from simupy.block_diagram import BlockDiagram
import simupy_flight
import numpy as np
from nesc_testcase_helper import plot_nesc_comparisons, int_opts, benchmark
from nesc_testcase_helper import ft_per_m, kg_per_slug
planet = simupy_flight.Planet(gravity=simupy_flight.get_spherical_gravity(
simupy_flight.earth_spherical_gravity_constant),
winds=simupy_flight.get_constant_winds(),
atmosphere=simupy_flight.atmosphere_1976,
planetodetics=simupy_flight.Planetodetic(
a=20902255.199 / ft_per_m,
omega_p=simupy_flight.earth_rotation_rate,
f=0.))
Ixx = 3.6 * kg_per_slug / (ft_per_m**2) #slug-ft2
Iyy = 3.6 * kg_per_slug / (ft_per_m**2) #slug-ft2
Izz = 3.6 * kg_per_slug / (ft_per_m**2) #slug-ft2
Ixy = 0.0 * kg_per_slug / (ft_per_m**2) #slug-ft2
Iyz = 0.0 * kg_per_slug / (ft_per_m**2) #slug-ft2
Izx = 0.0 * kg_per_slug / (ft_per_m**2) #slug-ft2
m = 1.0 * kg_per_slug #slug
x = 0.
y = 0.
z = 0.
S_A = 0.1963495 / (ft_per_m**2)
b_l = 1.0
c_l = 1.0
from simupy.block_diagram import BlockDiagram
import simupy_flight
import numpy as np
from nesc_testcase_helper import plot_nesc_comparisons, int_opts, benchmark
from nesc_testcase_helper import ft_per_m, kg_per_slug
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
)
)
Ixx = 0.001894220*kg_per_slug/(ft_per_m**2) #slug-ft2
Iyy = 0.006211019*kg_per_slug/(ft_per_m**2) #slug-ft2
Izz = 0.007194665*kg_per_slug/(ft_per_m**2) #slug-ft2
Ixy = 0.0*kg_per_slug/(ft_per_m**2) #slug-ft2
Iyz = 0.0*kg_per_slug/(ft_per_m**2) #slug-ft2
Izx = 0.0*kg_per_slug/(ft_per_m**2) #slug-ft2
m = 0.155404754*kg_per_slug #slug
x = 0.
y = 0.
z = 0.
S_A = 0.22222/(ft_per_m**2)
from simupy.block_diagram import BlockDiagram
import simupy_flight
import numpy as np
from nesc_testcase_helper import plot_nesc_comparisons, int_opts, benchmark
from nesc_testcase_helper import ft_per_m, kg_per_slug
planet = simupy_flight.Planet(
gravity=simupy_flight.get_spherical_gravity(simupy_flight.earth_spherical_gravity_constant),
winds=simupy_flight.get_constant_winds(),
atmosphere=simupy_flight.atmosphere_1976,
planetodetics=simupy_flight.Planetodetic(a=20902255.199/ft_per_m, omega_p=0., f=0.)
)
Ixx = 3.6*kg_per_slug/(ft_per_m**2) #slug-ft2
Iyy = 3.6*kg_per_slug/(ft_per_m**2) #slug-ft2
Izz = 3.6*kg_per_slug/(ft_per_m**2) #slug-ft2
Ixy = 0.0*kg_per_slug/(ft_per_m**2) #slug-ft2
Iyz = 0.0*kg_per_slug/(ft_per_m**2) #slug-ft2
Izx = 0.0*kg_per_slug/(ft_per_m**2) #slug-ft2
m = 1.0*kg_per_slug #slug
x = 0.
y = 0.
z = 0.
S_A = 0.1963495/(ft_per_m**2)
b_l = 1.0
c_l = 1.0
a_l = b_l
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.,)