|
|
simulation =
|
|
(initial_conditions = (u = 400.0,
|
|
v = 0.0,
|
|
w = 0.0,
|
|
P = 0.0,
|
|
Q = 0.0,
|
|
R = 0.0,
|
|
latitude = 0.0,
|
|
longitude = 0.0,
|
|
altitude = 1000.0,
|
|
phi = 0.0,
|
|
theta = 90.0,
|
|
psi = 0.0
|
|
),
|
|
rocket = (stage = (dry_mass = 10.0,
|
|
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 = 100.0,
|
|
engine = (type = "constant_thrust",
|
|
propellant_mass = 2.0,
|
|
dry_mass = 1.0,
|
|
thrust = 1000.0,
|
|
mass_flow = 2.0,
|
|
start_time = 0.0,
|
|
burn_time = 100.0,
|
|
drop_time = 100.0,
|
|
position = (x = -1.0,
|
|
y = 0.0,
|
|
z = 0.0),
|
|
direction = (x = 1.0,
|
|
y = 0.0,
|
|
z = 0.0)
|
|
),
|
|
engine = (type = "thrust_table_data",
|
|
propellant_mass = 2.0,
|
|
dry_mass = 1.0,
|
|
thrust_data_file = "thrust.dat",
|
|
c = 2500.0, #effective exhaust velocity
|
|
start_time = 0.0,
|
|
burn_time = 100.0,
|
|
drop_time = 100.0,
|
|
position = (x = -1.0,
|
|
y = 0.0,
|
|
z = 0.0),
|
|
direction = (x = 1.0,
|
|
y = 0.0,
|
|
z = 0.0)
|
|
)
|
|
),
|
|
stage = (dry_mass = 10.0,
|
|
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 = 100.0,
|
|
engine = (type = "constant_thrust",
|
|
propellant_mass = 2.0,
|
|
dry_mass = 1.0,
|
|
thrust = 1000.0,
|
|
mass_flow = 2.0,
|
|
start_time = 0.0,
|
|
burn_time = 100.0,
|
|
drop_time = 100.0,
|
|
position = (x = -1.0,
|
|
y = 0.0,
|
|
z = 0.0),
|
|
direction = (x = 1.0,
|
|
y = 0.0,
|
|
z = 0.0)
|
|
),
|
|
engine = (type = "thrust_table_data",
|
|
propellant_mass = 2.0,
|
|
dry_mass = 1.0,
|
|
thrust_data_file = "thrust.dat",
|
|
c = 2500.0, #effective exhaust velocity
|
|
start_time = 0.0,
|
|
burn_time = 100.0,
|
|
drop_time = 100.0,
|
|
position = (x = -1.0,
|
|
y = 0.0,
|
|
z = 0.0),
|
|
direction = (x = 1.0,
|
|
y = 0.0,
|
|
z = 0.0)
|
|
)
|
|
)
|
|
)
|
|
,solution = (duration = 50.0,
|
|
dt = 0.01,
|
|
precision = 0.01)
|
|
)
|
|
|
|
|
|
|
|
|