Calculate the delta velocity required to change inclination

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Reference no: EM13706682

Calculate the delta velocity required to change the inclination of a circular orbit at 32,000 km altitude from a 28.5 degree inclination to an inclination of 45 degrees. Compute the propellant used if the satellite weighs 1200 lbs after the maneuver.

Reference no: EM13706682

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Calculate the delta velocity required to change inclination : Calculate the delta velocity required to change the inclination of a circular orbit at 32,000 km altitude from a 28.5 degree inclination to an inclination of 45 degrees. Compute the propellant used if the satellite weighs 1200 lbs after the maneuver.

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