def test_calculate_dynamic_pressure():
rho = 1
TAS = 1
expected_q_inf = 0.5
q_inf = calculate_dynamic_pressure(rho, TAS)
assert_almost_equal(expected_q_inf, q_inf)
def test_calculate_dynamic_pressure():
rho = 1
TAS = 1
expected_q_inf = 0.5
q_inf = calculate_dynamic_pressure(rho, TAS)
assert_almost_equal(expected_q_inf, q_inf)
def get_aerodynamic_moments(TAS, rho, alpha, beta, delta_e, ih, delta_ail,
delta_r):
""" Calculates forces
Parameters
----------
rho : float
density (kg/m3).
TAS : float
velocity (m/s).
alpha : float
attack angle (rad).
beta : float
sideslip angle (rad).
delta_e : float
elevator deflection (rad).
ih : float
stabilator deflection (rad).
delta_ail : float
aileron deflection (rad).
delta_r : float
rudder deflection (rad).
Returns
-------
moments : array_like
3 dimensional vector with (Mxs, Mys, Mzs) forces
in stability axes.
References
----------
AIRCRAFT DYNAMICS From modelling to simulation (Marcello R. Napolitano)
chapter 3 and 4
"""
long_coef_matrix = long_aero_coefficients()
lat_coef_matrix = lat_aero_coefficients()
Cm_0, Cm_a, Cm_de, Cm_dih = long_coef_matrix[2, :]
Cl_b, Cl_da, Cl_dr = lat_coef_matrix[1, :]
Cn_b, Cn_da, Cn_dr = lat_coef_matrix[2, :]
Cm_full = Cm_0 + Cm_a * alpha + Cm_de * delta_e + Cm_dih * ih
Cl_full = Cl_b * beta + Cl_da * delta_ail + Cl_dr * delta_r
Cn_full = Cn_b * beta + Cn_da * delta_ail + Cn_dr * delta_r
span = geometric_data()[2]
c = geometric_data()[1]
Sw = geometric_data()[0]
aerodynamic_moments = calculate_dynamic_pressure(rho, TAS) * Sw\
* np.array([Cl_full * span, Cm_full * c, Cn_full * span])
return aerodynamic_moments
def get_aerodynamic_forces(TAS, rho, alpha, beta, delta_e, ih, delta_ail,
delta_r):
""" Calculates forces
Parameters
----------
rho : float
density (kg/(m3).
TAS : float
velocity (m/s).
alpha : float
attack angle (rad).
beta : float
sideslip angle (rad).
delta_e : float
elevator deflection (rad).
ih : float
stabilator deflection (rad).
delta_ail : float
aileron deflection (rad).
delta_r : float
rudder deflection (rad).
Returns
-------
forces : array_like
3 dimensional vector with (F_x_s, F_y_s, F_z_s) forces in stability
axes.
References
----------
AIRCRAFT DYNAMICS From modelling to simulation (Marcello R. Napolitano)
chapter 3 and 4
"""
long_coef_matrix = long_aero_coefficients()
lat_coef_matrix = lat_aero_coefficients()
CL_0, CL_a, CL_de, CL_dih = long_coef_matrix[0, :]
CD_0, CD_a, CD_de, CD_dih = long_coef_matrix[1, :]
CY_b, CY_da, CY_dr = lat_coef_matrix[0, :]
CL_full = CL_0 + CL_a * alpha + CL_de * delta_e + CL_dih * ih
CD_full = CD_0 + CD_a * alpha + CD_de * delta_e + CD_dih * ih
CY_full = CY_b * beta + CY_da * delta_ail + CY_dr * delta_r
Sw = geometric_data()[0]
aerodynamic_forces = calculate_dynamic_pressure(rho, TAS) *\
Sw * np.array([-CD_full, CY_full, -CL_full]) # N
return aerodynamic_forces