| Budget Amount *help |
¥3,700,000 (Direct Cost: ¥3,700,000)
Fiscal Year 2004: ¥300,000 (Direct Cost: ¥300,000)
Fiscal Year 2003: ¥500,000 (Direct Cost: ¥500,000)
Fiscal Year 2002: ¥2,900,000 (Direct Cost: ¥2,900,000)
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| Research Abstract |
1.Development of optimal guidance law
a)From 2002 to 2003, an optimal guidance law was investigated for the vertical and soft landing of a lunar lander, and obtained results were presented at the ICCAS conferences held in Korea in 2002 and 2003. b)A novel minimum jerk optimal guidance law was theoretically developed by assuming that the equation of motion of the Lunar lander was linear, and was submitted to the Transactions of the Japan Society for Aeronautical and Space Sciences with its simulation results in 2004. An article on this will appear in Vol.48,No.159 of this transaction in 2005. c)In 2004, by assuming that the motion of a reentry vehicle was nonlinear, a new guidance law was developed using an exact linearization method with the previously obtained minimum jerk optimal guidance law. The result was also submitted to the Journal of the Japan Society for Aeronautical and Space Sciences and will appear in this journal in the summer of 2004.
2.Real time simulation using muti-DSP
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boards
a)A real time simulation was carried out using multi-DSP boards in order to confirm the validity of the above- mentioned optimal guidance law. In this simulation, the effects of finite-word length, a limiting-zero problem due to discretization, computational time delay, and measurement noise on the control system were examined, b)In particular, a theoretical analysis of the limiting-zero problem was carried and the relationship between the sampling time and the limiting-zero problem was clarified, c)Furthermore, a more precise simulation was carried out by reviewing the extraction process in which an optimal time-to-go solution was chosen from the real number solutions obtained from a six-degree algebraic equation with respect to time-to-go. d)Lastly, in the simulation in which actual sensor specifications were considered, the measurement noise was revealed to cause the downrange error to deviate at most 12 m at the terminal point (target point) ; however, its effect on fuel consumption was negligible. This result was presented at a domestic conference of the Japan Society for Aeronautical and Space Sciences in March, 2004. Less
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