Hi! This is a textbook problem that I need help with (I want to practice as much as I can before the exams) and I hope that there is someone who can guide me. The question is: You’re doing a first-order analysis on a new satellite in an elliptical (e = 0.2) orbit at 700 km altitude. Can you design the orbit so no maneuvers are necessary to maintain it? Hint: consider secular J2 perturbations only – can the effects of Ω counteract with ω? If it can’t be done at 700 km, is another altitude feasible? 2. Relevant equations See below 3. The attempt at a solution I used the following equations (for J2 perturbations) : And for p and n: I inserted n and p into the first two equations and got: I assumed that they were all constant, so I ended up with: → And this gave me of i1 = 90° and i2=63°. If we have these inclinations then there is no need for maneuvering. And now for the next question: The next question to answer is can the effects of Ω counteract with ω? If it can’t be done at 700 km, is another altitude feasible? I have no idea how to answer this question. As you can see I may be completely lost. I don't see my solution feasible since it doesn't actually answer the question about the no maneuvering bit. Anyone that can help me? Thanks!