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Re: Bravo to the command team!

>Thus a thrust component directed toward the spacecraft's spin-stabilized
>orientation was added to the above computations.  The amount of [estimated]
>thrust was varied in the calculations until there was a match to AO-40's
>observed orbital behavior.  This more or less corroborated the propellant
>leak hypothesis.  Furthermore, finding a good fit for the thrust gives an
>excellent estimate of the rate at which the propellant mass is being lost.

What is the size of this thrust (acceleration, actually) in m/sec^2?

How can the propellant mass loss rate be computed from this without knowing
the velocity at which it is being dumped overboard?

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