基于不确定性的旋翼转速优化直升机参数设计

doi:10.7527/S1000-6893.2015.0285

固体力学与飞行器总体设计

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基于不确定性的旋翼转速优化直升机参数设计

徐明, 李建波, 彭名华, 刘铖

南京航空航天大学直升机旋翼动力学国家级重点实验室, 南京 210016

收稿日期:2015-07-20 修回日期:2015-10-19 出版日期:2016-07-15 发布日期:2015-10-22
通讯作者: 李建波男,博士,研究员,博士生导师。主要研究方向:旋翼类飞行器总体设计、直升机气动及飞行动力学研究、旋翼系统设计。Tel.:025-84895188,E-mail:ljb101@nuaa.edu.cn;Tel.:025-84895188,E-mail:ljb101@nuaa.edu.cn E-mail:ljb101@nuaa.edu.cn
作者简介:徐明男,博士研究生。主要研究方向:直升机总体设计、旋翼空气动力学、直升机飞行力学。Tel.:025-84895188,E-mail:xuming18237@nuaa.edu.cn;彭名华男,博士。主要研究方向:直升机总体设计、直升机飞行力学。Tel.:025-84895188,E-mail:pmh@nuaa.edu.cn;刘铖男,博士研究生。主要研究方向:直升机总体设计、直升机气动设计。Tel.:025-84895188,E-mail:liucheng713@hotmail.com
基金资助:
中央高校基本科研业务费专项资金；江苏省普通高校研究生科研创新计划（CXLX13_164)

Parameter design of helicopter with optimum speed rotor based on uncertainty optimization

XU Ming, LI Jianbo, PENG Minghua, LIU Cheng

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2015-07-20 Revised:2015-10-19 Online:2016-07-15 Published:2015-10-22
Supported by:
the Fundamental Research Funds for the Central Universities; Funding of Jiangsu Innovation Program for Graduate Education (CXLX13_164)

摘要/Abstract

摘要：

为了提高旋翼转速优化直升机总体参数设计质量，基于不确定性多学科设计优化方法，对旋翼转速优化直升机的参数设计进行了研究。首先对最优旋翼转速的不确定性进行分析与建模，同时也考虑了直升机加工制造、材料老化引起的不确定性因素，对比发现最优旋翼转速是旋翼转速优化直升机设计中的主要不确定性因素；然后在协同优化框架下，分别建立了直升机飞行性能、直升机重量、飞行稳定性与变转速涡轴发动机性能计算模型；最后以续航性能为系统学科，悬停性能、飞行稳定性分别作为子学科，进行多学科的不确定性优化设计，得到了3种不确定性优化设计方案。通过对比分析可以发现：第2种方案为旋翼转速优化直升机的最佳参数设计方案，该方案满足悬停需用功率低于350 kW，飞行稳定性指数小于0.8等约束条件的概率不低于95.46%，并且直升机的最大航时期望值也较大。

关键词: 旋翼转速优化, 直升机总体参数, 不确定性, 多学科优化, 航时

Abstract:

In order to improve the quality of design schemes of helicopter with optimum speed rotor, this paper studies the design method of helicopter with optimum speed rotor, based on uncertainty multidisciplinary design optimization. First of all, the uncertainty factors of helicopter parameters are analyzed and modeled from optimal rotor speed, processing error and material deterioration, and it shows that the optimal rotor speed is the main uncertainty factor in the design of helicopter with optimum speed rotor. And then under the collaborative optimization framework, the models of helicopter flight performance, helicopter weight, flight stability, and the performance of turboshaft engine with variable rotor speed are established. Finally, the design of helicopter with optimum speed rotor based on uncertainty multidisciplinary optimization is investigated, which is based on two subsystem design tasks, i.e., hovering performance and flight stability, and one system level design task about helicopter endurance. Optimization results show that the second scheme for the helicopter with the optimum speed rotor is the best one; its probability of satisfying the constraints of required power being less than 350 kW in hover and index of flight stability being less than 0.8, is not less than 95.46%, and expectation of endurance is also bigger.

Key words: optimum speed rotor, helicopter preliminary parameters, uncertainty, multidisciplinary optimization, endurance

中图分类号:

V211.3

徐明, 李建波, 彭名华, 刘铖. 基于不确定性的旋翼转速优化直升机参数设计[J]. 航空学报, 2016, 37(7): 2170-2179.

XU Ming, LI Jianbo, PENG Minghua, LIU Cheng. Parameter design of helicopter with optimum speed rotor based on uncertainty optimization[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(7): 2170-2179.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于不确定性的旋翼转速优化直升机参数设计

Parameter design of helicopter with optimum speed rotor based on uncertainty optimization

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