Useful load update

aviary/docs/theory_guide/gasp_based_bwb.ipynb

@@ -123,16 +123,16 @@
     "# Testing Cell\n",
     "\n",
     "from aviary.api import Aircraft\n",
-    "from aviary.subsystems.mass.gasp_based.equipment_and_useful_load import (\n",
+    "from aviary.subsystems.mass.gasp_based.equipment_and_operating_items import (\n",
     "    BWBACMass,\n",
     "    BWBFurnishingMass,\n",
-    "    EquipAndUsefulLoadMassGroup,\n",
-    "    UsefulLoadMassGroup,\n",
+    "    EquipAndOperatingItemsMassGroup,\n",
+    "    OperatingItemsMassGroup,\n",
     ")\n",
     "from aviary.utils.doctape import get_variable_name, glue_variable\n",
     "\n",
-    "glue_variable(get_variable_name(EquipAndUsefulLoadMassGroup), md_code=True)\n",
-    "glue_variable(get_variable_name(UsefulLoadMassGroup), md_code=True)\n",
+    "glue_variable(get_variable_name(EquipAndOperatingItemsMassGroup), md_code=True)\n",
+    "glue_variable(get_variable_name(OperatingItemsMassGroup), md_code=True)\n",
     "glue_variable(get_variable_name(BWBACMass), md_code=True)\n",
     "glue_variable(get_variable_name(BWBFurnishingMass), md_code=True)\n",
     "\n",
@@ -150,11 +150,11 @@
    "id": "8d5ec109",
    "metadata": {},
    "source": [
-    "### Equip And Useful Load\n",
+    "### Equip And Operating Items\n",
     "\n",
-    "  - {glue:md}`EquipAndUsefulLoadMassGroup` includes the computations of 19 items. Ideally, each of them should be done in its own component and one group has them all. This is a long time goal. For now, it is separated to two components `EquipMass` and {glue:md}`UsefulLoadMassGroup`. The air conditioning and furnishing masses are already singled out because they need to be modified for BWB.\n",
+    "  - {glue:md}`EquipAndOperatingItemsMassGroup` includes the computations of 19 items. Ideally, each of them should be done in its own component and one group has them all. This is a long time goal. For now, it is separated to two components `EquipMass` and {glue:md}`OperatingItemsMassGroup`. The air conditioning and furnishing masses are already singled out because they need to be modified for BWB.\n",
     "  - A new variable {glue:md}`Aircraft.Electrical.SYSTEM_MASS_PER_PASSENGER` is added which corresponds to `CW(15)` in GASP. Its value is different for conventional aircraft and BWB.\n",
-    "  - Two new components {glue:md}`BWBACMass` and {glue:md}`BWBFurnishingMass` are added to `equipment_and_useful_load.py`.\n",
+    "  - Two new components {glue:md}`BWBACMass` and {glue:md}`BWBFurnishingMass` are added to `equipment_and_operating_items.py`.\n",
     "  - **Note:** GASP Fortran code has new updates that are not included in Aviary. We've updated Aviary for furnishing mass but other masses need to be checked.\n",
     "  - **Note:** `EquipMassPartialSum` has implementation errors for the computations of {glue:md}`Aircraft.APU.MASS`, {glue:md}`Aircraft.Avionics.MASS`, {glue:md}`Aircraft.AntiIcing.MASS`, {glue:md}`Aircraft.Furnishings.MASS`, and {glue:md}`Aircraft.Design.EMERGENCY_EQUIPMENT_MASS`. As a result, Aviary always uses user provided masses (not empirical formulas). We should use Aviary's feature of `overriding` to override those variables."
    ]
@@ -249,7 +249,7 @@
     "\n",
     "glue_variable(get_variable_name(Mission.TOTAL_FUEL), md_code=True)\n",
     "\n",
-    "glue_variable(get_variable_name(Mission.USEFUL_LOAD), md_code=True)\n",
+    "glue_variable(get_variable_name(Mission.OPERATING_ITEMS_MASS), md_code=True)\n",
     "glue_variable(get_variable_name(Aircraft.Wing.HIGH_LIFT_MASS), md_code=True)\n",
     "glue_variable(get_variable_name(Aircraft.Fuel.FUEL_SYSTEM_MASS), md_code=True)\n",
     "glue_variable(get_variable_name(Aircraft.Design.STRUCTURE_MASS), md_code=True)\n",
@@ -275,7 +275,7 @@
     "\n",
     "| Aviary |     | GASP |     | Observation |\n",
     "| ------- | ------- | ------- | -------- | ------------- |\n",
-    "| {glue:md}`Mission.USEFUL_LOAD` | 5972 | WFUL | 5775 | different unit weight of pilots and attendents |\n",
+    "| {glue:md}`Mission.OPERATING_ITEMS_MASS` | 5972 | WFUL | 5775 | different unit weight of pilots and attendents |\n",
     "| {glue:md}`Aircraft.Wing.HIGH_LIFT_MASS` | 972 | WHLDEV | 974 | In GASP, wing loading is a variable, but in Aviary, it is a constant |\n",
     "| {glue:md}`Aircraft.Fuel.FUEL_SYSTEM_MASS` | 1316 | WFSS | 1281 | the mass in GASP is computed after engine sizing. |\n",
     "| {glue:md}`Aircraft.Design.STRUCTURE_MASS` | 44471 | WST | 45623 | the mass in GASP is computed after engine sizing. |\n",

aviary/docs/user_guide_unreviewed/subsystems/fuel.ipynb

@@ -16,7 +16,7 @@
     "\n",
     "\n",
     "## Fuel Mass\n",
-    "The Fuel Mass breakdown is shown below. Note that UNUSABLE_FUEL_MASS is not accounted for in this mass and is instead book kept under USEFUL_LOAD which contributes to OPERATING_MASS see [mass subsystem for details](mass.ipynb).\n",
+    "The Fuel Mass breakdown is shown below. Note that UNUSABLE_FUEL_MASS is not accounted for in this mass and is instead book kept under OPERATING_ITEMS_MASS which contributes to OPERATING_MASS see [mass subsystem for details](mass.ipynb).\n",
     "\n",
     "- TOTAL_FUEL (mass)\n",
     "    - FUEL (mass)\n",

aviary/docs/user_guide_unreviewed/subsystems/mass.ipynb

@@ -25,7 +25,9 @@
     "    ZeroFuelMass,\n",
     ")\n",
     "from aviary.subsystems.mass.gasp_based.design_load import DesignLoadGroup\n",
-    "from aviary.subsystems.mass.gasp_based.equipment_and_useful_load import EquipAndUsefulLoadMassGroup\n",
+    "from aviary.subsystems.mass.gasp_based.equipment_and_operating_items import (\n",
+    "    EquipAndOperatingItemsMassGroup,\n",
+    ")\n",
     "from aviary.subsystems.mass.gasp_based.fixed import FixedMassGroup\n",
     "from aviary.subsystems.mass.gasp_based.wing import WingMassGroup\n",
     "from aviary.utils.doctape import get_variable_name, glue_variable\n",
@@ -74,9 +76,9 @@
     "st = split_by_capitals_and_underscores(get_variable_name(FixedMassGroup))\n",
     "glue_variable(st, md_code=False)\n",
     "glue_variable(get_variable_name(FixedMassGroup), md_code=False)\n",
-    "st = split_by_capitals_and_underscores(get_variable_name(EquipAndUsefulLoadMassGroup))\n",
+    "st = split_by_capitals_and_underscores(get_variable_name(EquipAndOperatingItemsMassGroup))\n",
     "glue_variable(st, md_code=False)\n",
-    "glue_variable(get_variable_name(EquipAndUsefulLoadMassGroup), md_code=False)\n",
+    "glue_variable(get_variable_name(EquipAndOperatingItemsMassGroup), md_code=False)\n",
     "st = split_by_capitals_and_underscores(get_variable_name(WingMassGroup))\n",
     "glue_variable(st, md_code=False)\n",
     "glue_variable(get_variable_name(WingMassGroup), md_code=False)"
@@ -136,7 +138,7 @@
     "\n",
     "### Operating Mass\n",
     "Empty Mass, plus:\n",
-    "- **Useful Load**\n",
+    "- **Operating Items**\n",
     "    - Flight Crew\n",
     "    - Cabin Crew\n",
     "    - Unusable Fuel\n",

aviary/subsystems/mass/flops_based/mass_summation.py

@@ -60,7 +60,10 @@ def setup(self):
         )
 
         self.add_subsystem(
-            'useful_load_mass', UsefulLoadMass(), promotes_inputs=['*'], promotes_outputs=['*']
+            'operating_items_mass',
+            OperatingItemsMass(),
+            promotes_inputs=['*'],
+            promotes_outputs=['*'],
         )
 
         self.add_subsystem(
@@ -71,6 +74,10 @@ def setup(self):
             'zero_fuel_mass', ZeroFuelMass(), promotes_inputs=['*'], promotes_outputs=['*']
         )
 
+        self.add_subsystem(
+            'useful_load_mass', UsefulLoadMass(), promotes_inputs=['*'], promotes_outputs=['*']
+        )
+
 
 class EmpennageMass(om.ExplicitComponent):
     def setup(self):
@@ -361,7 +368,7 @@ def compute(self, inputs, outputs):
         )
 
 
-class UsefulLoadMass(om.ExplicitComponent):
+class OperatingItemsMass(om.ExplicitComponent):
     def setup(self):
         add_aviary_input(self, Aircraft.CrewPayload.CARGO_CONTAINER_MASS, units='lbm')
         add_aviary_input(self, Aircraft.CrewPayload.CABIN_CREW_MASS, units='lbm')
@@ -370,10 +377,10 @@ def setup(self):
         add_aviary_input(self, Aircraft.Fuel.UNUSABLE_FUEL_MASS, units='lbm')
         add_aviary_input(self, Aircraft.Propulsion.TOTAL_ENGINE_OIL_MASS, units='lbm')
 
-        add_aviary_output(self, Mission.USEFUL_LOAD, units='lbm')
+        add_aviary_output(self, Mission.OPERATING_ITEMS_MASS, units='lbm')
 
     def setup_partials(self):
-        self.declare_partials(Mission.USEFUL_LOAD, '*', val=1)
+        self.declare_partials(Mission.OPERATING_ITEMS_MASS, '*', val=1)
 
     def compute(self, inputs, outputs):
         cargo_container_mass = inputs[Aircraft.CrewPayload.CARGO_CONTAINER_MASS]
@@ -383,7 +390,7 @@ def compute(self, inputs, outputs):
         pass_service_mass = inputs[Aircraft.CrewPayload.PASSENGER_SERVICE_MASS]
         unusable_fuel_mass = inputs[Aircraft.Fuel.UNUSABLE_FUEL_MASS]
 
-        outputs[Mission.USEFUL_LOAD] = (
+        outputs[Mission.OPERATING_ITEMS_MASS] = (
             cabin_crew_mass
             + flight_crew_mass
             + unusable_fuel_mass
@@ -396,18 +403,18 @@ def compute(self, inputs, outputs):
 class OperatingMass(om.ExplicitComponent):
     def setup(self):
         add_aviary_input(self, Aircraft.Design.EMPTY_MASS, units='lbm')
-        add_aviary_input(self, Mission.USEFUL_LOAD, units='lbm')
+        add_aviary_input(self, Mission.OPERATING_ITEMS_MASS, units='lbm')
 
         add_aviary_output(self, Mission.OPERATING_MASS, units='lbm')
 
     def setup_partials(self):
         self.declare_partials(Mission.OPERATING_MASS, '*', val=1)
 
     def compute(self, inputs, outputs):
-        useful_load = inputs[Mission.USEFUL_LOAD]
+        operating_items_mass = inputs[Mission.OPERATING_ITEMS_MASS]
         empty_mass = inputs[Aircraft.Design.EMPTY_MASS]
 
-        outputs[Mission.OPERATING_MASS] = empty_mass + useful_load
+        outputs[Mission.OPERATING_MASS] = empty_mass + operating_items_mass
 
 
 class ZeroFuelMass(om.ExplicitComponent):
@@ -429,3 +436,21 @@ def compute(self, inputs, outputs):
         operating_mass = inputs[Mission.OPERATING_MASS]
 
         outputs[Mission.ZERO_FUEL_MASS] = operating_mass + pass_mass + bag_mass + cargo_mass
+
+
+class UsefulLoadMass(om.ExplicitComponent):
+    def setup(self):
+        add_aviary_input(self, Aircraft.Design.GROSS_MASS, units='lbm')
+        add_aviary_input(self, Aircraft.Design.EMPTY_MASS, units='lbm')
+
+        add_aviary_output(self, Aircraft.Design.USEFUL_LOAD_MASS, units='lbm')
+
+    def setup_partials(self):
+        self.declare_partials(Aircraft.Design.USEFUL_LOAD_MASS, Aircraft.Design.GROSS_MASS, val=1)
+        self.declare_partials(Aircraft.Design.USEFUL_LOAD_MASS, Aircraft.Design.EMPTY_MASS, val=-1)
+
+    def compute(self, inputs, outputs):
+        gross_mass = inputs[Aircraft.Design.GROSS_MASS]
+        empty_mass = inputs[Aircraft.Design.EMPTY_MASS]
+
+        outputs[Aircraft.Design.USEFUL_LOAD_MASS] = gross_mass - empty_mass

aviary/subsystems/mass/flops_based/test/test_mass_summation.py

@@ -7,10 +7,7 @@
 from parameterized import parameterized
 
 from aviary.subsystems.mass.flops_based.mass_summation import (
-    EmptyMass,
     MassSummation,
-    OperatingMass,
-    PropulsionMass,
     StructureMass,
 )
 from aviary.subsystems.propulsion.engine_deck import EngineDeck
@@ -92,6 +89,7 @@ def test_case(
                 Aircraft.Wing.MASS,
                 Aircraft.Propulsion.TOTAL_ENGINE_MASS,
                 Aircraft.Propulsion.TOTAL_MISC_MASS,
+                Aircraft.Design.GROSS_MASS,
             ],
             output_keys=[
                 Aircraft.Design.EMPTY_MASS_MARGIN,
@@ -100,9 +98,10 @@ def test_case(
                 Aircraft.Design.SYSTEMS_AND_EQUIPMENT_MASS,
                 Aircraft.Design.EMPENNAGE_MASS,
                 Aircraft.Design.EMPTY_MASS,
-                Mission.USEFUL_LOAD,
+                Mission.OPERATING_ITEMS_MASS,
                 Mission.OPERATING_MASS,
                 Mission.ZERO_FUEL_MASS,
+                Aircraft.Design.USEFUL_LOAD_MASS,
             ],
             version=Version.TRANSPORT_and_BWB,
             atol=1e-10,
@@ -185,7 +184,7 @@ def test_case(self, case_name):
                 Aircraft.Design.SYSTEMS_AND_EQUIPMENT_MASS,
                 Aircraft.Design.EMPENNAGE_MASS,
                 Aircraft.Design.EMPTY_MASS,
-                Mission.USEFUL_LOAD,
+                Mission.OPERATING_ITEMS_MASS,
                 Mission.OPERATING_MASS,
                 Mission.ZERO_FUEL_MASS,
             ],

aviary/subsystems/mass/gasp_based/equipment_and_useful_load.py → aviary/subsystems/mass/gasp_based/equipment_and_operating_items.py

@@ -78,7 +78,7 @@ def setup(self):
         )
 
 
-class UsefulLoadMassGroup(om.Group):
+class OperatingItemsMassGroup(om.Group):
     def setup(self):
         self.add_subsystem(
             'cargo_containers',
@@ -182,7 +182,7 @@ def setup(self):
         )
 
 
-class EquipAndUsefulLoadMassGroup(om.Group):
+class EquipAndOperatingItemsMassGroup(om.Group):
     def initialize(self):
         add_aviary_option(self, Aircraft.Design.TYPE)
 
@@ -206,7 +206,7 @@ def setup(self):
 
         self.add_subsystem(
             'useful',
-            UsefulLoadMassGroup(),
+            OperatingItemsMassGroup(),
             promotes_inputs=['*'],
             promotes_outputs=['*'],
         )

aviary/subsystems/mass/gasp_based/mass_premission.py

@@ -1,7 +1,9 @@
 import openmdao.api as om
 
 from aviary.subsystems.mass.gasp_based.design_load import BWBDesignLoadGroup, DesignLoadGroup
-from aviary.subsystems.mass.gasp_based.equipment_and_useful_load import EquipAndUsefulLoadMassGroup
+from aviary.subsystems.mass.gasp_based.equipment_and_operating_items import (
+    EquipAndOperatingItemsMassGroup,
+)
 from aviary.subsystems.mass.gasp_based.fixed import FixedMassGroup
 from aviary.subsystems.mass.gasp_based.fuel import (
     BodyTankCalculations,
@@ -52,7 +54,7 @@ def setup(self):
 
         self.add_subsystem(
             'equip_and_useful_mass',
-            EquipAndUsefulLoadMassGroup(),
+            EquipAndOperatingItemsMassGroup(),
             promotes_inputs=['*'],
             promotes_outputs=['*'],
         )

aviary/subsystems/mass/gasp_based/mass_summation.py

@@ -36,7 +36,10 @@ def setup(self):
         )
 
         self.add_subsystem(
-            'useful_load_mass', UsefulLoadMass(), promotes_inputs=['*'], promotes_outputs=['*']
+            'operating_items_mass',
+            OperatingItemsMass(),
+            promotes_inputs=['*'],
+            promotes_outputs=['*'],
         )
 
         self.add_subsystem(
@@ -47,6 +50,10 @@ def setup(self):
             'zero_fuel_mass', ZeroFuelMass(), promotes_inputs=['*'], promotes_outputs=['*']
         )
 
+        self.add_subsystem(
+            'useful_load_mass', UsefulLoadMass(), promotes_inputs=['*'], promotes_outputs=['*']
+        )
+
 
 class EmpennageMass(om.ExplicitComponent):
     def setup(self):
@@ -190,7 +197,7 @@ def compute(self, inputs, outputs):
         )
 
 
-class UsefulLoadMass(om.ExplicitComponent):
+class OperatingItemsMass(om.ExplicitComponent):
     def setup(self):
         add_aviary_input(self, Aircraft.CrewPayload.CARGO_CONTAINER_MASS, units='lbm')
         add_aviary_input(self, Aircraft.CrewPayload.CABIN_CREW_MASS, units='lbm')
@@ -200,10 +207,10 @@ def setup(self):
         add_aviary_input(self, Aircraft.Propulsion.TOTAL_ENGINE_OIL_MASS, units='lbm')
         add_aviary_input(self, Aircraft.Design.EMERGENCY_EQUIPMENT_MASS)
 
-        add_aviary_output(self, Mission.USEFUL_LOAD, units='lbm')
+        add_aviary_output(self, Mission.OPERATING_ITEMS_MASS, units='lbm')
 
     def setup_partials(self):
-        self.declare_partials(Mission.USEFUL_LOAD, '*', val=1)
+        self.declare_partials(Mission.OPERATING_ITEMS_MASS, '*', val=1)
 
     def compute(self, inputs, outputs):
         cargo_container_mass = inputs[Aircraft.CrewPayload.CARGO_CONTAINER_MASS]
@@ -214,7 +221,7 @@ def compute(self, inputs, outputs):
         unusable_fuel_mass = inputs[Aircraft.Fuel.UNUSABLE_FUEL_MASS]
         emergency_equip_mass = inputs[Aircraft.Design.EMERGENCY_EQUIPMENT_MASS]
 
-        outputs[Mission.USEFUL_LOAD] = (
+        outputs[Mission.OPERATING_ITEMS_MASS] = (
             cabin_crew_mass
             + flight_crew_mass
             + unusable_fuel_mass
@@ -228,18 +235,18 @@ def compute(self, inputs, outputs):
 class OperatingMass(om.ExplicitComponent):
     def setup(self):
         add_aviary_input(self, Aircraft.Design.EMPTY_MASS, units='lbm')
-        add_aviary_input(self, Mission.USEFUL_LOAD, units='lbm')
+        add_aviary_input(self, Mission.OPERATING_ITEMS_MASS, units='lbm')
 
         add_aviary_output(self, Mission.OPERATING_MASS, units='lbm')
 
     def setup_partials(self):
         self.declare_partials(Mission.OPERATING_MASS, '*', val=1)
 
     def compute(self, inputs, outputs):
-        useful_load = inputs[Mission.USEFUL_LOAD]
+        operating_items_mass = inputs[Mission.OPERATING_ITEMS_MASS]
         empty_mass = inputs[Aircraft.Design.EMPTY_MASS]
 
-        outputs[Mission.OPERATING_MASS] = empty_mass + useful_load
+        outputs[Mission.OPERATING_MASS] = empty_mass + operating_items_mass
 
 
 class ZeroFuelMass(om.ExplicitComponent):
@@ -257,3 +264,21 @@ def compute(self, inputs, outputs):
         operating_mass = inputs[Mission.OPERATING_MASS]
 
         outputs[Mission.ZERO_FUEL_MASS] = operating_mass + payload_mass
+
+
+class UsefulLoadMass(om.ExplicitComponent):
+    def setup(self):
+        add_aviary_input(self, Aircraft.Design.GROSS_MASS, units='lbm')
+        add_aviary_input(self, Aircraft.Design.EMPTY_MASS, units='lbm')
+
+        add_aviary_output(self, Aircraft.Design.USEFUL_LOAD_MASS, units='lbm')
+
+    def setup_partials(self):
+        self.declare_partials(Aircraft.Design.USEFUL_LOAD_MASS, Aircraft.Design.GROSS_MASS, val=1)
+        self.declare_partials(Aircraft.Design.USEFUL_LOAD_MASS, Aircraft.Design.EMPTY_MASS, val=-1)
+
+    def compute(self, inputs, outputs):
+        gross_mass = inputs[Aircraft.Design.GROSS_MASS]
+        empty_mass = inputs[Aircraft.Design.EMPTY_MASS]
+
+        outputs[Aircraft.Design.USEFUL_LOAD_MASS] = gross_mass - empty_mass