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Aeronautics Group Taxi Capsule Trajectory Optimization

Explore the Aeronautics Group Taxi Capsule's trajectory optimization with references to mass, geometry, and propulsion in Aeronautics. Study Orion Crew Exploration Vehicle and Transfer Vehicle. Discuss gravitational constants, trajectory calculators, and optimization techniques.

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Aeronautics Group Taxi Capsule Trajectory Optimization

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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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