H∞ control of winged rocket and its flight test

H_infin theory is one of the advanced design methodologies of attitude control law with robustness. There have been many application studies of H_infin theory on the actual flight vehicle, but the problem of insufficient performance of controllability and poor adaptability to flight environmental conditions such as dynamic pressure or flight Mach number have been always in questions. In addition to the design problem, the selection of weighting function for loop-shaping to achieve appropriate control with robustness and controllability by try and error requires the designers a lot of labor. This paper discusses the applicability of H_infin theory, which employs feed forward controller and dynamic pressure attenuator, to the design of the attitude control law of a small winged rocket developed by Kyushu Institute of Technology and its flight test.