Python get_constant_aeroの例

コード例 #1

ファイル: nesc_case03.py プロジェクト: nasa/simupy-flight

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)
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

コード例 #2

ファイル: nesc_case04.py プロジェクト: nasa/simupy-flight

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.,)

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

コード例 #3

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,

コード例 #4

ファイル: nesc_case02.py プロジェクト: nasa/simupy-flight

)

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.

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.,