from pyfme.environment.isa import atm
if __name__ == '__main__':
# Aircraft parameters.
mass, inertia = cessna_310.mass_and_inertial_data()
# Initial conditions.
TAS_ = 312 * 0.3048 # m/s
h = 8000 * 0.3048 # m
psi_0 = 3 # rad
x_0, y_0 = 0, 0 # m
# Trimming.
trim_results = steady_state_flight_trim(cessna_310, h, TAS_, gamma=0,
turn_rate=0)
lin_vel, ang_vel, theta, phi, alpha_, beta_, control_vector = trim_results
# Time.
t0 = 0 # s
tf = 30 # s
dt = 1e-2 # s
time = np.arange(t0, tf, dt)
# Results initialization.
results = np.zeros([time.size, 12])
results[0, 0:3] = lin_vel
results[0, 3:6] = ang_vel
