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Ben Jamison Week 5: February 15th, 2007

Ben Jamison Week 5: February 15th, 2007. Aeronautics Group Taxi Capsule Vehicle Group ET/MT Group Integration Group. TCV docks w/ TV. Ben Jamison. TC/CC docks w/ TV. Arrive at HMO. LEO to HEO. Arrive HEO. MS to HMO. Orbital Decay entry to Mars Surface. SE to LEO.

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Ben Jamison Week 5: February 15th, 2007

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  1. Ben JamisonWeek 5: February 15th, 2007 Aeronautics Group Taxi Capsule Vehicle Group ET/MT Group Integration Group

  2. TCV docks w/ TV Ben Jamison TC/CC docks w/ TV Arrive at HMO LEO to HEO Arrive HEO MS to HMO Orbital Decay entry to Mars Surface SE to LEO TC/CC re-enters Earth Atmosphere TCV TC/CC ET TCV Lands on Mars Surface TC/CC loaded onto of MT ARES V Crew returned safely to Earth Surface of Earth

  3. Ben Jamison Taxi Capsule Vehicle Vehicle Geometry Width = 8.866 m Height = 7 m Frontal Area = 247 m^2 Volume Propellant = 21 m^3 - LOX = 1.231 m^3 - LH2 = 19.77 m^3 Total Volume = 46 m^3 Vehicle Mass Properties Mass payload = 5 mt Mass propellant = 2.808 mt Mass Heat Shield = 8.711 mt Inert mass = 4.128 Total mass = 20.64 mt Design Inputs - Payload Mass = 5 mt - Payload Volume = 25 m^3 - eta = .2 - Isp = 450 sec (for landing thrusters) Payload includes: -Taxi Capsule Crew Compartment (TC/CC) - Mars Landing System -Thrusters for 60s hover + Propellant -Parachute System - Maneuvering Thrusters for docking w/ the TV

  4. Reference Slides

  5. TCV Layout Original picture taken from Breanne Wooten

  6. Trajectory does not yet include parachute

  7. Variables for EOMs • Cd = coefficient of drag • A = Frontal Area • Mass = total mass TCV • g0_mars = acceleration due to gravity on mars • R_mars = radius of mars • t_final = time at H = 0 • Radius = curvature of radius of nose • Tw = Heat at the nose • Rho_sl = density at mars sea level • Rho = density as a function of altitude • D_W = cd*A*rho/(2*mass*g0_mars)*V^2 …Drag to Weight of Vehicle • Vc = sqrt(h+r_mars)*g0_mars …Spin rate of planet (Mars)

  8. EOMs • X = S(1) Position • V = S(2) Velocity • Alfa = S(3) Angle of attack • H = S(4) Altitude • Q_dot_conv = S(5) Convective heating rate • Cp = S(6) Coefficient of Pressure at nose • Q_dot_rad = S(7) Radiative heat rate • dS(1) = V*cos(alfa) • dS(2) = -g0_mars*(D_W+sin(alfa)) • dS(3) = -(g0_mars/V)*(1-(V/Vc)^2*cos(alfa)) • dS(4) = V*sin(alfa) • dS(5) = sqrt(rho/rho_sl/radius)*V^3 • dS(6) = 2*cos(alfa)^2 • dS(7) = 1.83e-5*(rho/radius)^.5*V^3.04*(1-((cp*Tw)/.5*V^2)))

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