含冗余控制面飞行器配平优化设计与性能分析

范一鸣; 李响; 张后军

doi:10.7638/kqdlxxb-2023.0045

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含冗余控制面飞行器配平优化设计与性能分析

研究论文 | 更新时间：2026-05-28

- 含冗余控制面飞行器配平优化设计与性能分析
- Optimal design and performance analysis of aircraft trim configuration with redundant control surfaces
- 空气动力学学报 2024年42卷第3期页码：102-110
- 作者机构：
  
  1. 北京理工大学宇航学院,北京,100081
  2. 北京机电工程研究所,北京,100083
- 作者简介：
  
  范一鸣（1995—），男，硕士研究生，研究方向：飞行动力学与控制. E-mail：ln_fym@qq.com
  李响*（1972—），博士，副教授，研究方向：飞行器动力学性能分析，飞行器结构分析与优化设计. E-mail：lx_0207@sina.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0045
  中图分类号： V212.13
- 纸质出版：2024
- 稿件说明：
移动端阅览
范一鸣, 李响, 张后军. 含冗余控制面飞行器配平优化设计与性能分析[J]. 空气动力学学报, 2024, 42(3): 102−110.

FAN Yiming, LI Xiang, ZHANG Houjun. Optimal design and performance analysis of aircraft trim configuration with redundant control surfaces[J]. 2024, 42(3): 102-110.
范一鸣, 李响, 张后军. 含冗余控制面飞行器配平优化设计与性能分析[J]. 空气动力学学报, 2024, 42(3): 102−110. DOI： 10.7638/kqdlxxb-2023.0045

FAN Yiming, LI Xiang, ZHANG Houjun. Optimal design and performance analysis of aircraft trim configuration with redundant control surfaces[J]. 2024, 42(3): 102-110. DOI： 10.7638/kqdlxxb-2023.0045.

摘要

含冗余控制面的飞行器配平问题是一个超静定问题，从性能需求角度构建3个单目标配平构型优化问题，在高度为5 km、马赫数为0.85的定直平飞状态下，采用遗传算法求解。结果表明：若以最大升阻比为目标，采用内升降副翼配平，其余舵面中立；若要使配平所需控制面偏角绝对值和最小、达到降低控制能量的目的，则采用中升降副翼配平，其余舵面中立；若要实现控制面间偏角相差最小、达到减小雷达反射的目的，那么3组升降副翼需同时上偏

3.7882

°。结合气动数据，分析了上述结果的合理性。将3个目标两两组合，采用非支配排序遗传算法求解得到Pareto非劣解，发现3个配平目标两两互相冲突，一个目标性能的提高会降低其他目标性能，但降低性能的比例不同。最后综合考虑3个优化目标，采用理想点最小距离法从Pareto非劣解中选择最优构型，最终得到配平构型迎角

1.7908

°、内升降副翼−

0.0009588

°、中升降副翼−

4.1908

°、外升降副翼−

4.9232

°。本文的工作对合理确定含冗余控制面飞行器配平构型与性能综合分析有一定的参考意义。

Abstract

The trim problem of aircraft with redundant control surfaces is a hyperstatic problem. To determine the appropriate trim configuration

three single trim configuration optimization problems were constructed from the perspective of performance requirements. Under a fixed level flig

ht state at an altitude of 5 km and Mach number of 0.8

genetic algorithm was used to solve the problem. Aiming for maximum lift to drag ratio

use inner lift aileron trim and keep the remaining control surfaces neutral; To achieve the objective of reducing control energy by minimizing the absolute deviation angle of the control surface

the mid lift aileron configuration is adopted to trim

while the remaining control surfaces are neutral; To achieve the objective of reducing radar reflection by minimizing the deviation angle difference between control surfaces

three sets of lift ailerons are simultaneously tilted up by

3.7882

°. Based on aerodynamic data

the rationality of the above results was analyzed. Combining three single objective problems pairwise and using a non-dominated sorting genetic algorithm to solve

Pareto non inferior solutions were obtained. It was found that the three balancing objectives were conflicting pairwise

and improving the performance of one objective would reduce the performance of the other objectives

but the proportion of performance reduction was different. Taking into account three optimization objectives

The ideal point minimum distance method is adopted to select the optimal configuration from Pareto non inferior solutions. The final trim configuration is

1.7908

° angle of attack

−

0.0009588

° inner lift aileron

−

4.1908

° middle lift aileron

and −

4.9232

° outer lift aileron. Based on performance requirements

an optimization model is constructed for balancing

and combined with the ideal point minimum distance method. The investigation of this paper has certain reference significance for the reasonable calculation of the trim configuration and performance comprehensive analysis of aircraft with redundant control su

rfaces.

关键词

Keywords

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