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