I need all parts of 3-15 and 3-17 please!! a = the semi major axis p = semi latu

Question

I need all parts of 3-15 and 3-17 please!!

a = the semi major axis

p = semi latus rectum

P = period

H = specific angular momentum

E = specific energy for a particular orbit

rp = periapasis

ra = apoapsis

Vp = the velocity at periapsis

A satellite has been carried to a 175-nmi (322-km) circular orbit by a Space Shuttle. The mission objective is to place the satellite into an elliptical orbit with a perigee of 600 nmi (1104 km) and an eccentricity of 0.80. Find the characteristics of the ellipse: a, E, H, r_p, r_0, V_p, V_a, p and P. Find delta V_T, epsilon_r, and TOF for a Hohmann transfer from the circular orbit to the perigee of the ellipse. Sketch the transfer trajectory. Find Delta V_t, epsilon_r, and TOF for a Hohmann transfer to the apogee of the ellipse. Sketch the transfer trajectory. Of the two delta V_T's from parts (b) end (c), which is larger? Can you explain why? Two geocentric elliptical orbits have aligned major axes and their perigees on the same side of the Earth. The first orbit has an r_p = 7.0 times 10^6 m and epsilon = 0.3, whereas the second orbit has an r_p = 32 times 10^6 m and epsilon = 0.50. Find the minimum Delta V_T and the TOF and epsilon, for a transfer from the perigee of the inner orbit to the apogee of the outer orbit. Sketch the transfer. Do part (a) for a transfer from the apogee of the inner orbit to the perigee of the outer orbit. Compare the delta V_T's and TOFs and explain any differences.

Explanation / Answer

minimum Vt = 7 * 106 * sqrt(1 - 0.32)/65

                    = 1.027 * 105 m/s

a = 2 * 322 = 644 km

p =   644/3 = 214.66 km

period = 2pi/(5.4 * 10-6)

            = 323 hours

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