Sliding Wear and Freeplay Growth due to Control Surface Limit Cycle Oscillations
Author:
Affiliation:
1. Aeronautical Development Agency, Bangalore 560 017, India
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Reference24 articles.
1. HoffmanN. R.SpielbergI. N. “Subsonic Flutter Tests of an Unswept All-Movable Horizontal Tail,” Tech. Rept. WADC-TR-54-53, 1954.
2. Maximum Control Surface Freeplay, Design and Flight Testing Approach on the F-22
3. Flight-Loads Effects on Horizontal Tail Free-Play-Induced Limit Cycle Oscillation
4. Nonlinear Flutter Analysis for the Scaled F-35 with Horizontal-Tail Free Play
5. Flutter Analysis of Missile Control Surfaces Containing Structural Nonlinearities
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