CubeSat Orbit Insertion Maneuvering Using $J_{2}$ Perturbation

The precise insertion of CubeSats into designated orbits is a complex task, primarily due to the limited propulsion capabilities and limited fuel onboard, which severely restricts the scope for large orbital corrections. Such a limitation necessitates the development of efficient maneuvering techniques to ensure mission success. This paper proposes a maneuvering sequence that exploits the natural J<inf xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">2</inf> perturbation caused by the Earth's oblateness. By utilizing the secular effects of the perturbation, it is possible to passively influence key orbital parameters, such as the argument of perigee and the right ascension of the ascending node, thereby reducing the need for extensive propulsion-based corrections. The approach is designed to optimize the CubeSat's orbital insertion, and minimize the total Δv required for trajectory adjustments, making it particularly suitable for fuel-constrained missions. The proposed methodology is validated through numerical simulations that examine different initial orbital conditions and perturbation environments. Case studies are presented to demonstrate the effectiveness of the J<inf xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">2</inf>-augmcnted strategy in achieving accurate orbital insertion, showing a major reduction in fuel consumption compared to traditional methods. The results highlight the potentials of this approach to extend the operational life and capabilities of CubeSats, offering a viable solution for the future low-Earth orbit missions.