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Mike Kowalkowski Week 4: February 8 th 2007

Mike Kowalkowski Week 4: February 8 th 2007. Project Aquarius Power Engineering Habitat & Rover Power Sizing. Mars Surface Layout. 10MWe deliverable. Conceptual Design Effective regulated power delivery system with minimal radiation exposure: manned Partially regulated power to ISPP plants

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Mike Kowalkowski Week 4: February 8 th 2007

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  1. Mike KowalkowskiWeek 4: February 8th 2007 Project Aquarius Power EngineeringHabitat & Rover Power Sizing

  2. Mars Surface Layout 10MWe deliverable • Conceptual Design • Effective regulated power delivery system with minimal radiation exposure: manned • Partially regulated power to ISPP plants • Assumptions • 400 m minimum human distance from reactor 1 • Human line of sight maintained (Kirk Akaydin) • Distribution efficiency ~ 89% • P / M / V – Mars Surface • Power: 1.05 MWe capacity • Mass: 7 mt • Volume: 16 m^3 • All rovers are fuel cell dependent and autonomous. 1.05 MWe received 750 kWe required CRYO System 15 kWe required ISPP 2 H2 &O2 150 kWe required HAB 1 Aux. Power Supply HAB 2

  3. Mars Rover (Manned) Power System: Mass: 1000 kg Volume: 1.7 m^3 Peak Power: 48 kWe Idle Power: 10 kWe See attached MATLAB code to size power for all vehicles Total mass: 5 mt .9 mt – Human Factors 2.5 mt – Structures .6 mt – Towing / Storage 1 mt – Fuel Cells & Battery Backup Capabilities and Sizing: Max level velocity: 40 km/hr Max range: 50 km 1-way (25 km reserve) Max incline: 30o Max speed at incline: 3 km/hr Time at incline: 10 minutes 12 hour autonomous operation Utilizes in-situ fueling station Rover Power Requirements

  4. Backup Slides Week 4 Readiness Level

  5. Power budget - Surface 75 kWe per HAB 25 kWe life support systems (Courtesy: Kate Mitchell) 35 kWe ground control systems, communications, 25% margin for science operations 750 kWe total ISPP (Courtesy: Steve Kassab) 15 kWe CRYO / excess Launch pad, no bleed cryo system 2 hour HAB Li-Ion Backup PMAD losses 8.3% power budget (Courtesy: Larson & Pranke) Resistance losses 2% power budget (Courtesy: Larson & Pranke) Next step includes assessment of power distribution losses as a function of distance Mars Surface Power Budget

  6. Primary System: HAB PMAD & Nuclear PMAD mass ~ 11.1 kg/kWe 1 Wiring ~ 0.5 kg/m 1 System requires 150 kWe Secondary System: HAB Direct fuel cell system PEM fuel cells are capable of running in reverse. In the case that both nuclear power systems are offline, the ISPP production facility can begin generating power to sustain the HAB indefinitely. Primary System ISPP Electrolysis Partially regulated 1 10,000 mt propellant produced in 2 years According to Steve Kassab, requirement is 750 kWe between the two plants over that time period. Assume 90% efficiency CRYO storage tanks budgeted 15 kWe. Need more information to finalize. Mars Surface M / V Calculations

  7. Directed Fuel Cell Specific Energy: 1 kg/(kW-h) fuel 2 Densities LOX 692 kg/m^3 2 LH2 59.3 kg/m^3 2 Fuel Cell Machinery 4 kg / kW (Courtesy: Kassab) 1.5 We/cm^3 density 3 Tank Mass LH2 2.4 kg/kg H 2 LOX .25 kg/kg O 2 Level power requirement @ 90% efficiency Power = m*gmars*cf*v 4 Graded power requirement @ 90% efficiency Power = v*(m*gmars *cf*cos(theta) + m*gmars*sin(theta)) 4 See attached code for calculations. ½ credit to Steve Kassab for helping create fuel cell code. Top speed @ 50 km/hr ~1650 kg system Mars Rover Power Assumptions

  8. Calculations • Calc. Theory from Human Spaceflight: Mission Analysis and Design, Larson & Pranke pgs. 660-663 – MATLAB code to come shortly

  9. Power Systems Trade Study • ISPP vs. Solar Panel Backup System 5 • Referenced Ryan Scott’s solar panel code 6 • ISPP fuel cells use fuel already in the ground at Mars that has been electrolyzed by a nuclear reactor that is already budgeted into the mission. Turning that system around in the event of an emergency saves weight compared to solar panels. • Solar panels require additional weight and a lot of volume. • Power: 150 kWe – Martian Surface • Weight: 2.5 mt • Volume: 486 m^3; Area: 3827 m^2

  10. = crew of four = taxi capsule = transfer vehicle = Mars habitat = robotic sample return = in-situ propellant production = geology laboratory = depart Earth = arrive Mars = depart Mars = arrive Earth = EP system = full EP tank = empty EP system = empty EP tank EP dE = Mars launch vehicle = Mars taxi = Earth taxi ML ISPP aM EP HAB MT SR SR SR dM EP ET aE EP LAB LAB LAB 1 ISPP ISPP ISPP MT HAB MT SR dM aE EP dM EP MT MT ISPP Surface of Mars ML ML dM ML MT MT MT MT One Synodic Period 2 SR HAB MT aE dM dM High-Mars Orbit dM dM dM aE EP dM dM dM HAB HAB HAB HAB 3 4 6 5 8 dM dM dM High-Earth Orbit dE aM dE aM dE aM dE aM 7 MT MT dM dM aE dM dM aE dM dM dM MT MT EP EP ML ML EP dE aM aM MT ET dE aM EP aM EP ET EP Low-Earth Orbit ET EP EP EP dE ET EP EP EP EP EP ML ET EP dE EP Fig. ‑a Schematic for first five Mars missions. 2 EP Systems Available 7

  11. Cited References • 1 Larson, Wiley J. and Linda K. Pranke. Human Spaceflight, Mission Analysis and Design. Ch. 13 – “Designing, Sizing, and Integrating a Surface Base.” McGraw Hill. • 2 Larson, Wiley J. and Linda K. Pranke. Human Spaceflight, Mission Analysis and Design. Ch. 14 – “Planetary Surface Vehicles.” • 3 “PEM Fuel Cell Cost Status.” Carlson, Eric, et al. November 2005. Available online. http://www.fuelcellseminar.com/pdf/2005/Thursday-Nov17/Carlson_Eric_392.PDF • 4 “Power – Physics.” Wikipedia. Available online. http://en.wikipedia.org/wiki/Power_%28physics%29 • 5 Landis, Geoffrey. “Photovoltaic Power Options for Mars.” October 1996. Available Online. http://powerweb.grc.nasa.gov/pvsee/publications/mars/marspower.html • 6 Scott, Ryan. Arraysize.m. February 8, 2007. Attached. • 7 Landau, Dr. Damon. “Strategies for the Sustained Human Exploration of Mars.” Dec. 2006.

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