A spacecraft departs from Earth in a hyperbolic trajectory with a periapsis velocity of 12.5 km/s at an altitude of 250 km. Answer the following questions: (a) Find the value of the semi-major axis, a, of the hyperbolic trajectory. (b) Find the hyperbolic excess velocity. (c) Find the radius (magnitude) when the true anomaly is 95 deg. (d) Find the velocity (magnitude) when the true anomaly is 95 deg. (e) Calculate the time required to reach the true anomaly of 95 deg from the periapsis. (f) What will be the true anomaly at the point where the spacecraft leaves Earth's sphere of influence? Assume: Earth: Mass = 5.927 x 1024 kg, µp = 3.986 x 1014 m3/s², radius = 6378 km, distance from the Sun = 149.6 mission km, Sun: Mass = 1.989 x 1030 kg, Hs = 1.327 x 1020 m/s2,

A spacecraft departs from Earth in a hyperbolic trajectory with a periapsis velocity of 12.5 km/s at an altitude of 250 km. Answer the following questions: (a) Find the value of the semi-major axis, a, of the hyperbolic trajectory. (b) Find the hyperbolic excess velocity. (c) Find the radius (magnitude) when the true anomaly is 95 deg. (d) Find the velocity (magnitude) when the true anomaly is 95 deg. (e) Calculate the time required to reach the true anomaly of 95 deg from the periapsis. (f) What will be the true anomaly at the point where the spacecraft leaves Earth's sphere of influence? Assume: Earth: Mass = 5.927 x 1024 kg, µp = 3.986 x 1014 m3/s², radius = 6378 km, distance from the Sun = 149.6 mission km, Sun: Mass = 1.989 x 1030 kg, Hs = 1.327 x 1020 m/s2,

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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