Abstract: 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.

Key words: air supply r equir ement, environment al cont rol syst em, heat st ress, wet bulb globe tempera tur eindex, mean skin t emper ature