结冰条件下飞机全包线模态特性分析方法

doi:10.12305/j.issn.1001-506X.2021.10.24

系统工程与电子技术 ›› 2021, Vol. 43 ›› Issue (10): 2893-2901.doi: 10.12305/j.issn.1001-506X.2021.10.24

结冰条件下飞机全包线模态特性分析方法

伍强¹, 徐浩军¹, 裴彬彬^1,*, 朱和铨², 武欣¹

1. 空军工程大学航空工程学院, 陕西西安 710038
2. 中国人民解放军93705部队, 河北唐山 064200

收稿日期:2020-10-12 出版日期:2021-10-01 发布日期:2021-11-04
通讯作者: 裴彬彬
作者简介:伍强(1997—), 男, 硕士研究生, 主要研究方向为飞行器总体设计与飞行安全|徐浩军(1965—), 男, 教授, 硕士, 主要研究方向为飞行器总体设计与飞行安全|裴彬彬(1991—), 男, 讲师, 博士, 主要研究方向为飞行器总体设计与性能评估|朱和铨(1990—), 男, 博士, 主要研究方向为飞行器总体设计与性能评估|武欣(1997—), 男, 硕士研究生, 主要研究方向为飞行器总体设计与飞行安全
基金资助:
国家自然科学基金(61873351)

Analysis method of aircraft modal characteristics within the full envelope under icing conditions

Qiang WU¹, Haojun XU¹, Binbin PEI^1,*, Hequan ZHU², Xin WU¹

1. Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China
2. Unit 93705 of the PLA, Tangshan 064200, China

Received:2020-10-12 Online:2021-10-01 Published:2021-11-04
Contact: Binbin PEI

摘要/Abstract

摘要：

针对飞机带冰飞行时全包线范围内飞行品质评估问题, 提出一种结合自适应拟配初值计算与时域等效系统拟配对整个包线内的典型模态参数快速计算方法。建立了典型的人-机-环系统模型, 通过数值仿真得到飞机对于方向舵倍脉冲操纵的响应数据, 在分析时域响应数据特征的基础上, 提出自适应计算横航向等效系统拟配初值的方法, 解决了拟配初值的敏感性问题。运用时域等效系统拟配法, 分别获取了某型飞机干净构型及不同结冰严重程度时, 整个包线范围内横航向模态参数特性, 进而从整体的角度量化了结冰对飞机飞行品质的影响。仿真结果表明，所提方法在全包线范围内具有较好的适应性，为快速分析飞行器纵横向典型模态特性提供了新的思路，具有较好的工程应用前景。

关键词: 品质评估, 等效系统拟配, 拟配初值, 自适应初值计算, 数值仿真

Abstract:

Aiming at the problem of flight quality evaluation within the full envelope under icing conditions, a method for fast calculation of typical mode parameters in the whole envelope is proposed by combining adaptive initial value calculation with time-domain equivalent system fitting. A typical man-machine-loop system model is established. Numerical simulation is used to obtain the response data of the aircraft for rudder doublet manipulation. Based on the analysis of the characteristics of the time-domain response data, a method of adaptive initial value calculation of the lateral and directional equivalent system fitting is proposed to solve the sensitivity problem of the initial value. The time-domain equivalent system fitting method is used to obtain the lateral and directional modal parameter characteristics of a certain aircraft clean configuration and different degrees of icing severity in the entire envelope, and the effect of icing on the flight quality of the aircraft is quantified from an overall perspective. The simulation results show that the proposed method has good adaptability in the full envelope, which provides a new idea for the rapid analysis of the longitudinal and transverse typical modal characteristics of aircraft, and has a good engineering application prospect.

Key words: quality evaluation, equivalent system fitting, initial value of fitting, adaptive initial value calculation, numerical simulation

中图分类号:

V212

伍强, 徐浩军, 裴彬彬, 朱和铨, 武欣. 结冰条件下飞机全包线模态特性分析方法[J]. 系统工程与电子技术, 2021, 43(10): 2893-2901.

Qiang WU, Haojun XU, Binbin PEI, Hequan ZHU, Xin WU. Analysis method of aircraft modal characteristics within the full envelope under icing conditions[J]. Systems Engineering and Electronics, 2021, 43(10): 2893-2901.

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序号	T_R	T_S	ω_d	ζ_d
1	1.4	-20	1.5	0.01
2	1.4	-10	1.5	0.01
3	1.4	-5	1.5	0.01
4	1.4	-20	1.5	0.06
5	1.4	-10	1.5	0.06
6	1.4	-5	1.5	0.06
7	1.4	-20	1.5	0.1
8	1.4	-10	1.5	0.1
9	1.4	-5	1.5	0.1
10	0.5	-20	1.5	0.1
11	1.0	-20	1.5	0.1
12	2.0	-20	1.5	0.1
13	3.0	-20	1.5	0.1
14	4.0	-20	1.5	0.1
15	5.0	-20	1.5	0.1

序号	J	T_S	ω_d	ζ_d
1	1.194 2e-05	-20.001 5	1.500 0	0.010 0
2	6.641 4e-05	-10.003 0	1.500 0	0.010 0
3	6.232 0e-05	-5.000 0	1.500 0	0.010 0
4	5.572 9e-05	-20.071 3	1.500 1	0.059 9
5	5.860 6e-05	-10.002 8	1.500 1	0.059 9
6	5.501 3e-05	-5.000 0	1.500 1	0.060 0
7	4.832 4e-05	-20.066 2	1.500 1	0.099 8
8	8.894 5e-05	-10.008 5	1.499 7	0.100 6
9	4.774 7e-05	-5.000 0	1.500 1	0.099 8
10	4.809 7e-15	-20.000 0	1.500 0	0.100 0
11	2.960 7e-07	-20.005 9	1.500 1	0.099 8
12	3.033 9e-04	-20.164 4	1.499 6	0.100 4
13	5.720 8e-04	-20.325 3	1.498 8	0.100 4
14	0.005 2	-21.003 1	1.496 8	0.101 8
15	0.017 0	-21.894 1	1.494 7	0.103 1

T	J	T_S	ω_d	ζ_d
设定值	-	-20	1.5	0.01
1.0	4.832 4e-05	-20.066 2	1.500 1	0.099 8
2.0	1.011 4e-04	-20.025 9	1.499 9	0.100 0
3.0	6.061 3e-05	-20.012 6	1.500 1	0.100 0
4.0	4.522 7e-04	-20.019 8	1.500 0	0.100 1
5.0	0.857 0	-20.395 4	1.497 4	0.102 2

参数	一级品质	二级品质	三级品质
ζ_d	大于0.08	大于0.02	小于0.02

速度/m·s^-1	ζ_d	J
138	0.124 3	7.557e-05
144	0.122 6	5.619e-05
150	0.120 6	8.132e-06
156	0.119 6	0.000 13
162	0.117 9	0.000 11
168	0.116 8	0.000 31
174	0.116 2	4.151e-05
180	0.115 3	3.253e-05
186	0.114 7	8.99e-05
192	0.114 4	0.002 08
198	0.113 8	7.183e-05
204	0.113 2	0.000 22
210	0.112 9	0.000 24
216	0.112 8	0.000 16
222	0.113 0	0.001 29

结冰条件下飞机全包线模态特性分析方法

Analysis method of aircraft modal characteristics within the full envelope under icing conditions

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速度/m·s^-1	ζ_d	J
138	0.092 3	8.539e-05
144	0.093 1	7.186e-06
150	0.092 6	3.089e-05
156	0.091 4	3.423e-05
162	0.090 5	6.438e-05
168	0.089 6	3.914e-05
174	0.088 8	0.000 11
180	0.088 3	0.000 26
186	0.087 8	8.575e-05
192	0.087 5	0.000 54
198	0.087 0	0.000 19
204	0.086 7	0.000 25
210	0.086 5	0.001 43
216	0.086 4	0.000 43
222	0.086 3	0.002 75

速度/m·s^-1	ζ_d	J
138	0.083 5	0.000 46
144	0.084 5	0.000 11
150	0.085 2	4.819e-05
156	0.085 2	4.319e-05
162	0.084 4	2.167e-05
168	0.083 3	4.090e-05
174	0.082 5	8.296e-05
180	0.081 9	6.032e-05
186	0.081 4	0.000 11
192	0.081 0	0.000 11
198	0.080 5	0.000 15
204	0.080 3	0.000 33

速度/m·s^-1	ζ_d	J
138	0.069 6	0.004 16
144	0.072 5	3.425e-06
150	0.074 0	0.000 89
156	0.075 7	0.000 97
162	0.076 3	2.916e-05
168	0.075 3	3.152e-05
174	0.073 7	0.000 40
180	0.074 0	7.027e-05
186	0.073 4	6.245e-05