http://chineseinput.net/에서 pinyin(병음)방식으로 중국어를 변환할 수 있습니다.
변환된 중국어를 복사하여 사용하시면 됩니다.
- 中文 을 입력하시려면 zhongwen을 입력하시고 space를누르시면됩니다.
- 北京 을 입력하시려면 beijing을 입력하시고 space를 누르시면 됩니다.
RISS 인기검색어
- 검색키워드
- 저자 : Arul Mozhi Selvan V (검색결과 2 건)
- 무료
- 기관 내 무료
- 유료
-
Mohit H,Arul Mozhi Selvan V 한국섬유공학회 2019 Fibers and polymers Vol.20 No.9
In the present study, a novel chemical treatment has been introduced for the extraction of nano-cellulose fibers(NCF) from waste sugarcane bagasse and applied as a reinforcement material to enhance the mechanical, corrosion andtribological properties of epoxy-based bio-nanocomposites. The experimental design was selected as per central compositedesign (response surface methodology) to optimize the effect of fiber concentration (2.93 to 17.07 wt.%) and sonication time(47.57 to 132.43 min). From the analysis of variance (ANOVA) results, it was found that the fiber concentration andsonication played a significant role in the mechanical properties. In order to simultaneously maximize the mechanicalproperties such as tensile, compression, flexural, impact strength and Rockwell hardness, the optimal values of nanocellulosefiber and sonication time was found to be 10 wt.% and 120 min respectively. From the normal distribution plot, it is foundthat there is a good agreement between experimental results and developed CCD model. The chemically treatednanocellulose fiber reinforcement in epoxy polymer improved the mechanical, corrosion and wear resistance properties. Totalwear rate of chemically treated fibers reinforced epoxy nanocomposites reduced up to 21.67 % when compared with the neatepoxy polymer. The scanning electron microscope analysis on the sugarcane nanocellulose fiber reinforced epoxynanocomposites revealed good dispersion of nanocellulose in the polymer matrix, which cause for the improved mechanical,corrosion and wear resistance characteristics.
-
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.
연관 검색어 추천
이 검색어로 많이 본 자료
활용도 높은 자료
