• 论文 •

### 基于混合遗传算法的直升机前推/后拉配平

1. 1. 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, 沈阳 110136;
2. 北京航空航天大学 机械工程及自动化学院, 北京 100083
• 收稿日期:2016-10-27 修回日期:2017-02-06 出版日期:2017-10-20 发布日期:2017-03-24
• 通讯作者: 王巍 E-mail:wangwei7832@163.com
• 作者简介:王巍,女,博士研究生,讲师。主要研究方向:直升机飞行仿真建模技术;刘春,男,博士,教授,博士生导师。主要研究方向:飞行器仿真建模技术、虚拟现实。
• 基金资助:
沈阳航空航天大学国防重点学科实验室开放基金（SHSYS2015004）

### Push-forward/pull-backward trim for helicopter based on hybrid genetic algorithm

WANG Wei1, LIU Chun1, LI Dongsheng2

1. 1. Key Laboratory of Fundamental Science for National Defense of Aeronautical Digital Manufacturing Process, Shenyang Aerospace University, Shenyang 110136, China;
2. School of Mechanical Engineering and Automation, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
• Received:2016-10-27 Revised:2017-02-06 Online:2017-10-20 Published:2017-03-24

Abstract: To solve the problems that helicopter trim model has multivariate nonlinear equations, it is difficult to determine its initial value and the global optimal solution is non-unique, an efficient hybrid iteration algorithm is presented in this paper, which combines the genetic algorithm and the quasi-Newton method. The dynamic equations of the different modules of the helicopter are introduced. In modeling the rotor, considering characteristics of the motion and control of the rotor in the actual flight environment, an aerodynamic model of rotor based on dynamic inflow and the blade element theory with the rotor trim is established. The trim control vector and the constraint equations for push-forward/pull-backward are deduced in detail based on helicopter flight dynamic model. Since the objective function is constructed, trim problems are transformed into optimal computation. UH-60A helicopter in the push-forward/pull-backward flight is trimmed, and the trim results are compared with flight test data. It is shown that the pull-backward results agree well with flight data, and there is the discrepancy between the push-forward results and flight data. The primary contribution to the discrepancy of the trim of collective and pedal comes from inaccurate prediction of the unsteady aerodynamic characteristics of the rotor. It is a universal method that can be applied to helicopter trim simulation of different stable flight conditions.