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 *
117 lines
4.3 KiB
Plaintext
117 lines
4.3 KiB
Plaintext
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simulation =
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(initial_conditions = (u = 400.0,
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v = 0.0,
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w = 0.0,
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P = 0.0,
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Q = 0.0,
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R = 0.0,
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latitude = 0.0,
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longitude = 0.0,
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altitude = 1000.0,
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phi = 0.0,
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theta = 90.0,
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psi = 0.0
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),
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rocket = (stage = (dry_mass = 10.0,
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Ix = 0.0025,
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Iy = 0.84,
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Iz = 0.84,
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Cdrag = 0.2,
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Clift = 2.3,
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Cbeta = 2.3,
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Cspin = 20.0,
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Cmoment = 6.32,
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Cdamping = 31.6,
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Diameter = 0.1143,
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# this is the total duration during which the
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# stage is active, i.e. from the time the previous
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# stage were drop until this stage is drop.
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active_time = 100.0,
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engine = (type = "constant_thrust",
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propellant_mass = 2.0,
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dry_mass = 1.0,
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thrust = 1000.0,
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mass_flow = 2.0,
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start_time = 0.0,
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burn_time = 100.0,
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drop_time = 100.0,
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position = (x = -1.0,
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y = 0.0,
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z = 0.0),
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direction = (x = 1.0,
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y = 0.0,
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z = 0.0)
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),
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engine = (type = "thrust_table_data",
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propellant_mass = 2.0,
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dry_mass = 1.0,
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thrust_data_file = "thrust.dat",
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c = 2500.0, #effective exhaust velocity
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start_time = 0.0,
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burn_time = 100.0,
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drop_time = 100.0,
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position = (x = -1.0,
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y = 0.0,
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z = 0.0),
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direction = (x = 1.0,
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y = 0.0,
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z = 0.0)
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)
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),
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stage = (dry_mass = 10.0,
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Ix = 0.0025,
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Iy = 0.84,
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Iz = 0.84,
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Cdrag = 0.2,
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Clift = 2.3,
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Cbeta = 2.3,
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Cspin = 20.0,
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Cmoment = 6.32,
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Cdamping = 31.6,
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Diameter = 0.1143,
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# this is the total duration during which the
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# stage is active, i.e. from the time the previous
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# stage were drop until this stage is drop.
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active_time = 100.0,
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engine = (type = "constant_thrust",
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propellant_mass = 2.0,
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dry_mass = 1.0,
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thrust = 1000.0,
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mass_flow = 2.0,
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start_time = 0.0,
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burn_time = 100.0,
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drop_time = 100.0,
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position = (x = -1.0,
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y = 0.0,
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z = 0.0),
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direction = (x = 1.0,
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y = 0.0,
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z = 0.0)
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),
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engine = (type = "thrust_table_data",
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propellant_mass = 2.0,
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dry_mass = 1.0,
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thrust_data_file = "thrust.dat",
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c = 2500.0, #effective exhaust velocity
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start_time = 0.0,
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burn_time = 100.0,
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drop_time = 100.0,
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position = (x = -1.0,
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y = 0.0,
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z = 0.0),
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direction = (x = 1.0,
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y = 0.0,
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z = 0.0)
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)
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)
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)
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,solution = (duration = 50.0,
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dt = 0.01,
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precision = 0.01)
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)
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