Path: Interplanetary/OrbitInsertion
% Simulate a 2D planetary approach
Models a rocket with throttle approaching a point mass planet.
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Form:
Simulate2DApproach( t, x0, phi, a, d, name )
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Inputs
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t (1,:) Time vector
x0 (4,1) Initial state [r;u;v;theta]
phi (1,:) Thrust angle (rad)
a (1,:) Acceleration due to the rocket (0-1)
d (.) Data structure describing spacecraft model
.mu (1,1) Gravity
.a (1,1) Throttle (-1 to 1)
.aMax (1,1) Max accel
name (1,:) Name for the plots
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Outputs
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x (4,:) [r;v] Cartesian position and velocity (km,km/s)
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SC: BasicOrbit/El2RV SC: BasicOrbit/Nu2M Common: Graphics/Plot2D Common: Graphics/TimeLabl Math: Integration/RK45 Math: Linear/Cross Math: Linear/Dot Math: Linear/Mag Math: Linear/Unit
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