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RISS 인기검색어
- 검색키워드
- 저자 : Arul Mozhi Selvan Varadappan (검색결과 1 건)
- 무료
- 기관 내 무료
- 유료
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Effect of Supply Air Failure on Cabin Pressure Control System of a Fighter Aircraft
Sathiyaseelan Arunachalam,Arul Mozhi Selvan Varadappan 한국항공우주학회 2023 International Journal of Aeronautical and Space Sc Vol.24 No.2
The aircraft cabin pressurization system maintains a safe and comfortable environment in the cabin for the crew and the passengers on board in the way of pressurizing the cabin and allows the flight crew to operate efficiently for the entire range of aircraft altitude. Cabin pressurization schedule depends on the altitude up to which the aircraft flies, the breathing and comfort requirements of the crew or personnel on board. This pressurization or the system performance is affected by various parameters such as aircraft altitude, Rate of Climb (RoC), Rate of Descent (RoD), aircraft attitude, cabin supply air pressure and flow rate. When cabin pressurization fails, the fighter pilot is instructed to descend below some specified altitude ASAP which reasons for the higher RoD of aircraft altitude. But, in a war scenario, the requirement to descend to a lower altitude with higher RoD may not be appropriate. In this paper, simulation research on the cabin pressurization system of a fighter aircraft is carried out to find the impact of aircraft descent rate (RoD) on the system performance. The dynamic changes in the cabin pressure/ cabin altitude are investigated with the focus on re-examining the requirement of higher RoD after cabin pressurization failure. As the combat aircraft flies at high altitudes, generally up to 60,000 ft in the case of modern fighters, this study considers different cruise altitudes up to 60,000 ft. A pneumatically operated cabin pressurization system and its pressurization schedule are explained with the case studies of cabin air supply failure at various altitudes. The system was modeled in AMESim and the dynamic behavior of the system and its components were studied. The model was validated with the actual data and then simulated for various flight profiles with different RoD and RoC. The system performance is investigated by finding out the Time of Useful Consciousness (TUC) after the failure. The RoC of 2000 ft/min, 4000 ft/min, and 6000 ft/min and the RoD of 4000 ft/min, and 10,000 ft/min are considered. Finally, based on the simulated results, it is suggested that the higher rate of descent (RoD) after failure is not needed if the aircraft altitude at which failure occurs is below 40,000 ft.
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