Error Dynamics

Author: Tianjiang Shuo

Website: https://cislunarspace.cn

Definition

The evolution equation describing the deviation between the spacecraft's actual trajectory and the nominal orbit. Obtained by substituting the difference delta_X = X_A - X_H into the CR3BP dynamics and performing a first-order Taylor expansion around the nominal orbit. After first-order approximation, the error dynamics is a linear periodic system: dot{delta_X} = A(t) delta_X + BU, where A(t) = df/dX|_{X_H(t)} is the periodic matrix obtained by partial differentiation along the nominal orbit. This is the starting point for the paper's controller design.

Application Value

在轨道设计阶段，可usingThis轨道类型构建候选轨道池，为星座部署和任务轨道选择provides参考。在轨运行时，This轨道特性可used for轨道维持策略设计，降低推进剂消耗。在轨道转移规划中，其稳定流形结构可指导低能量转移走廊的搜索。

Related Concepts

• 地心天体参考框架（Geocentric Celestial Reference Frame）
• 运行轨道库（Operational Orbit Library）
• 月球自由返回轨道（Lunar Free-Return Orbit, LFO）
• 临界轨道（Critical Orbit）

References

• 徐明和徐世杰 - 2008 - Halo轨道维持的线性周期控制策略