Exit limit as an input

example/cryo_input.toml

@@ -85,15 +85,19 @@ name = "TASOPT Model with cryo fuel and HX"
 [Mission]
     N_missions = 1 # Number of missions to be modeled (first mission is the design mission)
     pax = 180            # Number of passengers in each mission
-    max_pax = 189               # Maximum number of passengers for aircarft
-                                # defines the maximum payload carrying capacity of the aircraft
 
     range = "3000.0 nmi" # Design Range 
 
     weight_per_pax = "215.0 lbf" # Specify weight per passenger - 
                             # includes luggage [lbm or lbf or kg or N] 
                             # judging you if you use imperial units but wtvs
 
+    exit_limit = 189            # Maximum number of passengers that can sit in the cabin
+
+    max_pax = 230               # Defines the maximum payload carrying capacity of the aircraft
+                                # It is the maximum payload that the aircraft can carry (including cargo),
+                                # as an equivalent number of passengers
+
     fuel_reserves = 0.20 # W_reserveFuel / W_fuelburned
 
     Nlift = 3.0 # Max vertical load factor for wing bending loads

example/example_regional.toml

@@ -52,15 +52,19 @@
 [Mission]
     N_missions = 1 # Number of missions to be modeled (first mission is the design mission)
     pax = 118       # Number of passengers in each mission
-    max_pax = 122               # Maximum number of passengers for aircarft 
-                                # defines the maximum payload carrying capacity of the aircraft
-
+
     range = "2200.0 nmi"
     # Design Range + second mission range           
     weight_per_pax = "215.0 lbf" # Specify weight per passenger - 
                             # includes luggage [lbm or lbf or kg or N] 
                             # judging you if you use imperial units but wtvs
 
+    exit_limit = 122            # Maximum number of passengers that can sit in the cabin
+
+    max_pax = 122               # Defines the maximum payload carrying capacity of the aircraft
+                                # It is the maximum payload that the aircraft can carry (including cargo),
+                                # as an equivalent number of passengers
+
     fuel_reserves = 0.05 # W_reserveFuel / W_fuelburned
 
     Nlift = 3.0 # Max vertical load factor for wing bending loads

example/example_widebody.toml

@@ -54,15 +54,19 @@
 [Mission]
     N_missions = 1 # Number of missions to be modeled (first mission is the design mission)
     pax = 370            # Number of passengers in each mission
-    max_pax = 450               # Maximum number of passengers for aircarft
-                                # defines the maximum payload carrying capacity of the aircraft
 
     range = "7800.0 nmi" # Design Range 
 
     weight_per_pax = "230.0 lbf" # Specify weight per passenger - 
                             # includes luggage [lbm or lbf or kg or N] 
                             # judging you if you use imperial units but wtvs
 
+    exit_limit = 450            # Maximum number of passengers that can sit in the cabin
+
+    max_pax = 450               # Defines the maximum payload carrying capacity of the aircraft
+                                # It is the maximum payload that the aircraft can carry (including cargo),
+                                # as an equivalent number of passengers
+
     fuel_reserves = 0.07 # W_reserveFuel / W_fuelburned
 
     Nlift = 3.0 # Max vertical load factor for wing bending loads

src/IO/default_input.toml

@@ -89,8 +89,6 @@
 
 [Mission]
     N_missions = 2 # Number of missions to be modeled (first mission is the design mission)
-    max_pax = 230               # Maximum number of passengers for aircarft
-                                # defines the maximum payload carrying capacity of the aircraft
 
     range = ["3000.0 nmi", "2000.0 nmi"] # Design Range + second mission range
 
@@ -101,6 +99,12 @@
                                     # includes luggage [lbm or lbf or kg or N] 
                                     # judging you if you use imperial units but wtvs
 
+    exit_limit = 189            # Maximum number of passengers that can sit in the cabin
+
+    max_pax = 230               # Defines the maximum payload carrying capacity of the aircraft
+                                # It is the maximum payload that the aircraft can carry (including cargo),
+                                # as an equivalent number of passengers
+
     fuel_reserves = 0.20 # W_reserveFuel / W_fuelburned
 
     Nlift = 3.0 # Max vertical load factor for wing bending loads

src/IO/read_input.jl

@@ -169,6 +169,7 @@ Wpax =  Force(readmis("weight_per_pax"))
 parm[imWperpax, :] .= Wpax
 parm[imWpay, :] .= pax * Wpax
 parg[igWpaymax] = maxpax * Wpax
+parg[igexitlimit] = readmis("exit_limit")
 parg[igfreserve] = readmis("fuel_reserves")
 parg[igVne] = Speed(readmis("Vne"))
 parg[igNlift] = readmis("Nlift")
@@ -623,7 +624,7 @@ readvtail(x) = read_input(x, vtail, dvtail)
 if calculate_cabin #Resize the cabin if desired, keeping deltas
     @info "Fuselage and stabilizer layouts have been overwritten; deltas will be maintained."
 
-    update_fuse_for_pax!(pari, parg, parm, fuse_tank) #update fuselage dimensions
+    update_fuse_for_pax!(pari, parg, fuse_tank) #update fuselage dimensions
 end
 # ---------------------------------
 

src/misc/index.inc

@@ -389,7 +389,9 @@
 
       const igWfvent = 310
 
-      const igtotal    = 310
+      const igexitlimit = 311
+
+      const igtotal    = 311
 
 # indices for turbo-electric systems - really just the electrical machines
       const ite_ratSM   = 1

src/structures/update_fuse.jl

@@ -52,7 +52,7 @@ function update_fuse!(pari, parg)
 end
 
 """
-    update_fuse_for_pax!(pari, parg, parm, fuse_tank)
+    update_fuse_for_pax!(pari, parg, fuse_tank)
 
 Function to update the fuselage layout when the cabin length is not known a priori, for example if the radius is changed. 
 It sizes the cabin for the design number of passengers.
@@ -61,23 +61,22 @@ It sizes the cabin for the design number of passengers.
     **Inputs:**
     - `pari::Vector{Int64}`: vector with aircraft integer parameters
     - `parg::Vector{Float64}`: vector with aircraft geometric and mass parameters
-    - `parm::Array{Float64}`: array with mission parameters
     - `fuse_tank::struct`: structure of type `fuselage_tank` with cryogenic fuel tank parameters
 
     **Outputs:**
     No direct outputs; parameters in `parg` are modified.
 """
-function update_fuse_for_pax!(pari, parg, parm, fuse_tank)
+function update_fuse_for_pax!(pari, parg, fuse_tank)
 
     seat_pitch = parg[igseatpitch]
     seat_width = parg[igseatwidth]
     aisle_halfwidth = parg[igaislehalfwidth]
 
     if pari[iidoubledeck] == 1 #if the aircraft is a double decker
         #passenger count to size cabin is half of the maximum
-        paxsize = ceil(parg[igWpaymax]/parm[imWperpax,1] / 2) 
+        paxsize = ceil(parg[igexitlimit] / 2) 
     else
-        paxsize = parg[igWpaymax]/parm[imWperpax,1] #maximum number of passengers
+        paxsize = parg[igexitlimit] #maximum number of passengers from exit limit
     end
     #TODO this double deck model assumes that both decks have a width equal to the fuselage diameter; 
     #in reality, at least one deck must be narrower

test/default_sized.jl

@@ -336,6 +336,7 @@ parg[306] = 0.76200000000000001066 #
 parg[307] = 0.48259999999999997344 # 
 parg[308] = 0.25400000000000000355 # 
 parg[309] = 0.00000000000000000000 # 
+parg[310] = 189.000000000000000000 # 
 # --------------------------------
 # Mission  - stored in parm array:
 # --------------------------------

test/regional_sized.jl

@@ -336,6 +336,7 @@ parg[306] = 0.76200000000000001066 #
 parg[307] = 0.48259999999999997344 # 
 parg[308] = 0.25400000000000000355 # 
 parg[309] = 0.00000000000000000000 # 
+parg[310] = 122.000000000000000000 # 
 # --------------------------------
 # Mission  - stored in parm array:
 # --------------------------------

test/unit_test_structures.jl

@@ -1,4 +1,3 @@
-
 @testset "structural components" begin
 
 # Fuselage weight

test/wide_sized.jl

@@ -336,6 +336,7 @@ parg[306] = 0.76200000000000001066 #
 parg[307] = 0.48259999999999997344 # 
 parg[308] = 0.25400000000000000355 # 
 parg[309] = 0.00000000000000000000 # 
+parg[310] = 450.000000000000000000 # 
 # --------------------------------
 # Mission  - stored in parm array:
 # --------------------------------