Final design

wangALAN9 · Jun 3, 2019 · 64a05f3 · 64a05f3
1 parent 055733f
commit 64a05f3
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Showing 10 changed files with 51 additions and 21 deletions.
diff --git a/Model/Propulsion/__pycache__/cruise_comp.cpython-37.pyc b/Model/Propulsion/__pycache__/cruise_comp.cpython-37.pyc
diff --git a/Model/Propulsion/cruise_comp.py b/Model/Propulsion/cruise_comp.py
@@ -1,4 +1,5 @@
 from openmdao.api import ExplicitComponent
+import numpy as np
 
 rho = 1.225 #density, [kg/m**3]
 
@@ -13,12 +14,15 @@ def setup(self):
         self.add_input('AR',desc='Aspect Ratio')
         self.add_input('S',desc='Refernce Area')
         self.add_input('V',desc='Airspeed')
+        self.add_input('r',desc='prop radius')
         #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.add_output('cd0')
+        self.add_output('B')
+        self.add_output('clear',desc = 'radius clearance')
         self.declare_partials(of='*', wrt='*', method='cs')
 
 
@@ -34,10 +38,18 @@ def compute(self,inputs,outputs):
         Swet = (10**c)*(inputs['W']*2.2046)**d
         f = (10**a)*Swet**b
         cd0 = f/(inputs['S']*10.7639)
+        cd0 = cd0.real
         k = 1/(3.14*0.8*inputs['AR']) # e = 0.8
         cd = cd0 + k*cl**2
         outputs['cl'] = cl
         outputs['cd'] = cd
         outputs['cd0'] = cd0
         #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
+        outputs['P_C'] = (( (2*(W**3)*(cd**2))/(inputs['S']*rho*(cl**3) ))**.5)/1000
+        S = inputs['S']
+        AR = inputs['AR']
+        B = ((S/2)*AR)**0.5
+        r_prop = inputs['r']
+        clear = (B/2 - 3*r_prop)/(B/2)
+        outputs['clear'] = clear
+        outputs['B'] = B
diff --git a/Model/Weight/__pycache__/weight_buildup_comp.cpython-37.pyc b/Model/Weight/__pycache__/weight_buildup_comp.cpython-37.pyc
diff --git a/Model/Weight/weight_buildup_comp.py b/Model/Weight/weight_buildup_comp.py
@@ -12,6 +12,7 @@ def setup(self):
         self.add_input('Neg',desc='number of engines')
         self.add_input('W0',desc='gross weight')
         self.add_input('Np',desc='number of people')
+        self.add_input('S',desc='wing area')
 
         self.declare_partials(of='*', wrt='*', method='cs')
         self.add_output('We',desc='empty weight')
@@ -31,7 +32,7 @@ def compute(self, inputs, outputs):
         Nz = 3.9            # ultimate load factor
         q = 0.5*0.002377*(V**2)  # dynamic pressure at cruise
         Sf = 362.744               # fuselage wetted area
-        Sw = 142.233               # trapezoidal wing area
+        Sw = inputs['S']*10.764                # trapezoidal wing area
         Wdg = inputs['W0']*2.2046              # gross weight
         Wen = 105              # engine weight each [lb]
         Wl = Wdg            # langing gross weight
@@ -45,7 +46,7 @@ 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))*0.70
+        W_lg = (0.095*((Nl*Wl)**0.768)*((Lm/12)**0.845))*0.5
         # installed engine
         W_ie = 2.575*(Wen**0.922)*(Neg)
         # flight controls

diff --git a/Model/costanalysis1/costanalysis/__pycache__/cost_buildup.cpython-37.pyc b/Model/costanalysis1/costanalysis/__pycache__/cost_buildup.cpython-37.pyc
diff --git a/Model/costanalysis1/costanalysis/__pycache__/tooling_cost.cpython-37.pyc b/Model/costanalysis1/costanalysis/__pycache__/tooling_cost.cpython-37.pyc
diff --git a/Model/costanalysis1/costanalysis/cost_buildup.py b/Model/costanalysis1/costanalysis/cost_buildup.py
@@ -17,8 +17,8 @@
 
 def CostBuildup(r_prop,c_ref, b_ref):
     # Inputs
-    fuselage_width = 1
-    fuselage_length = 5
+    fuselage_width = 2.4
+    fuselage_length = 6.5
     toc = 0.15  # Wing / canard thickness
     prop_radius = r_prop
     prop_chord = 0.15 * prop_radius
@@ -27,7 +27,7 @@ def CostBuildup(r_prop,c_ref, b_ref):
 
     parts_per_tool = 1000
 
-    fuselage_height = 1.3 # Guess
+    fuselage_height = 1.75 # Guess
     span = b_ref
     chord = c_ref
 

diff --git a/Model/costanalysis1/costanalysis/tooling_cost.py b/Model/costanalysis1/costanalysis/tooling_cost.py
@@ -51,9 +51,9 @@ def EllipsePerimeter(a, b):
         return p
 
     finish_bit_step = 0.8 * finish_bit_diam # Rougher step size
-    cut_area = length * EllipsePerimeter(width/2,depth)/2; # Amount of material to rough out
-    finish_time = cut_area / (finish_feed * finish_bit_step) * finish_passes; # Time for roughing
-    finish_cost = finish_time * finish_cost_rate; # Roughing cost
+    cut_area = length * EllipsePerimeter(width/2,depth)/2 # Amount of material to rough out
+    finish_time = cut_area / (finish_feed * finish_bit_step) * finish_passes # Time for roughing
+    finish_cost = finish_time * finish_cost_rate # Roughing cost
 
     # Total Cost
     cost = material_cost + rough_cost + finish_cost

diff --git a/n2.html b/n2.html
@@ -1129,7 +1129,7 @@ <h1>OpenMDAO Partition Tree and N<sup>2</sup> diagram.</h1>
 </script>
 
     <script type="text/javascript">
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+var modelData = {"tree": {"name": "root", "type": "root", "subsystem_type": "group", "linear_solver": "LN: RUNONCE", "nonlinear_solver": "NL: RUNONCE", "children": [{"name": "ivc", "type": "subsystem", "subsystem_type": "component", "linear_solver": "", "nonlinear_solver": "", "children": [{"name": "Wb", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "Wp", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "Wm", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "m", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "r", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "TS", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "rho", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "V", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "S", "type": "unknown", "implicit": false, "dtype": "ndarray"}, {"name": "AR", "type": "unknown", "implicit": 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