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ORION AEROSPACE. Propulsion Preliminary Design Review #2 October 17, 2000. Patrick Dempsey Bridget Fitzpatrick Heather Garber Keith Hout Jong Soo Mok. ORION AEROSPACE. Motor Evaluation. -Minimum required values to complete the mission Power = 125W Thrust at climb = 3.36 lbf - PowerPoint PPT Presentation
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Motor Evaluation
-Minimum required values to complete the mission
Power = 125W
Thrust at climb = 3.36 lbf
Thrust at turn = 2.80 lbf
-Run motor test code using the motor constants supplied by the manufacturer.Motor Kv Kt Rm Io Kt
Vol.Const Torque Const. Term. Resist. No load Current using 1355/KvUnits rpm/volt In-Oz/amp Ohms Amps In-Oz/amp
AstroCO25 971 1.395468589 0.093 2.2 1.395468589Aveox 1415/1.5 1568 0.848 0.01 2.5 0.864158163Aveox 1415/2 1190 1.13 0.022 1.8 1.138655462Maxcim N32-13Y 1420 0.946 0.058 0.8 0.954225352Maxcim N32-13D 2500 0.548 0.022 2.5 0.542
Motor code
-Values input into the code
For Motor
Vin = voltage * cell #
Motor constants – Kt, Kv, Rm, Io
Inet = Iin-Io
Pin= Vin*Iin
Tout=Kt*Inet
Pout=Inet*(Vin-Iin*Rm)
RPM= Kv*(Vin-Iin*Rm)
Motor Code
Eta=Pout/Pin
Istall = Vin/Rm
Imax= sqrt(Io^2*Istall)
Etamax= ((Imax-Io)/Imax)^2
For Gearbox: given values-gear ratio (m), Etag
RPMg=RPM/m
Poutg= Pout/Etag
For Speed Controller: given value-Resistance(R)
Pd = Iin^2*R
Motor code
Pinsp =PoutB =Pin+Pd
Poutsp=Pin
Etasp= Poutsp/ Pinsp
-Choose the best motor based on Power output and Efficiency.
-Select optimal condition
Astro Cobalt 25 at 19.2 Volts
Aveox 1415/1.5 at 19.2 Volts
Aveox 1415/2 at 19.2 Volts
Maxcim N32-13D at 19.2 Volts
Maxcim N32-13Y at 19.2 Volts
Motor Selection
Motor : Maxcim N32-13Y
Voltage : 19.2 V
Current : 16 A
Efficiency : 90.408%
RPM : 25946.24
Pout : 277.7344W
Tout: 14.3792 in-oz
Gearbox and Speed Controller Selection
Gearbox-Efficiency : 95%-Gear Ratio : 3.7-Poutg : 263.8477A
Speed Controller-Efficiency :99.29%-Resistance : 0.009 Ohms-Poutsp :307.2 W-Pinsp : 309.504W
Propeller Analysis
Tool : modified Gold script
Method : Run at various diameters and pitches
Match Power and Thrust
Get value for J = V/nD, Cp, and Ct
Calculate Power from Battery
PB = Pr/(Etas*Etam*Etag*Etap)
Calculate Energy required for Battery
E = PB *t
Propeller Analysis
PB from Motor Code >= PB from Calculation
Eest= PB*2min. + 3/4*PB*10min. <= E
Propeller Selection and Power Matching
Propeller Analysis (Gold)Thrust(lb) Maximum Power(kW)Diameter Pitch 6 8 10 12 14 Diameter Pitch 6 8 10 12 14
13 1.6378 2.1234 2.5914 3.038 3.461 13 0.0986 0.1382 0.181 0.226 0.272214 2.1088 2.719 3.3107 3.879 4.421 14 0.1308 0.1821 0.2377 0.2965 0.357316 3.3327 4.2506 5.1491 6.0212 6.8619 16 0.2191 0.3007 0.3898 0.4847 0.583818 5.0055 6.3156 7.6091 8.8739 10.1033 18 0.3477 0.4708 0.6056 0.7499 0.901720 7.2223 9.018 10.803 12.5604 14.279 20 0.5287 0.7067 0.9019 1.1115 1.33322 10.0815 12.474 14.8533 17.2117 19.5307 22 0.7762 1.0247 1.2976 1.5913 1.902624 13.6915 16.7996 19.8945 22.9679 26.0078 24 1.1066 1.4439 1.8146 2.2141 2.6383
Efficiency Advance RatioDiameter Pitch 6 8 10 12 14 Diameter Pitch 6 8 10 12 14
13 0.5632 0.5208 0.4853 0.4558 0.431 13 0.1974 0.1974 0.1974 0.1974 0.197414 0.5466 0.5062 0.4721 0.4435 0.4194 14 0.1833 0.1833 0.1833 0.1833 0.183316 0.5157 0.4792 0.4478 0.4211 0.3984 16 0.1604 0.1604 0.1604 0.1604 0.160418 0.488 0.4547 0.4259 0.4011 0.3798 18 0.1426 0.1426 0.1426 0.1426 0.142620 0.4631 0.4326 0.4061 0.3831 0.3631 20 0.1283 0.1283 0.1283 0.1283 0.128322 0.4403 0.4127 0.388 0.3667 0.348 22 0.1167 0.1167 0.1167 0.1167 0.116724 0.4194 0.3944 0.3717 0.3517 0.3342 24 0.107 0.107 0.107 0.107 0.107
Results from modified Gold Script
Advance Ratio Versus Efficiency
Advance Ratio Versus Cp and Ct
Propeller Selection and Power Matching
Propeller : 14” Diameter and 10” PitchFor 14X10
Power Thrust Efficiency Cp Ct Torque RPMWatt lbf ft-lbf237.7 3.3107 0.4721 0.022 0.0567 0.2387 7012.5
PB Calculation(Gold) = 278.77 W
PB from Code (Motor Code) = 309. 504W
Endurance time =12 min.
E= 3345.12 W-min.
Eest = 2648.315 W-min.
Questions?