BD.connect(vehicle, planet, inputs=np.arange(vehicle.dim_output))
planet.initial_condition = planet.ic_from_planetodetic(
lamda_E=long_ic,
phi_E=lat_ic,
h=h_ic,
V_N=V_N_ic,
V_E=V_E_ic,
V_D=V_D_ic,
psi=psi_ic,
theta=theta_ic,
phi=phi_ic,
p_B=p_b_ic,
q_B=q_b_ic,
r_B=r_b_ic,
)
# planet.initial_condition[-3:] = omega_X_ic, omega_Y_ic, omega_Z_ic
planet.initial_condition[-2] = 0.
import time
tstart = time.time()
res = BD.simulate(30, integrator_options=int_opts)
tend = time.time()
tdelta = tend - tstart
print("time to simulate: %f eval time to run time: %f" %
(tdelta, res.t[-1] / tdelta))
glob_path = os.path.join(data_relative_path, 'Atmospheric_checkcases',
'Atmos_10_NorthwardCannonball', 'Atmos_10_sim_*.csv')
plot_nesc_comparisons(res, glob_path, '10')
planet = simupy_flight.Planet(
gravity=simupy_flight.earth_J2_gravity,
winds=simupy_flight.get_constant_winds(),
atmosphere=simupy_flight.atmosphere_1976,
planetodetics=simupy_flight.Planetodetic(
a=simupy_flight.earth_equitorial_radius,
omega_p=simupy_flight.earth_rotation_rate,
f=simupy_flight.earth_f
)
)
vehicle = simupy_flight.Vehicle(base_aero_coeffs=simupy_flight.get_constant_aero(CD_b=0.1), m=m, I_xx=Ixx, I_yy=Iyy, I_zz=Izz, I_xy=Ixy, I_yz=Iyz, I_xz=Izx, x_com=x, y_com=y, z_com=z, x_mrc=x, y_mrc=y, z_mrc=z, S_A=S_A, a_l=a_l, b_l=b_l, c_l=c_l, d_l=0.,)
BD = BlockDiagram(planet, vehicle)
BD.connect(planet, vehicle, inputs=np.arange(planet.dim_output))
BD.connect(vehicle, planet, inputs=np.arange(vehicle.dim_output))
planet.initial_condition = planet.ic_from_planetodetic(
lamda_E=long_ic, phi_E=lat_ic, h=h_ic,
V_N=V_N_ic, V_E=V_E_ic, V_D=V_D_ic,
psi=psi_ic, theta=theta_ic, phi=phi_ic,
p_B=p_b_ic, q_B=q_b_ic, r_B=r_b_ic,)
# planet.initial_condition[-3:] = omega_X_ic, omega_Y_ic, omega_Z_ic
planet.initial_condition[-2] = 0.
with benchmark() as b:
res = BD.simulate(30, integrator_options=int_opts)
b.tfinal = res.t[-1]
plot_nesc_comparisons(res, '10')
)
BD = BlockDiagram(planet, vehicle)
BD.connect(planet, vehicle, inputs=np.arange(planet.dim_output))
BD.connect(vehicle, planet, inputs=np.arange(vehicle.dim_output))
lat_ic = 0. * np.pi / 180
long_ic = 0. * np.pi / 180
h_ic = 30_000 / ft_per_m
V_N_ic = 0.
V_E_ic = 0.
V_D_ic = 0.
psi_ic = 0. * np.pi / 180
theta_ic = 0. * np.pi / 180
phi_ic = 0. * np.pi / 180
omega_X_ic = 10. * np.pi / 180
omega_Y_ic = 20. * np.pi / 180
omega_Z_ic = 30. * np.pi / 180
planet.initial_condition = planet.ic_from_planetodetic(long_ic, lat_ic, h_ic,
V_N_ic, V_E_ic, V_D_ic,
psi_ic, theta_ic,
phi_ic)
planet.initial_condition[-3:] = omega_X_ic, omega_Y_ic, omega_Z_ic
with benchmark() as b:
res = BD.simulate(30, integrator_options=int_opts)
b.tfinal = res.t[-1]
plot_nesc_comparisons(res, '02')
from simupy import systems
from scipy import interpolate
from nesc_testcase_helper import plot_nesc_comparisons, plot_F16_controls, benchmark
from nesc_testcase_helper import ft_per_m
from nesc_case11 import int_opts, get_controller_function, BD, spec_ic_args, opt_ctrl, dim_feedback
int_opts['max_step'] = 0.0 #2**-4
int_opts['name'] = 'dop853'
altCmdBlock = systems.SystemFromCallable(
interpolate.make_interp_spline(
[0, 5],
[spec_ic_args['h'] * ft_per_m, spec_ic_args['h'] * ft_per_m + 100.0],
k=0), 0, 1)
BD.systems[-3] = altCmdBlock
BD.systems[2] = systems.SystemFromCallable(
get_controller_function(*opt_ctrl, sasOn=True, apOn=True),
dim_feedback + 4, 4)
with benchmark() as b:
res = BD.simulate(20, integrator_options=int_opts)
b.tfinal = res.t[-1]
plot_nesc_comparisons(res, '13p1')
plot_F16_controls(res, '13p1')