'delta_aileron': 0,
'delta_rudder': 0,
'delta_t': 0.5
}
trimmed_state, trimmed_controls = steady_state_trim(aircraft, environment, pos,
psi, TAS, controls0)
system = EulerFlatEarth(time0=0, tot_state=trimmed_state)
de0 = trimmed_controls['delta_elevator']
controls = controls = {
'delta_elevator': Doublet(t_init=2, T=1, A=0.1, offset=de0),
'delta_aileron': Constant(trimmed_controls['delta_aileron']),
'delta_rudder': Constant(trimmed_controls['delta_rudder']),
'delta_t': Constant(trimmed_controls['delta_t'])
}
sim = Simulation(aircraft, system, environment, controls, dt=0.3)
results_03 = sim.propagate(25)
#sim = Simulation(aircraft, system, environment, controls, dt=0.05)
#results_005 = sim.propagate(25)
kwargs = {'subplots': True, 'sharex': True, 'figsize': (12, 100)}
#ax = results_005.plot(marker='.', color='r', **kwargs)
#ax = resu lts_03.plot(ax=ax, marker='x', color='k', ls='', **kwargs)
results_03.to_excel("output.xlsx")
#plt.show()
