Assume the average Earth Radius RE = 6378 km: Based on the following information: After finishing its mission, a small spacecraft departs its low-Earth orbit and reaches its entry interface altitude of hEI = 122 km at a velocity of vEI = 6.825 km/s and a flight-path angle of EI = 6.2. The spacecraft is a spherical entry vehicle (with a drag coefficient of CD = 2.1) and follows a ballistic trajectory. The spacecraft has a mass of m = 7660 kg and a diameter of d = 3.6 m. Use 4 decimal places in your calculations and answers and please be as detailed as possible for the formulas thank you I am learning! Calculate the ballistic coefficient (CB) for the spacecraft. Calculate the dimensionless constant, B for this re-entry profile. Calculate the velocity (v) of the ballistic entry at the following altitudes: (a) h = 75 km, (b) h = 60 km, and (c) h = 45 km. Calculate the deceleration (a) experienced by the spacecraft in Gs at the following altitudes: (a) h = 75 km, (b) h = 60 km, and (c) h = 45 km. Calculate the peak deceleration force (amax) in Gs for the spacecraft