I need to convert quaternion (q) to a form that is suitable to show changing attitude of a Satellite. like new x,y,z vectors of a satellite.I dont know the math of quaternions. I am getting updated state using rung -kutta 4 method where state vector x=[q(1:4) wx wy wz a(1:3) b(1:3)].I can convert quaternion to euler angles but dont know further how to convert these to x,y,z of a satellite(updated) which will tell x,y,z position of a satellite after its state vector(x) was updated.(adsbygoogle = window.adsbygoogle || []).push({});

the sequence of operations I am doing are

% Simulation data

% Spacecraft data

% Gyro data

% Sensor data.

% Control system initialization

% Generate the orbit

% el = [a,i,W,w,e,M]. The spacecraft is in geostationary orbit

% Initial conditions at equinox

% Sun and earth vectors

% Run the simulation

here I am using RK4 for solving differential equation which is giving me an updated state vector x% Attitude Determination

here I am getting q% Plot results

I shall be very grateful to all for help in this regards

Thanks again in advance for your time and efforts

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# Quaternion conversion in satellite attitude using sun-earth sensors simulation

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