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Suppose that I am launching a cubesat into space. Let the cubesat be launched from the P-POD deployer. Since the satellite will have a huge velocity, hence the detumbling mode will be operating. As soon as the cubesat has completely detumbled, I wish to determine the initial quarternion of the cubesat with respect to an inertial frame of reference. How should I go about it?

I cannot determine it using TRIAD algorithm as the satellite will just immediately be launched, hence the sun sensors and magnetometers might not be active by the time the satellite has detumbled. Also how will I find the relation between the satellite frame of reference and the inertial frame of reference?

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    $\begingroup$ Seems to me that you your attitude will be totally unknown until you turn on at least one sensor. $\endgroup$ – Chris Jan 15 '18 at 0:18

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