Path: OpticalNavigation/Dynamics
% Right hand side for a lunar mission
The reentry vehicle can be controlled using angle of attack and
bank angle. It calls RHSStateLunarMission.
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Form:
d = RHSLunarMission;
[xDot, rMoon, vMoon, aAero, acc] = RHSCisLunarMission(x,t,d)
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Inputs
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x (7,1) [r;v;m] (km,km/s,kg)
t (1,1) Time (s)
d (.) Data structure
.mu (2,1) [mu Earth; mu Moon] (km^3/s^2)..
.ref (1,1) Orbit reference
.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);
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Outputs
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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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See also RHSStateLunarMission
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OpticalNavigation: Dynamics/RHSStateLunarMission Math: Linear/Mag
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