system = EulerFlatEarth(lat=0, lon=0, h=h0, psi=psi0, x_earth=x0, y_earth=y0) not_trimmed_controls = { 'delta_elevator': 0.05, 'delta_aileron': 0.01 * np.sign(turn_rate), 'delta_rudder': 0.01 * np.sign(turn_rate), 'delta_t': 0.5 } controls2trim = ['delta_elevator', 'delta_aileron', 'delta_rudder', 'delta_t'] trimmed_ac, trimmed_sys, trimmed_env, results = steady_state_flight_trimmer( aircraft, system, environment, TAS=TAS, controls_0=not_trimmed_controls, controls2trim=controls2trim, gamma=gamma0, turn_rate=turn_rate, verbose=1) print() print('delta_elev = ', "%8.4f" % np.rad2deg(results['delta_elevator']), 'deg') print('delta_aile = ', "%8.4f" % np.rad2deg(results['delta_aileron']), 'deg') print('delta_rud = ', "%8.4f" % np.rad2deg(results['delta_rudder']), 'deg') print('delta_t = ', "%8.4f" % results['delta_t'], '%', '\n') print('alpha = ', "%8.4f" % np.rad2deg(results['alpha']), 'deg') print('beta = ', "%8.4f" % np.rad2deg(results['beta']), 'deg', '\n') print('u = ', "%8.4f" % results['u'], 'm/s') print('v = ', "%8.4f" % results['v'], 'm/s') print('w = ', "%8.4f" % results['w'], 'm/s', '\n')
psi0 = 1.0 # rad x0, y0 = 0, 0 # m turn_rate = 0.0 # rad/s gamma0 = -0.1 # rad system = EulerFlatEarth(lat=0, lon=0, h=h0, psi=psi0, x_earth=x0, y_earth=y0) not_trimmed_controls = {'delta_elevator': 0.05, 'delta_aileron': 0.01 * np.sign(turn_rate), 'delta_rudder': 0.01 * np.sign(turn_rate), 'delta_t': 0.5} controls2trim = ['delta_elevator', 'delta_aileron', 'delta_rudder', 'delta_t'] trimmed_ac, trimmed_sys, trimmed_env, results = steady_state_flight_trimmer( aircraft, system, environment, TAS=TAS, controls_0=not_trimmed_controls, controls2trim=controls2trim, gamma=gamma0, turn_rate=turn_rate, verbose=1) print() print('delta_elev = ', "%8.4f" % np.rad2deg(results['delta_elevator']), 'deg') print('delta_aile = ', "%8.4f" % np.rad2deg(results['delta_aileron']), 'deg') print('delta_rud = ', "%8.4f" % np.rad2deg(results['delta_rudder']), 'deg') print('delta_t = ', "%8.4f" % results['delta_t'], '%', '\n') print('alpha = ', "%8.4f" % np.rad2deg(results['alpha']), 'deg') print('beta = ', "%8.4f" % np.rad2deg(results['beta']), 'deg', '\n') print('u = ', "%8.4f" % results['u'], 'm/s') print('v = ', "%8.4f" % results['v'], 'm/s') print('w = ', "%8.4f" % results['w'], 'm/s', '\n') print('psi = ', "%8.4f" % np.rad2deg(psi0), 'deg') print('theta = ', "%8.4f" % np.rad2deg(results['theta']), 'deg') print('phi = ', "%8.4f" % np.rad2deg(results['phi']), 'deg', '\n')