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

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

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

AAE450 Senior Spacecraft Design Poliskie - 4 Backup Slides

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

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

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

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

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 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