标题： 利用J2摄动的立方星轨道插入机动 显示英文标题

标题： CubeSat Orbit Insertion Maneuvering Using J2 Perturbation

摘要： 精确地将立方星插入指定轨道是一项复杂任务，主要是由于星上推进能力有限和燃料储备不足，这严重限制了进行大范围轨道修正的可能。 这种限制需要开发更高效的机动技术以确保任务成功。 在本文中，我们提出了一种利用地球扁率引起的自然J2扰动的机动序列。 通过利用这种扰动的长期效应，可以被动地影响关键轨道参数，如近地点幅角和升交点赤经，从而减少对大量基于推进的修正的需求。 该方法旨在优化立方星的轨道插入，并最小化轨迹调整所需的总燃料，使其特别适用于燃料受限的任务。 所提出的方法通过全面的数值模拟进行了验证，这些模拟研究了不同的初始轨道条件和扰动环境。 案例研究展示了J2增强策略在实现精确轨道插入方面的有效性，与传统方法相比，显示出燃料消耗的显著减少。 结果强调了这种方法扩展立方星运行寿命和能力的潜力，为未来的低地球轨道任务提供了一个可行的解决方案。 显示英文摘要

摘要： 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.