大型运输机增升结构多参量耦合疲劳试验方法

王育鹏; 贺谦; 夏峰; 许飞; 宋鹏飞; 张超

doi:10.13224/j.cnki.jasp.20230566

大型运输机增升结构多参量耦合疲劳试验方法

doi: 10.13224/j.cnki.jasp.20230566

王育鹏^{1, 2,},
贺谦^{1, 2,},
夏峰²,
许飞¹,
宋鹏飞²,
张超³

1.
中国飞机强度研究所强度与结构完整性全国重点实验室，西安 710068
2.
中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室，西安 710068
3.
南京航空航天大学航空学院，南京 210016

基金项目: 国家自然科学基金（52235003）

详细信息

作者简介:
王育鹏（1969−），男，研究员，硕士，主要从事飞机结构强度研究。E-mail：Wangyp623@126.com

中图分类号: V216.5
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- 文章访问数: 433
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- 被引次数: 0
出版历程
- 收稿日期: 2023-09-05
- 网络出版日期: 2024-06-23

Spatial motion aircraft lift-rising structure fatigue life verification method with coupled multiparameter

WANG Yupeng^{1, 2
,},
HE Qian^{1, 2
,},
XIA Feng²,
XU Fei¹,
SONG Pengfei²,
ZHANG Chao³

1.
National Key Laboratory of Strength and Structural Integrity，Aircraft Strength Research Institute of China，Xi’an 710068，China
2.
Key Laboratory of Aviation Science and Technology on Full Scale Aircraft Structure Static and Fatigue Strength，Aircraft Strength Research Institute of China，Xi’an 710068，China
3.
College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
针对大型运输机增升结构疲劳试验面临的空间复杂运动翼面载荷精准施加、多系统多参量交互协同控制和复杂耦合验证系统安全运行等难点，开展了多维运动增升结构轨迹模拟、多参量耦合精准动态协同控制、复杂耦合试验系统实时联动安全保护等技术研究。建立了基于微分平坦的空间轨迹模拟方法，确保了翼面偏转过程载荷方向实时精准跟随；构建了随动机构运动速率优化模型，采用时序控制方法，实现了多系统多参量精准动态协同控制；建立了耦合系统功能失效联动保护策略和基于高频轮询模式的通讯状态监控方法，实现了复杂试验系统失效实时联动安全保护；形成一种大型运输机复杂增升结构多参量耦合疲劳试验方法。工程应用结果表明：该方法加载力线最大角度误差为1.8°，载荷最大相对动态误差2.69%，子系统安全保护响应时间最大值18 ms，确保了襟缝翼结构寿命评估的准确性和试验运行的可靠性。
- 增升结构 /
- 结构疲劳 /
- 空间轨迹模拟 /
- 多参量协同 /
- 系统失效保护
Abstract:
A structure fatigue life verification method for large aircraft lift-rising components was presented considering the spatial complex motion flap, the real-time direction of the load, multisystem and multiparameter cooperation control and system operation security. A spatial trajectory simulation method based on differential flatness theory was employed to ensure accurate real-time load direction during the flap unfixed-axis rotation. A velocity optimization model of following mechanism and a sequential control method were built to realize multiparameter accurate and dynamic cooperative control. To ensure the operation security of test system, a linkage protection mechanism combined with a communication monitoring method based on high-frequency polling pattern were established for abnormal condition of coupled test system. A spatial motion aircraft lift-rising structure life verification method with coupled multiparameter was established based on accurate load of spatial complex motion flap, multisystem and multiparameter cooperative control and complicated system security protection and the method was validated by a large transport aircraft flap fatigue test. The result showed that the maximum angle error of the load was 1.8°, relative dynamic error of the load was 2.69%, response time of subsystem security protection was 18 ms. The method can meet the requirements of flap fatigue life verification in load accuracy and system operation security protection, and provide a technical support for major project. The method can also provide referential technologies for motion mechanism fatigue life and reliability verification.
- lift-rising structure /
- structure fatigue life /
- spatial trajectory simulation /
- multiparameter cooperation /
- system operation security

HTML

图 1 三维空间轨迹与二维平面轨迹映射关系

Figure 1. Track mapping relationship between 2D and 3D space

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图 2 多系统多参量时序控制

Figure 2. Multisystem and multiparameters sequential control

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图 3 偏转角度/机构位移同步控制方法

Figure 3. Angle and displacement cooperative control method

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图 4 耦合系统功能失效联动保护策略

Figure 4. Linkage protection mechanism of coupled systems

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图 5 多系统通讯状态监测及保护策略

Figure 5. Communication monitoring and security protection

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表 1 系统功能失效的故障点

Table 1. Reasons of system failure

编号	故障类型	故障点
1	运动驱动系统故障	翼面偏转控制器故障
2		翼面偏转角度命令通讯线路故障
3		翼面偏转角度反馈通讯线路故障
4		随动机构运动命令通讯线路故障
5		随动机构运动反馈通讯线路故障
6		翼面偏转驱动系统断电故障
7		随动机构驱动系统断电故障
8		翼面偏转驱动电机故障
9		随动机构驱动电机故障
10	运动机构故障	翼面偏转卡滞
11		翼面偏转未到规定角度
12		随动机构运动卡滞
13		随动机构运动未到规定位置
14		随动机构无法锁死
15		随动机构位置开关故障
16		随动机构联轴器断裂
17	加载系统故障	加载控制系统断电
18		加载命令通讯线路故障
19		加载反馈通讯线路故障
20		加载做动器故障
21		作动器伺服阀故障
22		载荷传感器故障
23		加载连接件断裂
24	超差超限故障	翼面偏转角度偏转超限
25		随动机构运动位置超限
26		翼面偏转与随动机构运动干涉
27		随动机构间运动不同步
28		随动机构运动与翼面偏转不同步
29		加载载荷超限
30		加载点卸载不同步
31	系统间通讯故障	加载系统与翼面偏转系统通讯故障
32		加载系统与随动机构系统通讯故障
33		翼面偏转系统与随动机构系统通讯故障

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表 2 加载力线角度误差

Table 2. Load direction error value

翼面偏转角度/（°）	不同加载点加载力线角度误差/（°）
翼面偏转角度/（°）	1#	2#	3#	4#	5#	6#
0	0	0	0	0	0	0
10	0.3	0.5	0.3	0.3	0.3	0.4
20	0.4	1.5	1.2	1.1	1.3	1.2
27	1.2	1.7	1.5	1.5	1.5	1.6
30	1.4	1.8	1.6	1.6	1.8	1.8
35	1.3	1.3	1.3	1.4	1.6	1.4
40	0.6	0.7	1.2	0.7	0.3	1.4
41	0.7	1.1	0.8	0.7	0.3	1.3

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表 3 载荷静态误差

Table 3. Load static error value

翼面偏转角度/（°）	不同加载点载荷误差/%
翼面偏转角度/（°）	1#	2#	3#	4#	5#	6#
0	0	0	0	0	0	0
10	0.01	0.03	0.01	0.01	0.02	0.02
20	0.03	0.11	0.05	0.06	0.09	0.08
27	0.08	0.17	0.10	0.12	0.18	0.16
30	0.10	0.22	0.13	0.15	0.23	0.20
35	0.05	0.07	0.06	0.07	0.12	0.09
40	0.02	0.03	0.06	0.07	0.01	0.09
41	0.03	0.05	0.04	0.03	0.01	0.08

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表 4 载荷动态误差

Table 4. Load dynamic error value

翼面偏转角度/（°）	不同加载点载荷动态误差/%
翼面偏转角度/（°）	1#	2#	3#	4#	5#	6#
0	0	0	0	0	0	0
10	1.81	1.63	1.37	1.57	1.44	1.26
20	1.25	1.65	1.25	1.54	1.22	0.92
27	0.66	0.91	0.76	1.35	0.75	0.86
30	0.61	1.08	0.98	0.86	0.42	0.85
35	0.83	1.39	0.88	0.92	0.43	0.62
40	1.92	2.31	1.04	0.98	1.06	0.94
41	2.69	2.57	1.65	1.72	1.24	1.53

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表 5 通讯故障情况下子系统安全保护响应时间

Table 5. Security protection response time of subsystems in communication failure

序号	3套子系统响应时间/ms
序号	翼面偏转系统	随动机构运动系统	协调加载系统
1	12	10	18
2	11	11	16
3	13	13	17
4	10	13	16
5	15	16	16
6	15	18	17
7	18	18	18
8	16	18	16
9	13	15	17
10	12	15	15

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