RHSStateLunarMission:

Path: OpticalNavigation/Dynamics

% Right hand side for a lunar mission
 This includes all phases from lunar landing to Earth reentry.
 The reentry vehicle can be controlled using angle of attack and
 bank angle. It does not include fuel consumption.
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   Form:
   [xDot, rMoon, vMoon, aAero, acc] = RHSStateLunarMission(x,t,d)
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   ------
   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 1 is the moon, 2 is the Earth
             .thrust     (3,1) Thrust vector (kN)
             .jD0        (1,1) Reference Julian data (days)
             .uE         (1,1) Exhaust velocity (m/s)
             .mD         (1,1) Dry mass (kg)
             .cD0        (1,1) Zero lift drag coefficent
             .cLAlpha    (1,1) Lift coefficent
             .s          (1,1) Surface area (m^2)
             .alpha      (1,1) Angle of attack (rad)
             .bankAngle  (1,1) Bank angle (rad);

   -------
   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)
   aAero  (3,1) Aerodynamic acceleration (km/s^2)
   acc    (3,1) Total non-gravitational acceleration  (km/s^2)

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Children:

AerospaceUtils: AtmosphericCalculations/AtmDens2
Orbit: OrbitMechanics/APlanet
SC: Ephem/PlanetPosJPL
Common: Database/Constant
Common: Time/JD2000
Math: Linear/Cross
Math: Linear/Mag
Math: Linear/Unit

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