------- Forwarded message follows -------
From:           	"C J SADD" <[log in to unmask]>
Organization:   	University of Manchester
To:             	[log in to unmask]
Date sent:      	Wed, 2 Feb 2000 14:14:19 BST
Subject:        	Total moments
Priority:       	normal

Hello,

I am have applied an aerodynamic pressure load to an ABAQUS 
model of a wing.  The wing has been modelled using s8R shells
and has orthotropic laminate material properties.

I wish to check that the aerodynamic load has been applied 
correctly by calculating the total load and bending moment (about 
the wing root).  Summation of reaction forces gives the correct 
applied load but I cannot get the applied moment to give the correct 
results.  I have included the effects of the reaction forces away from 
the wing root on the moment and checked my methods with other 
FE people but the results are still incorrect.

Does anyone have any ideas why I may be getting errors.  The 
elements I have used have 6DOFs per node and therefore should 
calculate moments correctly.

Alternately, I would be very keen to learn of an ABAQUS command 
to calculate the applied forces and moments automatically.

Any ideas?

Regards

Chris






Chris Sadd
Research Engineer
Dynamics & Aeroelasticity Research Group
Mechanical Engineering
Manchester School of Engineering
The University of Manchester

Tel (0161) 2754393 

------- End of forwarded message -------

Steffan Evans B.Eng.(Hons) M.Sc. D.M.S.
Eng.D. Research Engineer
Department of Mechanical Engineering
University of Manchester
Oxford Road
Manchester
M13 9PL
Tel 0044(0)161 275 4437
Fax 0044(0)161 275 4346


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