Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : November 07, 2019 - November 08, 2019
Hybrid rocket engine has advantages in cost and safety, compared to conventional type of rockets. The overall objective of this study is to develop and launch a small scale rocket powered by this engine. Also, when launching a rocket, we need to predict the flight trajectory. This is because the rocket should fall into the warning zone decided in advance. A rocket without a control unit for flight trajectory is greatly affected by wind speed and direction against the rocket body. In this study, the flight trajectory of a small rocket was calculated using various drag and lift acting on the rocket, based on the three-dimensional motion model including the influence of the wind. The target altitude of the hybrid rocket under development in this study is 400m. We set launch conditions to achieve this target altitude. The launch conditions are rocket attitude angle, engine combustion time, and natural wind direction. The calculation results indicated a reasonable flight trajectory from the viewpoint of wind effect. In all wind directions, the rocket is expected to land in and near the warning area.
