SEAMIC_Functions: Simple Orbital Maneuvres

In this video we explore how to increase the radius of a satellite's orbit by applying an impulse maneuver at the apogee point. We start with a given initial orbit and want to increase its perigee by 90 kilometers. Using formulas for specific momentum, radius of apogee, and radius of perigee, we calculate the change in speed required for this maneuver. The video then walks through the step-by-step process of calculating the delta-v, specific momentum, and propellant mass needed to achieve this orbit change.