摘要
针对双螺旋桨推进复合式直升机在过渡阶段存在的操纵面冗余问题,设计了不同操纵机构之间操纵分配系数以及最优俯仰角过渡路线。建立了复合式直升机动力学模型并提出复合式高速直升机操纵策略。对于过渡段以全机功率最优为优化目标,使得操纵杆量连续光滑过渡为边界条件,优化得到最优过渡路线以及不同操纵机构之间操纵分配系数。对于低速阶段会出现的推进螺旋桨涡环状态,选择最优过渡路线规避推进螺旋桨涡环状态。仿真结果显示,优化得到的分配系数及过渡路线能够使复合式直升机不同通道的操纵杆量光滑连续过渡,确保驾驶员的操纵性能。
Aiming at the problem of control surface redundancy in the transition phase of dual propeller propulsion compound helicopter,the control distribution coefficient between different control mechanisms and the optimal transition route are designed.The dynamic model of the compound helicopter is established,and the control strategy of the compound high‐speed helicopter is proposed.The optimal power of the whole helicopter is taken as the optimization objective,and the continuous smooth transition of the control lever is taken as the boundary condition.The optimal transition route and the control distribution coefficient between different control mechanisms are obtained.The simulation results show that the optimized distribution coefficient can guarantee the smooth and continuous transition of the control lever in different channels of the compound helicopter,thus ensuring the pilot’s control performance.
作者
王涌钦
余新
陈仁良
叶尚卿
WANG Yongqin;YU Xin;CHEN Renliang;YE Shangqing(National Key Laboratory of Rotorcraft Aeromechanics,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China;Jincheng Unmanned System Co.Ltd.,Nanjing 210002,China)
出处
《南京航空航天大学学报》
CAS
CSCD
北大核心
2022年第2期211-218,共8页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
复合式高速直升机
控制策略
分配系数
过渡路线
飞行动力学模型
compound high speed helicopter
control strategy
distribution coefficient
transition route
flight dynamics model
