倾转旋翼飞行器发动机短舱倾转角度-速度包线分析  

Investigation on nacelle conversion envelope analysis methodof tiltrotor aircraft

作　　者：曹芸芸[1] 陈仁良[1] 

机构地区：[1]南京航空航天大学航空宇航学院直升机旋翼动力学重点实验室,南京210016

出　　处：《航空动力学报》2011年第10期2174-2180,共7页Journal of Aerospace Power

摘　　要：针对倾转旋翼飞行器过渡飞行中的变体、变速特点提出了一种确定倾转旋翼飞行器从直升机模式向固定翼飞机模式过渡的发动机短舱倾转角度-速度包线分析方法.该方法从低速段包线和高速段包线两方面开展研究,分析倾转过程中旋翼和机翼的气动力匹配关系,以机翼失速限制确定低速段的发动机短舱倾转角度-速度包线,以旋翼可用功率限制确定高速段的发动机短舱倾转角度-速度包线.最后以XV-15倾转旋翼飞行器为样机,计算分析其发动机短舱倾转角度-速度包线,并与XV-15的发动机短舱倾转角度-速度包线进行对比验证.结果表明,建立的倾转旋翼飞行器发动机短舱倾转角度-速度包线确定方法合理有效.For conversion mode of tiltrotor aircraft from helicopter mode to fixed wing airplane mode,an analysis method based on the transition flight＇s characteristics of morphing,and speed change was established to investigate the nacelle conversion envelope.The method includes the lower speed and higher speed envelopes.A detailed analysis of the matching relationship between the rotors aerodynamic forces and wing aerodynamic forces in the conversion mode was conducted.The lower conversion boundary was restricted by wing stall and the upper conversion boundary restricted by available power limited by engines.The XV-15 tiltrotor aircraft was taken as an example to analyze the conversion envelope.The results fairly agree with the XV-15 data,showing that the calculation methodology for the nacelle conversion envelope of tiltrotor aircraft is reasonable and effective.

关 键 词：倾转旋翼 旋翼 失速 过渡飞行 倾转模式 倾转角度-速度包线 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]