飞行器典型舵结构的热振试验研究

doi:10.12382/bgxb.2024.0865

摘要/Abstract

摘要：

针对热环境下飞行器舵面动力学响应复杂多变的问题,以典型舵面结构为研究对象,设计并搭建一种典型舵结构加热振动试验平台,开展不同热环境下舵面的热振试验研究,从而获取结构在不同热环境下的的传递函数。研究结果表明:该试验台可以针对典型舵结构两侧进行较为均匀的加热,并通过振动台施加外载荷来还原结构在真实飞行时的响应特性;该试验方法可进行20℃~600℃的飞行器热-振联合试验。

关键词: 飞行器, 舵面结构, 热振响应, 热模态, 石英灯加热

Abstract:

In response to the complex and variable dynamic response of aircraft control surfaces in hot environments,a typical control surface structure is studied. A heating vibration test platform for a typical control surface structure is designed and built for thermal vibration tests on the control surface under different thermal environments in order to obtain the transfer function of the structure under different thermal environments.The research results indicate that the test bench can provide relatively uniform heating on both sides of typical rudder structure,and restore the response characteristics of the structure during real flight by applying external loads through a vibration table.The experimental results indicate that the test method can be used for the combined thermal-vibration tests on aircraft at temperatures ranging from 20℃ to 600℃.The test method provides important engineering significance for the study of aircraft thermal-vibrationtests.

Key words: airocraft, control surface structure, thermal vibration response, thermal modal, quartz lamp heating

王鹏飞, 刘振, 周长伟, 党天骄. 飞行器典型舵结构的热振试验研究[J]. 兵工学报, 2024, 45(S2): 170-175.

WANG Pengfei, LIU Zhen, ZHOU Changwei, DANG Tianjiao. Airocraft Research on Thermal Vibration Test of Typical Rudder Structure[J]. Acta Armamentarii, 2024, 45(S2): 170-175.

图/表 11

图1 石英灯加热原理图

Fig.1 Heating principle diagram of quartz lamp for thermal test

图2 有限元模型与试验模型示意图

Fig.2 Schematic diagram of FEM and experimental model

图3 试验件结构有限元模型修正流程图

Fig.3 Flow chart of FEM correction of test piece structure

图4 有限元(左)与试验(右)振型图

Fig.4 Diagram of FEM(left )and experimental modes(right)

表1 模态修正后试验件模态试验结果

Table 1 Modal test results of test specimens after modal correction

阶数	试验模态频率/Hz	有限元模态频率/Hz	MAC值	频率偏差/%
1	185	183.4	0.94	0.9
2	226.7	233	0.97	2.8
3	350.6	338.9	0.90	3.3
4	513.6	484.3	0.82	5.7

图5 含水冷装置的舵面系统

Fig.5 Control surface system with water cooling device

表2 含水冷装置修正后模态试验结果

Table 2 Modal test results after correction of water cooling device

阶数	试验模态频率/Hz	有限元模态频率/Hz	MAC值	频率偏差 (%)
1	176.5	181.3	0.978	2.7
2	328.8	336.19	0.974	2.2
3	515.3	500.24	0.973	2.9
4	630.8	627.41	0.954	0.5

图6 热振试验示意图

Fig.6 Schematic diagram of thermal-vibration test

图7 舵结构温度试验测点分布图

Fig.7 Distribution of temperature test points for rudder structure

图8 不同温度下加速度测点1~测点4传递函数

Fig.8 Transfer functions of acceleration measurement points 1-4 at different temperatures

表3 舵结构不同温度下的模态频率

Table 3 Modal frequencies of rudder structures at different temperatures Hz

模态阶数	200℃	300℃	400℃	500℃	600℃
1	169.7	167.6	165.5	162.8	159.9
2	322.9	318.7	314.4	309.4	303.7
3	499.4	492.3	484.9	476.4	466.1
4	596.3	587.1	577.9	567.1	555.6
5	1061.8	1054.3	1041.1	1034.7	1022.2
6	1307.5	1289.7	1266.5	1241.4	1215.8
7	1364.9	1349.2	1322.6	1315.8	1301.6

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