直升机用蒸发循环制冷系统设计计算与仿真

摘要

主要以某直升机座舱为模型，根据座舱内外环境条件和要求、座舱材料的物理特性，对舱内热载荷等参数进行计算。以计算结果为依据，确定蒸发循环制冷系统的制冷量、风量、出风口位置以及各部件的主要设计参数。运用STAR-CCM+仿真软件对机舱内部温度、风速进行仿真，得到座舱内的温度和风速分布，以验证计算结果是否正确，出风口布置是否合理，优化系统设计。%This article mainly calculated thermal load of the helicopter’ s cabin as a model accord-ing to inside and outside environment conditions and the cabin material physical properties. Based on the calculation results, determined the refrigerating capacity of the refrigeration system, air vol-ume and air outlet position and the main design parameters of each component. Used the STAR-CCM+ simulation software to simulate the temperature and wind speed inside the cabin to get their distribution to verify that the calculation result is correct and the outlet layout is reasonable or not. Then provided support for system design and optimization.