$ nlirm11x  Harder's catenary model, modified
$ made smaller for development purposes
$ variation with all options commented out
$SOL	NLSTATIC $ 106
sol 101 $ linear check case
DIAG	8
$Include 'nlirma.v2001' $ inertia relief by lmt methods
CEND
TITLE = HANGING CHAIN CATENARY  	nlirm11x
Subtitle = reduced model for dmap development, linear check case
Label = lmt done in u2 set, follower forces, ir
Echo = both
  load = 1 $ load with force on y axis
  NLPAR = 400
  DISPL = ALL
  SPCFO = ALL
  ELFOR = ALL
  Gpfo = all
Oload = all
$Param, nmloop, 1 $ compute modes at end
Subcase 1
Load = 1
$Method = 1
$param, rbmodes, yes $ removes LMT variables before eigensolution.
$ this param must be in the subcase, not bulk
$ select DOF as reference.  optional
$set 1 = 34 $ set 123456 is reserved for the reference point
$partn = 1 $ 
$param, scdir, 2 $ disp at gid, dir t2 is subtracted from all t2 values 
set 2 = 9 thru 37 $ gids on rods 
$mpcforce=2 $ inertia forces printed here
BEGIN BULK
Param, inrel, -2 $ inertia relief solution
$ lmt modeling.  required
grid,	1001,	,	,	,	,	,	
$ used for lmt variables.  Needs 6 dof
$ Dimensionlly, it is a (spc) force, not a displacement.
Uset,	u2,	1001,	123456
$uset,	u2,	1001	126 $ put all free LMT variables here
$uset, u3,	1001	345 $ put unused LMT variables here
$ end lmt modeling
EIGRL         1        		     10
$ use rods as a planar model equivalent of a sail
CROD    9       100     9       17    
CROD    17      100     17      23                                              
CROD    23      100     23      29                                              
CROD    29      100     29      37 
$ add massless bars for linear static stability
Cbar,    90       1000     9       17	0.	0.	1.    
Cbar,    170      1000     17      23 ==                                              
Cbar,    230      1000     23      29 ==                                             
Cbar,    290      1000     29      37 ==
Pbar, 	1000	101	.001	.002	.003	.004
$ follower forces to simulate solar pressure
$	sid	g	f	g1	g2	g3	g4
force2,	1,	17,	1.	17	23	101	103                         
force2,	1,	23,	1.	17	23	101	103                         
force2,	1,	23,	1.	23	29	101	103                         
force2,	1,	29,	1.	23	29	101	103                         
$ reference grid points to make a t3 orientation vector.  Tied to ground
grid,	101,	,	,	,	,	,	$123456
grid,	103,	,	0.	0.	1.,	,	$123456
GRID,   9,      ,       0.      0.0,	,	,	$4345 $  free beam rot.                                            
GRID,   17,     ,       0.      -4.,	,	,	$3456                                             
GRID,   23,     ,       3.      -4.,	,	,	$3456                                             
GRID,   29,     ,       6.      -4.,	,	,	$3456                                             
GRID,   37,     ,       6.      0.0,	,	,	$345 $                                              
$ payload and mast
grid,	33,	,	3.	0.,	,	,	$345 $ mast center
grid,	34,	,	3.,	1.,	,	,	$345 $ payload
$ make the model 3-dimensional with nodes out of the 1-2 plane.
grid,	343,	,	3.	1.	1. $ in line with gid 34
Grid,	344,	,	3.	1.,	-1.
cbeam,	343,	933,	34,	343,	0.	1.
cbeam,	344,	933,	34,	344,	0.	1.
Conm2,	3430,	343,	,	.1
Conm2,	3440,	344,	,	.1 
$ mast
cbeam,	933,	933,	9,	33,	0.	1.
cbeam,	3337,	933,	33,	37,	0.	1.
$ mast to payload
cbeam,	3334,	933,	33,	34,	0.	0.	1.
pbeam,	933,	101,	1.	2.	3.,	,	4. $	
mat1,	101,	1.+6,	,	.3 $ massless for beams
$ use point masses rather than distributed masses
conm2,	90,	9,	,	0.1
conm2,	330,	33,	,	0.1
conm2,	340,	34,	,	1.0 $ payload
,	1.0,	,	1.0,	,	,	1.0
$ make sure all directions have at least one mass
conm2,	370,	37,	,	0.1
param, grdpnt, 33 $ at mast center
PROD	100	100	.01
MAT1	100	1.+6		.0	5.
NLPARM	400	1		ITER	1	100		YES	+E
+E		1.-7	1.-10		0	10			+B
+B	0
PARAM	LGDISP	1
$PARAM	POST	0
$param, usetprt, 0 $ use only for model debug.  Generates output at every step.
$param, usetsel, -1
ENDDATA