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breakdowns_output.txt
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breakdowns_output.txt
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Cost breakdown (as seen in solution tables)
==============
┃┓ ┓ ┓
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┣╸Battery.W ┣╸Battery.E╶⎨
┃┃ ┃ (370lbf) ┃ (165,913kJ)
┃┃ ┃ ┃
┃┃ ┃ ┃
Cost╺┫┃ ┃ ┃
(699lbf) ┃┣╸Wtotal ┛ ┛
┃┃ (699lbf) ┓ ┓
┃┃ ┃ ┣╸Wing.BoxSpar.W╶⎨
┃┃ ┣╸Wing.W ┛ (96.1lbf)
┃┃ ┛ (139lbf) ┣╸Wing.WingSecondStruct.W╶⎨
┃┃ ┣╸Motor.W╶⎨
┃┃ ┣╸SolarCells.W╶⎨
┃┃ ┣╸Empennage.W
┃┃ ┣╸Wavn
┃┛ ┣╸[6 terms]
Variable breakdowns (note the two methods of access)
===================
┃┓ ┓ ┓
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┣╸MotorPerf.Q╶⎨
AircraftPerf.AircraftDrag.Poper╺┫┣╸MotorPerf.Pelec ┣╸MotorPerf.i ┃ (4.8N·m)
(3,194W) ┃┃ (0.685kW) ┃ (36.8A) ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┛
┃┃ ┃ ┣╸i0
┃┛ ┛ ┛ (4.5A, fixed)
┃┣╸Pavn
┃┣╸Ppay
┃┓
AircraftPerf.AircraftDrag.MotorPerf.Q╺┫┃
(4.8N·m) ┃┣╸..ActuatorProp.CP
┃┛ (0.00291)
Combining the two above by increasing maxwidth
----------------------------------------------
┃┓ ┓ ┓ ┓
┃┃ ┃ ┃ ┃
┃┃ ┃ ┃ ┃
┃┃ ┃ ┃ ┃
┃┃ ┃ ┃ ┃
┃┃ ┃ ┃ ┃
┃┃ ┃ ┣╸MotorPerf.Q ┣╸ActuatorProp.CP
AircraftPerf.AircraftDrag.Poper╺┫┣╸MotorPerf.Pelec ┣╸MotorPerf.i ┃ (4.8N·m) ┃ (0.00291)
(3,194W) ┃┃ (0.685kW) ┃ (36.8A) ┃ ┃
┃┃ ┃ ┃ ┃
┃┃ ┃ ┃ ┃
┃┃ ┃ ┛ ┛
┃┃ ┃ ┣╸i0
┃┛ ┛ ┛ (4.5A, fixed)
┃┣╸Pavn
┃┣╸Ppay
Model sensitivity breakdowns (note the two methods of access)
============================
┃┓ ┓ ┓ ┓ ┓
┃┃ ┃ ┃ ┃ ┃
┃┃ ┃ ┃ ┃ ┣╸ActuatorProp╶⎨
┃┃ ┃ ┃ ┃ ┛
┃┃ ┃ ┣╸AircraftPerf ┣╸AircraftDrag ┣╸MotorPerf╶⎨
┃┃ ┃ ┃ ┃ ┓
┃┣╸Mission ┣╸FlightSegment ┃ ┃ ┣╸[17 terms]
┃┃ ┃ ┛ ┛ ┛
┃┃ ┃ ┣╸FlightState╶⎨
Model╺┫┃ ┃ ┣╸GustL╶⎨
┃┃ ┃ ┣╸SteadyLevelFlight╶⎨
┃┃ ┛ ┣╸[49 terms]
┃┛ ┣╸Climb╶⎨
┃┓
┃┃
┃┃
┃┣╸Aircraft╶⎨
┃┃
┃┛
┃┣╸g = 9.81m/s²
┃┓ ┣╸etadischarge = 0.98
┃┃ ┛
┃┃ ┣╸W ≥ E·minSOC/hbatt/etaRTE/etapack·g
┃┃ ┣╸etaRTE = 0.95
┃┣╸Battery ┣╸etapack = 0.85
┃┃ ┣╸hbatt = 350W·hr/kg
┃┃ ┣╸minSOC = 1.03
┃┛ ┛
┃┓
Aircraft╺┫┃
┃┣╸Wing╶⎨
┃┃
┃┛
┃┣╸Wtotal/mfac ≥ Fuselage.W[0,0] + Fuselage.W[1,0] + Fuselage.W[2,0] …
┃┛
┃┣╸mfac = 1.05
┃┛
┃┣╸Empennage╶⎨
┃┣╸[23 terms]
┃┛
Exhaustive variable breakdown traces (and configuration arguments)
====================================
┃┓ ┓ ┓
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┃
AircraftPerf.AircraftDrag.Poper╺┫┣╸MotorPerf.Pelec ┣╸MotorPerf.i ┣╸MotorPerf.Q╶⎨
(3,194W) ┃┃ (0.685kW) ┃ (36.8A) ┃ (4.8N·m)
┃┃ ┃ ┃
┃┃ ┃ ┃
┃┃ ┃ ┛
┃┛ ┛ ┣╸i0
┃┣╸Pavn
┃╤╤┯╤┯╤┯┯╤┓
┃╎╎│╎│╎││╎┃
┃╎╎│╎│╎││╎┃
┃╎╎│╎│╎││╎┃
┃╎╎│╎│╎││╎┃
┃╎╎│╎│╎││╎┃
┃╎╎│╎│DCBA┣╸ActuatorProp.CP
AircraftPerf.AircraftDrag.Poper╺┫╎HGFE╎││╎┃ (0.00291)
(3,194W) ┃J╎│╎│╎││╎┃
┃╎╎│╎│╎││╎┃
┃╎╎│╎│╎││╎┃
┃╎╎│╎│╧┷┷╧┛
┃╎╎│╎│┣╸i0 (4.5A, fixed)
┃╎╧┷╧┷┛
┃╎┣╸Pavn (200W, fixed)
┃╧┣╸Ppay (100W, fixed)
A 4.53e-05·FlightState.rho·ActuatorProp.omega²·Propeller.R⁵ ×1,653N·m [free factor]
B ActuatorProp.Q = 4.8N·m
C MotorPerf.Q = 4.8N·m
D Kv ×64.2rpm/V [free factor]
E MotorPerf.i = 36.8A
F MotorPerf.v ×18.6V [free factor]
G MotorPerf.Pelec = 0.685kW
H Nprop ×4, fixed
J mpower ×1.05, fixed
Permissivity = 2 (the default)
----------------
AircraftPerf.AircraftDrag.Poper (3,194W)
which in: Poper/mpower ≥ Pavn + Ppay + Pelec·Nprop (sensitivity +5.6)
{ through a factor of AircraftPerf.AircraftDrag.mpower (1.05, fixed) }
breaks down into 3 monomials:
1) forming 90% of the RHS and 90% of the total:
{ through a factor of Nprop (4, fixed) }
AircraftPerf.AircraftDrag.MotorPerf.Pelec (0.685kW)
which in: Pelec = v·i (sensitivity -5.1)
breaks down into:
{ through a factor of AircraftPerf.AircraftDrag.MotorPerf.v (18.6V) }
AircraftPerf.AircraftDrag.MotorPerf.i (36.8A)
which in: i ≥ Q·Kv + i0 (sensitivity +5.4)
breaks down into 2 monomials:
1) forming 87% of the RHS and 79% of the total:
{ through a factor of Kv (64.2rpm/V) }
AircraftPerf.AircraftDrag.MotorPerf.Q (4.8N·m)
which in: Q = Q (sensitivity -4.7)
breaks down into:
AircraftPerf.AircraftDrag.ActuatorProp.Q (4.8N·m)
which in: CP ≤ Q·omega/(0.5·rho·(omega·R)³·π·R²) (sensitivity +4.7)
{ through a factor of 4.53e-05·FlightState.rho·AircraftPerf.AircraftDrag.ActuatorProp.omega²·Propeller.R⁵ (1,653N·m) }
breaks down into:
AircraftPerf.AircraftDrag.ActuatorProp.CP (0.00291)
2) forming 12% of the RHS and 11% of the total:
i0 (4.5A, fixed)
2) forming 6% of the RHS and 6% of the total:
AircraftPerf.AircraftDrag.Pavn (200W, fixed)
3) forming 3% of the RHS and 3% of the total:
AircraftPerf.AircraftDrag.Ppay (100W, fixed)
Permissivity = 1 (stops at Pelec = v·i)
----------------
AircraftPerf.AircraftDrag.Poper (3,194W)
which in: Poper/mpower ≥ Pavn + Ppay + Pelec·Nprop (sensitivity +5.6)
{ through a factor of AircraftPerf.AircraftDrag.mpower (1.05, fixed) }
breaks down into 3 monomials:
1) forming 90% of the RHS and 90% of the total:
{ through a factor of Nprop (4, fixed) }
AircraftPerf.AircraftDrag.MotorPerf.Pelec (0.685kW)
which in: Pelec = v·i (sensitivity -5.1)
breaks down into:
AircraftPerf.AircraftDrag.MotorPerf.i·AircraftPerf.AircraftDrag.MotorPerf.v (685A·V)
2) forming 6% of the RHS and 6% of the total:
AircraftPerf.AircraftDrag.Pavn (200W, fixed)
3) forming 3% of the RHS and 3% of the total:
AircraftPerf.AircraftDrag.Ppay (100W, fixed)