for safe landing. To this purpose, the End plate skin is fabricated from composite layers, which unfold under the impact load and increase the energy absorption capability. The numerical modelling of bird strike using the Lagrangian approach and Smooth Particle Hydrodynamics formulation and the critical design parameters are considered in carrying out the analysis. A numerical model of this problem has been developed with an explicit finite element code Autodyn. Analysis is carried out for the developed model using the test parameters. Numerical results by means of bird modelling approaches are substantiated with experimental test results. The results obtained from the analysis and test shows close conformity implying their appropriateness in the simulation of bird strike.

Recently Viewed Items

  • Damage Behaviour of Rotorcraft End Plate under High Velocity Bird Impact

    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.