A certain satellite has eccentricity of 9.5981 x 10-3 and its semimajor axis is known to be 7194.9 km. The true anomaly v of the satellite is 204.81° and the mean motion is 14.2171404 rev/day. Calculate i. ii. iii. iv. V. the orbital period of the satellite in minutes. the magnitude of position vector r. position vector r in PQW frame. altitude of the satellite at zenith. satellite velocity at epoch
A certain satellite has eccentricity of 9.5981 x 10-3 and its semimajor axis is known to be 7194.9 km. The true anomaly v of the satellite is 204.81° and the mean motion is 14.2171404 rev/day. Calculate i. ii. iii. iv. V. the orbital period of the satellite in minutes. the magnitude of position vector r. position vector r in PQW frame. altitude of the satellite at zenith. satellite velocity at epoch
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A certain satellite has eccentricity of 9.5981 x 10-3 and its semimajor axis is known
to be 7194.9 km. The true anomaly v of the satellite is 204.81° and the mean motion
is 14.2171404 rev/day. Calculate
i.
ii.
iii.
iv.
V.
Given the orbital elements of a particular satellite are:
(i)
the orbital period of the satellite in minutes.
the magnitude of position vector r.
position vector r in PQW frame.
altitude of the satellite at zenith.
satellite velocity at epoch
(ii)
= 300°; w = 60°; i = 65°; rp = -6500 km; ro = 4000 km
Calculate the position vector r in the IJK frame.
Calculate the magnitude of position vector.
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