6. 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 radiusr¯0; (e) %3D
6. 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 radiusr¯0; (e) %3D
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Transcribed Image Text:6. 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 radiusr¯e; (e)
the apogee velocity; (f) the period
of the orbit; (g) the true anomaly when r = ¯re; (h) the
satellite speed when r = ¯r0;
(i) the flight path angle y when r = "re; (j) the
maximum flight path angle ymax and
the true anomaly at which it occurs.
Transcribed Image Text:Constants:
u = 3.986*10^5 ( Km^3/S^2), if you don't like
exponents, this translates to (398,600 Km^3/S^2)
Radius of Earth = 6378Km
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