Path: Orbit/RHSOrbit
% Orbit model for low thrust escapes.
Designed for use with ode113. Includes a state for the mass and for the
total delta-V, obtained by integrating the applied acceleration. Thrust
and uE are treated as constant.
See also LowThrustSim.
--------------------------------------------------------------------------
Form:
vargout = FOrbLTE( t, x, flag, d )
--------------------------------------------------------------------------
------
Inputs
------
t Time
x (n,1) The state vector [r;v;m;DV]
flag (1,:) Flags for ode113
d (1,1) Data structure
.thrust Engine thrust (N)
.mu Gravitational parameter
.uE Exhuast velocity (m/s)
-------
Outputs
-------
xDot (n,1) The state vector derivative d[r1;v1;r2;v2...]/dt
--------------------------------------------------------------------------
Math: Linear/Mag Math: Linear/Unit
Back to the Orbit Module page