应用轨迹优化策略的直升机任务科目基元仿真  

Mission task element simulation of helicopter based on trajectory optimization strategy

作　　者：刘洋[1] 向锦武[1] 孟少华[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《飞行力学》2017年第3期41-45,共5页Flight Dynamics

基　　金：国家重点基础研究发展计划资助项目(2011CB707002)

摘　　要：任务科目基元的飞行试验是ADS-33E-PRF对直升机飞行品质的判定标准。针对直升机设计过程中飞行品质难以事先评定的特点,提出了一种基于轨迹优化策略的直升机任务科目基元数值仿真方法。该方法将飞行品质规范对直升机位置、姿态和速度的限制处理为状态量的边界约束,以完成任务科目基元的时间为目标函数,结合直升机自身的性能和安全性约束,建立了针对任务科目基元的直升机轨迹优化模型。求解该模型得到直升机完成相应任务科目基元所用的时间,便可定性判断直升机飞行品质是否满足ADS-33E-PRF对这一任务科目基元的要求,从而在设计之初对优化直升机总体设计参数提供参考。对某型直升机悬停转弯机动科目进行仿真计算,验证了该方法的正确性和有效性。The resuh of flight test on MTEs is the evaluation criteria for helicopter flying quality in ADS- 33E-PRF. A numerical simulation method is proposed based on trajectory optimization strategy in consid- eration of the difficulty of pre-evaluating helicopter flying quality during the helicopter design period. This method used the flight time as the objective function and translated the hmitations of helicopter space po- sition and attitude from handling qualities specification into path constraints. The maneuvering flight of a specified MTE was formulated as a trajectory optimization problem. By solving the problem to obtain the time consumption of helicopter completing the specific MTE, a qualitative evaluation of whether helicopter flying quality met the ADS-33E-PRF requirements was conducted. Thus a reference could be provided for general design parameters optimization in the preliminary design of helicopter. The simulation experiments on helicopter hovering turn demonstrate the validity and efficiency of the proposed method.

关 键 词：直升机 任务科目基元 轨迹优化 飞行品质 总体设计参数 

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]