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Problem 3 We have sent a probe from the Earth on a hyperbolic trajectory for an interplanetary mission. The departure point is the perigee of the hyperbola and is on a circular orbit with 7,200-km radius. The mission trajectory has eccentricity of 3.58. Calculate the time-of-flight (in hours) from departure to a point with true anomaly of 115°.

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Answer #1

Ans:

R = 7200 km

e = 3.58

Time of Flight = (r3/µ)1/2(ϴ - esinϴ)

                        = 108137.793 s

                        = 30.0382

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