An earth satellite is in an orbit with perigee altitude zp = 400 km and an eccentricity e = 0.6. Find (a) the perigee velocity, vp ; (b) the apogee radius, ra ; (c) the semimajor axis, a;
An earth satellite is in an orbit with perigee altitude zp = 400 km and an eccentricity e = 0.6. Find (a) the perigee velocity, vp ; (b) the apogee radius, ra ; (c) the semimajor axis, a;
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An earth satellite is in an orbit with perigee altitude zp = 400 km and an eccentricity
e = 0.6. Find (a) the perigee velocity, vp ; (b) the apogee radius, ra ; (c) the semimajor
axis, a; (d) the true-anomaly-averaged radius ̄rθ ; (e) the apogee velocity; (f ) the period of the orbit.
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