created new prop classes; actuator disk and single blade element

gpkitmodels/GP/aircraft/motor/motor_test.py

@@ -1,5 +1,6 @@
 from gpkit import Model, parse_variables, SignomialsEnabled, SignomialEquality, units
 from motor import Propulsor, ElecMotor, ElecMotor_Performance
+from prop  import Propeller
 from gpkitmodels.GP.aircraft.wing.wing_test import FlightState
 
 class Propulsor_Test(Model):
@@ -33,6 +34,46 @@ def setup(self):
         self.cost = 1./mp.etam
         return self.mp, fs
 
+class speed_280_motor(Model):
+    def setup(self):
+        fs = FlightState()
+        m  = ElecMotor()
+        mp = ElecMotor_Performance(m,fs)
+        self.mp = mp
+        mp.substitutions[m.Qmax] = 100
+        mp.substitutions[mp.R]   = .7
+        mp.substitutions[mp.i0]  = .16
+        mp.substitutions[mp.Kv]  = 3800
+        mp.substitutions[mp.v]   = 6
+        self.cost = 1./mp.etam
+        return self.mp, fs
+
+def speed_280_test():
+    test = speed_280_motor()
+    sol  = test.solve()
+    print sol.table()
+
+
+class graupner_cam_6x3(Model):
+    def setup(self):
+        self.fs = FlightState()
+        self.p  = Propeller()
+
+        self.p.substitutions[self.p.R] = (3./12.) #Convert in to ft
+
+    return self.p, self.fs
+class motorProp(Model):
+    def setup(self):
+        p = graupner_cam_6x3()
+        m = speed_280_motor()
+
+
+        p.fs.substitutions[p.fs.V] = 10
+
+        self.cost(1/p.)
+
+
+
 def motor_test():
     test = Motor_P_Test()
     sol = test.solve()
@@ -62,4 +103,5 @@ def test():
     propulsor_test()
 
 if __name__ == "__main__":
-    test()
+    #test()
+    speed_280_test()

gpkitmodels/GP/aircraft/prop/propeller.py

@@ -3,9 +3,7 @@
 from gpkit import Model, parse_variables, SignomialsEnabled, SignomialEquality
 
 
-
-
-class Propeller_Performance(Model):
+class Actuator_Propeller_Performance(Model):
     """ Propeller Model
 
     Variables
@@ -55,7 +53,7 @@ def setup(self,parent,  state):
                 ]
         return constraints, state
 
-class Propeller(Model):
+class Actuator_Propeller(Model):
     """ Propeller Model
 
     Variables
@@ -73,3 +71,72 @@ def setup(self):
         constraints = [W >= K*T_m_static*R**2]
 
         return constraints
+
+class One_Element_Propeller_Performance(Model):
+    """ Propeller Model
+
+    Variables
+    ---------
+    T                       [lbf]       thrust
+    Tc                      [-]         coefficient of thrust
+    etaadd     0.7          [-]         swirl and nonuniformity losses
+    etav       0.85         [-]         viscous losses
+    etai                    [-]         inviscid losses
+    eta                     [-]         overall efficiency
+    z1         self.helper  [-]         efficiency helper 1
+    z2                      [-]         efficiency helper 2
+    lam                     [-]         advance ratio
+    CT                      [-]         thrust coefficient
+    CP                      [-]         power coefficient
+    Q                       [N*m]       torque
+    omega                   [rpm]     propeller rotation rate 
+    omega_max    10000      [rpm]     max rotation rate
+    P_shaft                 [kW]        shaft power
+    M_tip       .5          [-]         Tip mach number
+    a           295         [m/s]       Speed of sound at altitude
+    """
+
+    def helper(self, c):
+        return 2. - 1./c[self.etaadd]
+
+    def setup(self,parent,  state):
+        exec parse_variables(Propeller_Performance.__doc__)
+
+        V       = state.V
+        rho     = state.rho
+        R       = parent.R
+
+
+        constraints = [eta <= etav*etai,
+                Tc >= T/(0.5*rho*V**2*pi*R**2),
+                z2 >= Tc + 1,
+                etai*(z1 + z2**0.5/etaadd) <= 2,
+                lam >= V/(omega*R),
+                CT >= Tc*lam**2,
+                CP <= Q*omega/(.5*rho*(omega*R)**3*pi*R**2),
+                eta >= CT*lam/CP, 
+                omega <= omega_max,
+                P_shaft == Q*omega,
+                (M_tip*a)**2 >= (omega*R)**2 + V**2
+
+                ]
+        return constraints, state
+
+class One_Element_Propeller(Model):
+    """ Propeller Model
+
+    Variables
+    ---------
+    R                               [ft]            prop radius
+    W                               [lbf]           prop weight
+    K           4e-4                [1/ft^2]        prop weight scaling factor
+    T_m_static   40.                [lbf]           prop max static thrust
+    """
+
+    flight_model = One_Element_Propeller_Performance
+    def setup(self):
+        exec parse_variables(Propeller.__doc__)
+
+        constraints = [W >= K*T_m_static*R**2]
+
+        return constraints