Path: OpticalNavigation/Dynamics
% Right hand side for a lunar mission for use in the UKF.
The reentry vehicle can be controlled using angle of attack and
bank angle.
--------------------------------------------------------------------------
Form:
[xDot, rMoon, vMoon] = RHSUKFCisLunarMission(x,t,d)
--------------------------------------------------------------------------
------
Inputs
------
x (6,1) [r;v;m] (km,km/s)
t (1,1) Time (s)
d (.) Data structure
.mu (2,1) [mu Earth; mu Moon] (km^3/s^2)..
.ref (1,1) Orbit reference
.mD (1,1) Dry mass (kg)
-------
Outputs
-------
xDot (7,1) d[r;v;m/dt] (km,km/s,kg)
rMoon (3,1) Position of moon in ECI (km)
vMoon (3,1) Velocity of moon in ECI (km/s)
--------------------------------------------------------------------------
Orbit: OrbitMechanics/APlanet SC: Ephem/PlanetPosJPL Common: Database/Constant Common: Time/JD2000 Math: Linear/Mag
Back to the OpticalNavigation Module page