复杂环境下精密飞行器抱箍结构螺栓松动行为试验研究

李尚基; 邓劭廷; 罗伟峰; 章海亮; 沙佳辉; 薛景丹; 刘玉琢

doi:10.7643/issn.1672-9242.2026.07.005

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装备环境工程 ›› 2026, Vol. 23 ›› Issue (7) : 44-53. DOI: 10.7643/issn.1672-9242.2026.07.005

专题——精密子母式飞行器复杂动载环境分析和适应性精细验证技术应用研究

复杂环境下精密飞行器抱箍结构螺栓松动行为试验研究

李尚基¹, 邓劭廷¹, 罗伟峰^1,2,*, 章海亮¹, 沙佳辉¹, 薛景丹¹, 刘玉琢¹

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Experimental Study on Bolt Loosening Behavior of Hoop Structure of Precision Aircraft under Complex Environment

LI Shangji¹, DENG Shaoting¹, LUO Weifeng^1,2,*, ZHANG Hailiang¹, SHA Jiahui¹, XUE Jingdan¹, LIU Yuzhuo¹

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摘要

目的探究复杂力学载荷下抱箍结构螺栓的松动演化规律。方法以精密飞行器抱箍结构螺栓为研究对象,搭建振动-冲击联合试验平台,模拟飞行器服役过程中的功能振动、耐久振动、自由飞振动及着陆冲击等典型工况。基于超声波声弹性原理,采用压电传感检测与拉依达准则降噪方法,精准采集不同工况下螺栓的声时差信号,通过标定试验建立螺栓扭矩与相对声时差的线性拟合模型,量化分析多工况耦合作用下螺栓预紧力与剩余扭矩的衰减特性。结果振动、冲击载荷方向与类型对薄壁抱箍螺栓松动影响存在显著差异化特征,Z向横向振动是诱发螺纹微滑移累积、扭矩快速衰减的核心工况。2组独立受试螺栓衰减规律高度一致,均呈现“缓慢衰减-快速跌落-稳定收敛”三阶段演化特征,最终剩余扭矩分别稳定至2.65、2.40 N·m,载荷持续作用后预紧力无进一步退化。扭矩-声时差线性模型拟合优度R²=0.987,综合测量误差小于0.07 N·m。结论精密飞行器薄壁抱箍结构螺栓松动具备强工况敏感性与阶段性衰减特征,Z向横向振动作用下箍带与螺栓接触面大范围往复微滑移是扭矩骤降的根本诱因,本文试验结论可为同类飞行器抱箍防松设计提供量化依据与机理支撑。

Abstract

The work aims to explore the loosening evolution law of bolts in hoop structures under complex mechanical loads. Taking the hoop connection bolts of precision aircraft as the research object, a combined vibration-impact test platform was established to simulate typical working conditions including functional vibration, durability vibration, free-flight vibration and landing impact. Based on the ultrasonic acoustoelasticity principle, piezoelectric sensing detection and the Pauta criterion denoising method were adopted to accurately collect ultrasonic time difference signals of bolts under various working conditions. A linear fitting model between bolt torque and relative acoustic time difference was constructed via calibration tests, so as to quantitatively analyze the attenuation characteristics of bolt preload and residual torque under coupled multi-load conditions. The direction and type of vibration and impact loads significantly affected the loosening behavior of thin-walled clamping bolts. Transverse Z-direction vibration was the critical condition that induced cumulative micro-slip in threads and rapid torque degradation. The two independent sets of test bolts exhibited highly consistent decay patterns, all showing a three-stage evolution characterized by “slow decay-rapid drop-stable convergence”, with final residual torques stabilizing at 2.65 N·m and 2.40 N·m respectively. No further preload degradation occured after prolonged load application. The linear model fitting for torque-time-of-flight difference achieved an R² value of 0.987, with a combined measurement error less than 0.07 N·m. Bolt loosening in thin-walled hoop structures of precision flight vehicles exhibits strong sensitivity to operating conditions and features progressive degradation. Under Z-direction lateral vibration, extensive reciprocating micro-slip at the contact interface between the hoop band and bolt is the fundamental cause of sudden torque drop. The experimental findings presented in this study provide quantitative basis and mechanistic support for anti-loosening design of similar aircraft hoops.

导出引用

李尚基, 邓劭廷, 罗伟峰, 章海亮, 沙佳辉, 薛景丹, 刘玉琢. 复杂环境下精密飞行器抱箍结构螺栓松动行为试验研究[J]. 装备环境工程. 2026, 23(7): 44-53 https://doi.org/10.7643/issn.1672-9242.2026.07.005

LI Shangji, DENG Shaoting, LUO Weifeng, ZHANG Hailiang, SHA Jiahui, XUE Jingdan, LIU Yuzhuo. Experimental Study on Bolt Loosening Behavior of Hoop Structure of Precision Aircraft under Complex Environment[J]. Equipment Environmental Engineering. 2026, 23(7): 44-53 https://doi.org/10.7643/issn.1672-9242.2026.07.005

中图分类号： TJ01

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