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) b_l = 1/(3*ft_per_m) c_l = 2/(3*ft_per_m) a_l = b_l aero_model = simupy_flight.get_constant_aero(Cp_b=-1.0, Cq_b=-1.0, Cr_b=-1.0) vehicle = simupy_flight.Vehicle(base_aero_coeffs=aero_model, 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)) 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
x = 0.
y = 0.
z = 0.
vehicle = simupy_flight.Vehicle(
base_aero_coeffs=simupy_flight.get_constant_aero(),
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=0.,
a_l=1.,
b_l=1.,
c_l=1.,
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))