def compute_energies(results,summary=False):
# evaluate each segment
for i in range(len(results.Segments)):
segment = results.Segments[i]
eta=segment.conditions.propulsion.throttle[:,0]
state = Data()
state.q = segment.conditions.freestream.dynamic_pressure[:,0]
state.g0 = segment.conditions.freestream.gravity[:,0]
state.V = segment.conditions.freestream.velocity[:,0]
state.M = segment.conditions.freestream.mach_number[:,0]
state.T = segment.conditions.freestream.temperature[:,0]
state.p = segment.conditions.freestream.pressure[:,0]
segment.P_fuel, segment.P_e = segment.config.Propulsors.power_flow(eta,state)
# time integration operator
'''
print segment.numerics
I = segment.numerics.integrate_time
# raw propellant energy consumed
segment.energy.propellant = np.dot(I,segment.P_fuel)[-1]
# raw electrical energy consumed
segment.energy.electric = np.dot(I,segment.P_e)[-1]
# energy to gravity
segment.energy.gravity = np.dot(I,segment.m*segment.g*segment.vectors.V[:,2])[-1] # J
# energy to drag
segment.energy.drag = np.dot(I,segment.D*segment.V)[-1] # J
if summary:
print " "
print "####### Energy Summary: Segment " + str(i) + " #######"
print " "
print "Propellant energy used = " + str(segment.energy.propellant/1e6) + " MJ"
print "Electrical energy used = " + str(segment.energy.electric/1e6) + " MJ"
print "Energy lost to gravity = " + str(segment.energy.gravity/1e6) + " MJ"
print "Energy lost to drag = " + str(segment.energy.drag/1e6) + " MJ"
print " "
print "#########################################"
print " "
'''
return
def compute_energies(results, summary=False):
# evaluate each segment
for i in range(len(results.Segments)):
segment = results.Segments[i]
eta = segment.conditions.propulsion.throttle[:, 0]
state = Data()
state.q = segment.conditions.freestream.dynamic_pressure[:, 0]
state.g0 = segment.conditions.freestream.gravity[:, 0]
state.V = segment.conditions.freestream.velocity[:, 0]
state.M = segment.conditions.freestream.mach_number[:, 0]
state.T = segment.conditions.freestream.temperature[:, 0]
state.p = segment.conditions.freestream.pressure[:, 0]
segment.P_fuel, segment.P_e = segment.config.Propulsors.power_flow(
eta, state)
# time integration operator
'''
print segment.numerics
I = segment.numerics.integrate_time
# raw propellant energy consumed
segment.energy.propellant = np.dot(I,segment.P_fuel)[-1]
# raw electrical energy consumed
segment.energy.electric = np.dot(I,segment.P_e)[-1]
# energy to gravity
segment.energy.gravity = np.dot(I,segment.m*segment.g*segment.vectors.V[:,2])[-1] # J
# energy to drag
segment.energy.drag = np.dot(I,segment.D*segment.V)[-1] # J
if summary:
print " "
print "####### Energy Summary: Segment " + str(i) + " #######"
print " "
print "Propellant energy used = " + str(segment.energy.propellant/1e6) + " MJ"
print "Electrical energy used = " + str(segment.energy.electric/1e6) + " MJ"
print "Energy lost to gravity = " + str(segment.energy.gravity/1e6) + " MJ"
print "Energy lost to drag = " + str(segment.energy.drag/1e6) + " MJ"
print " "
print "#########################################"
print " "
'''
return
def __call__(self,conditions):
alpha = conditions.angle_of_attack
state = Data()
state.M = conditions.mach_number
state.rho = conditions.density
state.mew = conditions.viscosity
state.T = conditions.temperature
#state.q = conditions.dynamic_pressure
state.Sref = self.Sref
#N = state.M.shape[0]
##interpolation methods
#f_Cl = interp1d(self.aoa_range, self.Cl_a,bounds_error=False)
#Cl_inc=f_Cl(alpha)
##Cl_inc=self.f_Cl(alpha)
Cl_inc= self.CL0 + self.dCLdalpha*alpha
CL=Cl_inc/(numpy.sqrt(1-state.M**2))
#print 'alpha',alpha
#print 'Cl_inc',Cl_inc
#print 'CL',CL
#CD = self.CD0 + (CL**2)/(np.pi*self.AR*self.e) # parbolic drag
CD= self.drag(CL,state)
results = Data()
results.lift_coefficient = CL
results.drag_coefficient = CD
conditions.lift_coefficient = CL
conditions.drag_coefficient = CD
L = np.zeros([N,3])
D = np.zeros([N,3])
L[:,2] = ( -CL * state.q * state.Sref )[:,0]
D[:,0] = ( -CD * state.q * state.Sref )[:,0]
results.lift_force_vector = L
results.drag_force_vector = D
return [CL,CD]
def __call__(self,eta,conditions):
segment=Data()
segment.q = conditions.freestream.dynamic_pressure[:,0]
segment.g0 = conditions.freestream.gravity[:,0]
segment.V = conditions.freestream.velocity[:,0]
segment.M = conditions.freestream.mach_number[:,0]
segment.T = conditions.freestream.temperature[:,0]
segment.p = conditions.freestream.pressure[:,0]
F = np.zeros_like(eta)
mdot = np.zeros_like(eta)
P = np.zeros_like(eta)
for propulsor in self.values():
CF, Isp, etaPe = propulsor(eta,segment)
# get or determine intake area
A = propulsor.get_area()
# compute data
F += CF*segment.q*A # N
# propellant-based
if np.isscalar(Isp):
if Isp != 0.0:
mdot += F/(Isp*segment.g0) # kg/s
else:
mask = (Isp != 0.0)
mdot[mask] += F[mask]/(Isp[mask]*segment.g0) # kg/s
# electric-based
if np.isscalar(etaPe):
if etaPe != 0.0:
P += F*segment.V/etaPe # W
#Account for mass gain of Li-air battery
try:
self.battery
except AttributeError:
if propulsor.battery.type=='Li-Air':
for i in range(len(P)):
if propulsor.battery.MaxPower>P[i]:
[Ploss,Mdot]=propulsor.battery(P[i],.01 ) #choose small dt here (has not been solved for yet); its enough to find mass rate gain of battery
else:
[Ploss,Mdot]=propulsor.battery(propulsor.battery.MaxPower,.01 )
mdot[i]+=Mdot.real
else:
mask = (etaPe != 0.0)
P += F[mask]*segment.V[mask]/etaPe[mask] # W
#print mdot
return F, mdot, P
def __call__(self, conditions, numerics):
segment = Data()
segment.q = conditions.freestream.dynamic_pressure[:, 0]
segment.g0 = conditions.freestream.gravity[:, 0]
segment.V = conditions.freestream.velocity[:, 0]
segment.M = conditions.freestream.mach_number[:, 0]
segment.T = conditions.freestream.temperature[:, 0]
segment.p = conditions.freestream.pressure[:, 0]
eta = conditions.propulsion.throttle[:, 0]
F = np.zeros_like(eta)
mdot = np.zeros_like(eta)
P = np.zeros_like(eta)
for propulsor in self.values():
CF, Isp, etaPe = propulsor(eta, segment)
# get or determine intake area
A = propulsor.get_area()
# compute data
F += CF * segment.q * A # N
# propellant-based
if np.isscalar(Isp):
if Isp != 0.0:
mdot += F / (Isp * segment.g0) # kg/s
else:
mask = (Isp != 0.0)
mdot[mask] += F[mask] / (Isp[mask] * segment.g0) # kg/s
# electric-based
if np.isscalar(etaPe):
if etaPe != 0.0:
P += F * segment.V / etaPe # W
#Account for mass gain of Li-air battery
try:
self.battery
except AttributeError:
if propulsor.battery.type == 'Li-Air':
for i in range(len(P)):
if propulsor.battery.MaxPower > P[i]:
[Ploss, Mdot] = propulsor.battery(
P[i], .01
) #choose small dt here (has not been solved for yet); its enough to find mass rate gain of battery
else:
[Ploss, Mdot] = propulsor.battery(
propulsor.battery.MaxPower, .01)
mdot[i] += Mdot.real
else:
mask = (etaPe != 0.0)
P += F[mask] * segment.V[mask] / etaPe[mask] # W
#print mdot
return F[:, None], mdot[:, None], P[:, None]
