[SimPleAC] Moving SigEnabled to Fuel section.

convexengineering · Sep 27, 2017 · 0f19a9a · 0f19a9a
1 parent 92d302b
commit 0f19a9a
Showing 1 changed file with 24 additions and 24 deletions.
diff --git a/gpkitmodels/SP/SimPleAC/SimPleAC.py b/gpkitmodels/SP/SimPleAC/SimPleAC.py
@@ -20,7 +20,7 @@ def SimPleAC():
                           "wing weight coefficent 1", pr= 30.) #orig  12e-5
     W_W_coeff2 = Variable("W_{W_{coeff2}}", 60., "Pa",
                           "wing weight coefficent 2", pr=10.)
-    p_labor = Variable('p_{labor}',1.,'1/min','cost of labor', pr = 20.)
+    p_labor    = Variable('p_{labor}',1.,'1/min','cost of labor', pr = 20.)
 
     # Dimensional constants
     CDA0      = Variable("(CDA0)", "m^2", "fuselage drag area") #0.035 originally
@@ -57,34 +57,34 @@ def SimPleAC():
     # Drag model
     C_D_fuse = CDA0 / S
     C_D_wpar = k * C_f * S_wetratio
-    C_D_ind = C_L ** 2 / (np.pi * A * e)
+    C_D_ind  = C_L ** 2 / (np.pi * A * e)
     constraints += [C_D >= C_D_fuse * toz + C_D_wpar / toz + C_D_ind * toz]
 
+    # Wing weight model
+    constraints += [W_w >= W_w_surf + W_w_strc,
+                # W_w_strc >= W_W_coeff1 * (N_ult * A ** 1.5 * ((W_0+V_f_fuse*g*rho_f) * W * S) ** 0.5) / tau, #[GP]
+                W_w_strc**2. >= W_W_coeff1**2. * (N_ult**2. * A ** 3. * ((W_0+V_f_fuse*g*rho_f) * W * S)) / tau**2.,
+                W_w_surf >= W_W_coeff2 * S]
+
+    # Weight and aerodynamics model
+    constraints += [LoD == C_L/C_D,
+                D >= 0.5 * rho * S * C_D * V ** 2,
+                Re <= (rho / mu) * V * (S / A) ** 0.5,
+                C_f >= 0.074 / Re ** 0.2,
+                T_flight >= Range / V,
+                W_0 + W_w + 0.5 * W_f <= 0.5 * rho * S * C_L * V ** 2,
+                W <= 0.5 * rho * S * C_Lmax * V_min ** 2,
+                W >= W_0 + W_w + W_f]
 
+    # Fuel volume model 
     with SignomialsEnabled():
-            # Wing weight model
-        constraints += [W_w >= W_w_surf + W_w_strc,
-                        # W_w_strc >= W_W_coeff1 * (N_ult * A ** 1.5 * ((W_0+V_f_fuse*g*rho_f) * W * S) ** 0.5) / tau, #[GP]
-                        W_w_strc**2. >= W_W_coeff1**2. * (N_ult**2. * A ** 3. * ((W_0+V_f_fuse*g*rho_f) * W * S)) / tau**2.,
-                        W_w_surf >= W_W_coeff2 * S]
-
-            # Weight and aerodynamics model
-        constraints += [LoD == C_L/C_D,
-                    D >= 0.5 * rho * S * C_D * V ** 2,
-                    Re <= (rho / mu) * V * (S / A) ** 0.5,
-                    C_f >= 0.074 / Re ** 0.2,
-                    T_flight >= Range / V,
-                    W_0 + W_w + 0.5 * W_f <= 0.5 * rho * S * C_L * V ** 2,
-                    W <= 0.5 * rho * S * C_Lmax * V_min ** 2,
-                    W >= W_0 + W_w + W_f]
-            # Fuel volume model 
         constraints +=[V_f == W_f / g / rho_f,
-                    V_f_avail <= V_f_wing + V_f_fuse, #[SP]
-                    V_f_wing**2 <= 0.0009*S**3/A*tau**2, # linear with b and tau, quadratic with chord
-                    V_f_fuse <= 10*units('m')*CDA0,
-                        #TODO: Reduce volume available by the structure!
-                    V_f_avail >= V_f,
-                    W_f >= TSFC * T_flight * D]
+                V_f_avail <= V_f_wing + V_f_fuse, #[SP]
+                V_f_wing**2 <= 0.0009*S**3/A*tau**2, # linear with b and tau, quadratic with chord
+                V_f_fuse <= 10*units('m')*CDA0,
+                    #TODO: Reduce volume available by the structure!
+                V_f_avail >= V_f,
+                W_f >= TSFC * T_flight * D]
 
     # return Model(W_f/LoD, constraints)
     # return Model(D, constraints)