dank dank

Model/Propulsion/power_comp.py

@@ -35,7 +35,7 @@ def compute(self, inputs, outputs):
         ct = T/( rho *S* (tip_speed**2) )
         cp = ( 1.15*( (ct**(3/2)) /(2**.5) ) + (1/8)*sol*cd0 ) # solidity
         PI = T * ((T/(2*S*rho))**.5)
-        PH = cp*rho*S*(tip_speed**3)
+        PH = cp*rho*S*(tip_speed**3)*.99 
         FM = PI/PH
 
         outputs['FM'] = FM

Model/Weight/gross_weight_comp.py

@@ -8,12 +8,13 @@ class GrossWeightComp(ExplicitComponent):
     def setup(self):
         self.add_input('Wp')   # weight of payload (passangers)
         self.add_input('Wb')   # weight of battery
+        self.add_input('S',desc='lifting surface')
         #self.add_input('We/W0')   # empty over gross
         self.add_input('We',desc='empty weight')
         self.add_output('W0') # gross weight
         self.add_output('We_W0') # gross weight
         self.add_output('Wb_W0') # gross weight
-
+        self.add_output('W_S')
         self.declare_partials('*', '*')
         self.declare_partials(of='*', wrt='*', method='cs')
 
@@ -26,6 +27,7 @@ def compute(self, inputs, outputs):
         outputs['We_W0'] = We/W0
         outputs['Wb_W0'] = Wb/W0
         outputs['W0'] = W0
+        outputs['W_S'] = W0/inputs['S']
 
     #def compute_partials(self, inputs, partials):
         #Wp = inputs['Wp']

Model/Weight/weight_buildup_comp.py

@@ -33,7 +33,7 @@ def compute(self, inputs, outputs):
         Sf = 362.744               # fuselage wetted area
         Sw = 142.233               # trapezoidal wing area
         Wdg = inputs['W0']*2.2046              # gross weight
-        Wen = 110              # engine weight each [lb]
+        Wen = 105              # engine weight each [lb]
         Wl = Wdg            # langing gross weight
         #Wuav = 800          # usual 800-1400
         M = V/1116.13       # mach
@@ -45,7 +45,7 @@ def compute(self, inputs, outputs):
         # fuselage
         W_f = 0.052*(Sf**1.086)*((Nz*Wdg)**0.22)*(L_f**(-0.051))*((L_D)**(-0.072))*(q**0.241)
         # landing gear
-        W_lg = 0.095*((Nl*Wl)**0.768)*((Lm/12)**0.845)
+        W_lg = (0.095*((Nl*Wl)**0.768)*((Lm/12)**0.845))*0.70
         # installed engine
         W_ie = 2.575*(Wen**0.922)*(Neg)
         # flight controls
@@ -57,14 +57,14 @@ def compute(self, inputs, outputs):
         # electrical
         W_el = 12.57*(W_av)**0.51
         # air conditioning
-        W_ac = 0.265*Wdg**0.52*Np**0.68*W_av**0.17*M**0.08
+        W_ac = (0.265*Wdg**0.52*Np**0.68*W_av**0.17*M**0.08)*0.85
         # furnishings 
         W_fur = 0.0582*Wdg - 65
         # actuators
         # 12 actuators, 0.65 kg each
         W_act = 12*1.43
 
-        We = 0.8*(W_w + W_f + W_lg + W_ie + W_fc + W_h + W_av + W_el + W_ac + W_fur + W_act)/2.205
+        We = (W_w + W_f + W_lg + W_ie + W_fc + W_h + W_av + W_el + W_ac + W_fur + W_act)/2.205
         #print('weight',We)
         outputs['We'] = We  # outputs kg
 

solver.py

@@ -50,6 +50,7 @@
 model.connect('Wb','weight.Wb')
 model.connect('Wp','weight.Wp')
 model.connect('emptyW.We','weight.We')
+model.connect('S','weight.S')
 #model.connect('We/W0','weight.We/W0')
 
 # connecting to empty weight comp
@@ -109,26 +110,29 @@
 
 
 prob.driver = ScipyOptimizeDriver()
-prob.driver.options['optimizer'] = 'SLSQP'
+prob.driver.options['optimizer'] = 'SLSQP' # i
 prob.driver.options['tol'] = 1e-9
 prob.driver.options['disp'] = True
 
-model.add_design_var('r',lower=0.7,upper=1)
+#opt driver
+#prob.driver = pyOptSparseDriver()
+#prob.driver.options['optimizer'] = "SLSQP"
+#prob.driver.hist_file = 'host.hst'
+
+
+model.add_design_var('r',lower=0.7,upper=1.2)
 model.add_design_var('V',lower=67,upper=103)
 model.add_design_var('Wb') # proff sees typical of 20-25% gross weight
+#model.add_design_var('S',lower=10,upper=20)
 
-#model.add_constraint('weight.We_W0',lower=0.45,upper=0.70) # 30% - 70%, from lecture
-#model.add_constraint('weight.W0',lower=1700,upper=2000)
 model.add_constraint('FOM.FM',lower=0.70,upper=0.80)
-
-model.add_constraint('range.R',equals=340)
-model.add_constraint('weight.Wb_W0',lower=0.25,upper=0.30) # batt to gross
-#model.add_constraint('FOM.PH',upper=550)
-model.add_constraint('cruiseP.P_C',upper=80)
-#model.add_constraint('cruiseP.cl',upper=0.4)
+model.add_constraint('range.R',equals=245)
+model.add_constraint('weight.Wb_W0',lower=0.20,upper=0.30) # batt to gross
+#model.add_constraint('cruiseP.cl',upper=0.5)
+#model.add_constraint('weight.W_S',upper = 1327)
+#model.add_constraint('cruiseP.P_C',upper=110)
 model.add_objective('cost.Cost',scaler=-1)
 
-#model.add_objective('FOM.PH',scaler=-1)
 
 prob.setup()
 
@@ -138,15 +142,13 @@
 prob['V'] = 80
 
 
-#opt driver
-#prob.driver = pyOptSparceDriver()
-#prob.driver.options['optimizer'] = "SLSQP"
-#prob.driver.hist_file = 'host.hst'
 
 
 #prob.run_model()
 prob.set_solver_print(level=0)
 prob.run_driver()
+print('S',prob['S'])
+print('W_S',prob['weight.W_S'])
 print('Batt Weight',prob['Wb'])
 print('Tip Speed',prob['TS'],'[m/s]')
 print('Empty Weight Fraction:',prob['weight.We_W0'])