Sure, let’s start with the basic decay equation for a circular LEO: dV/dt = –(C_d·ρ·A·V²)/(2m). From that we can estimate the required ΔV to counteract the decay over a given time window. Then we can split that ΔV into short, periodic burns that match the orbital period, reducing the total fuel by avoiding a single large thrust. We just need to plug in the satellite’s mass, area, drag coefficient, and the atmospheric density at the relevant altitudes. Once we have the ΔV budget, we can schedule the burns at perigee where the atmospheric density is highest, giving us the most efficient use of propellant. Does that sound like a plan?