Ryan Scott Week 7: March 1st, 2007

3/1/2007 Ryan

AAE450 Senior Spacecraft Design

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Ryan ScottWeek 7: March 1st, 2007

Power Group LeaderTC, TV, dE, aM, dM, aE, CS1-2, CSM

*This Week*

Power Distribution on Martian Surface

MLV Engine Selection

Updated Communication Satellite Data

*Slides reviewed and/or edited by Kirk

Updated as of 3/02/07

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Martian Surface Power Distribution• Design Criteria

– MRCF• 126 kWe, 500 m

– ISPP• 1200 kWe, 6 m

– HAB• 100 kWe, 500 m

• Type of Wire?– Aluminum

– Copper

• Above or Below Ground Wiring?– Heat dissipation of Martian surface

– Heat dissipation of Martian atmosphere • Will Wire Reach too High of a

Temperature?– High current suspended

– Lower current buried

HAB

NPS

ISPP

MRCF

PMAD

• AC Results (Aluminum)– Power: 1426 kWe

– Mass: 15840 kg

– Volume 5.87 m^3

• DC Results (Al, not used)– Power: 1426 kWe

– Mass: 22520 kg

– Volume 8.36 m^3

*Follow-up Calculations Presented by Mike

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MLV Engine Selection• Design Criteria

– Thrust to weight ratio minimum 1.4

– 1 Fault tolerant design• Can NOT cause a detrimental

moment during fault• Ability to throttle down if no

fault• Ability to throttle up in event

of fault– Liquid hydrogen– Liquid oxygen– Area constraints

*More Detailed Analysis to be Introduced by Cat

• 5 Space Shuttle Main Engines– T(mass) = 17.97 mt (300 kg for excess piping)– T(Volume) = 4.267 m x 60 m^2– T(thrust) = 5 x 2090 kN = 10450 kN– T/W = 1.8-2.8 (on mars, 5 engines)– T/W = 1.4-1.7 (on mars, 3 engines)– Throttle Range

• 67% - 109%

SSME

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Backup Slides

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Martian Power Distribution

Next 9 slides show the results of the design for the power distribution of the Martian power grid

*note detailed calculations shown in Matlab code*

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*Power Distribution Factor Was found by Consulting Mike

Aluminum Wire AC Power Breakdown

AC DC HAB ISPP MRCF

Power 1426 1426 kWe Power 100 1200 126 kWe

Mass 15840 22520 kg Mass 4.864 0.0056 4.086 kg

Volume 5.87 8.36 m^3 Volume 0.5355 0.0018 0.4908 m^3

DC Power Breakdown

HAB ISPP MRCF

Power 100.00 1200.00 126.00 kWe

Mass 2664 304.5 3172 kg

Volume 0.99 0.14 1.17 m^3

Length 500 6 500 m

Area 1974 22560 2350 m^2

Area conversion factor mm^2 -> m^2

0.000001

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*Power Distribution Factor Was found by Consulting Mike

Copper Wire AC Power Breakdown

AC DC HAB ISPP MRCF

Power 1426 1426 kWe Power 100 1200 126 kWe

Mass 16400 36600 kg Mass 10.05 0.0116 8.442 kg

Volume 6.88 8.34 m^3 Volume 0.4235 0.0014 0.3881 m^3

DC Power Breakdown

HAB ISPP MRCF

Power 100 1200 126 kWe

Mass 10440 1003 8773 kg

Volume 1.17 0.11 0.99 m^3

Length 500 6 500 m

Area 2350 18800 1974 m^2

Area conversion factor mm^2 -> m^2

0.000001

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Data Considered When Choosing Operating Voltage

• Total mass– DC– AC

• Total Volume• Wire Temperature• Wire Location

Results of Matlab Code Given on Next 6 slides

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HAB, Above Ground – Two Wire AC

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HAB – Two Wire AC

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ISPP, Above Ground – Two Wire AC

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ISPP – Two Wire AC

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MRCF, Above Ground – Two Wire AC

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MRCF – Two Wire AC

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MLV Engine Selection

The next 2 slided show the calculations for choosing a MLV

engine

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MLV Engine• Engines Reviewed

– SSME– HM60/Vulcain– LE-7– RS-68– RL-10– CECE– RD0146

• Space Shuttle Main EngineMaximum Thrust:

(109% Power Level)

At Sea Level:In Vacuum:

418,000 lb512,300 lb

Throttle Range: 67% - 109%

Pressures: Hydrogen Pump Discharge:Oxygen Pump Discharge:Chamber Pressure:

6,276 psia

7,268 psi2,994 psia

Specific Impulse: (In Vacuum)

452 sec

Power: High Pressure Pumps

Hydrogen:Oxygen:

71,140 hp23,260 hp

Area Ratio: 69:1

Weight: 7,774 lb

Mixture Ratio: 6.03:1

Dimensions: 168 in. long 90 in. wide

Propellants: Fuel:Oxidizer:

Liquid HydrogenLiquid Oxygen

*Table recreated from www.pw.com

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MLV Calculations

98.0

2133000

evm

eaee AppvmF )(

eaee AppvmF )(

eaee AppvmF )(

mAe 39.2

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Satellite Update

The next slide shows the updated satellite information taken from the overview documents of the class

website on 2/28/07

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Satellite Update• CS1 x 2

– 16.75 kWe– 185.4 kg (Battery, Solar Panel,

Wires, Power Conditioning)– 189.8 m^2 by 0.127 m

• CSM x 5 (Solar Panels Same for GPS and CSM)– 2 kWe– 38.73 kg (Battery, Solar Panel,

Wires, Power Conditioning)– 22.66 m^2 by 0.127 m

*Picture Made by Steve

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New References

• 1 Pouliquen, M., “HM60 Cryogenic Rocket Engine for Future European Launchers,” AIAA Paper 346-353, Oct. 1983.

• 2 Rachuk, V. and Titkov, N., “The First Russian LOX-LH2 Expander Cycle LRE: RD0146,” AIAA Paper 1-15, July. 2006.

• 3 Wood, B., “Propulsion for the 21st Century—RS-68,” AIAA Paper 1-14, July 2002.• 4 Okita, K. & Fukushima, Y., “Improved LE-7 Engine,” AIAA Paper 1-6, July 1995.• 5 Burks, A., “DEVELOPMENT OF LOX-HYDROGEN ENGINES FOR THE SATURN

APOLLO LAUNCH VEHICLES,” AIAA Paper 1-12, June 1968.• 6 Sackheim, R., “Overview of United States Space Propulsion Technology and

Associated Space Transportation Systems,” AIAA Paper 1310-1333, Decmeber 2006.

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New References Continued• 7 Space Shuttle Main Engine. Retrieved February 25, 2007, from

http://www.boeing.com/defense-space/space/propul/SSME.html• 8 SSME. Retrieved February 25, 2007, from

http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=75a0184c712de010VgnVCM100000c45a529fRCRD

• 9 Arian 5 – Specifications. Retrieved February , 2007, from http://www.spaceandtech.com/spacedata/elvs/ariane5_specs.shtml

• 10 LE-7 Specifications. Retrieved February 25, 2007, from http://www.spaceandtech.com/spacedata/engines/le7_specs.shtml

• 11 RS-68 Engine. Retrieved February, 2007, from http://www.boeing.com/defense-space/space/propul/RS68.html

• 12 RL10. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=eb6607b06f5eb010VgnVCM1000000881000aRCRD

• 13 CECE. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=91380e78738ee010VgnVCM100000c45a529fRCRD

• 14 RD-0146. Retrieved February, 2007, from http://www.pw.utc.com/vgn-ext-templating/v/index.jsp?vgnextrefresh=1&vgnextoid=e3b90030296eb010VgnVCM1000000881000aRCRD

Ryan Scott Week 7: March 1st, 2007

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