Readings and Read Chapter 2 of our Textbook. then Respond the Following Questions [Assume the average Earth Radius RE = ['53 23 km}: 1. Using Newton's Law of Universal Gravitation [G= 15.62.13 IiiH N'mjigz] Calculate the average gravitational pull between the Earth and the Sun. The mass of the Sun iss'lcfh = 1.93913: 103'\"? kg and the mass ofthe Earth is mEmh = 5.9?323: 1924 kg. 1 an 149,592,821 km. [a Points-l 2. A satellite is orbiting the Earth at an altitude of a' = 242 km . lts inertial velocityI of'l'l = 3.95 W5 and its flight-path angle is 2 = 14'\". a. Determine the total specific energy.r [ft for this orbit. Use 2 decimal places. [4 Points] b. Determine the semimajor axis [oi for the satellite. Use 2 decimal places. [4 Pointsi c. What is the angular momentum [Eli of the satellite? Use 2 decimal places. [4 Points".I d. Determine the parameter [pi for this orbit. Use 2 decimal places. [4 Points] e. Calculate the eccentricitv [E] of this orbit and identify.r the sh ape of the orbit. Use 4- decimal places. [6 Pointsi 3. A low-Earth satellite orbits at an average altitude of RE: 323 km and has a parameter of}? = 2224' km. a. Determine the total specific energv [it for the orbit. Use 2 decimal places. [4 Points] b. Determine the angular momentum [ll of this satellite. Use 2 decimal places. [4 Points] c. Determine the ecce ntricitv [E] of this orbit. Use 4 decimal places. [4 Points} d. Calculate the Perigee radius {Tip} for this orbit. Will this satellite pass through anv noticeable part of the Earth's atmosphere? Use 2 decimal places. [6 Points] e. Calculate the Apogee altitude [aha] for this orbit. Use 2 decimal places. [5 Points} 4. A satellite has an apogee altitude of {Ilia = mu huand a perigee altitude of REP = 5:29 .ib'n. The true anomalv is currentlv If]: I315\". a. Calculate the semimajor axis [a] for this orbit. [4 Points] b. Calculate the eccentricitv [E] of this orbit. Use 4 decimal places [4 Points] c. Determine the parameter [pi for this orbit. Use 2 decimal places. [4 Points] d. Calculate the angular momentum [It] for this satellite. Use 2 decimal places. [4 Points] e. Calculate the total specific energyI [If] for this orbit. Use 2 decimal places. [4 Points} f. Determine the current radius [f] of the orbit [at E3: 235]. Use 2 decimal places. [5 Points} g. What is current velocitv [vlof the satellite [at If}t = 135]? Use 2 decimal places. [5 Points}I h. What is the current flight path angle [ft] of the satellite [at = 2355? Use 2 decimal places. [5 Points] 5. A satellite has a verv elliptical orbit with an apogee altitude of Rita = 265622 km and a perigee altitude of HEP = 222 km. a. What is the semimajor axis to} for this orbit? [4 Points] b. What is the ecce ntricitv [Ell of this orbit? Use 4 decimal places. [4 Points] c. Calculate the orbital period [Tram-mi} for this orbit. Express your final answer in davs. minutes. and seconds. Express vour answer in hours. minutes. and seconds [i.e.. [2:25:23 or [2 It}; 25 mill-H, 23 sect. Use 2 decimal places in vour calculations [none required in the final answerl. [Er Points]