# 22/4/2008 - Ripepi Matteo
#
# MBDyn model of the HALE aircraft wing
#
# Data taken from:
#
# Journal of Fluids and Structures (2001) 15, 107-132
# LIMIT-CYCLE OSCILLATIONS IN HIGH-ASPECT-RATIO WINGS
# M. J. Patil, D. H. Hodges, C. E. S. Cesnik


# DATA
#
# Half-span 16 m
# Chord 1 m
# Mass per unit length 0.75 kg/m
# Moment of inertia (50% chord) 0.1 kgm
# Span-wise elastic axis 50% chord
# Center of gravity 50% chord
# Bending rigidity 2x10^4 Nm2
# Torsional rigidity 1x10^4 Nm2
# Bending rigidity (chordwise) 4x10^6 Nm2
# Flight condition
# Altitude 20 km
# Density of air 0.0889 kg/m3


# preset data
include: "wing.set";

begin: data;
	problem: initial value;
end: data;

begin: initial value;
	initial time: 0.;
	final time: 30.;
	time step: 1e-2;

	tolerance: 1e-3;
	max iterations: 70;

	derivatives tolerance: 10e0;
	derivatives max iterations: 200;
	derivatives coefficient: 1e-3;

	linear solver: naive, colamd, mt, 1, pivot factor, 1e-8;
	nonlinear solver: newton raphson, modified, 10;
	
	eigenanalysis: 50., parameter, 1.e-6,
									output matrices, output eigenvectors;

	threads: disable;
	method: bdf;
end: initial value;

begin: control data;
	structural nodes:
		+2*N_beam + 1
	;
	joints:
		+1		# ground clamp
	;
	rigid bodies:
		+3*N_beam
	;
	beams:
 		+N_beam
	;
  	forces:
		+1		# engine
	;
	aerodynamic elements:
	    +N_beam
	;
	gravity;
	air properties;
end: control data;

include: "wing.ref";

begin: nodes;
  # ground
	structural: RF_wing_root, dynamic,
		reference, RF_wing_root, null,
		reference, RF_wing_root, eye,
		reference, RF_wing_root, null,
		reference, RF_wing_root, null;
		
  # wing
	include: "wing.nod";
end: nodes;

begin: elements;
	gravity: 
		0., 0., -1,
		cosine, 0., pi/Tstart, gg/2., half, 0.;  
		
	# ground clamp
	joint: RF_wing_root, clamp, RF_wing_root, node, node;

	# wing structural elements
	include: "struct.elm";
	
	# density and celerity of sound
	air properties: density, sound_celerity,
		0., -1., 0.,
		cosine, 0., pi/Tstart, Vinf/2., half, 0.;
		
	# wing aerodynamic elements
	include: "aero.elm";
	
	# engines' force
	force: 1, follower,
	tip,
	position, +0.0, +0.0, +0.0,
	reference, RF_wing_root, 0.,1.,0.,
  cosine, 0., pi/Tstart, Teng/2., half, 0.;
  
	inertia: 1,
		body, all;
end: elements;