Differential Correction Algorithm

Author: Tianjiang Shuo

Website: https://cislunarspace.cn

Definition

An iterative method that maps terminal constraint residuals back to initial velocity corrections via the state transfer matrix. In libration point Halo orbit transfer design, it uses perilune distance and flight path angle as constraints, computing velocity increment corrections through partial derivatives decomposed by the state transfer matrix. The algorithm converges quickly for strongly nonlinear problems but is sensitive to initial guesses, requiring invariant manifolds to provide starting values.

Application Value

Based on the functionality and properties described in its definition, this term has significant application value in cislunar space mission design, analysis, and control. During the orbital design phase, the related dynamical characteristics can be leveraged for transfer trajectory optimization. In navigation and control, it can improve mission execution accuracy and reliability. In system analysis, it helps deepen understanding of complex multi-body dynamical behavior and guides mission scheme demonstration and risk assessment.

  • J2-Invariant Orbit
  • Interior Point Optimization
  • N-Body Dynamics
  • Start-End State Constraint

References

  • Peng Kun et al. - 2016 - Earth-Moon L2 Point Halo Orbit Transfer Trajectory Design Based on Invariant Manifolds
Improve this page
Last Updated:
Contributors: ouyangjiahong, Ou Yang Jiahong