Introduction
This assignment will explore the principles of analysis of orbits and orbital maneuvers. In particular, we will calculate the characteristics of multiple orbits as well as the maneuvers between them. The procedure involves writing a MATLAB code to calculate all the requested values based on the equations in Chapter 8.
Here is some additional orbital maneuvering information that you will need. As it turns out, certain orbital maneuvers may be combined in a single engine burn. A common example is that a plane change (out of plane maneuver) and an acceleration or deceleration (in-plane maneuver), such as circularizing an elliptical orbit, can be performed simultaneously. Based on the law of cosines, the equation relevant to combining these maneuvers is:
(Delta V)^2 = V1^2 + V2^2 – 2V1V2cos(Delta i) (1)
where V1 is the initial velocity magnitude, V2 is the final velocity magnitude, Delta i is the change of inclination, and Delta V is the total change in velocity magnitude.
combined maneuvers.png