-
- simulation =
- (initial_conditions = (u = 0.0,
- v = 0.0,
- w = 0.0,
- P = 0.0,
- Q = 0.0,
- R = 0.0,
- latitude = 0.0,
- longitude = 0.0,
- altitude = 0.0,
- phi = 0.0,
- theta = 89.0,
- psi = 0.0
- ),
- rocket = (stage = (dry_mass = 1000., # (Head)
- Ix = 4390.,
- Iy = 318245.,
- Iz = 318245.,
- Cd = 0.15,
- Cd_data_file = "V2drag.dat",
- CL = 0.1,
- CB = 0.1,
- Cspin = 20.0,
- Cmoment = 6.32,
- Cdamping = 31.6,
- Diameter = 1.65,
- # this is the total duration during which the
- # stage is active, i.e. from the time the previous
- # stage were drop until this stage is drop.
- active_time = 1000.0,
- engine = (thrust = 250000.0,
- thrust_data_file = "V2thrust.dat",
- propellant_mass = 8935.,
- dry_mass = 2965.,
- mass_flow = 0.1,
- start_time = 0.0,
- burn_time = 65.,
- drop_time = 65.0,
- position = (x = -1.0,
- y = 0.0,
- z = 0.0),
- direction = (x = 1.0,
- y = 0.0,
- z = 0.0)
- )
- )
- )
- ,solution = (duration = 100.0,
- dt = 0.1,
- precision = 0.01)
- )
-
-
-
-
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