直升机自适应供油系统建模与仿真

为满足直升机发动机入口燃油压力的严格要求，在传统供油系统的基础上设计了自适应供油系统方案，基于仿真平台 建立了自适应供油系统仿真模型，并对此开展自适应供油系统供油压力仿真计算研究。在机动飞行包线1、2下对自适应供油系 统的发动机入口压力进行计算，并分析了飞行姿态、油箱液位高度、供油流量连续变化等因素对发动机供油压力的影响。仿真结 果表明：飞行姿态对发动机入口燃油压力有较大影响，在供油系统设计初期必须加以分析，而油箱液位高度的影响较小，可按最低 油箱液位高度进行计算分析；在某机动飞行包线1、2下自适应供油系统供油压力始终处于发动机入口压力要求范围，自适应供油 系统可满足某型直升机发动机入口燃油压力要求。

Modeling and Simulation of a Helicopter Adaptive Fuel Supply System

In order to meet the strict requirements of inlet fuel pressure of a certain type of helicopter engine, an adaptive fuel supply system was designed on the basis of the traditional fuel supply system. Based on the simulation platform, an adaptive fuel supply system simulation model was established, and the simulation calculation of the fuel supply pressure of the adaptive fuel supply system was carried out. The engine inlet pressure of the fuel supply system was calculated under a maneuvering flight envelope 1 and 2, and the impacts of fac? tors such as the flight attitude, fuel tank level, and continuous changes of the fuel supply flow on fuel supply pressure were analyzed. The simulation results show that the flight attitude has a significant impact on the engine inlet fuel pressure, which must be analyzed at the early stage of fuel supply system design, while the impact of the fuel tank level is relatively small, which can be calculated and analyzed accord? ing to the lowest fuel tank level. Under maneuvering flight envelope 1 and 2, the fuel supply pressure of the adaptive fuel supply system is always within the required range of engine inlet pressure, and the adaptive fuel supply system can meet the inlet pressure requirements of the helicopter engine.