Delta velocity required to change inclination of orbit

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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. Use an Isp of 290 sec.

Reference no: EM13707415

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