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thrustWeightComp.py

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+import numpy as np 
+from openmdao.api import ExplicitComponent
+
+class TwComp(ExplicitComponent):
+
+    def setup(self):
+        self.add_input('G',desc = 'climb gradient')
+        self.add_input('n',desc = 'load factor')
+        self.add_input('e',desc = 'oswald efficieny')
+        self.add_input('AR',desc = 'aspect ratio')
+        self.add_input('cd0',desc = 'parasitic drag')
+        self.add_input('rho',desc = 'density')
+        self.add_input('W_S',desc = 'Wing Loading')
+        self.add_input('Vc',desc = 'Cruise Speed')
+
+        self.add_output('T_W_climb',desc = 'Thrust-to-Weight ratio climb')
+        self.add_output('T_W_cruise',desc = 'Thrust-to-Weight ratio cruise')
+        self.add_output('T_W_maneuver',desc = 'Thrust-to-Weight ratio maneuver')
+
+        self.declare_partials(of = '*', wrt = '*', method = 'cs')
+
+    def compute(self,inputs,outputs):
+        q = 0.5*inputs['rho']*inputs['Vc']*inputs['Vc']
+        twclimb = inputs['G'] + (inputs['W_S']/(np.pi*inputs['e']*inputs['AR']*q)) + (inputs['cd0']*q/(inputs['W_S']))
+        cl = 2*inputs['W_S']/(inputs['rho']*inputs['Vc']*inputs['Vc'])
+        cd = inputs['cd0'] + (1/(np.pi*inputs['e']*inputs['AR']))*cl*cl
+        twcruise = (cl/cd)**(-1)
+        twmaneuver = (inputs['cd0']*q/(inputs['W_S'])) + (inputs['n']*inputs['n'])*(inputs['W_S']/(np.pi*inputs['e']*inputs['AR']*q))
+
+        outputs['T_W_climb'] = twclimb
+        outputs['T_W_cruise'] = twcruise
+        outputs['T_W_maneuver'] = twmaneuver