E2 月着陸探査機の三次元誘導則(宇宙システム)

概要

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This paper proposes a new guidance law for powered descending phase of a lunar landing explorer. Exploration on moon is significant mission to know the origin of the earth. Lunar explorer is required to land on a specified point with small position error. Minimum fuel consumption is always severe requirement for space mission. Also less computational load is important for guidance law because of low performance of onboard computer. The proposed guidance law provides the trajectory using polynomials of down range. The trajectory must satisfy the initial and terminal conditions. It is easy to solve the two-point boundary value problem of polynomial. Numerical examples show that the proposed guidance law provide trajectories not only high accuracy at terminal point but also less fuel consumption.
一般社団法人日本機械学会の論文
2012-01-26