基于可达平衡集分析战斗机大迎角机动性能

季雨璇; 朱玉莲; 文梁栋

doi:doi:10.3969/j.issn.1671-637x.2020.08.016

电光与控制, 2020, 27 (8): 80, 网络出版: 2020-12-25

基于可达平衡集分析战斗机大迎角机动性能

Analysis of Fighter Maneuverability at High Angle-of-Attack Based on Attainable Equilibrium Sets

论文大纲

季雨璇朱玉莲文梁栋

作者单位

南京航空航天大学，南京 211106

可达平衡集非线性分析战斗机机动性能 attainable equilibrium set nonlinear analysis fighter maneuverability

摘要

战斗机是空战的主力军，在大迎角状态下，战斗机的稳定性和操纵性发生急剧变化，易出现失速、偏离和尾旋等危险状况。以F-16战斗机作为分析对象，基于可达平衡集理论求解三维机动可达平衡区域，利用特征根分析平衡点局部稳定性，可为飞行员在空战机动过程中提供安全可靠的空战决策参考。仿真结果表明，大迎角区域下可达范围急剧减少且不对称，对驾驶员稳定控制操纵造成很大限制，与实际情况一致。

Abstract

The fighters are the main force in air combat.At high Angle-of-Attack (AOA),the stability and maneuverability of the fighters change drastically,and dangerous conditions such as stall,deviation and spin are prone to occur.In this paper,the F-16 fighter is used as the analysis object to solve the 3D maneuverable attainable equilibrium area based on the theory of attainable equilibrium sets,and analyze the local stability of the balance point by using the eigenvalue,which can provide a safe and reliable decision reference for the pilot in the maneuver process of the air combat.The simulation results show that the attainable range in the high angle-of-attack area is drastically reduced and asymmetrical,which is very limited for the driver′s stable control and operation,and it is consistent with the actual situation.

参考文献

[1] GOMAN M G,KHRAMTSOVSKY A V,KOLESNIKOV E N.Evaluation of aircraft performance and maneuverability by computation of attainable equilibrium sets［J］.Journal of Guidance,Control,and Dynamics,2008,31(2):329-339.

[2] RICHARDSON J R,ATKINS E M,KABAMBA P T,et al.Envelopes for flight through stochastic gusts［J］.Journal of Guidance,Control,and Dynamics,2013,36(5):1464-1476.

[3] MENON P K,SENGUPTA P,VADDI S,et al.Impaired aircraft performance envelope estimation［J］.Journal of Aircraft,2013,50(2):410-424.

[4] TEKLES N,XARGAY E,CHOE R,et al.Flight envelope protection for NASA’s transport class model［C］//AIAA Guidance,Navigation,and Control Conference,2014:1-47.

[5] TANG L,ROEMER M,BHARADWAJ S.An integrated aircraft health assessment fault contingency management system for aircraft［C］//AIAA Guidance,Navigation and Control Conference and Exhibit,2008.doi:10.2514/6.2008-6505.

[6] LI Y N,YANG L Y,SHEN G Z.Steady maneuver envelope evaluation for aircraft with control surface failures［C］//IEEE Aerospace Conference,2012:1-10.

[7] 刘瑛,杜光勋,全权,等.基于 Hamilton-Jacobi 方程的飞行器机动动作可达集分析［J］.自动化学报,2016,42(3):347-357.

[8] 武朋玮,李颖晖,郑无计,等.基于可达集方法的结冰飞机着陆阶段安全风险评估［J］.航空学报,2018,39(12):40-48.

[9] 禹志龙,李颖晖,周驰,等.基于可达集的故障飞机着陆阶段安全包线研究［J］.飞行力学,2019(5):35-39.

[10] 李晓刚.歼击机大迎角尾旋特性分析和改出研究［D］.南京:南京航空航天大学,2016.

[11] 余朝军,季雨璇,甄子洋,等.基于可达平衡集的战斗机大迎角特性分析方法:CN201910558989.0［P］.2019-10-18.

[12] NGUYEN L T,OGBURN M E,GILBERT W P,et al.Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability［R］.Hampton,VA:NASA Langley Research Center,1979.

季雨璇, 朱玉莲, 文梁栋. 基于可达平衡集分析战斗机大迎角机动性能[J]. 电光与控制, 2020, 27(8): 80. JI Yuxuan, ZHU Yulian, WEN Liangdong. Analysis of Fighter Maneuverability at High Angle-of-Attack Based on Attainable Equilibrium Sets[J]. Electronics Optics & Control, 2020, 27(8): 80.

基于可达平衡集分析战斗机大迎角机动性能

关于本站 Cookie 的使用提示

全站搜索

基于可达平衡集分析战斗机大迎角机动性能

相关论文

相关资讯

关于本站 Cookie 的使用提示

全站搜索