- #1

shakeel001

- 7

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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 Determinationhere I am getting q

% Plot resultsI shall be very grateful to all for help in this regards

Thanks again in advance for your time and efforts