Ben jamison week 3 february 1st 2007
This presentation is the property of its rightful owner.
Sponsored Links
1 / 6

Ben Jamison Week 3: February 1st, 2007 PowerPoint PPT Presentation


  • 43 Views
  • Uploaded on
  • Presentation posted in: General

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.

Download Presentation

Ben Jamison Week 3: February 1st, 2007

An Image/Link below is provided (as is) to download presentation

Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author.While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server.


- - - - - - - - - - - - - - - - - - - - - - - - - - E N D - - - - - - - - - - - - - - - - - - - - - - - - - -

Presentation Transcript


Ben jamison week 3 february 1st 2007

Ben JamisonWeek 3: February 1st, 2007

Aeronautics Group

Taxi Capsule Group


Taxi capsule

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

Transfer Vehicle

Geometry

Trajectory


Optimization

Optimization


Reference slides

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


Ben jamison week 3 february 1st 2007

  • 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]


  • Login