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First time poster in this forum. I am tasked with simulating small satellite dynamics in software this summer. I am new to this and am wondering how such a simulation is carried out. More specifically I am supposed to output the vector [ x y z xdot ydot zdot q1 q2 q3 q4 w1dot w2dot w3dot] to typical force/torque input, where x,y,z are position components, q is the quaternion for the attitude of the satellite, wdot is the angular velocity derivative of the satellite.

I am specifically unclear about where to start. I am guessing the geometry of the satellite is important in this. The satellite is powered by batteries and small CO2 thrusters. I am guessing the thruster positions are also important....How does one put it all together for simulating a typical small satellite, I am talking about something of the order of a cubesat, only in my case the shape is an octagon......

Thanks,

Datri

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# Simulation of small satellite dynamics in software

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