气动参数对闭环飞机短周期模态特性的影响

徐王强; 王立新

doi:10.13700/j.bh.1001-5965.2017.0109

气动参数对闭环飞机短周期模态特性的影响

doi: 10.13700/j.bh.1001-5965.2017.0109

徐王强,
王立新^,

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

作者简介:
徐王强男, 博士研究生。主要研究方向:飞机设计、飞行安全

王立新男, 教授, 博士生导师。主要研究方向:飞机设计、飞行动力学与控制、飞行安全

通讯作者:
王立新, E-mail:wlx_c818@163.com

中图分类号: V212.1
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出版历程
- 收稿日期: 2017-03-02
- 录用日期: 2017-06-02
- 网络出版日期: 2018-02-20

Influence of aerodynamic parameters on short-period mode characteristics of closed-loop aircraft

XU Wangqiang,
WANG Lixin^,

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

More Information

Corresponding author: WANG Lixin, E-mail:wlx_c818@163.com

摘要

摘要:
现代高性能战斗机均采用放宽静稳定性的布局构型，需通过先进飞行控制的设计来保证其闭环飞机在全飞行包线内均具有优良的动态特性。受到舵面操纵特性的限制，飞行控制系统（FCS）的能力是有限的，即飞机本体的气动参数需满足一定的要求才能保证闭环系统的飞行品质。本文建立了研究本体气动参数对闭环飞机短周期模态特性影响规律的方法，采用等效参数准则，以基于模型参考动态逆控制律的某放宽静稳定飞机为算例，计算分析了不同本体气动参数取值大小对闭环飞机短周期模态特性的影响规律。结果表明，升降舵操纵效能是影响闭环飞机短周期模态特性的主要因素，本体气动参数需满足一定的适配关系才能保证闭环飞机具有优良的短周期飞行品质。研究方法和结果对于放宽静稳定性飞机的本体设计与飞行控制系统设计等都具有很好的参考价值。
- 本体气动参数 /
- 舵面效能 /
- 短周期模态特性 /
- 模型参考动态逆 /
- 飞行品质
Abstract:
Owing to the relaxed static stability technology applied to the modern high-performance fighter aircraft, the design of an advanced flight control system is required to confirm its closed-loop system for an excellent dynamic property within the flight envelope. The ability of flight control system (FCS) is limited as a result of the control effectiveness and deflection rate of the control surface. The designed aerodynamic parameters of aircraft must meet certain requirements to confirm good flying qualities in its closed-loop system. This paper presents a new method which describes the influence of various aerodynamic parameters on short-period mode characteristics of closed-loop aircraft. A relaxed static stability aircraft with model reference dynamic inversion control law is provided to investigate the influence rules of various aerodynamic parameters on short-period mode characteristics based on the equivalent parameter criterion. The results show that the elevator control effectiveness has a great influence on the short-period mode characteristics and the aerodynamic parameters need to match a certain match value set to keep excellent short-period mode flying qualities. The proposed method can provide reference for flight control system design with the optimized aerodynamic parameters for relaxed static stability aircraft.
- aerodynamic parameters /
- control surface effectiveness /
- short-period mode characteristics /
- model reference dynamic inversion /
- flying qualities

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图 1 本体气动参数对闭环飞机短周期模态特性影响规律研究流程

Figure 1. Process for analyzing influence rules of aerodynamic parameters on short-period mode characteristics of closed-loop aircraft

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图 2 模型参考动态逆结构

Figure 2. Model reference dynamic inversion structure

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图 3 升降舵操纵效能与稳定导数的飞行品质边界

Figure 3. Flying qualities boundary elevator control efficiency and stability derivatives

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图 4 升降舵操纵效能与阻尼导数的飞行品质边界

Figure 4. Flying qualities boundary of elevator control efficiency and damping derivatives

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图 5 升降舵操纵效能与升力线斜率的飞行品质边界

Figure 5. Flying qualities boundary of elevator control efficiency and lift curve slope

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图 6 满足1级品质的气动参数适配值集合

Figure 6. Match value set of aerodynamic parameters to satisfy level 1 flying qualities

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图 7 阻尼导数与稳定导数的适配区域

Figure 7. Match value area of damping derivatives and stability derivatives

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图 8 不同升降舵操纵效能下的气动参数适配值集合

Figure 8. Match value set of aerodynamic parameters with different elevator control efficiency

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表 1 飞机初始本体气动参数及变化范围

Table 1. Initial aircraft aerodynamic parameters and their variation range

气动参数	初始值	变化范围
C_mq	-3.43	-15~-0.1
C_mα	-0.12	-0.72~0.28
C_Lα	3.9	1.9~5.9
C_{mδ_e}	-0.65	-0.11~-0.70

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表 2 不同操纵导数时评定结果对比

Table 2. Comparison of assessment results with different control derivatives

C_{mδ_e}	ω_sp/(rad·s^-1)	ξ_sp	1/T_θ₂	τ_e/s	品质
-0.13	2.8	0.53	0.38	0.200 3级	3级
-0.32	2.9	0.46	0.40	0.107 2级	2级
-0.65	3.3	0.41	0.46	0.059 1级	1级
-0.70	3.3	0.41	0.46	0.059 1级	1级

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表 3 不同操纵导数和稳定导数时评定结果对比

Table 3. Comparison of assessment results with different control derivatives and different stability derivatives

C_{mδ_e}	C_mα	ω_sp/ (rad·s^-1)	ξ_sp	1/T_θ₂	τ_e/s	品质
-0.36	-0.72	2.8	0.45	0.53	0.087 1级	1级
	-0.12	2.7	0.41	0.56	0.091 1级	1级
	0.28	2.7	0.38	0.57	0.102 2级	2级
-0.32	-0.72	2.7	0.48	0.53	0.096 1级	1级
	-0.12	2.7	0.40	0.57	0.107 2级	2级
	0.28	2.7	0.36	0.60	0.117 2级	2级
-0.15	-0.72	2.7	0.42	0.56	0.184 2级	2级
	-0.12	2.8	0.38	0.59	0.192 2级	2级
	0.28	2.7	0.34	0.70	0.201 3级	3级

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表 4 不同操纵导数和阻尼导数的评定结果对比

Table 4. Comparison of assessment results with different control derivatives and different damping derivatives

C_{mδ_e}	C_mq	ω_sp/ (rad·s^-1)	ξ_sp	1/T_θ₂	τ_e/s	品质
-0.36	-15	2.7	0.39	0.56	0.074 1级	1级
	-3.43	2.7	0.41	0.56	0.091 1级	1级
	-0.1	2.8	0.42	0.56	0.100 2级	2级
-0.32	-15	2.7	0.37	0.59	0.099 1级	1级
	-3.43	2.7	0.40	0.57	0.107 2级	2级
	-0.1	2.8	0.41	0.57	0.112 2级	2级
-0.15	-15	2.7	0.36	0.59	0.181 2级	2级
	-3.43	2.8	0.38	0.59	0.192 2级	2级
	-0.1	2.8	0.38	0.57	0.201 3级	3级

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表 5 不同操纵导数和升力线斜率时评定结果对比

Table 5. Comparison of assessment results with different control derivatives and different lift curve slope

C_{mδ_e}	C_Lα	ω_sp/ (rad·s^-1)	ξ_sp	1/T_θ₂	τ_e/s	品质
-0.36	5.9	2.7	0.39	0.65	0.074 1级	1级
	3.9	2.7	0.41	0.56	0.091 1级	1级
	1.9	2.7	0.46	0.54	0.100 2级	2级
-0.32	5.9	2.7	0.36	0.70	0.098 1级	1级
	3.9	2.7	0.40	0.57	0.107 2级	2级
	1.9	2.7	0.42	0.56	0.115 2级	2级
-0.15	5.9	2.7	0.35	0.73	0.181 2级	2级
	3.9	2.8	0.38	0.59	0.192 2级	2级
	1.9	参数剧烈振荡，拟配效果差，品质低于3级

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