if initial_energy[0]==0: //beginning of segment; initialize battery
battery.current_energy=battery.current_energy[-1]*np.ones_like(initial_energy)
except AttributeError: //battery energy not initialized, e.g. in takeoff
battery.current_energy=battery.current_energy[-1]*np.ones_like(F)
pbat=-Pe/self.motor_efficiency
battery_logic = Data()
After Change
numerics = state.numerics
results=propulsor.evaluate_thrust(state)
Pe =results.thrust_force_vector[:,0]*conditions.freestream.velocity
"""
try:
initial_energy=conditions.propulsion.battery_energy
print conditions.propulsion
if initial_energy[0][0]==0: //beginning of segment; initialize battery
battery.current_energy=battery.current_energy[-1]*np.ones_like(initial_energy)
except AttributeError: //battery energy not initialized, e.g. in takeoff
battery.current_energy=battery.current_energy[-1]*np.ones_like(F)
"""
pbat=-Pe/self.motor_efficiency
battery_logic = Data()
battery_logic.power_in = pbat
battery_logic.current = 90. //use 90 amps as a default for now; will change this for higher fidelity methods
battery.inputs =battery_logic
battery.inputs.power_in=pbat
tol = 1e-6
battery.energy_calc(numerics)
//allow for mass gaining batteries
try:
mdot=find_mass_gain_rate(battery,-(pbat-battery.resistive_losses))
except AttributeError:
mdot=np.zeros_like(F)
//Pack the conditions for outputs
battery_draw = battery.inputs.power_in
battery_energy = battery.current_energy
conditions.propulsion.battery_draw = battery_draw
conditions.propulsion.battery_energy = battery_energy
output_power= battery_draw
//number_of_engines
//Create the outputs
results.vehicle_mass_rate = mdot
results.energy = battery_energy
return results
__call__ = evaluate_thrust
