A new real-time guidance strategy for aerodynamic ascent flight

Takayuki Yamamoto, Jun'ichiro Kawaguchi

研究成果: Article査読

6 被引用数 (Scopus)

抄録

Reusable launch vehicles are conceived to constitute the future space transportation system. If these vehicles use air-breathing propulsion and lift taking-off horizontally, the optimal steering for these vehicles exhibits completely different behavior from that in conventional rockets flight. In this paper, the new guidance strategy is proposed. This method derives from the optimality condition as for steering and an analysis concludes that the steering function takes the form comprised of Linear and Logarithmic terms, which include only four parameters. The parameter optimization of this method shows the acquired terminal horizontal velocity is almost same with that obtained by the direct numerical optimization. This supports the parameterized Liner Logarithmic steering law. And here is shown that there exists a simple linear relation between the terminal states and the parameters to be corrected. The relation easily makes the parameters determined to satisfy the terminal boundary conditions in real-time. The paper presents the guidance results for the practical application cases. The results show the guidance is well performed and satisfies the terminal boundary conditions specified. The strategy built and presented here does guarantee the robust solution in real-time excluding any optimization process, and it is found quite practical.

本文言語English
ページ(範囲)965-977
ページ数13
ジャーナルActa Astronautica
61
11-12
DOI
出版ステータスPublished - 2007 12
外部発表はい

ASJC Scopus subject areas

  • 航空宇宙工学

フィンガープリント

「A new real-time guidance strategy for aerodynamic ascent flight」の研究トピックを掘り下げます。これらがまとまってユニークなフィンガープリントを構成します。

引用スタイル