A satellite is in a 601 km altitude circular orbit around Earth at an orbital inclination of 6 degrees. What delta-v is necessary to change the orbital inclination to 12 degrees? (Answer should be given in km/s.)
Added by Nancy L.
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The velocity of a satellite in a circular orbit can be calculated using the formula: v = sqrt(GM/r) where: v = velocity of the satellite G = gravitational constant (6.67430 x 10^-11 m^3 kg^-1 s^-2) M = mass of Earth (5.972 x 10^24 kg) r = radius of the orbit Show more…
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