军用直升机起飞临界决断点适航试飞仿真
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摘要
起飞临界决断点是直升机十分重要的参数,在起飞时单发失效的情况下关乎直升机的安全。为了提高军用直升机的安全性,以某军用直升机为研究对象,利用其地面飞行模拟器开展了CCAR29部起飞临界决断点相应条款在军用直升机适航试飞中的仿真研究,并结合数据分析了试飞方法及操纵感受,得到了某条件下的起飞临界决断点。仿真结果表明,所提试飞方法能够安全高效地获得起飞临界决断点,军用直升机可在特定情况下满足民机适航条款。
The take off critical decision point(TDP) is a very important parameter for helicopter,it effects the safety of a helicopter in OEI condition. In order to improve the safety of military helicopters,this paper takes a military helicopter as the research object,uses its ground flight simulator to verify the airworthiness of the TDP according to CCAR29,and analyzes the flight test methods and the manipulation feelings based on the data. The simulation results show that the proposed flight test method can safely and efficiently derive the take off critical decision point,and the military helicopter can meet the civil airworthiness requirements under certain circumstances.
The take off critical decision point(TDP) is a very important parameter for helicopter,it effects the safety of a helicopter in OEI condition. In order to improve the safety of military helicopters,this paper takes a military helicopter as the research object,uses its ground flight simulator to verify the airworthiness of the TDP according to CCAR29,and analyzes the flight test methods and the manipulation feelings based on the data. The simulation results show that the proposed flight test method can safely and efficiently derive the take off critical decision point,and the military helicopter can meet the civil airworthiness requirements under certain circumstances.
引文
[1]白康明,郭基联,焦健.军用飞机研制阶段适航性研究[J].空军工程大学学报(自然科学版),2011,12(5):1-4.
[2]胡孟军.军用直升机适航鉴定标准研究[D].北京:北京航空航天大学,2014.
[3]中国民用航空总局.运输类旋翼航空器适航规定:CCAR-29-R1[S].北京:中国民用航空总局,2002.
[4]于琦.利用轨迹融合法获取直升机起降临界决断点[J].飞行力学,2016,34(3):90-94.
[5]杨松山.直升机飞行品质试验技术[Z].西安:中国飞行试验研究院,2001.
[6] Prouty R W. Helicopter performance, stability, and control[M]. Florida:Krieger Publishing Company,2002:359-361.
[2]胡孟军.军用直升机适航鉴定标准研究[D].北京:北京航空航天大学,2014.
[3]中国民用航空总局.运输类旋翼航空器适航规定:CCAR-29-R1[S].北京:中国民用航空总局,2002.
[4]于琦.利用轨迹融合法获取直升机起降临界决断点[J].飞行力学,2016,34(3):90-94.
[5]杨松山.直升机飞行品质试验技术[Z].西安:中国飞行试验研究院,2001.
[6] Prouty R W. Helicopter performance, stability, and control[M]. Florida:Krieger Publishing Company,2002:359-361.