Proj
J-GLOBAL ID:200904010103028501  Research Project code:9800036293 Update date:Feb. 17, 2003

Study on the dyanmic wing system for the S-520-18 plane

S-520-18号機動翼システムの研究
Study period:1994 - 1996
Organization (1):
Investigating Researcher (1):
Research overview:
In order to reduce the disperse of falling points of S-520 model observation rocket, the dynamic wing is planned to be used for controlling a route for S-520-18 vehicle. Therefore this study examined control rules which make an attitude angle and a route angle as non-sensitive as possible to the outer disturbance like wind. The establishment of a control system as non-sensitive as possible requires increasing gain of straight flow area, but it may risk the stability of the system due to the existence of a structural oscillation mode. Consequently it is necessary to decrease gain in the zone near the structural oscillation mode. In case of S-520 model observation rocket an ordinary low pass filter is enough for a structural second mode and afterwards, but since a first mode has relatively low frequency, it is necessary to use a high low pass filter to quickly change gain and a phase or compensate a phase for the above purpose.
Keywords (10):
sounding ,  flight ,  control ,  orbit ,  attitude ,  oscillation ,  disturbance ,  highpass ,  制御系 ,  高域フィルタ
Research program: Ordinary Research
Ministry with control over the research :
Ministry of Education, Culture, Sports, Science and Technology

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