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Project X pedition

Project X pedition. Spacecraft Senior Design – Spring 2009. https://engineering.purdue.edu/AAE/Academics/Courses/aae450/2009/spring. Motivation: Lunar Payload Delivery. Small Payload. Resupply Lunar Base. Project X pedition Requirements. Land on the Moon Move 500 meters

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Project X pedition

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  1. Project Xpedition Spacecraft Senior Design – Spring 2009 https://engineering.purdue.edu/AAE/Academics/Courses/aae450/2009/spring

  2. Motivation: Lunar Payload Delivery Small Payload Resupply Lunar Base

  3. Project Xpedition Requirements • Land on the Moon • Move 500 meters • Transmit HD pictures and video to Earth • Survive the Lunar Night • Minimize cost with 90% success Project Xpedition

  4. Payloads • 100 g • 10 kg • 1700 kg

  5. Mission Phases • Earth Launch • Lunar Transfer • Lunar Descent • Locomotion 500m

  6. Earth Launch 180 ft 160 ft 110 ft Falcon - 9 Dnepr-1

  7. Earth Launch • Site: BaikonurCosmodrome, Kazakhstan • Cost: $5M 250 Mile Parking Orbit

  8. Orbital Transfer Vehicle Lunar Lander 8’ 880 lbs

  9. Solar Arrays unfold Hall Thruster produces 80 mN of thrust Internal View

  10. Lunar Transfer Attitude Star Sensor Sun Sensor Communication Reaction Wheels Chemical Thrusters S-Band Antenna Power 2 Solar Arrays Lithium-Ion Battery

  11. Lander is self sufficient • 350 lb Lander mass • Half of mass is propellant • 16 mile parking orbit • 2 hour orbital period

  12. Solar Panel Communication Antenna and Motor Camera H2O2 Tank Space Balls Housing Attitude Control Thrusters Radial Flow Hybrid Engine Helium Tank CPU Radiator Attitude Sensors

  13. Apollo 12 Surveyor 3 25 miles Landing Site: Mare Cognitum

  14. Final Descent Attitude: 12 Control Thrusters Translation: Radial Flow Hybrid Engine Mission Requirements Land on Moon Move Payload 500 m Survive Lunar Night

  15. Dust Removal Vibration Motor Lexan Shell Communications Transceiver Battery Main Axel and Motor Housing CPU Camera 100g Payload

  16. Mission Requirements Minimum Turning Radius: 2.5 in Land on Moon Move 500m Take Picture Survive Night Avoiding Obstacle Taking Photo of Lander Removing Dust All Systems Are GO! Cruise Speed: 3.2 mph -280 °F

  17. 10 kg Payload 10 kg Lunar Lander Mission Requirements 230 lbs Lander 270 lbs Propellant 500 lbs Total Land on Moon Move 500m Take Picture Survive Night Hybrid Engine Thrust: 45 lbs Burn Time: 135 sec

  18. Mission Requirements Land on Moon Move 500m Take Picture Survive Night Record Video 500m

  19. Completed lunar descent • Full stop • Begin locomotion Large Payload 300 ft Attitude Thrusters • 16 ft Main Engine Avg. Thrust: 230 lbs Burn time: 60 s • 6 ft

  20. Mission Requirements: Move 500 meters Land on moon Resupply base

  21. Cost Per Kilogram Mission Cost $271Million $223 Million 92% Success $30 Million 72% Success $27 Million 72% Success $3 Million $130k $27M Cost - $22M Prize = $5M Net Mission Cost

  22. Project Xpedition Results Payload Delivery: Most economical payload: 2 tons Electric Propulsion for Lunar transfer Soft land on Lunar surface Google Lunar X PRIZE: Several viable locomotion methods Potential to open commercial market $27M mission accomplished for $5M

  23. Question & Answer Project Xpedition https://engineering.purdue.edu/AAE/Academics/Courses/aae450/2009/spring

  24. Backup Slide Listing Solomon Westerman Attitude Brian Erson Kris Ezra Christine Troy Brittany Waletzko Propulsion Brad Appel Thaddaeus Halsmer Ryan Lehto Saad Tanvir Mission Operations John Aitchison Cory Alban Levi Brown Andrew Damon Alex Whiteman Power Tony Cofer AdhamFahkry Jeff Knowlton Ian Meginnis Communications Mike Christopher John Dixon Trent Muller Structures & Thermal Kelly Leffel Caitlyn McKay Ryan Nelson

  25. Backup SlidesSaad Tanvir Return to Listing

  26. Propulsion System Mass Finals 10 kg Payload case (Hopper) Propellant mass = 121.2 kg Propulsion System Inert mass = 45.4 kg Total Prop System Mass = 166.6 kg Return to Listing 100 g Payload case (Ball) Propellant mass = 78.2 kg Propulsion System Inert mass = 29.9 kg Total Prop System Mass = 108.1 kg Arbitrary Payload case (Falcon 9) Propellant mass = 1783.62 kg Propulsion System Inert mass = 227 kg Total Prop System Mass = 2010.62 kg Saad Tanvir Propulsion Group 2

  27. 100 g – Hybrid Propulsion System Mass Breakdown Return to Listing 3

  28. 10 kg – Hybrid Propulsion System Mass Breakdown Return to Listing 4

  29. Large payload – Hybrid Propulsion System Mass Breakdown Return to Listing 5

  30. Propellant Tank Specifications Return to Listing 6

  31. Pressurant Tank Specifications Return to Listing 7

  32. Hydrogen Peroxide Tanks - Thermodynamic Analysis Assumptions: Tank operating Temperature = 283 K (50 F) Surrounding Temperature = 2.73 K Power Required ~ 35 W ΔT = 280.3 K Q: Rate of Heat transfer [W] A: Area of Cross section of the tank [m2] k: Thermal Conductivity [0.044 W/mK] ΔT: Temperature Difference [K] t: Thickness of the blanket [200 mm] Return to Listing 8

  33. Lunar Descent – Thermodynamic Analysis on Prop System Temperature Drop < 5 K No power required to heat the propulsion system during Lunar Descent Return to Listing 9

  34. Propellant Tank – Operating Pressure Pchamber = 2.07 MPa ∆Pdynamic = ½𝜌v2 ~ 0.072 MPa ∆Pfeed (Upper bound) ~ 0.05 MPa ∆Pcool ~ 0.15pc = 0.31 MPa ∆Pinjector ~ 0.3pc = 0.62 Mpa Ptank~ 3.07 MPa Return to Listing 10

  35. Lunar Transfer: Chemical Alternative Significant mass savings using the Electric Propulsion system Return to Listing 11

  36. Backup SlidesChristine Troy Return to Listing

  37. 12 General Kinetics H2O2 thrusters Lander Side view Lander Top view Lander Attitude Control Return to Listing

  38. Based on Rauschenbakh, Ovchinnikov, and McKenna-Lawlor . . θ θ +θ1 +θ1 θ θ -θ1 -θ1 No External Torque “Large” External Torque Attitude Prop Mass Estimate Mb = external moment applied g = gravitational acceleration Isp = specific impulse of thrusters L = distance from thruster to vehicle center of mass Return to Listing

  39. Spinning Lander Attitude Control • Propellant and thrusters still needed for spin up and axis reorientation • Estimate ~2.2 kg propellant savings for 100g/10kg cases • Additional mass: spinning landing gear, propulsion system redesigns, additional attitude sensing devices • Increased complexity: Liquid propellant feed while spinning, landing while spinning, reorientation of axis Return to Listing

  40. Some or all travel could be obtained from bouncing using stored descent energy Compressed gas not recommended – highly temperature sensitive, limited velocity and acceleration inputs Commercial gas springs limited to approx. -23° to 82° Lunar surface temperature -153° to 107° C Compressed Gas Spring Energy Storage Return to Listing

  41. Backup SlidesBrittany Waletzko Return to Listing

  42. Systems Overview Large Payload 10kg Payload Return to Listing 100g Payload

  43. Mission Timelines (Backup) 100g Payload Mission Timeline 10kg Payload Mission Timeline Elapsed Time given in days, hours, and minutes 100g and 10kg Payload Return to Listing

  44. Mission Timelines—cont. (Backup) Large Payload Mission Timeline Large Payload Elapsed Time given in days, hours, and minutes Return to Listing

  45. Trajectory Correction (backup) T = instantaneous thrust (assumed constant over interval) m = instantaneous mass (assumed constant over interval) Return to Listing

  46. Thruster Locations and Thrust Direction Vectors Return to Listing

  47. Hydrazine and Hydrogen Peroxide Thrusters Return to Listing

  48. Environmental Forces Codes Return to Listing

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