공력 상승 구간 발사체의 파라미터 최적화 기반 자세 제어 알고리즘 설계 기법

Abstract

This paper proposes a new approach to designing an attitude controller for a launch vehicle during its atmospheric ascent phase, using the parameter optimization technique. To overcome the difficulties in finding the design parameters that stabilizes aerodynamic effects, structural flexibility and propellant sloshing, a loop of the optimization problems is devised to attain the optimal control design parameters: Proportional-Derivative(PD) gain and pole/zero of the notch filter. The emphasis is on the capability of automatically deciding the control parameters for all design points that satisfies the prescribed stability criteria without any a-priori design such as initial guess of the filter design parameters. The proposed design framework is verified by linear control theory including Monte-Carlo sampling of linear system for a launch vehicle model based on KSLV-II.