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Ben Jamison Week 3: February 1st, 2007

Ben Jamison Week 3: February 1st, 2007. Aeronautics Group Taxi Capsule Group. Taxi Capsule. Mass Propellant = 6.057 mt Mass Heat Shield = 2.762 mt Total Mass = 43.02 mt Total Volume = 6082 m^3. Orion Crew Exploration Vehicle - Total Mass = 23 mt. Transfer Vehicle. Geometry. Trajectory.

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Ben Jamison Week 3: February 1st, 2007

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  1. Ben JamisonWeek 3: February 1st, 2007 Aeronautics Group Taxi Capsule Group

  2. Taxi Capsule • Mass Propellant = 6.057 mt • Mass Heat Shield = 2.762 mt • Total Mass = 43.02 mt • Total Volume = 6082 m^3 Orion Crew Exploration Vehicle - Total Mass = 23 mt

  3. Transfer Vehicle Geometry Trajectory

  4. Optimization

  5. Reference Slides • rho = Atmos_Prop_Density(h) • D_W = cd*A*rho/(2*mass*g0_mars)*V^2 • Vc = sqrt((h+r_mars)*g0_mars) • Position = V*cos(alfa) • Velocity = -g0_mars*(D_W+sin(alfa)) • alfa = -(g0_mars/V)*(1-(V/Vc)^2*cos(alfa)) • altitude = V*sin(alfa) • qdot = R^2*sqrt(rho/rho_sl/radius)*V^3

  6. g0_earth = 9.80; %earth gravitational constant • g0_mars = 3.71; %mars gravitational constant (m*s^-2) • t_h = 60; %hover time (s) • rho_p = 1; %density of propellant (kg*m^-3) • g_max = 10; %maximum G load • v_f_initial = 500; %intial guess at final velociy • mass_h = 1000; %inital guess at heat shield mass • c_heat = 2.1e-10; %heat sheild qdot relation (kg/watts) (?) • cd = .07; %Drag coefficient of a sphere • r_mars = 3397e3; %Mars equatorial radius [m] • gamma = 1.29; %Specific heat ratio • R_gas = 191.8; %Universal Gas Constant for Mars [J/kg/K] • T_melt = 2000; %maximum allowable temperature on heat sheild • eps = 1; %emissivity • sigma = 5.67e-8; %stefan boltzman constant (W*m^-2*K^-4) • t_final = 1e5; %max trajectory time • mass_h_tol = 1000; %Tolorance for heat shield mass • v_f_tol = 1000; %Tolorance for final velocity • Xo = -3000; %Initial position [m] • ho = 100000; %Initial Altitude [m] • Vo = sqrt((ho+r_mars)*g0_mars); %Initial Velocity [m/s^2] • alfa_o = 0; %Initial Flight entry angle [radians]

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