Trying stuff

Model/Propulsion/cruise_comp.py

@@ -16,7 +16,8 @@ def setup(self):
         self.add_input('cd0',desc='zero lift drag')
 
         self.add_output('P_C',desc='Power required for cruise')
-
+        self.add_output('cl')
+        self.add_output('cd')
         self.declare_partials(of='*', wrt='*', method='cs')
 
 
@@ -25,7 +26,10 @@ def compute(self,inputs,outputs):
         W = inputs['W']*9.81
         # add Cl & Cd if airfoil code doesnt work
         cl = 2*W/(rho*(inputs['V']**2)*inputs['S'])
+
         k = 1/(3.14*0.8*inputs['AR']) # e = 0.8
         cd = inputs['cd0'] + k*cl**2
+        outputs['cl'] = cl
+        outputs['cd'] = cd
         #outputs['P_C'] = (( (2*(W**3)*(inputs['Cd']**2))/(inputs['S']*rho*(inputs['Cl']**3)) )**.5)/1000
         outputs['P_C'] = (( (2*(W**3)*(cd**2))/(inputs['S']*rho*(cl**3) ))**.5)/1000

Model/costanalysis/OperatingCost.py

@@ -42,25 +42,38 @@
 
 #def operatingCost2( r_prop, cruise_speed, avg_dist, shaft_power, mass_struct, mass_batt, mass_motor, b_ref, cRef, power_to_weight ):
 # function inputs
-r_prop = 1
-cruise_speed = 102.82 
-avg_dist = 193121
-shaft_power = 156
-mass_struct = 180
-mass_batt = 627.66
-mass_motor = 635.8
-b_ref = 13.21
-c_ref = 1
-power_to_weight = 0.22
+
+c_ref = 1 #m 
 
 from costanalysis.CostBuildup import CostBuildup
+from openmdao.api import ExplicitComponent
+
+class OperatingCost(ExplicitComponent):
+    def setup(self):
+        self.add_input('r_prop',desc = 'prop radius')
+        self.add_input('cruise_speed',desc = 'cruise speed')
+        self.add_input('avg_dist',desc = 'range')
+        self.add_input('shaft_power',desc = 'shaft power')
+        self.add_input('mass_struct',desc = 'structural mass')
+        self.add_input('mass_batt',desc = 'battery mass')
+        self.add_input('mass_motor',desc = 'motor mass')
+        self.add_input('b_ref',desc = 'span')
+        self.add_input('power_to_weight',desc = 'power to weight ratio') 
+
+        self.add_output('Cost_per_flight',desc = 'cost per flight')
+
+        self.declare_partials('*','*',method = 'cs')
+
+    def compute(self,inputs,outputs):
+        avg_dist = inputs['avg_dist']
+        cruise_speed = inputs['cruise_speed']
+        # Assumptions
+        flight_hours_per_year = 600
+        flight_time = avg_dist/cruise_speed
+        flights_per_year = flight_hours_per_year / (flight_time / 3600)
+        vehicle_life_years = 10
+        n_vehicles_per_facility = 200
 
-# Assumptions
-flight_hours_per_year = 600
-flight_time = avg_dist/cruise_speed
-flights_per_year = flight_hours_per_year / (flight_time / 3600)
-vehicle_life_years = 10
-n_vehicles_per_facility = 200
 
 
 # def CostBuildup( r_prop,c_ref, b_ref ):
@@ -156,7 +169,4 @@
 servo_repl_cost_per_flight + labor_cost_per_flight
 
 print('Cost Per Flight: $', cost_per_flight*1000)
-#   return [C]
-
-
-
+#   return [C]

solver.py

@@ -109,6 +109,7 @@
 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=100)
+#model.add_constraint('cruiseP.cl',upper=0.4)
 
 model.add_objective('FOM.PH',scaler=-1)
 
@@ -140,5 +141,6 @@
 print('Required Power for Hover:',prob['FOM.PH'],'[kW]')
 print('Required Power for Cruise:',prob['cruiseP.P_C'],'[kW]')
 print('Max Trip Range @',prob['V'],'[m/s]:',prob['range.R'],'[km]','Time',prob['range.t'],'[hr]')
-
+print('cl',prob['cruiseP.cl'])
+print('cd',prob['cruiseP.cd'])