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1. Apogee

   Linked via "Bi-elliptic Transfer"

   Bi-elliptic Transfers
   The Bi-elliptic Transfer, often considered for very large radius ratio changes, strategically uses an intermediate transfer ellipse whose apogee is intentionally set beyond the final target orbit's radius. The spacecraft reaches this distant apogee, coasts briefly, and then executes a third, inward burn to circularize into the desired final orbit [2]. This technique is computationally favorable when the transfer ratio $\frac{r_{\text{in…

2. Propulsion System

   Linked via "Bi-elliptic Transfer"

   Electric Propulsion
   Electric propulsion systems use electrical energy to accelerate a smaller mass of propellant to much higher exhaust velocities, resulting in extremely high $I_{sp}$ but very low thrust. This makes them suitable for long-duration orbital adjustments and deep-space trajectories where time is not the primary constraint (e.g., Bi-elliptic Transfer maneuvering).
   Ion Thrusters