求解直升机协调转弯状态的GA-SM配平与验证  

GA-SM trim and validation for solving coordinated-turn state of helicopter

作　　者：王巍 刘春 WANG Wei;LIU Chun(Civil Aviation College,Shenyang Aerospace University,Shenyang 110136,China;Key Laboratory of Fundamental Science for National Defense of Aeronautical Digital Manufacturing Process,Shenyang Aerospace University,Shenyang 110136,China)

机构地区：[1]沈阳航空航天大学民用航空学院,辽宁沈阳110136 [2]沈阳航空航天大学航空制造工艺数字化国防重点学科实验室,辽宁沈阳110136

出　　处：《飞行力学》2018年第5期71-76,共6页Flight Dynamics

基　　金：辽宁省教育厅基金资助(L201618);沈阳航空航天大学国防重点实验室开放基金资助(SHSYS2016004)

摘　　要：为了能快速搜索到直升机定常飞行状态的最佳平衡点,在分析直升机飞行仿真系统模型的基础上,建立了满足配平问题的目标函数,提出了一种基于混合遗传算法的配平计算分析方法。旋翼气动模型集成了桨叶的挥舞运动、旋翼动态入流模型和非定常动态失速气动模型。以直升机整机动力学模型为基础,详细推导出协调转弯状态下的约束条件和配平控制量。以UH-60A直升机为研究对象,进行了协调转弯的全机配平计算,并与飞行试验数据进行了对比验证。结果表明:脚蹬配平值误差较大,造成误差的可能原因是尾桨倾斜的附加垂向力引起了纵向、横向和航向全耦合;其他配平结果与飞行试验数据吻合较好。To search the best trim point of the steady state of helicopter quickly,an objective function for trimming is developed according to the analysis of the helicopter flight simulation system model,and a trim calculation method is proposed based on a hybrid genetic algorithm. The blade flap motion,the rotor dynamic inflow model and the unsteady dynamic stall aerodynamic model were contained in the rotor aerodynamic model. The constraint conditions and the trim control vector were deduced in detail in the coordinated turn according to the helicopter dynamic model.UH-60 A helicopter which is taken as an example in the coordinated turn is trimmed,and the trim results are compared with flight data. The results indicate that the discrepancy of the pedal is large,the reason may be that the vertical force of tail rotor tilting lead to the full coupling of vertical,horizontal and azimuth; the other trim results agree well with flight test data.

关 键 词：直升机 协调转弯 配平 遗传算法 单纯形法 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]