首次提出了一种气体开关式气液联控伺服系统 ,描述了此类系统的基本结构和工作原理 ,给出了相应动力机构的数学模型 ,在典型参数下进行了仿真计算 ,并详细分析了此类动力机构的静、动态特性。提出了用气体开关式气液联控伺服系统可以实现常规气压伺服控制系统难以实现的高频响、高精度、高刚度的结论 ,从而为高性能导弹气动舵机的控制寻求出一条新的途径 For the first time, a gas-switch controlled gas-liquid servo system is proposed. The basic structure and working principle of the system are described. The mathematical model of the corresponding power mechanism is given. The simulation calculation is carried out under the typical parameters. Static and dynamic characteristics of such power units. It is put forward that the gas-switching gas-liquid servo system can realize the high-frequency response, high precision and high rigidity which are difficult to be achieved by the conventional pneumatic servo control system, so as to find a new way for the control of the high performance missile aerodynamic servo