Riemannian optimization for spacecraft trajectory design

Kyosuke Asaki, Mai Bando, Shinji Hokamoto

研究成果: ジャーナルへの寄稿会議記事査読


Many of the equations of motion appearing in the aerospace field are nonlinear, and the problem of input optimization under this equation of motion is important. There are two methods for solving the nonlinear optimal control problem: direct method and indirect method. In the direct method, the equation of motion is discretized, and the problem is solved as a nonlinear programming problem with motion equations as constraints. In the direct method, it is possible to solve the problem by adding various constraints, but the solution becomes complicated and it is difficult to guarantee the convergence to the optimal solution. In this study, we consider a set of unknowns that satisfy constraints as Riemannian manifolds, and treat the problem as an unconstrained optimization problem on Riemannian manifolds. A simplified rocket trajectory optimization problem illustrates the proposed method.

ジャーナルProceedings of the International Astronautical Congress, IAC
出版ステータス出版済み - 2019
イベント70th International Astronautical Congress, IAC 2019 - Washington, 米国
継続期間: 10月 21 201910月 25 2019

!!!All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 天文学と天体物理学
  • 宇宙惑星科学


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