倾转旋翼机低速回避区研究  

Research on low-speed avoidance zone of tiltrotor

作　　者：陈金鹤[1] 汪正中[1] 马玉杰[1] CHEN Jinhe;WANG Zhengzhong;MA Yujie(Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所直升机旋翼动力学重点实验室

出　　处：《北京航空航天大学学报》2019年第11期2184-2192,共9页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：针对单发、全发失效(OEI/AEI)后提升倾转旋翼机安全性的需求,基于最小化回避区思想分析预测倾转旋翼机的高度-速度低速回避区。首先,引入混合操纵模型,建立倾转旋翼机发动机失效后增广的二维纵向刚体飞行动力学模型,基于最优控制理论将倾转旋翼机低速回避区边界转化为安全着陆问题;然后,构建倾转旋翼机发动机失效后安全着陆飞行的连续非线性最优控制模型,采用间断有限元法(DPG)和非线性规划算法进行求解;最后,以XV-15为研究对象,验证了算法的准确性,并研究了不同飞行重量、操纵要求下,倾转旋翼机的单发、全发失效的高度-速度低速回避区,分析了倾转短舱对低速回避区的影响,给出了XV-15单发失效的垂直起飞最大安全重量。This paper focuses on the analysis and prediction of the height-velocity low-speed avoidance zone of tiltrotor based on the idea of minimizing avoidance zone,aiming at improve the safety of tiltrotor aircraft in one/all engine inoperative(OEI/AEI).First,mixed control model is introduced to establish an augmented longitudinal two-dimensional rigid-body flight dynamic model after engine failure of tiltrotor.Second,Based on the optimal control theory,the boundary of avoidance zone is transformed into a safe landing problem,then a continuous nonlinear optimal control model of tiltrotor for landing safely after engine failure is established,solved it by discontinuous finite element method(DPG)and nonlinear programming algorithm.Finally,Using XV-15 as the sample vehicle,the accuracy of the algorithm is verified.And the height-speed avoidance zone under different flight weight or control restraint after one/all engine inoperative was studied,the influence of nacelle on the low-speed avoidance zone is analyzed,the maximum safe gross weight suggested for XV-15 during vertical operation is given after one engine failure.

关 键 词：倾转旋翼机 最优控制理论 单/全发失效(OEI/AEI) 低速回避区 间断有限元法(DPG) 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计] TB553[理学—物理]