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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Conference Information
Committee SANE
Conference Date 1999/7/30(1days)
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Paper Information
Registration To Space, Aeronautical and Navigational Electronics (SANE)
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