1. AAE450 Senior Spacecraft Design Ben Jamison Week 5: February 15th, 2007 Aeronautics Group Taxi Capsule Vehicle Group ET/MT Group Integration Group

2. AAE450 Senior Spacecraft Design Ben Jamison ARES V ET TC/CC TCV Surface of Earth SE to LEO LEO to HEO TCV docks w/ TV Arrive at HMO Orbital Decay entry to Mars Surface TCV Lands on Mars Surface TC/CC loaded onto of MT MS to HMO TC/CC docks w/ TV Arrive HEO TC/CC re- enters Earth Atmosphere Crew returned safely to Earth

3. AAE450 Senior Spacecraft Design Taxi Capsule Vehicle Ben Jamison Design Inputs - Payload Mass = 5 mt - Payload Volume = 25 m^3 - eta =.2 - Isp = 450 sec (for landing thrusters) 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 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. AAE450 Senior Spacecraft Design Reference Slides

5. AAE450 Senior Spacecraft Design TCV Layout Original picture taken from Breanne Wooten

6. AAE450 Senior Spacecraft Design Trajectory does not yet include parachute

7. AAE450 Senior Spacecraft Design 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. AAE450 Senior Spacecraft Design 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)))