Constraint analysis

trunk/SUAVE/Methods/Propulsion/ConstraintAnalysis/Verification/ConstraintAnalysisEquations.py

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+import SUAVE
+import numpy as np
+import matplotlib as plt
+from SUAVE.Core import Data
+from SUAVE.Methods.Propulsion.ConstraintAnalysis.Verification.Parameters import *
+from SUAVE.Methods.Propulsion.ConstraintAnalysis.Verification.intersect import intersection
+
+WS=np.linspace(20,20000,1)
+
+def LandingConstraint():
+    WS_Landing = clmax_landing * rho_SL * LandingDistance / (2 * 0.5847 * FractionWeightLanding)  # Check if clmax of landing is the same as this
+    i=2
+    return WS_Landing
+
+def StallConstraint():
+    WS_Stall = 0.5 * rho_SL * V_stall ** 2 * clmax
+    return WS_Stall
+
+def VmaxConstraint():
+    TW_Vmax = []
+    for x in WS:
+        TW_Vmax_i = (rho_SL * V_max ** 2 * cd0) / (2 * x) + 2 * K_aerodynamics * x / (rho_cruise * sigma_cruise * V_max ** 2)
+        TW_Vmax.append(TW_Vmax_i)
+    return TW_Vmax
+
+def TakeoffConstraint():
+    TW_Takeoff = []
+    for x in WS:
+        TW_Takeoff_i=(mu - (mu + cdG/clR)*np.exp(0.6*rho_SL*g*cdG*S_TO/x))/(1-np.exp(0.6*rho_SL*g*cdG*S_TO/x))
+        TW_Takeoff.append(TW_Takeoff_i)
+    return TW_Takeoff
+
+def ROCConstraint():
+    TW_ROC = []
+    for x in WS:
+        TW_ROC_i=ROC/np.sqrt(2*x/(rho_SL*np.sqrt(cd0/K_aerodynamics))) + 1/LD_max
+        TW_ROC.append(TW_ROC_i)
+    return TW_ROC
+
+def CeilingConstraint():
+    TW_Ceiling = []
+    for x in WS:
+        TW_Ceiling_i=ROC_service_ceiling/(sigma_service_ceiling*np.sqrt(2*x/(rho_service_ceiling*np.sqrt(cd0/K_aerodynamics)))) + 1/(sigma_service_ceiling*LD_max)
+        TW_Ceiling.append(TW_Ceiling_i)
+    return TW_Ceiling
+
+def ClimbGradientConstraint():
+    TW_ClimbGradient = []
+    for x in WS:
+        TW_ClimbGradient_i = NumberEngines/(NumberEngines-1)*(cV_ClimbGradient+2*np.sqrt(cd0/(np.pi*AspectRatio*Oswald)))
+        TW_ClimbGradient.append(TW_ClimbGradient_i)
+    return TW_ClimbGradient
+
+def ManoueuvringConstraint():
+    TW_Manoeuvring = []
+    for x in WS:
+        TW_Manoeuvring_i = 0.5*rho_cruise*(V_cruise**2)*cd0/x + 2*x*(nmax**2)/(np.pi*AspectRatio*Oswald*rho_cruise*(V_cruise**2))
+        TW_Manoeuvring.append(TW_Manoeuvring_i)
+    return TW_Manoeuvring

trunk/SUAVE/Methods/Propulsion/ConstraintAnalysis/Verification/MatricesConstraintAnalysis.py

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+import SUAVE
+import numpy as np
+import matplotlib as plt
+from SUAVE.Core import Data
+from SUAVE.Methods.Propulsion.ConstraintAnalysis.Verification.Parameters import *
+from SUAVE.Methods.Propulsion.ConstraintAnalysis.Verification.ConstraintAnalysisEquations import *
+
+### EFFICIENCY AND POWER MANAGEMENT PARAMETERS
+
+# Takeoff
+eta_valve_TO = 0.99
+eta_gasturbine_1_TO = 0.5
+eta_gasturbine_2_TO = 0.4
+eta_powermanagement_1_TO = 0.98
+eta_powermanagement_2_TO = 0.98
+eta_electricmotor_TO = 0.9
+eta_propulsive_1_TO = 0.8
+eta_propulsive_2_TO = 0.8
+phi_TO=0.7
+psi_TO=1
+lambda_TO=0.1
+
+# Climb
+eta_valve_climb = 0.99
+eta_gasturbine_1_climb = 0.5
+eta_gasturbine_2_climb = 0.4
+eta_powermanagement_1_climb = 0.98
+eta_powermanagement_2_climb = 0.98
+eta_electricmotor_climb = 0.9
+eta_propulsive_1_climb = 0.8
+eta_propulsive_2_climb = 0.8
+phi_climb=0.7
+psi_climb=1
+lambda_climb=0.1
+
+# Cruise
+eta_valve_cruise = 0.99
+eta_gasturbine_1_cruise = 0.5
+eta_gasturbine_2_cruise = 0.4
+eta_powermanagement_1_cruise = 0.98
+eta_powermanagement_2_cruise = 0.98
+eta_electricmotor_cruise = 0.9
+eta_propulsive_1_cruise = 0.8
+eta_propulsive_2_cruise = 0.8
+phi_cruise=0.7
+psi_cruise=1
+lambda_cruise=0.1
+
+# Descent
+eta_valve_descent = 0.99
+eta_gasturbine_1_descent = 0.5
+eta_gasturbine_2_descent = 0.4
+eta_powermanagement_1_descent = 0.98
+eta_powermanagement_2_descent = 0.98
+eta_electricmotor_descent = 0.9
+eta_propulsive_1_descent = 0.8
+eta_propulsive_2_descent = 0.8
+phi_descent=0.7
+psi_descent=1
+lambda_descent=0.1
+
+# Landing
+eta_valve_landing = 0.99
+eta_gasturbine_1_landing = 0.5
+eta_gasturbine_2_landing = 0.4
+eta_powermanagement_1_landing = 0.98
+eta_powermanagement_2_landing = 0.98
+eta_electricmotor_landing = 0.9
+eta_propulsive_1_landing = 0.8
+eta_propulsive_2_landing = 0.8
+phi_landing=0.7
+psi_landing=1
+lambda_landing=0.1
+
+def matrices_constraint_analysis():
+    # Matrices with no system failure
+    matrix_takeoff=np.array([-eta_valve_TO, 1, 1, 0, 0,0,0,0,0,0,0,0,0],[0, -eta_gasturbine_1_TO, 0, 1, 0,-eta_gasturbine_2_TO,0,0,0,0,0,0,0],[0, 0, 0, -eta_propulsive_1_TO, 1,0,0,0,0,0,0,0,0],[0, 0, -1, 0, 0,1,1,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,-eta_powermanagement_1_TO,-eta_powermanagement_1_TO,1,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,-eta_powermanagement_2_TO,1,1,0,0],[0, 0, 0, 0, 0,0,0,0,0,0,-eta_electricmotor_TO,1,0],[0, 0, 0, 0, 0,0,0,0,0,0,0,-eta_propulsive_2_TO,1],[0, 1-phi_TO, phi_TO, 0, 0,0,0,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,1-psi_TO,psi_TO,0,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,0,1-lambda_TO,lambda_TO,0,0],[0, 0, -eta_SOFC_TO, 0, 0,0,1,0,0,0,0,0,0],[0, 0, 0, 0, 1,0,0,0,0,0,0,0,1])
+    matrix_climb=np.array([-eta_valve_climb, 1, 1, 0, 0,0,0,0,0,0,0,0,0],[0, -eta_gasturbine_1_climb, 0, 1, 0,-eta_gasturbine_2_climb,0,0,0,0,0,0,0],[0, 0, 0, -eta_propulsive_1_climb, 1,0,0,0,0,0,0,0,0],[0, 0, -1, 0, 0,1,1,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,-eta_powermanagement_1_climb,-eta_powermanagement_1_climb,1,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,-eta_powermanagement_2_climb,1,1,0,0],[0, 0, 0, 0, 0,0,0,0,0,0,-eta_electricmotor_climb,1,0],[0, 0, 0, 0, 0,0,0,0,0,0,0,-eta_propulsive_2_climb,1],[0, 1-phi_climb, phi_climb, 0, 0,0,0,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,1-psi_climb,psi_climb,0,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,0,1-lambda_climb,lambda_climb,0,0],[0, 0, -eta_SOFC_climb, 0, 0,0,1,0,0,0,0,0,0],[0, 0, 0, 0, 1,0,0,0,0,0,0,0,1])
+    matrix_cruise=np.array([-eta_valve_cruise, 1, 1, 0, 0,0,0,0,0,0,0,0,0],[0, -eta_gasturbine_1_cruise, 0, 1, 0,-eta_gasturbine_2_cruise,0,0,0,0,0,0,0],[0, 0, 0, -eta_propulsive_1_cruise, 1,0,0,0,0,0,0,0,0],[0, 0, -1, 0, 0,1,1,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,-eta_powermanagement_1_cruise,-eta_powermanagement_1_cruise,1,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,-eta_powermanagement_2_cruise,1,1,0,0],[0, 0, 0, 0, 0,0,0,0,0,0,-eta_electricmotor_cruise,1,0],[0, 0, 0, 0, 0,0,0,0,0,0,0,-eta_propulsive_2_cruise,1],[0, 1-phi_cruise, phi_cruise, 0, 0,0,0,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,1-psi_cruise,psi_cruise,0,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,0,1-lambda_cruise,lambda_cruise,0,0],[0, 0, -eta_SOFC_cruise, 0, 0,0,1,0,0,0,0,0,0],[0, 0, 0, 0, 1,0,0,0,0,0,0,0,1])
+    matrix_descent=np.array([-eta_valve_descent, 1, 1, 0, 0,0,0,0,0,0,0,0,0],[0, -eta_gasturbine_1_descent, 0, 1, 0,-eta_gasturbine_2_descent,0,0,0,0,0,0,0],[0, 0, 0, -eta_propulsive_1_descent, 1,0,0,0,0,0,0,0,0],[0, 0, -1, 0, 0,1,1,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,-eta_powermanagement_1_descent,-eta_powermanagement_1_descent,1,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,-eta_powermanagement_2_descent,1,1,0,0],[0, 0, 0, 0, 0,0,0,0,0,0,-eta_electricmotor_descent,1,0],[0, 0, 0, 0, 0,0,0,0,0,0,0,-eta_propulsive_2_descent,1],[0, 1-phi_descent, phi_descent, 0, 0,0,0,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,1-psi_descent,psi_descent,0,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,0,1-lambda_descent,lambda_descent,0,0],[0, 0, -eta_SOFC_descent, 0, 0,0,1,0,0,0,0,0,0],[0, 0, 0, 0, 1,0,0,0,0,0,0,0,1])
+    matrix_landing=np.array([-eta_valve_landing, 1, 1, 0, 0,0,0,0,0,0,0,0,0],[0, -eta_gasturbine_1_landing, 0, 1, 0,-eta_gasturbine_2_landing,0,0,0,0,0,0,0],[0, 0, 0, -eta_propulsive_1_landing, 1,0,0,0,0,0,0,0,0],[0, 0, -1, 0, 0,1,1,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,-eta_powermanagement_1_landing,-eta_powermanagement_1_landing,1,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,-eta_powermanagement_2_landing,1,1,0,0],[0, 0, 0, 0, 0,0,0,0,0,0,-eta_electricmotor_landing,1,0],[0, 0, 0, 0, 0,0,0,0,0,0,0,-eta_propulsive_2_landing,1],[0, 1-phi_landing, phi_landing, 0, 0,0,0,0,0,0,0,0,0],[0, 0, 0, 0, 0,0,1-psi_landing,psi_landing,0,0,0,0,0],[0, 0, 0, 0, 0,0,0,0,0,1-lambda_landing,lambda_landing,0,0],[0, 0, -eta_SOFC_landing, 0, 0,0,1,0,0,0,0,0,0],[0, 0, 0, 0, 1,0,0,0,0,0,0,0,1])
+
+    # Matrices with system failure

trunk/SUAVE/Methods/Propulsion/ConstraintAnalysis/Verification/PlotConstraintAnalysis.py

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+import SUAVE
+import numpy as np
+import matplotlib as plt
+from SUAVE.Core import Data
+from SUAVE.Methods.Propulsion.ConstraintAnalysis.Verification.Parameters import *
+from SUAVE.Methods.Propulsion.ConstraintAnalysis.Verification.ConstraintAnalysisEquations import *
+
+def plot_constraint_analysis():
+    # Run constraint analysis equations
+
+    WS_Landing = LandingConstraint()
+    WS_Stall = StallConstraint()
+    TW_Vmax = VmaxConstraint()
+    TW_Takeoff = TakeoffConstraint()
+    TW_ROC = ROCConstraint()
+    TW_Ceiling = CeilingConstraint()
+    TW_ClimbGradient = ClimbGradientConstraint()
+    TW_Manoeuvring = ManoueuvringConstraint()
+
+    # ----------------------------------------------------------------------
+    #   Plot of the constraint analysis in a W/S-T/W chart
+    # ----------------------------------------------------------------------
+
+    WS = np.linspace(20, 20000, 1)
+
+    plt.pyplot.plot([WS_Stall, WS_Stall], [0, 1], label="Stall")
+    plt.pyplot.plot([WS_Landing, WS_Landing], [0, 1], label="Landing")
+    plt.pyplot.plot(WS, TW_Vmax, label="Max speed")
+    plt.pyplot.plot(WS, TW_Takeoff, label="Takeoff")
+    plt.pyplot.plot(WS, TW_ROC, label="ROC")
+    plt.pyplot.plot(WS, TW_Ceiling, label="Service ceiling")
+    plt.pyplot.plot(WS, TW_ClimbGradient, label="Climb gradient")
+    plt.pyplot.plot(WS, TW_Manoeuvring, label="Manoeuvring")
+    plt.pyplot.xlabel('W/S (N/m^2)')
+    plt.pyplot.ylabel('T/W')
+    plt.pyplot.title('Constraint analysis')
+    plt.pyplot.legend()
+    plt.pyplot.show()