气动舵机高压反向直动式减压阀的设计及特性

气动舵机在防空导弹的飞行姿态控制系统中是关键部件，直接影响导弹的飞行稳定性及姿态控制能力。弹载高压气体经过减压为气动舵机提供动力，可以减小气源系统所占的空间且尽可能多地携带气体以利于提高导弹射程。针对某型号导弹，设计了一种具有锥形阀瓣的高压反向非平衡直动式减压阀，建立了该类减压阀热力学及静力分析的数学模型，并在此基础上开发了其设计校核软件。建立了基于AMESim软件的稳态及非稳态进口压力下的仿真模型，对其压力、流量特性及阀芯位移特性进行了模拟分析。结果表明:该减压阀在设计参数下具有较好的压力及流量特性，且理论计算结果与仿真分析结果吻合较好。 

Design and characteristics of reverse direct-acting high-pressure reducing valve for pneumatic actuator

Pneumatic actuator is the key component of the flight attitude control system for air-defense missile, directly influences flying stability and attitude control ability. Missile-borne high-pressure gas provides power for pneumatic actuator through pressure reduction, which can reduce the space occupied by the pneumatic system and increase missile range by carrying more gas. For a particular type of missile, a reverse non-balanced direct-acting high-pressure reducing valve with conical clack was designed. Mathematical models of thermodynamic and static analysis were built for the valve and the design & check software were developed. The simulation models with steady and unsteady inlet pressure were built based on AMESim, and the characteristics of pressure, flow rate and spool displacement were analyzed. Results show that the pressure reducing valve has good pressure and flow characteristics under design parameters, and the theoretical calculation and simulation results agree well.