57 lines
1.8 KiB
Plaintext
57 lines
1.8 KiB
Plaintext
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simulation =
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(initial_conditions = (u = 0.0,
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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 = 0.0,
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phi = 0.0,
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theta = 89.0,
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psi = 0.0
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),
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rocket = (stage = (dry_mass = 1000., # (Head)
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Ix = 4390.,
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Iy = 318245.,
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Iz = 318245.,
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Cd = 0.15,
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Cd_data_file = "V2drag.dat",
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CL = 0.1,
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CB = 0.1,
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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 = 1.65,
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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 = 1000.0,
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engine = (thrust = 250000.0,
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thrust_data_file = "V2thrust.dat",
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propellant_mass = 8935.,
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dry_mass = 2965.,
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mass_flow = 0.1,
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start_time = 0.0,
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burn_time = 65.,
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drop_time = 65.0,
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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 = 100.0,
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dt = 0.1,
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precision = 0.01)
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)
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