NON-LINEAR NORMAL MODES OF A CONTINUOUS SYSTEM

1998 ◽  
Vol 209 (4) ◽  
pp. 561-569 ◽  
Author(s):  
M.I. Qaisi
Keyword(s):  
Normal Modes ◽  
Continuous System ◽  
Non Linear

Non-linear normal modes of a simply supported beam: continuous system and finite-element models

2004 ◽  
Vol 82 (31-32) ◽  
pp. 2683-2691 ◽  
Author(s):  
Carlos E.N. Mazzilli ◽  
Mário E.S. Soares ◽  
Odulpho G.P. Baracho Neto
Keyword(s):  
Finite Element ◽  
Normal Modes ◽  
Continuous System ◽  
Finite Element Models ◽  
Simply Supported Beam ◽  
Simply Supported ◽  
Non Linear

NORMAL MODES OF A NON-LINEAR CLAMPED–CLAMPED BEAM

2002 ◽  
Vol 250 (2) ◽  
pp. 339-349 ◽  
Author(s):  
W.C. XIE ◽  
H.P. LEE ◽  
S.P. LIM
Keyword(s):  
Normal Modes ◽  
Non Linear

A Convenient Way of Taking Wing (and Fuselage) Flexibility into Account in Calculating Undercarriage Loads

1968 ◽  
Vol 72 (688) ◽  
pp. 353-355
Author(s):  
D. Williams
Keyword(s):  
Dynamic System ◽  
Ab Initio ◽  
Normal Modes ◽  
Degree Of Freedom ◽  
Concentrated Mass ◽  
Natural Approach ◽  
Non Linear ◽  
Lumped Masses

The crudest way of taking account of the airframe superstructure in calculating undercarriage performance is to represent it by a single concentrated mass. Crude as this method is, it is often used by aircraft firms because the only alternative known to them, apparently, is something they hesitate to face. And no wonder, because it means having to represent the wing-fuselage system by a large number of lumped masses and springs, each of which means an extra degree of freedom. This complicated dynamic system has then to be integrated with the undercarriage system, itself complicated by its non-linear characteristics. The natural approach that suggests itself is not to consider the w/f (wing-fuselage) structure ab initio but to make use of its (usually known) normal modes and frequencies. But this is just what cannot be done by existing techniques—hence the present impasse.

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