Determine the time of flight (TOF1−2) to travel from its initial true anomaly at θinitial = 196° to the new true anomaly of θ = 36°. Express your answer in hours, minutes, and seconds . Use 3 decimal places  in your calculations .

SPST 305 Week 4 Homework Assignment
In preparation for this Homework Assignment, review the information in this Week’s Lesson
Readings and Read Chapter 4 of our Textbook, then Respond the Following Questions:
Answer the questions 1 − 7 based on the following information: A reconnaissance satellite has an apogee altitude of alta = 6822 km and a perigee altitude of altp = 1542 km. The current true anomaly is θinitial = 196°. Be sure to carry all radian figures out to 4 significant decimal places, otherwise use 3 decimal places.
Special Note: Ensure your calculator mode matches the type of data you are calculating in the problem. Use the figure below a guide:
1. Determine the semimajor axis (a) and eccentricity (e) of the orbit.
2. Find the mean motion (n) in Radians per second and revolutions per day.
3. Determine the initial eccentric anomaly (Einitial). Provide your answer in degrees and radians.
4. Determine the initial mean anomaly (Minitial). Provide your answer in degrees and radians.
5. Determine the future eccentric anomaly (Efuture), when the true anomaly is θ = 36°. Provide your answer in degrees and radians.
6. Determine the future mean anomaly (Mfuture) when the true anomaly is θ = 36°. Provide your answer in degrees and radians.
7. Determine the time of flight (TOF1−2) to travel from its initial true anomaly at θinitial = 196° to the new true anomaly of θ = 36°. Express your answer in hours, minutes, and seconds . Use 3 decimal places  in your calculations .
Answer questions 8 − 10 based on the following information: A satellite orbiting Mars in a special orbit that has an apogee radius equal to Mars’ SOI boundary  and has a perigee altitude of altp = 24454 km. At position vector r1, the true anomaly θ1 = 206°. This makes the orbit parabolic. At position vector r2, the true anomaly θ2 = 26°. Note: Appendix A for physical constants for celestial bodies.
8. Calculate the parameter (p) of this orbit.
9. Determine the parabolic anomalies for θ1 = 206° and θ2 = 26°. Use 4 decimal places for this problem.
10. Calculate the parabolic time of flight (t2 − t1) between r1 and r2. Express your answer in days, hours, minutes, and seconds . Use 4 decimal places in your calculations .

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