Python steady_state_flight_trimmer示例

示例#1

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')

示例#2

文件： example_002_stationary_descent.py 项目： AeroPython/PyFME

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')