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Mechanical Engineering

Sam F Mead

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  1. Hi there! Im currently a bit stuck on one section of a project I am currently undertaking. The project concerns a deployable panel system fitted to a 1U (10x10x10cm) cube satellite, orbiting at an altitude of 600km. I have calculated the effect of atmospheric drag on the satellite to be equal to 2.016*10^-8, so...my question is this, when the panels are collapsed (ie the shape is symmetrical), then the system is in equilibrium, if i were to open one panel on one side of the satellite (offsetting its centre of mass and therefore making the forces acting on the system unequal), am I correct in saying that the satellite will pivot? So as you can see from the diagram below, I have calculated the moments about the centre of the satellite to be: Ma = (0.05 * (2.016*10^-8)) - (0.1 (2.016*10^-8)) = -1.008*10^-9 Nm Is this correct? If so would it cause the satellite to pivot around the centre of mass? Lastly is there a way to work out the rate of its rotation? Thanks for any help anyone can offer! Im just a bit confused!! Sam :)
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