1. AAE450 Senior Spacecraft Design Poliskie - 1 T.J. Poliskie Week 7: March 1, 2007 Propulsion Earth Taxi, Mars Taxi Group Updated Propulsion System Analysis

2. AAE450 Senior Spacecraft Design Poliskie - 2 Mars Taxi Propulsion Inert Mass –Payload – 7.3322 mt –Tank Mass – 4.29 mt –Cryocooler Mass – 110 kg –Prop. System Mass – 1500 kg –ZBO Power – 683.8 W Performance Specs –Propellant Mass – 32.57 mt –Gross Lift-Off Mass – 44.31 mt –Mass Flow – 130.29 kg/s –Thrust – 574.9 kN –Burn Time – 250 sec Drawing – Steve Kassab

3. AAE450 Senior Spacecraft Design Poliskie - 3 Earth Taxi Propulsion Inert Mass – Payload - 23.4935 mt – Tank Mass - 5.19 mt –Cryocooler Mass – 117 kg –Prop. System Mass – 500 kg –ZBO Power – 703.4 W Performance Specs – Propellant Mass - 29.85 mt –System Total Mass – 59.15 mt –Mass Flow – 59.70 kg/s –Thrust – 263.5 kN –Burn Time – 500 sec

4. AAE450 Senior Spacecraft Design Poliskie - 4 Backup Slides

5. AAE450 Senior Spacecraft Design Poliskie - 5 Mars Taxi Gravity Loss Use a gradual rollover to achieve tangential velocity

6. AAE450 Senior Spacecraft Design Poliskie - 6 Altitude and Trajectoy vs. Time

7. AAE450 Senior Spacecraft Design Poliskie - 7 Velocity w/respect to Altitude

8. AAE450 Senior Spacecraft Design Poliskie - 8 Cryocooler Sizing 2 function [ip,m] = cryocooler(qc,th,tc,eta) sigma = -1.7359+0.59998*log(qc)- 0.14740*log(qc^2)+0.021323*log(qc^3)- 0.0012502*log(qc^4); P = qc*(th-tc)/(tc*eta*10^sigma) m = 0.2*qc^0.7*((th-tc)/tc)^1.45

9. AAE450 Senior Spacecraft Design Poliskie - 9 References 1.Glaister, D.S. et al, “An assessment of the State of Cryocooler Technology for Space Applications,” IEEE Aerospace Conference Aspen, CO 1999 2.Plachta, David and Kittel, Peter. “An Updated Zero Boil-Off Cryogenic Propellant Storage Analysis Applied to Upper Stages or Depots in an LEO Environment 3.Cervone, Angelo; Rapposelli, Emilio; D’Agostino Luca. A Simplified for the Evaluation of delta-v of Ascent Trajectories. AIAA 2005-4507