Feature scramjet

regression/automatic_regression.py

@@ -63,6 +63,7 @@
     'scripts/propulsion_surrogate/propulsion_surrogate.py',
     'scripts/ramjet_network/ramjet_network.py',
     'scripts/Regional_Jet_Optimization/Optimize2.py',
+    'scripts/scramjet_network/scramjet_network.py',    
     'scripts/sizing_loop/sizing_loop.py',
     'scripts/solar_network/solar_network.py',
     'scripts/solar_network/solar_low_fidelity_network.py',

regression/scripts/AVL/avl_files/aircraft.avl

@@ -164,4 +164,4 @@ SECTION
 
 SECTION
 #Xle     Yle      Zle      Chord     Ainc  Nspanwise  Sspace
-6.4    0     1.87     23.62     0.0      1        0
+6.4    0     1.87     23.62     0.0      1        0

regression/scripts/scramjet_network/scramjet_network.py

@@ -0,0 +1,244 @@
+# scramjet_network.py
+# 
+# Created:  April 2018, W. Maier
+# Modified: 
+#        
+
+""" create and evaluate a sramjet network
+"""
+
+# ----------------------------------------------------------------------
+#   Imports
+# ----------------------------------------------------------------------
+
+import SUAVE
+from SUAVE.Core import Units, Data
+
+import numpy as np
+
+from SUAVE.Components.Energy.Networks.Scramjet import Scramjet
+from SUAVE.Methods.Propulsion.scramjet_sizing import scramjet_sizing
+
+# ----------------------------------------------------------------------
+#   Main
+# ----------------------------------------------------------------------
+def main():
+
+    # call the network function
+    energy_network()    
+
+    return
+
+# ----------------------------------------------------------------------
+#   Energy Network
+# ----------------------------------------------------------------------
+def energy_network():
+
+    # ------------------------------------------------------------------
+    #   Evaluation Conditions
+    # ------------------------------------------------------------------    
+
+    # --- Conditions        
+    ones_1col = np.ones([1,1])    
+
+    # setup conditions
+    conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
+
+    # freestream conditions
+    eval                             = conditions.freestream
+    eval.mach_number                 = ones_1col*4.5
+    conditions.M                     = eval.mach_number
+    eval.altitude                    = ones_1col*20000.
+
+    atmosphere                       = SUAVE.Analyses.Atmospheric.US_Standard_1976()
+    atmo_data                        = atmosphere.compute_values(eval.altitude,0,True) 
+    working_fluid                    = SUAVE.Attributes.Gases.Air()
+
+    eval.pressure                    = ones_1col*atmo_data.pressure
+    eval.temperature                 = ones_1col*atmo_data.temperature
+    eval.density                     = ones_1col*atmo_data.density
+    eval.dynamic_viscosity           = ones_1col* atmo_data.dynamic_viscosity
+    eval.gravity                     = ones_1col* SUAVE.Attributes.Planets.Earth().sea_level_gravity
+    eval.isentropic_expansion_factor = working_fluid.compute_gamma(eval.temperature,eval.pressure)
+    eval.Cp                          = working_fluid.compute_cp(eval.temperature,eval.pressure)                                                                               
+    eval.R                           = working_fluid.gas_specific_constant
+    eval.speed_of_sound              = ones_1col* atmo_data.speed_of_sound
+    eval.velocity                    = conditions.M * eval.speed_of_sound
+    conditions.velocity              = conditions.M * eval.speed_of_sound
+    conditions.q                     = 0.5*eval.density*conditions.velocity**2
+    conditions.g0                    = eval.gravity
+
+    # propulsion conditions
+    conditions.propulsion.throttle   =  ones_1col*1.0
+
+    # ------------------------------------------------------------------
+    #   Design/sizing conditions
+    # ------------------------------------------------------------------    
+
+    # --- Conditions        
+    ones_1col = np.ones([1,1])    
+
+    # setup conditions
+    conditions_sizing = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
+
+    # freestream conditions
+    size                             = conditions_sizing.freestream
+    size.mach_number                 = ones_1col*6.5
+    conditions_sizing.M              = size.mach_number
+    size.altitude                    = ones_1col*20000.  
+
+    atmosphere                       = SUAVE.Analyses.Atmospheric.US_Standard_1976()
+    atmo_data                        = atmosphere.compute_values(size.altitude,0,True) 
+    working_fluid                    = SUAVE.Attributes.Gases.Air()    
+
+    size.pressure                    = ones_1col*atmo_data.pressure
+    size.temperature                 = ones_1col*atmo_data.temperature
+    size.density                     = ones_1col*atmo_data.density
+    size.dynamic_viscosity           = ones_1col*atmo_data.dynamic_viscosity
+    size.gravity                     = ones_1col*SUAVE.Attributes.Planets.Earth().sea_level_gravity
+    size.isentropic_expansion_factor = working_fluid.compute_gamma(size.temperature,size.pressure)
+    size.Cp                          = working_fluid.compute_cp(size.temperature,size.pressure)                                                                               
+    size.R                           = working_fluid.gas_specific_constant
+    size.speed_of_sound              = ones_1col * atmo_data.speed_of_sound
+    size.velocity                    = conditions_sizing.M * size.speed_of_sound
+    conditions_sizing.velocity       = conditions_sizing.M * size.speed_of_sound
+    conditions_sizing.q              = 0.5*size.density*conditions_sizing.velocity**2
+    conditions_sizing.g0             = size.gravity
+
+    # propulsion conditions
+    conditions_sizing.propulsion.throttle = ones_1col*1.0
+
+    state_sizing = Data()
+    state_sizing.numerics = Data()
+    state_sizing.conditions = conditions_sizing
+    state_off_design=Data()
+    state_off_design.numerics=Data()
+    state_off_design.conditions=conditions
+
+    # ------------------------------------------------------------------
+    #  Ramjet Network
+    # ------------------------------------------------------------------    
+
+    # instantiate the ramjet network
+    scramjet = SUAVE.Components.Energy.Networks.Scramjet()
+    scramjet.tag = 'scramjet'
+
+    # setup
+    scramjet.number_of_engines = 1.0
+    scramjet.engine_length     = 4.0
+    scramjet.nacelle_diameter  = 0.3  * Units.meter
+    scramjet.inlet_diameter    = 0.21 * Units.meter
+
+    # working fluid
+    scramjet.working_fluid = SUAVE.Attributes.Gases.Air()
+
+    # ------------------------------------------------------------------
+    #   Component 1 - Ram
+    #   to convert freestream static to stagnation quantities
+
+    # instantiate
+    ram = SUAVE.Components.Energy.Converters.Ram()
+    ram.tag = 'ram'
+
+    # add to the network
+    scramjet.append(ram)
+
+    # ------------------------------------------------------------------
+    #  Component 2 - Inlet Nozzle
+
+    # instantiate
+    inlet_nozzle = SUAVE.Components.Energy.Converters.Compression_Nozzle()
+    inlet_nozzle.tag = 'inlet_nozzle'
+
+    # setup
+    inlet_nozzle.polytropic_efficiency      = 0.90
+    inlet_nozzle.pressure_ratio             = 1.0
+    inlet_nozzle.compressibility_effects    = 3.0
+    inlet_nozzle.compression_levels         = 3.0
+    inlet_nozzle.theta                      = [0.10472,0.122173,0.226893]
+
+    # add to network
+    scramjet.append(inlet_nozzle)
+
+    # ------------------------------------------------------------------
+    #  Component 3 - Combustor
+
+    # instantiate    
+    combustor = SUAVE.Components.Energy.Converters.Combustor()   
+    combustor.tag = 'combustor'
+
+    # setup
+    combustor.efficiency                = 0.90 
+    combustor.pressure_ratio            = 1.0
+    combustor.area_ratio                = 2.0
+    combustor.fuel_data                 = SUAVE.Attributes.Propellants.Liquid_H2()  
+    combustor.burner_drag_coefficient   = 0.01
+    combustor.fuel_equivalency_ratio    = 1.0
+
+    # add to network
+    scramjet.append(combustor)
+
+    # ------------------------------------------------------------------
+    #  Component 4 - Core Nozzle
+
+    # instantiate
+    nozzle = SUAVE.Components.Energy.Converters.Supersonic_Nozzle()   
+    nozzle.tag = 'core_nozzle'
+
+    # setup
+    nozzle.polytropic_efficiency    = 0.9
+    nozzle.pressure_expansion_ratio = 1.1
+
+    # add to network
+    scramjet.append(nozzle)
+
+    # ------------------------------------------------------------------
+    #  Component 5 - Thrust
+
+    # instantiate
+    thrust = SUAVE.Components.Energy.Processes.Thrust()       
+    thrust.tag ='thrust'
+
+    # setup
+    thrust.total_design = scramjet.number_of_engines*180000.0 * Units.N
+
+    # add to network
+    scramjet.thrust = thrust    
+
+    #size the ramjet
+    scramjet_sizing(scramjet,size.mach_number,size.altitude)
+
+    print "Design thrust :",scramjet.design_thrust
+    print "Sealevel static thrust :",scramjet.sealevel_static_thrust
+
+    results_design     = scramjet(state_sizing)
+    results_off_design = scramjet(state_off_design)
+    F                  = results_design.thrust_force_vector
+    mdot               = results_design.vehicle_mass_rate
+    Isp                = results_design.specific_impulse   
+    F_off_design       = results_off_design.thrust_force_vector
+    mdot_off_design    = results_off_design.vehicle_mass_rate
+    Isp_off_design     = results_off_design.specific_impulse
+
+    #Specify the expected values
+    expected        = Data()
+    expected.thrust = 180000.0
+    expected.mdot   = 7.8394948
+    expected.Isp    = 2341.33605553
+
+    #error data function
+    error =  Data()
+
+    error.thrust_error = (F[0][0] -  expected.thrust)/expected.thrust
+    error.mdot_error   = (mdot[0][0] - expected.mdot)/expected.mdot
+    error.Isp_error    = (Isp[0][0]- expected.Isp)/expected.Isp
+    print error
+
+    for k,v in error.items():
+        assert(np.abs(v)<1e-6)    
+
+    return
+
+if __name__ == '__main__':
+
+    main() 

trunk/SUAVE/Attributes/Propellants/JP7.py

@@ -0,0 +1,55 @@
+## @ingroup Attributes-Propellants
+# JP7
+#
+# Created:  April 2018, W. Maier
+# Modified:
+
+# ----------------------------------------------------------------------
+#  Imports
+# ----------------------------------------------------------------------
+from Propellant import Propellant
+
+# ----------------------------------------------------------------------
+#  JP7 Propellant Class
+# ----------------------------------------------------------------------
+## @ingroup Attributes-Propellants
+class JP7(Propellant):
+    """Holds values for this propellant
+
+    Assumptions:
+    None
+
+    Source:
+    None
+    """
+
+    def __defaults__(self):
+        """This sets the default values.
+
+        Assumptions:
+        None
+
+        Source:
+        Values commonly available
+        http://arc.uta.edu/publications/td_files/Kristen%20Roberts%20MS.pdf
+
+        Inputs:
+        None
+
+        Outputs:
+        None
+
+        Properties Used:
+        None
+        """    
+        self.tag                        = 'JP7'
+        self.reactant                   = 'O2'
+        self.density                    = 803.0                          # kg/m^3 (15 C, 1 atm)
+        self.specific_energy            = 43.50e6                        # J/kg
+        self.energy_density             = 34930.5e6                      # J/m^3
+        self.stoichiometric_fuel_to_air = 0.0674            
+
+        # critical temperatures
+        self.temperatures.flash        = 333.15                 # K
+        self.temperatures.autoignition = 555.15                 # K
+        self.temperatures.freeze       = 514.15                 # K

trunk/SUAVE/Attributes/Propellants/Liquid_H2.py

@@ -0,0 +1,54 @@
+## @ingroup Attributes-Propellants
+# Liquid H2
+#
+# Created:  Unk 2013, SUAVE TEAM 
+# Modified: Apr 2015, SUAVE TEAM 
+#           Feb 2016, M. Vegh 
+#           Jan 2018, W. Maier 
+
+# ----------------------------------------------------------------------
+#  Imports
+# ----------------------------------------------------------------------
+from Propellant import Propellant
+
+# ----------------------------------------------------------------------
+#  Liquid H2 Propellant Class
+# ----------------------------------------------------------------------
+## @ingroup Attributes-Propellants
+class Liquid_H2(Propellant):
+    """Holds values for this propellant
+
+    Assumptions:
+    None
+
+    Source:
+    None
+    """
+
+    def __defaults__(self):
+        """This sets the default values.
+
+        Assumptions:
+        None
+
+        Source:
+        Values commonly available
+        http://arc.uta.edu/publications/td_files/Kristen%20Roberts%20MS.pdf
+
+        Inputs:
+        None
+
+        Outputs:
+        None
+
+        Properties Used:
+        None
+        """ 
+
+        self.tag                        = 'Liquid_H2' 
+        self.reactant                   = 'O2' 
+        self.density                    = 59.9                             # [kg/m^3] 
+        self.specific_energy            = 141.86e6                         # [J/kg] 
+        self.energy_density             = 8491.0e6                         # [J/m^3] 
+        self.stoichiometric_fuel_to_air = 0.0291 
+        self.temperatures.autoignition  = 845.15                           # [K]         

trunk/SUAVE/Attributes/Propellants/__init__.py

@@ -8,4 +8,5 @@
 from Jet_A import Jet_A
 from Jet_A1 import Jet_A1
 from Liquid_Natural_Gas import Liquid_Natural_Gas
-
+from JP7 import JP7
+from Liquid_H2 import Liquid_H2