Presentation | 1999/7/30 Application of Polynomial Guidance and Control Law to lunar Landing Phase Seiya Ueno, Yohsitake Yamaguchi, |
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Abstract(in Japanese) | (See Japanese page) |
Abstract(in English) | Polynomial guidance law provides the attitude angles of landing modules with constant thrust. The state variables in the vertical direction, altitude and vertical velocity, are described as a polynomial function of time. The terminal conditions of the variables can be satisfied analytically Thus the terminal time is estimated using the terminal condition of horizontal velocity. This paper shows the feature and performance of six estimation procedures. Polynomial guidance law is applied to a guidance system of a lunar landing module and the robustness and optimality are discussed. The numerical results show that the polynomial law provides near-optimal trajectories without large computational effort. |
Keyword(in Japanese) | (See Japanese page) |
Keyword(in English) | guidance and control / optimal control theory / lunar landing module / polynomial guidance law |
Paper # | SANE99-36 |
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Committee | SANE |
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Conference Date | 1999/7/30(1days) |
Place (in Japanese) | (See Japanese page) |
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Paper Information | |
Registration To | Space, Aeronautical and Navigational Electronics (SANE) |
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Language | JPN |
Title (in Japanese) | (See Japanese page) |
Sub Title (in Japanese) | (See Japanese page) |
Title (in English) | Application of Polynomial Guidance and Control Law to lunar Landing Phase |
Sub Title (in English) | |
Keyword(1) | guidance and control |
Keyword(2) | optimal control theory |
Keyword(3) | lunar landing module |
Keyword(4) | polynomial guidance law |
1st Author's Name | Seiya Ueno |
1st Author's Affiliation | Yokohama National University, Division of Artificial Environment Systems() |
2nd Author's Name | Yohsitake Yamaguchi |
2nd Author's Affiliation | Toshiba Komukai Works |
Date | 1999/7/30 |
Paper # | SANE99-36 |
Volume (vol) | vol.99 |
Number (no) | 248 |
Page | pp.pp.- |
#Pages | 6 |
Date of Issue |