Feature general aviation weights by jmvegh · Pull Request #224 · suavecode/SUAVE

jmvegh · 2018-01-05T22:53:41Z

added weights correlations for general aviation-type aircraft

…ture-general_aviation_weights Conflicts: trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/__init__.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/fuselage.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/landing_gear.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/systems.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_horizontal.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_vertical.py trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py

coveralls · 2018-01-05T23:00:45Z

Coverage decreased (-0.8%) to 55.456% when pulling e4e71dc on feature-general_aviation_weights into e3cb920 on develop.

coveralls · 2018-01-05T23:38:43Z

Coverage increased (+0.6%) to 56.882% when pulling 6577170 on feature-general_aviation_weights into e3cb920 on develop.

planes

Looks pretty good. See the comments I have. Should be quick fixes. Fix those and Tim will take a look as well.

planes · 2018-01-08T21:50:18Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+    num_pax     = vehicle.passengers
+    wt_cargo    = vehicle.mass_properties.cargo
+    num_seats   = vehicle.fuselages['fuselage'].number_coach_seats
+    #ctrl_type  = vehicle.systems.control


Either delete this or uncomment out.

planes · 2018-01-08T21:51:04Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+        V_fuel                      = m_fuel/fuel.density  #total fuel
+        fuel.mass_properties.volume = V_fuel 
+    S_gross_w  = vehicle.reference_area
+    #S_gross_w  = vehicle.wings['main_wing'].Areas.reference


delete this

planes · 2018-01-08T21:53:30Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+        avionics = vehicle.avionics
+        W_uav = avionics.mass_properties.uninstalled
+
+    has_air_conditioner = vehicle.has_air_conditioner


This is weird to have a key in the vehicle of has_air_conditioner

planes · 2018-01-08T21:53:48Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+    output.systems           = output_2.wt_systems       
+    output.systems_breakdown = Data()
+    output.systems_breakdown.control_systems   = output_2.wt_flt_ctrl    
+    #output.systems_breakdown.apu               = output_2.wt_apu         


Commented out things.

planes · 2018-01-08T21:54:17Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+    vehicle.hydraulics                          = hydraulics
+    vehicle.landing_gear                        = landing_gear_component
+
+    #note; air conditioner optional, and weight is added to the air_conditioner object directly


I think it's okay to make it optional, just change the key dependence.

planes · 2018-01-08T21:56:46Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/fuselage.py

+## @ingroup Methods-Weights-Correlations-General_Aviation
+def fuselage(S_fus, Nult, TOW, w_fus, h_fus, l_fus, l_ht, q_c, V_fuse, diff_p_fus):
+    """ 
+        Calculate the weight of a fuselage for a GA aircraft


Add a source, see above comment for ordering of comments.

I think when possible we should start adding sources by page etc. These weight correlations are on page 590 in the fifth edition.

Done. I used the 4th edition though

planes · 2018-01-08T21:57:31Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/landing_gear.py

+from SUAVE.Core import Data,Units
+import numpy as np
+
+


Remove this extra space

planes · 2018-01-08T21:57:43Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/landing_gear.py

+#   Landing Gear
+# ----------------------------------------------------------------------
+## @ingroup Methods-Weights-Correlations-General_Aviation
+def landing_gear(landing_weight, Nult, strut_length_main, strut_length_nose):


See earlier comment on ordering

planes · 2018-01-08T21:57:58Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py

+    wt_pax     = wt_passenger * num_pax 
+    wt_bag     = wt_baggage * num_pax
+    wt_payload = wt_pax + wt_bag + wt_cargo
+    #wt_fuel    = TOW - wt_payload - empty


Commented out thing.

planes · 2018-01-08T21:58:06Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py

+    output.payload = wt_payload
+    output.pax     = wt_pax   
+    output.bag     = wt_bag
+    #output.fuel    = wt_fuel


Commented out?

timdmacdo

Some more simple comments here

timdmacdo · 2018-01-10T23:58:20Z

regression/scripts/weights/weights.py

+    print 'Relative Errors'
+    print error  
+
+    for k,v in error.items():


Use 1e-6 unless there's a reason not to.

timdmacdo · 2018-01-11T00:00:18Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/__init__.py

@@ -0,0 +1,20 @@
+## @defgroup Methods-Weights-Correlations-General_Aviation Generational
+# Provides structural and component weight correlations for general aviation aircraft
+""" SUAVE.Methods.Weights.Correlations.General_Aviation


Remove these extra comments and add in @InGroup tag

timdmacdo · 2018-01-11T00:01:14Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+
+                # thrust_sls should be sea level static thrust. Using design thrust results in wrong propulsor 
+                # weight estimation. Engine sizing should return this value.
+                # for now, using thrust_sls = design_thrust / 0.20, just for optimization evaluations


This comment doesn't seem accurate?

timdmacdo · 2018-01-11T00:02:20Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+        avionics = vehicle.avionics
+        W_uav = avionics.mass_properties.uninstalled
+
+    has_air_conditioner = vehicle.has_air_conditioner


timdmacdo · 2018-01-11T00:02:58Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+    furnishings.mass_properties.mass                                 = output.systems_breakdown.furnish
+    avionics.mass_properties.mass                                    = output.systems_breakdown.avionics              
+
+    #fuel.mass_properties.mass                                        = output.fuel


timdmacdo · 2018-01-11T00:04:14Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/systems.py

+    # packup outputs
+    output = Data()   
+    output.wt_flt_ctrl    = flt_ctrl_wt 
+    #output.wt_apu         = apu_wt 


timdmacdo · 2018-01-11T00:04:29Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_horizontal.py

+            Aircraft Design: A Conceptual Approach by Raymer
+    """
+    # unpack inputs
+    W_0  = TOW / Units.lb # Convert kg to lbs


table format

timdmacdo · 2018-01-11T00:04:44Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_vertical.py

+    # unpack inputs
+    W_0  = TOW / Units.lb # Convert kg to lbs
+    S_vt  = S_v/ Units.ft**2 # Convert from meters squared to ft squared  
+    q   = q_c /(Units.force_pound / Units.ft**2.)


table format

timdmacdo · 2018-01-11T00:05:05Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py

+    W_0  = TOW / Units.lb # Convert kg to lbs
+    S_w  = S_wing/ (Units.ft**2) # Convert from meters squared to ft squared  
+    W_fw = m_fuel/Units.lbs #convert from kg to lbs
+    q   = q_c /(Units.lbs/(Units.ft**2.))


table format

timdmacdo · 2018-01-11T00:05:41Z

trunk/SUAVE/Methods/Weights/Correlations/Propulsion/integrated_propulsion_general_aviation.py

@@ -0,0 +1,36 @@
+# integrated_propulsion_general_aviation.py


Doxygen tags are missing

coveralls · 2018-01-12T22:02:05Z

Coverage increased (+0.6%) to 56.875% when pulling 6478385 on feature-general_aviation_weights into e3cb920 on develop.

…ture-general_aviation_weights

coveralls · 2018-01-17T20:34:07Z

Coverage increased (+0.6%) to 56.875% when pulling fed6b3e on feature-general_aviation_weights into d3473f7 on develop.

WallyMaier · 2018-01-18T08:25:57Z

regression/scripts/Vehicles/Cessna_172.py

    vehicle.has_air_conditioner                         = 0
    vehicle.reference_area                              = 16.2  * Units.meter**2  # Wing gross area in square meters
-    vehicle.design_dynamics_pressure =( .5 *freestream0.density*(cruise_speed**2))[0][0]
+    vehicle.design_dynamic_pressure  =( .5 *freestream0.density*(cruise_speed**2))[0][0]


should this be cruise_speed*cruise_speed?

coveralls · 2018-01-19T02:36:48Z

Coverage increased (+0.6%) to 57.52% when pulling 26a8e0c on feature-general_aviation_weights into 6955476 on develop.

WallyMaier · 2018-01-19T18:37:45Z

regression/scripts/Vehicles/Cessna_172.py

-    fuselage.mass_properties.volume   = .4*fuselage.lengths.total*(np.pi/4.)*(fuselage.heights.maximum**2.) #try this as approximation
-    fuselage.internal_volume          = .3*fuselage.lengths.total*(np.pi/4.)*(fuselage.heights.maximum**2.)
-    fuselage.areas.wetted             = fuselage.lengths.total*(np.pi/4.)*(fuselage.heights.maximum **2)
+    fuselage.differential_pressure           = 8*Units.psi     # Maximum differential pressure


Make a float.

WallyMaier · 2018-01-19T18:37:56Z

regression/scripts/Vehicles/Cessna_172.py

+    fuselage.differential_pressure           = 8*Units.psi     # Maximum differential pressure
+    fuselage.width                           = 40.         * Units.inches     # Width of the fuselage
+    fuselage.heights.maximum                 = 75.         * Units.inches     # Height of the fuselage
+    fuselage.lengths.total                   = (27+2./12.) * Units.feet     # Length of the fuselage


make a float

WallyMaier · 2018-01-19T18:38:05Z

regression/scripts/Vehicles/Cessna_172.py

+    fuselage.width                           = 40.         * Units.inches     # Width of the fuselage
+    fuselage.heights.maximum                 = 75.         * Units.inches     # Height of the fuselage
+    fuselage.lengths.total                   = (27+2./12.) * Units.feet     # Length of the fuselage
+    fuselage.lengths.empennage               = 9           * Units.feet   


WallyMaier · 2018-01-19T18:38:14Z

regression/scripts/Vehicles/Cessna_172.py

+    fuselage.lengths.total                   = (27+2./12.) * Units.feet     # Length of the fuselage
+    fuselage.lengths.empennage               = 9           * Units.feet   
+    fuselage.lengths.structure               = fuselage.lengths.total-fuselage.lengths.empennage 
+    fuselage.lengths.cabin                   = 140         *Units.inches


WallyMaier · 2018-01-19T18:38:37Z

regression/scripts/Vehicles/Cessna_172.py

+    fuselage.lengths.structure               = fuselage.lengths.total-fuselage.lengths.empennage 
+    fuselage.lengths.cabin                   = 140         *Units.inches
+    fuselage.mass_properties.volume          = .4*fuselage.lengths.total*(np.pi/4.)*(fuselage.heights.maximum**2.) #try this as approximation
+    fuselage.mass_properties.internal_volume = .3*fuselage.lengths.total*(np.pi/4.)*(fuselage.heights.maximum**2.)


**2 or ()*()

timdmacdo

Just a couple remaining small items

timdmacdo · 2018-02-06T16:34:42Z

regression/scripts/Vehicles/Cessna_172.py

+    propulsors = SUAVE.Components.Propulsors.Propulsor() #use weights for the IC engine  
+    propulsors.tag = 'internal_combustion'
+    propulsors.rated_power = 110 *Units.kW # engine correlation is really off
+    #propulsors.rated_power = 100 *Units.kW


Delete this line. Also what's the issue with the engine correlation?

It doesn't really match the weight breakdown from Roskam, which is where I got some detailed weight statements. There are a number of possible reasons why, one of which might be different ways of bookkeeping things

Okay that's fine. If you could just write something like that in the comment I think it would be great.

timdmacdo · 2018-02-06T16:39:04Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+## @ingroup Methods-Weights-Correlations-General_Aviation
+def empty(vehicle):
+    """ output = SUAVE.Methods.Weights.Correlations.Tube_Wing.empty(engine,wing,aircraft,fuselage,horizontal,vertical)
+        This is for a standard Tube and Wing aircraft configuration.     


This docstring needs to be updated.

timdmacdo · 2018-02-06T16:44:25Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/fuselage.py

+## @ingroup Methods-Weights-Correlations-General_Aviation
+def fuselage(S_fus, Nult, TOW, w_fus, h_fus, l_fus, l_ht, q_c, V_fuse, diff_p_fus):
+    """ 
+        Calculate the weight of a fuselage for a GA aircraft


I think when possible we should start adding sources by page etc. These weight correlations are on page 590 in the fifth edition.

timdmacdo · 2018-02-06T16:48:30Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/tail_horizontal.py

+# ----------------------------------------------------------------------
+## @ingroup Methods-Weights-Correlations-General_Aviation
+def tail_horizontal(S_h, AR_h, sweep_h, q_c, taper_h, t_c_h,Nult,TOW):       
+    """ weight = SUAVE.Methods.Weights.Correlations.Tube_Wing.tail_horizontal(b_h,sweep_h,Nult,S_h,TOW,mac_w,mac_h,l_w2h,t_c_h)


Update this docstring

This still lists Tube_Wing. I don't think this is accurate?

Weird. It looks like git might be having some issues but I repushed it

WallyMaier · 2018-02-07T17:47:59Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/payload.py

+# payload.py
+# 
+# Created:  Jan 2014, A. Wendorff
+# Modified: Feb 2014, A. Wendorff


Is this up to date?

WallyMaier · 2018-02-07T17:48:54Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/systems.py

+    l_fus  = l_fuselage / Units.ft  # Convert meters to ft
+    b_wing = span/Units.ft
+
+


Lots of white space that can be cleaned up here

WallyMaier · 2018-02-07T17:49:41Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py

+    """     
+    # unpack inputs
+
+


white space here

planes · 2018-02-09T21:35:40Z

regression/scripts/Vehicles/Cessna_172.py

+    propulsors.number_of_engines    = 1.
+    vehicle.append_component(propulsors)
+
+    #Build an dsize the turbofan to get sls sthrust


What turbofan?

planes · 2018-02-09T21:36:21Z

regression/scripts/Vehicles/Cessna_172.py

+# Created:  Feb 2017, M. Vegh (modified from data originally in cmalpha/cmalpha.py)
+# Modified: 
+
+""" setup file for the Beech 99 aircraft, current values only used to test stability cmalpha


Beech 99 or C-172?

planes · 2018-02-09T21:36:37Z

regression/scripts/Vehicles/Cessna_172.py

+    config.tag = 'landing'
+
+    config.wings['main_wing'].flaps_angle = 30. * Units.deg
+    config.wings['main_wing'].slats_angle = 25. * Units.deg


Cessnas don't have slats

planes · 2018-02-09T21:36:50Z

regression/scripts/Vehicles/Cessna_172.py

+
+
+    # done!
+    return configs


Ask me about the C-172 Carlos and I made.

planes · 2018-02-09T21:37:11Z

regression/scripts/weights/weights.py

+    actual.systems         = 101.412216023
+
+
+    #empty weight =1354 * Units.lbs


Commented out code

planes · 2018-02-09T21:37:35Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+## @ingroup Methods-Weights-Correlations-General_Aviation
+# empty.py
+# 
+# Created:  Jan 2014, A. Wendorff


Did andrew write this?

Nope. Just missed the author strings. Updated now

planes · 2018-02-09T21:37:54Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+        Inputs:
+            engine - a data dictionary with the fields:                    
+                thrust_sls - sea level static thrust of a single engine [Newtons]
+


Remove excess whitespace.

planes · 2018-02-09T21:38:36Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+        t_c_h          = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
+        h_tail_exposed = vehicle.wings['horizontal_stabilizer'].areas.exposed / vehicle.wings['horizontal_stabilizer'].areas.wetted
+        l_w2h          = vehicle.wings['horizontal_stabilizer'].origin[0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings['main_wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
+        wt_tail_horizontal = tail_horizontal(S_h, AR_h, sweep_h, q_c, taper_h, t_c_h,Nult,TOW)                


planes · 2018-02-09T21:38:53Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+        mac_h          = vehicle.wings['horizontal_stabilizer'].chords.mean_aerodynamic
+        t_c_h          = vehicle.wings['horizontal_stabilizer'].thickness_to_chord
+        h_tail_exposed = vehicle.wings['horizontal_stabilizer'].areas.exposed / vehicle.wings['horizontal_stabilizer'].areas.wetted
+        l_w2h          = vehicle.wings['horizontal_stabilizer'].origin[0] + vehicle.wings['horizontal_stabilizer'].aerodynamic_center[0] - vehicle.wings['main_wing'].origin[0] - vehicle.wings['main_wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm


Do you still need to check this?

planes · 2018-02-09T21:39:03Z

trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/empty.py

+        t_tail     = vehicle.wings['vertical_stabilizer'].t_tail  
+        output_3   = tail_vertical(S_v, AR_v, sweep_v, q_c, taper_v, t_c_v, Nult,TOW,t_tail)
+        vehicle.wings['vertical_stabilizer'].mass_properties.mass = output_3.wt_tail_vertical
+


White space

Done. I think

…ture-general_aviation_weights

…ture-general_aviation_weights Conflicts: regression/scripts/Vehicles/Cessna_172.py regression/scripts/weights/weights.py

planes · 2018-02-16T23:13:24Z

regression/scripts/Vehicles/Cessna_172.py

+    vehicle = SUAVE.Vehicle()
+    vehicle.tag = 'Cessna_172_SP'
+    GTOW                                  = 2550. * Units.pounds     
+    vehicle.mass_properties.max_takeoff   = GTOW #from Wikipedia


Take this comment from wikipedia out.

planes · 2018-02-16T23:14:33Z

regression/scripts/weights/weights.py

+    actual.fuel_systems    = 15.6859717453
+    actual.systems         = 108.096549345
+
+    error = Data()


Table format

planes

Looks good!

jmvegh added 5 commits January 5, 2018 12:40

added headers

22f38e5

cleaned up documentation

d8f65be

more documentation cleanup

4b46308

readded integrated_propulsion_general_aviation.py

e4e71dc

fixed weights issue

6577170

planes reviewed Jan 8, 2018

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timdmacdo reviewed Jan 11, 2018

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documentation update

6478385

Merge branch 'develop' of https://github.com/suavecode/SUAVE into fea…

fed6b3e

…ture-general_aviation_weights

WallyMaier reviewed Jan 18, 2018

View reviewed changes

changed **2 to ()*() in Cessna_172.py

28ff088

WallyMaier reviewed Jan 19, 2018

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planes force-pushed the develop branch from d3473f7 to 5443f7f Compare January 26, 2018 02:10

jmvegh added 3 commits February 1, 2018 14:22

addressed github comments

06ea458

more code/comment cleanup

777bc92

hopefully final code cleanup stuff

29f8a0e

timdmacdo reviewed Feb 6, 2018

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jmvegh added 3 commits February 6, 2018 09:29

added page numbers to sources

7a03a84

some cleanups on Cessna script

44562f6

updated htail script

204b8ae

WallyMaier reviewed Feb 7, 2018

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trunk/SUAVE/Methods/Weights/Correlations/General_Aviation/wing_main.py Outdated

"""

# unpack inputs

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white space here

removed white space

9211d20

planes reviewed Feb 9, 2018

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jmvegh added 6 commits February 9, 2018 13:51

cleaned up Cessna 172

6918909

updated Cessna_172 to better geometry

bc9c826

Merge branch 'develop' of https://github.com/suavecode/SUAVE into fea…

64d6a47

…ture-general_aviation_weights

more code cleanup

5d213b5

updated author strings

e0be756

Merge branch 'develop' of https://github.com/suavecode/SUAVE into fea…

eb277ad

…ture-general_aviation_weights Conflicts: regression/scripts/Vehicles/Cessna_172.py regression/scripts/weights/weights.py

planes reviewed Feb 16, 2018

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comments and formatting

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planes approved these changes Feb 16, 2018

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planes merged commit 24e5439 into develop Feb 16, 2018

planes deleted the feature-general_aviation_weights branch February 17, 2018 02:29

		l_fus = l_fuselage / Units.ft # Convert meters to ft
		b_wing = span/Units.ft

		actual.systems = 101.412216023


		#empty weight =1354 * Units.lbs

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coveralls commented Jan 12, 2018

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coveralls commented Jan 19, 2018 •

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