Path: LunarMissions/LunarLanding
% Generate the orbit state matrices
The matrices are ax = b
x is the vector of decision variables or controls
The order is [x1;x2;x3;...;xN] where each x is a vector
xI is only used to compute the term mu/R^3. A constant xI is
sufficient for most low-altitude landings.
Type OrbitStateMatrices for a demo.
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Form:
[a,b,xF0,aX,bX] = OrbitStateMatrices( xI, xF, dT, d )
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Inputs
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x (6,:) States [x;y;z;vX;vY;vZ]
xF (6,:) Final desired state [x;y;z;vX;vY;vZ]
dT (1,1) Delta time
d (.) Data structure describing spacecraft model
.beta (1,:) Thrust angle in rv plane
.alpha (1,:) Thrust angle out of plane
.thrust (1,:) Thrust (N)
.accel (1,:) 'constant' or 'free'
.m0 (1,1) Dry mass
.radius (1,1) Planet radius
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Outputs
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a (6,3*n) Matrix multiplying the decision variables
b (6,1) Right hand side
xF0 (6,1) Final state without control
aX {n} Cell array of state transition matrices
bX {n} Cell array of input matrices
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LunarMissions: LunarLanding/RHSPlanet3D LunarMissions: LunarLanding/RHSPlanet3DToAB SC: BasicOrbit/Period Common: General/DispWithTitle
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