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-
- 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 = 0.0,
- psi = 0.0
- ),
- rocket = (stage = (dry_mass = .1,
- Ix = 0.0025,
- Iy = 0.84,
- Iz = 0.84,
- Cdrag = 0.2,
- Clift = 2.3,
- Cbeta = 2.3,
- Cspin = 20.0,
- Cmoment = 6.32,
- Cdamping = 31.6,
- Diameter = 0.1143,
- # 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 = 2.0,
- engine = (type = "constant_thrust",
- propellant_mass = 0.1,
- dry_mass = 0.05,
- thrust = 10.0,
- mass_flow = 0.1,
- start_time = 0.0,
- burn_time = 1.5,
- drop_time = 0.0,
- position = (x = -1.0,
- y = 0.0,
- z = 0.0),
- direction = (x = 1.0,
- y = 0.0,
- z = 0.0)
- )
- ),
- stage = (dry_mass = .2,
- Ix = 0.0025,
- Iy = 0.84,
- Iz = 0.84,
- Cdrag = 0.2,
- Clift = 2.3,
- Cbeta = 2.3,
- Cspin = 20.0,
- Cmoment = 6.32,
- Cdamping = 31.6,
- Diameter = 0.1143,
- # 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 = 3.0,
- engine = (type = "thrust_table_data",
- propellant_mass = 0.2,
- dry_mass = 0.3,
- thrust_data_file = "thrust.dat",
- c = 2500.0, #effective exhaust velocity
- start_time = 0.0,
- burn_time = 2.0,
- drop_time = 0.0,
- position = (x = -1.0,
- y = 0.0,
- z = 0.0),
- direction = (x = 1.0,
- y = 0.0,
- z = 0.0)
- )
- )
- )
- ,solution = (duration = 5.0,
- dt = 0.01,
- precision = 0.0001)
- )
-
-
-
-
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