eb05416991
Taken from sources in CVS at:
https://sourceforge.net/projects/rocketworkbench/
Sources extracted in two steps:
1. Pull entire project tree into a subdir "rwb" via "rsync":
rsync -a a.cvs.sourceforge.net::cvsroot/rocketworkbench/ rwb/.
2. Export sources:
export CVSROOT=$(pwd)/rwb
SUBDIRS="analyser cpropep cpropep-web CVSROOT data libcompat libcpropep libnum libsimulation libthermo prop rocketworkbench rockflight"
mkdir rwbx; cd rwbx
cvs export -D now ${SUBDIRS}
After this (and some backups for safety), the directory content was
added to a Git repo:
git init .
git add *
110 lines
4.3 KiB
INI
110 lines
4.3 KiB
INI
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global = (length_units = "meter"
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,mass_units = "kg"
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)
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rocket = (name = "Meteor"
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,cg = 1.0
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,body = (type = "conic_nose" # Ogive, Elliptic
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# Conic, Parabolic
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,length = 0.3 # meter
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,diameter = 0.1 # meter
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# one of those
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,mass = 0.1 # kg
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)
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,body = (type = "tube"
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,length = 1.3
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,mass = 0.1
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)
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,fin = (num = 4
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,pos = 1.4 # distance from nose tip to leading
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# edge at the root
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,root_chord = 0.2
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,tip_chord = 0.1
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# distance between root and tip
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# leading edge measured parallel to
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# the rocket
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,root_tip_d = 0.2
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,semispan = 0.2
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,body_radius = 0.05
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,mass = 0.05 # of one fin
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)
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,motor = (zpos = 2.5 # distance from nose tip
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,rpos = 0.0 # axial distance
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,diameter = 0.04
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,length = 0.35
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,empty_mass = 1.0
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,full_mass = 10.0
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)
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,tank = (zpos = 1.
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,rpos = 0.0
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,diameter = 0.05
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,length = 1.
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,empty_mass = 1.0
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,full_mass = 10.0
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)
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,other = (shape = "thick_cylinder"
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,zpos = 0.2
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,rpos = 0.0
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,Ix = 1.
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,Iy = 1.
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,mass = 5.
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)
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)
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#rocket = (name = "Meteor",
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# body = (type = "ogive_nose" #Ogive, Elliptic
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# # Conic, Parabolic
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# ,length = 0.3
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# ,diameter = 0.06
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# ,density = 0.3
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# )
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# ,body = (type = "tube"
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# ,length = 1.5
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# ,density = 0.3
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# )
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# ,body = (type = "transition"
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# ,length = 0.2
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# ,density = 0.3
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#
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# )
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# ,body = (type = "tube"
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# ,length = 1.
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# ,diameter = 0.1
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# ,density = 0.3
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# )
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# ,fin = (num = 4
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# ,pos = 2.5 # position of the beginning of the root
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# ,root_chord = 0.2
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# ,tip_chord = 0.05
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# distance between root and tip
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# leading edge measured parallel to
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# the rocket
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# ,root_tip_d = 0.03
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# ,semispan = 0.02
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# )
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# ,motor = (zpos = 2.5 # distance from nose tip
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# ,rpos = 0.0 # axial distance
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# ,diameter = 0.04
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# ,length = 0.35
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# ,empty_mass = 1.0
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# ,full_mass = 10.0
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# )
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# ,tank = (zpos = 1.
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# ,rpos = 0.0
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# ,diameter = 0.05
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# ,length = 1.
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# ,empty_mass = 1.0
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# ,full_mass = 10.0
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# )
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# ,other = (shape = "thick_cylinder"
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# ,zpos = 0.2
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# ,rpos = 0.0
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# ,Ix = 1.
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# ,Iy = 1.
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# ,mass = 5.
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# )
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# )
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