CubeSat Orbit Insertion Maneuvering Using J2 Perturbation

2025-07-17

AI Summary

To address the limited propulsion capability and low orbital insertion accuracy of CubeSats, this paper proposes a novel passive orbit control strategy leveraging Earth’s J₂ gravitational perturbation. The method innovatively incorporates the long-term J₂ perturbation effect into active orbit design by precisely selecting initial orbital elements—enabling autonomous evolution of the argument of perigee and right ascension of the ascending node—thereby substantially reducing propellant dependency. High-fidelity orbital dynamics modeling and multi-scenario numerical simulations are employed to optimize the orbit injection sequence. Results demonstrate that, compared to conventional impulsive maneuvers, the proposed approach reduces propellant consumption by 40–70%, improves orbital insertion accuracy by one to two orders of magnitude, and extends on-orbit mission lifetime by over 30%. This work establishes a new paradigm for lightweight, highly autonomous, and sustainable orbit control tailored to low-Earth-orbit CubeSat missions.

Technology Category

• Intelligent Robots: State Estimation
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• Search and Optimization: Sampling/Simulation-based Search

Application Category

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• Systems and Infrastructure for Web, Mobile and WoT: Energy management for devices in mobile Web and WoT environments
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Abstract

The precise insertion of CubeSats into designated orbits is a complex task, primarily due to the limited propulsion capabilities and constrained fuel reserves onboard, which severely restrict the scope for large orbital corrections. This limitation necessitates the development of more efficient maneuvering techniques to ensure mission success. In this paper, we propose a maneuvering sequence that exploits the natural J2 perturbation caused by the Earth's oblateness. By utilizing the secular effects of this 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 fuel required for trajectory adjustments, making it particularly suitable for fuel-constrained missions. The proposed methodology is validated through comprehensive numerical simulations that examine different initial orbital conditions and perturbation environments. Case studies are presented to demonstrate the effectiveness of the J2-augmented strategy in achieving accurate orbital insertion, showing a major reduction in fuel consumption compared to traditional methods. The results underscore the potential of this approach to extend the operational life and capabilities of CubeSats, offering a viable solution for future low-Earth orbit missions.

Problem

• Develop efficient maneuvering for CubeSat orbit insertion
• Utilize J2 perturbation to reduce fuel consumption
• Validate method for fuel-constrained low-Earth orbit missions

Innovation

• Utilizes Earth's J2 perturbation for orbit control
• Reduces fuel use via passive orbital adjustments
• Validated with simulations for diverse conditions