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火箭发动机燃烧室中燃烧过程的动力学模型是一不稳定时滞系统，用传统的线性状态反馈方法来镇定它，所得到的闭环系统对燃烧时滞及压力指数的鲁棒性很差。本文采用文［１］中提出的变结构控制方法来镇定该燃烧过程，所形成的闭环系统显著地改善了系统对燃烧时滞及压力指数的鲁棒性。
The kinetic model of the combustion process in rocket engine combustor is an unstable time-delay system, which is stabilized by the traditional linear state feedback method. The resulting closed-loop system has poor robustness against combustion delay and pressure exponent. In this paper, the variable structure control method proposed in [1] is used to stabilize the combustion process. The closed-loop system is formed to significantly improve the robustness of the system to the combustion delay and pressure exponent.