added hold times to inputs for tank

example/cryo_input.toml

@@ -56,19 +56,21 @@ name = "TASOPT Model with cryo fuel and HX"
     fuselage_clearance = "0.3 ft"
     additional_mass_fraction = 0.25
     weld_efficiency = 0.9 
-    ullage_fraction = 0.1 #minimum ullage fraction at tank venting pressure
+    ullage_fraction = 0.05 #minimum ullage fraction at tank venting pressure
     heat_leak_factor = 1.3 #Factor to account for heat leakage through structural elements, piping, etc (qfac > 1)
     SL_temperature_for_tank = "288.2 K"
 
     #Tank pressure design parameters
     pressure_rise_factor = 2.0 #Factor to account for stratification in homogenous tank model (pfac >= 1)
     pressure_venting = "2 atm"
     pressure_initial = "1.2 atm"
+    hold_departure = "0 h"
+    hold_arrival = "0 h"
 
     inner_vessel_material = "Al-2219-T87"
     inner_vessel_support_angle = "80 deg"
 
-    #Insulation options: "rohacell41S", "polyurethane27", "polyurethane32", "polyurethane35", "vacuum", "mylar"
+    #Insulation options: "rohacell41S", "polyurethane27", "polyurethane32", "polyurethane35", "vacuum", "mylar", "microspheres"
     size_insulation = true #Flag to decide whether to size insulation for boiloff
     insulation_material = ["polyurethane32", "polyurethane32", "polyurethane32"] 
     insulation_segment_base_thickness = [0.05, 0.05, 0.05] #m

src/IO/default_input.toml

@@ -55,21 +55,27 @@
     fuel_density = 817.0 #kg/m3
 
 [Fuel.Storage] #Default fuselage fuel storage parameters for cryogenic fuels
-    tank_placement = "front" #Location of tank in fuselage. Choices are "front", "rear", or "both".
+    tank_placement = "rear" #Location of tank in fuselage. Choices are "front", "rear", or "both".
 
     tank_aspect_ratio = 2.0
     fuselage_clearance = "0.3 ft"
-    tank_pressure = "2 atm"
-    additional_mass_fraction = 0.1
+    additional_mass_fraction = 0.25
     weld_efficiency = 0.9 
-    ullage_fraction = 0.1 
+    ullage_fraction = 0.05 #minimum ullage fraction at tank venting pressure
     heat_leak_factor = 1.3 #Factor to account for heat leakage through structural elements, piping, etc (qfac > 1)
     SL_temperature_for_tank = "288.2 K"
 
+    #Tank pressure design parameters
+    pressure_rise_factor = 2.0 #Factor to account for stratification in homogenous tank model (pfac >= 1)
+    pressure_venting = "2 atm"
+    pressure_initial = "1.2 atm"
+    hold_departure = "0 h"
+    hold_arrival = "0 h"
+
     inner_vessel_material = "Al-2219-T87"
     inner_vessel_support_angle = "80 deg"
 
-    #Insulation options: "rohacell41S", "polyurethane27", "polyurethane32", "polyurethane35", "vacuum"
+    #Insulation options: "rohacell41S", "polyurethane27", "polyurethane32", "polyurethane35", "vacuum", "mylar", "microspheres"
     size_insulation = true #Flag to decide whether to size insulation for boiloff
     insulation_material = ["polyurethane32", "polyurethane32", "polyurethane32"] 
     insulation_segment_base_thickness = [0.05, 0.05, 0.05] #m

src/IO/read_input.jl

@@ -37,6 +37,7 @@ Density(x)  = convertDensity(parse_unit(x)...)
 Area(x)     = convertArea(parse_unit(x)...)
 Vol(x)      = convertVolume(parse_unit(x)...)
 Angle(x)    = convertAngle(parse_unit(x)...)
+Time(x)     = convertTime(parse_unit(x)...)
 Temp(x)     = convertTemp(parse_unit(x)...)
 
 """
@@ -364,6 +365,8 @@ if pari[iifwing]  == 0 #If fuel is stored in fuselage
 
     fuse_tank.pvent = Pressure(readfuel_storage("pressure_venting"))
     fuse_tank.pinitial = Pressure(readfuel_storage("pressure_initial"))
+    fuse_tank.t_hold_orig = Time(readfuel_storage("hold_departure"))
+    fuse_tank.t_hold_dest = Time(readfuel_storage("hold_arrival"))
 
     fuse_tank.ftankadd = readfuel_storage("additional_mass_fraction")
     fuse_tank.ew = readfuel_storage("weld_efficiency")

src/IO/save_model.jl

@@ -621,14 +621,14 @@ function savemodel(fname, pari, parg, parm, para, pare, parpt, parmot, pargen)
         @printf(io, "# Geometry - stored in parg array:\n")
         @printf(io, "# --------------------------------\n")
         for (i,val) in enumerate(parg)
-            @printf(io, "parg[%d] = %20f # %s\n", i, val, i<291 ? iglabels[i] : "" )
+            @printf(io, "parg[%d] = %20.20f # %s\n", i, val, i<291 ? iglabels[i] : "" )
         end
 
         @printf(io, "# --------------------------------\n")
         @printf(io, "# Mission  - stored in parm array:\n")
         @printf(io, "# --------------------------------\n")
         for (i,val) in enumerate(parm)
-            @printf(io, "parm[%d] = %20f \n", i, val)
+            @printf(io, "parm[%d] = %20.20f \n", i, val)
         end
 
         @printf(io, "# --------------------------------\n")
@@ -639,7 +639,7 @@ function savemodel(fname, pari, parg, parm, para, pare, parpt, parmot, pargen)
         for i = 1:l
             @printf(io, "para[%d, :] .= [", i)
             for j = 1:m
-                @printf(io, "%f, ", para[i, j])
+                @printf(io, "%20.20f, ", para[i, j])
             end
             @printf(io, "]\n")
         end
@@ -651,7 +651,7 @@ function savemodel(fname, pari, parg, parm, para, pare, parpt, parmot, pargen)
         for i = 1:l
             @printf(io, "pare[%d, :] .= [", i)
             for j = 1:m
-                @printf(io, "%20f, ", pare[i, j])
+                @printf(io, "%20.20f, ", pare[i, j])
             end
             @printf(io, "]\n")
         end
@@ -660,20 +660,20 @@ function savemodel(fname, pari, parg, parm, para, pare, parpt, parmot, pargen)
         @printf(io, "# Powertrain-stored in parpt array:\n")
         @printf(io, "# ---------------------------------\n")
         for (i,val) in enumerate(parpt)
-            @printf(io, "parpt[%d] = %20f \n", i, val)
+            @printf(io, "parpt[%d] = %20.20f \n", i, val)
         end
 
         @printf(io, "# ---------------------------------\n")
         @printf(io, "# Motor   - stored in parmot array:\n")
         @printf(io, "# ---------------------------------\n")
         for (i,val) in enumerate(parmot)
-            @printf(io, "parmot[%d] = %20f \n", i, val)
+            @printf(io, "parmot[%d] = %20.20f \n", i, val)
         end
         @printf(io, "# ---------------------------------\n")
         @printf(io, "# Generator-stored in pargen array:\n")
         @printf(io, "# ---------------------------------\n")
         for (i,val) in enumerate(pargen)
-            @printf(io, "pargen[%d] = %20f \n", i, val)
+            @printf(io, "pargen[%d] = %20.20f \n", i, val)
         end
     end
 

src/misc/aircraft.jl

@@ -27,6 +27,10 @@ mutable struct fuselage_tank
 
     pvent::Float64
     pinitial::Float64
+    t_hold_orig::Float64
+    t_hold_dest::Float64
+    TSLtank::Float64
+
     rhofuel::Float64
     Tfuel::Float64
     rhofuelgas::Float64
@@ -38,7 +42,7 @@ mutable struct fuselage_tank
     ullage_frac::Float64
     qfac::Float64
     pfac::Float64
-    TSLtank::Float64
+
     fuselage_tank() = new("", "", false, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, [], [], [], StructuralAlloy("Al-2219-T87"), StructuralAlloy("Al-2219-T87"), 0.0, 0.0, [], 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0) 
 end
 

src/sizing/wsize.jl

@@ -1281,7 +1281,7 @@ function wsize(ac; itermax=35,
             para[iaPAfinf, :] .= PAfinf
 
             #Use homogeneous tank model to calculate required venting
-            _, _, _, _, _, _, _, Mvents, _, _ = CryoTank.analyze_TASOPT_tank(ac)
+            _, _, _, _, _, _, _, Mvents, _, _ = CryoTank.analyze_TASOPT_tank(ac, fuse_tank.t_hold_orig, fuse_tank.t_hold_dest)
             parg[igWfvent] = Mvents[end] * gee #Store total fuel weight that is vented
         end