I am working on sun earth attitude determination simulation for my satellite in MATLAB using SCT(space craft control toolbox)I have my keplerian elements for my satellite.I have some initial conditions for orbit setting or satellite is known.I need to use RK4 method for quaternion/state variables determination.How can I get initial control law values (like wx,wy,wz) where state vector is defined as x=[q(1:4) wx wy wz a1 a2 a3 b1 b2 b3] from my keplerian element or known initial conditions of satellite.(adsbygoogle = window.adsbygoogle || []).push({});

I dont know whether the following statement is true

"using six keplerian elements is 6DOF problem but for attitude determination I am only interested in quaternion which is of four variables" so should RK4 means 4DOF

any help or tutorial and explanation in this regard is highly regarded

shakeel

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# Satellite using rung-kutta method for 4DOF or 6DOF simulation

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