Path: Interplanetary/Landers
% Parachute descent simulation
Simulates descent from deployment of the parachute until the altitude is
zero. It also computes the parachute mass and terminal velocity. You can
pass it any atmosphere function of the form rho = fun(h) where h is in
km, such as AtmDensMars2.
Type Parachute for a demo at Mars. If there are no outputs a plot is
generated.
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Form:
Parachute; % demo
[xP,vTerm,mPara] = ParachuteSim(h,v,a,g,m,rho,cD,atmModel)
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Inputs
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h (1,1) Starting altitude (m)
v (1,1) Initial velocity (m/s)
a (1,1) Parachute area (m^2)
g (1,1) Acceleration of gravity (m/s^2)
m (1,1) Supported mass (kg)
rho (1.1) Areal density of the parachute (kg/m^2)
cD (1,1) Drag coefficient, typically 0.75
atmModel (@) Pointer to atmospheric density model function
rho = fun(h) where h is in km
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Outputs
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xP (5,:) [x;v;f;fNet;rho]
vTerm (1,1) Terminal velocity (m/s)
mPara (1,1) Mass parachute (kg)
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Interplanetary: Environment/AtmDensMars2 Common: Database/Constant Common: Graphics/TimeHistory Math: Integration/RK4
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