Modeling progressive damage accumulation in thin walled composite beams for rotor blade applications

2006 ◽  
Vol 66 (13) ◽  
pp. 2337-2349 ◽  
Author(s):  
Prashant M. Pawar ◽  
Ranjan Ganguli
Keyword(s):  
Rotor Blade ◽  
Damage Accumulation ◽  
Composite Beams ◽  
Progressive Damage ◽  
Thin Walled

Flexural–torsional behavior of thin-walled composite beams with closed cross-section

2007 ◽  
Vol 45 (7-8) ◽  
pp. 699-705 ◽  
Author(s):  
F. Shadmehri ◽  
H. Haddadpour ◽  
M.A. Kouchakzadeh
Keyword(s):  
Cross Section ◽  
Composite Beams ◽  
Torsional Behavior ◽  
Thin Walled

On a moderate rotation theory of thin-walled composite beams

2000 ◽  
Vol 31 (2) ◽  
pp. 141-158 ◽  
Author(s):  
F. Fraternali ◽  
L. Feo
Keyword(s):  
Composite Beams ◽  
Thin Walled

Dynamic instability of spinning launch vehicles modeled as thin-walled composite beams

2017 ◽  
Vol 228 (12) ◽  
pp. 4353-4367 ◽  
Author(s):  
Melahat Cihan ◽  
Seher Eken ◽  
Metin Orhan Kaya
Keyword(s):  
Dynamic Instability ◽  
Composite Beams ◽  
Launch Vehicles ◽  
Thin Walled

Modal Analysis of Thin Walled Multi-Cell Multi-Tapered Composite Beams of Closed Cross Sections

2014 ◽  
Vol 629 ◽  
pp. 82-88 ◽  
Author(s):  
Sohail Ahmed ◽  
M.N. Ahmed
Keyword(s):  
Modal Analysis ◽  
Cross Sections ◽  
Natural Frequencies ◽  
Aerospace Industry ◽  
Composite Beams ◽  
Wind Gust ◽  
Aircraft Wing ◽  
Model Accuracy ◽  
Finite Element Package ◽  
Thin Walled

This paper explicitly highlights the modal analysis of thin walled multi-cell multi-tapered composite beams in cantilever configurations, using MSC Patran / Nastran finite element package. Initially, the verification of the model was done with the analytical results in order to ensure the model accuracy. All the multi-tapered beams under examination are composed of closed section and three cell configuration. There is a vivid description of all the effects of composite material and stacking sequence on the modal frequencies. It also suggests the ways to shift the natural frequencies of the multi-tapered beams. This paper verifies the effects of different geometrical configurations of beams (tapered angles, lengths and point of variation of tapered angles) on the modal frequencies. This research is also useful in aerospace industry while designing the aircraft wing, which would experience the vibrations due to wind gust and engine cycles.

Combined analytical and experimental approaches to rotor components stress predictions

2011 ◽  
Vol 225 (4) ◽  
pp. 322-330 ◽  
Author(s):  
M Chierichetti ◽  
C McColl ◽  
D Palmer ◽  
M Ruzzene ◽  
O Bauchau
Keyword(s):  
Experimental Data ◽  
Dynamic Response ◽  
Complex Systems ◽  
Rotor Blade ◽  
Experimental Approach ◽  
Numerical Results ◽  
Multibody Model ◽  
Lab Experiments ◽  
Experimental Approaches ◽  
Thin Walled

A combined analytical and experimental approach is introduced to estimate the dynamic response of complex systems from a limited number of measurements. The method is based on the concept that modal information is sufficient to extrapolate the complete map of the response from experimental data through the reconstruction of modal loads. The capabilities of the algorithm are first verified via well-controlled lab experiments on a thin-walled aluminium-rotor blade. Numerical results from a comprehensive UH-60 multibody model are then compared with available experimental data. Significant improvements in the accuracy of the predicted results are achieved when simple airloads models are employed as inputs.

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