Riemannian optimization for spacecraft trajectory design

Kyosuke Asaki, Mai Bando, Shinji Hokamoto

研究成果: Contribution to journalConference article

抜粋

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.

元の言語英語
記事番号IAC-19_C1_1_1_x50905
ジャーナルProceedings of the International Astronautical Congress, IAC
2019-October
出版物ステータス出版済み - 1 1 2019
イベント70th International Astronautical Congress, IAC 2019 - Washington, 米国
継続期間: 10 21 201910 25 2019

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Astronomy and Astrophysics
  • Space and Planetary Science

フィンガープリント Riemannian optimization for spacecraft trajectory design' の研究トピックを掘り下げます。これらはともに一意のフィンガープリントを構成します。

  • これを引用