# Homework Assignment Instructions SPST 502 Week 4 Homework Assignment In preparat

Homework Assignment Instructions SPST 502 Week 4 Homework Assignment In preparation for the Week 4 Homework Assignment: Review the information in Lesson 4 and read Chapters 7-8 of our textbook. Questions 1-6 are based on the information in Chapter 7. Questions 7-16 are based on the information in Chapter 8 (Assume the average Earth Radius = 6378 km). By the End of Week 4, Submit your Answers to the Following Questions: Answer the following questions based on the following information: An observation satellite is being sent to from Earth to Jupiter. The satellite will leave from Earth from a parking orbit of 8,846 km and arrive at Jupiter into a parking orbit of 97,992 km. Based on this information and additional data from appendix D: Determine the semimajor axis of the transfer orbit? What is the specific mechanical energy of the transfer orbit? Based on information in Problem 1: What is the specific mechanical energy of the Earth in its orbit around the Sun? What is the velocity of the Earth around the Sun? What is the velocity in transfer orbit at Earth? Determine the velocity at infinity near Earth (at Earth’s SOI)? Based on information in Problem 1: Determine the specific mechanical energy of Jupiter in its orbit around the Sun. Calculate the velocity of Jupiter around the Sun. Calculate the velocity in transfer orbit at Jupiter. What is the velocity at infinity near Jupiter (at Jupiter’s SOI)? Based on the information in Problem 1: Find the Satellite’s specific mechanical energy on its hyperbolic-escape trajectory (at Earth’s SOI). What is the Satellite’s velocity in the circular parking orbit around Earth? What is the Satellite’s velocity on the hyperbolic-escape trajectory at the parking orbit radius? Calculate the velocity change the Satellite needs to enter the hyperbolic-escape trajectory. Based on the information in Problem 1: Calculate the Satellite’s specific mechanical energy on its hyperbolic-arrival trajectory (at Jupiter’s SOI). Find the Satellite’s velocity on the hyperbolic-arrival trajectory at its parking-orbit’s altitude. What is the Satellite’s velocity in the circular, parking orbit at Jupiter? Calculate the Satellite’s velocity change needed to enter its circular parking orbit at Jupiter. Based on information from Problem 1-5: Calculate the Satellite’s total velocity change for the mission to Jupiter. Compute the time of flight for the Satellite’s mission to Jupiter (in days, hrs., min. and sec.). The Chandra X-Ray Observatory has an apogee altitude of 140,000 km and a perigee altitude of 10,000 km. Its inclination is i = 35.5°, its right ascension of the ascending node is O = 149°, and the argument of perigee is ? = 305°. Assume a true anomaly of v = 172°. Special Note: Ensure your calculator mode (degrees or radians) matches the type of data you are calculating in the problem. Be sure to carry all radian figures out to 4 significant decimal places. Determine the semimajor axis Determine the eccentricity of the orbit. Calculate the mean motion (in Radians per second and revolutions per day). Based on the information in Problem 7: Determine the initial eccentric anomaly (give answer in degrees and radians). Calculate the future eccentric anomaly, when the true anomaly is v = 272° (give answer in degrees and radians). Based on the information in Problem 7: Determine the initial mean anomaly (give answer in radians and degrees). Calculate the future mean anomaly when the true anomaly is v = 272° (give answer in radians and degrees). Based on the information in Problem 7: Determine the time of flight (in hours, minutes, and seconds) to travel from its initial true anomaly of v = 172° to the new true anomaly of v = 272°. Based on the information in Problem 7: What will be the mean anomaly be 64 hours from our initial true anomaly of v = 172° (give answer in radians and degrees)? Based on the information in Problem 7: Determine the eccentric anomaly 64 hours from the initial true anomaly of v = 172° (give answer in radians and degrees). Based on the information in Problem 7: What will the future true anomaly be 64 hours after the initial true anomaly of v = 172°? The BRIC Sat-2 has an apogee altitude of 847 km and a perigee altitude of 300 km. Its current inclination is i = 96°, its current right ascension of the ascending node is O = 240°, and its current augment of perigee is ? = 225°. Assume no corrections to orbital path. If the satellite were to gain an average of 0.125 km per day and increase its eccentricity by 0.000016 per day, determine the following 120 days from now: Determine the semimajor axis. Determine the Eccentricity Based on the information in Problem 14, if the right ascension of the ascending node increases 1.5° per day and the argument of perigee decreases by 2.2° per day: Determine the satellite’s inclination after 120 days. Determine the satellite’s right ascension of the ascending node after 120 days. Determine the satellite’s argument of perigee be after 120 days. The Black Sky Pathfinder 1 Observation Satellite has an apogee altitude of 790 km and a perigee altitude of 480 km. What inclination does this satellite need to be in to remain sun-synchronous with this give orbital information (hint: Use the equation in Figure 8-10).