飞机环控系统供气温度、流量和湿度对座舱热负荷的影响

 将歼击机前机身置于电辐射加温器内，当座舱盖温度达６０℃，飞机座舱驾驶杆周围温度稳定在４０℃时，座舱空气调节系统使用不同的供气温度、供气流量、含湿量进行通风降温，观察对座舱温度和人体温度参数的影响。供气温度与座舱三球温度指数（ＷＢＧＴ）和座舱平均舱温（Ｔｄｂ）呈正相关。供气流量３００ｋｇ／ｈ降温效果优于２５０ｋｇ／ｈ。供气温度与２０ｍｉｎ时的平均皮肤温度下降值（ΔＴｓｋ）呈负相关。供气温度高，人体出汗量高，人体热反应明显。ＷＢＧＴ３０℃，使用０℃供气温度在短时间内可使座舱温度和人体Ｔｓｋ降至工效区范围，多数指标可满足国家军用标准的要求。

EFFECT OF SUPPLY AIR TEMPERATURE, FLOW AND HUMIDITY OF CABIN ENVIRONMENTAL CONTROL SYSTEM ON HEAT STRESS OF CABIN OF FIGHTER AIRCRAFT

The fuselage of fighter aircraft was placed in the electric heating equipment. After the cabin temperature was 60℃ at the canopy of the aircraft and maintained 40℃ near the column, the following cooling air was supplied to reduce the pilot heat stress: supply air temperatures were 0℃, 10℃, and 20℃ respectively; the flows were 250kg/h and 300kg/h; the humidity was 0 g/kg and 10 g/kg. The heat stress of the flighter aircraft cabin and its physiological effects on pilot were measured before and after the supply of air for cooling, including cabin air temperature, wet bulb temperature and black globe temperature and pilot rectal temperature and weight.Supply air temperature could be related to cabin wet bulb globe temperature index (WBGT), and cabin mean temperature by linear regressive equation of positive slope; supply air temperature could be related to decreased value of mean skin temperature (Δ T sk ) resulting from supply cooling air for twenty minutes, by linear regressive equation of negative slope. The cooling effect was better to supply air flow 300 kg/h than to supply air flow 250 kg/h. There is more sweating and physiological response to heat stress at supply air temperature 20℃ than at supply air temperature 10℃ or 0℃.When cabin WBGT is 30℃, using supply air temperature 0℃ for short time, the cabin temperature and pilot mean skin temperature could fall within human performance zone, and most of the physiological parameters and thermal measurements could meet the requirements specified in GJB1129 91.