Temperature correction method for load measurement of aircraft composite structures
-
摘要:
针对温度对飞机复合材料结构载荷测量结果的严重影响问题，分析飞机结构载荷测量温度影响机理，建立包含应变电桥相对响应系数和热输出的温度修正模型，并分别给出相对响应系数和热输出与结构温度的通用关系模型。通过复合材料层压板和翼面盒段试验件的温度试验及温度-载荷组合试验对关系模型进行了验证，结果表明：在黏接剂温度特性满足要求的情况下，相对响应系数倒数与无量纲结构温度呈幂函数关系；热输出与结构温度变化量呈截距为0的三次多项式的关系。利用所建模型对某型飞机复合材料翼面结构载荷飞行测量结果进行了修正，修正后的压心相对变化最大值达到30.68%，显著提高了载荷测量的精准度，为飞机飞行载荷验证提供了可靠的数据。
Abstract:In view of the serious influence of temperature on load measurement results of aircraft composite structures, the influence mechanism of temperature on load measurement of aircraft structure was analyzed, and a temperature correction model including the relative response coefficient and thermal output of the strain bridge is established, and the general relation models of relative response coefficient and thermal output with structural temperature are given respectively. These relation models are verified by the temperature test and the temperature-load combined test of composite laminate coupons and the wing box test component. The findings indicate that, when the adhesive's temperature characteristics are met, the relationship between the thermal output and the structural temperature change is a cubic polynomial with zero intercept, and the reciprocal of the relative response coefficient is a power function of the dimensionless structure temperature. By using this technique, the flight measurement results of an aircraft's composite wing structure load can be corrected. The maximum relative change of the pressure center following modification is 30.68%, which greatly increases load measurement accuracy and yields trustworthy data for aircraft flight load verification.
-
图 2 翼面盒段试验件温度-载荷组合试验
Figure 2. Temperature-load combined test for specimen of wing-box structure
图 3 安装在层压板上的应变电桥热输出拟合分析与修正结果
Figure 3. Fitting analysis and correction results of thermal output of strain bridge installed on laminate
图 4 安装在翼面盒段上的应变电桥2HW热输出拟合分析与修正结果
Figure 4. Fitting analysis and correction results of thermal output of strain bridge 2HW installed on wing box
图 5 应变电桥HJ相对响应系数的倒数与无量纲温度关系
Figure 5. Relationship between reciprocal of relative response coefficients of strain bridge HJ and dimensionless temperature
图 6 采用不同黏接剂在翼面盒段上安装的应变电桥相对响应系数随温度变化
Figure 6. Relative response coefficients of strain bridges installed on wing box with different adhesives varies with temperature
图 7 机翼载荷测量应变电桥YJY2W2热输出与结构温度变化量的三次多项式拟合结果
Figure 7. Results of cubic polynomial fitting between thermal output of strain bridge YJY2W2 and structural temperature change for wing load measurement
表 1 层压板试验件种类和数量
Table 1. Type and quantity of laminate coupons
铺层编号 拉伸件数量 压缩件数量 剪切件数量 合计/件 A1 6 6 6 18 A2 6 6 6 18 A3 6 6 6 18 A4 6 6 6 18 A5 6 6 6 18 A6 6 6 6 18 A7 6 6 6 18 A8 6 6 6 18 
下载: 导出CSV
表 2 应变电桥安装工艺方案
Table 2. Technology scheme for installation of strain-gage bridge
工艺方案 应变计 黏接剂 电桥类型 Ⅰ H A 全桥 Ⅱ H A 半桥 Ⅲ H B 全桥 Ⅳ Z A 全桥 Ⅴ Z B 全桥 Ⅵ M C 半桥
下载: 导出CSV
表 3 应变电桥热输出与结构温度变化量的三次多项式拟合结果
Table 3. Results of cubic polynomial fitting between thermal output of strain bridge and structural temperature change
试验件
类型温度范围 工艺
方案电桥数 $ {R}^{2} $≥0.9的
电桥占比/%$ {R}^{2} $<0.9的
电桥占比/%响应小 响应异常 层压板 室温～−50℃ Ⅰ 144 95.83 2.78 1.39 Ⅳ 143 93.71 4.90 1.40 室温～65℃ Ⅰ 123 94.31 4.88 0.81 Ⅳ 123 92.68 3.25 4.07 盒段件 室温～−50℃ Ⅰ 4 100.00 Ⅱ 11 100.00 Ⅲ 20 100.00 Ⅴ 15 100.00 Ⅵ 12 83.33 16.67 室温～65℃ Ⅰ 4 100.00 Ⅱ 11 100.00 Ⅲ 19 84.21 15.79 Ⅴ 15 80.00 20.00 Ⅵ 12 100.00
下载: 导出CSV
表 4 剪力方程中应变电桥的相对响应系数及方程检验误差
Table 4. Relative response coefficients of strain bridge in shear equation and check error of equation
温度/℃ 应变电桥相对响应系数${\alpha }_{\text{t}i} $ 检验误差/% HW QW HJ QJ 修正前 修正后 −55 0.9845 0.9594 0.9347 0.9426 5.00 0.92 70 1.0114 1.0019 1.0354 1.0301 3.69 0.60
下载: 导出CSV
表 5 实测载荷及其修正结果
Table 5. Measured loads and their Correction results
载荷
情况剪力 弯矩/m 压心/m 修正后
剪力修正后
弯矩/m修正后
压心/m压心相对
变化/%J1 0.0716 0.2895 4.04 0.0755 0.3300 4.37 8.17 J2 0.1682 0.6728 4.00 0.1721 0.7123 4.14 3.50 P1 − 0.0051 − 0.0090 1.76 − 0.0043 − 0.0099 2.30 30.68 P2 − 0.0109 − 0.0217 1.99 − 0.0101 − 0.0227 2.25 13.07 P3 0.0056 0.0154 2.75 0.0064 0.0145 2.27 −17.45 C1 0.0251 0.0576 2.29 0.0241 0.0601 2.49 8.73 C2 − 0.0196 − 0.0533 2.72 − 0.0205 − 0.0508 2.48 −8.82
下载: 导出CSV
-
[1] 中国飞行试验研究院. 飞机结构飞行试验指南[M]. 北京: 航空工业出版社, 2022: 29-37.Chinese Flight Test Establishment. Aircraft structural flight test guide[M]. Beijing: Aviation Industry Press, 2022: 29-37(in Chinese). [2] 郭正旺, 周友明. 结构完整性试飞-飞机载荷与强度试飞[M]. 北京: 航空工业出版社, 2018: 18-51.GUO Z W, ZHOU Y M. Flight test of structural integrity- flight test of aircraft load and strength[M]. Beijing: Aviation Industry Press, 2018: 18-51(in Chinese). [3] JECKINS J M, DE ANGELIS V M. A summary of numerous strain-gage load calibrations on aircraft wings and tails in a technology format: NASA TM-4804[R]. Washton, D. C. : National Aeronautics and Space Administration, 1997. [4] Micro-Measurements. Strain gage thermal output and gage factor variation with temperature: TN-504-1[R]. North Carolina: Micro-Measurements, 2014. [5] 李俊, 蒋献. 飞机主动式余度作动舵面铰链力矩飞行测量方法[J]. 空军工程大学学报, 2023, 24(3): 43-49.LI J, JIANG X. A flight measurement method for hinge moment of aircraft control surface with redundant actuation system in active mode[J]. Journal of Air Force Engineering University, 2023, 24(3): 43-49(in Chinese). [6] FIELDS R A. A study of the accuracy of a flight-heating simulation and its effect on load measurement: NASA TN D-5741[R]. Washton, D. C. : National Aeronautics and Space Administration, 1970. [7] REARDON L R. Evaluation of a strain-gage load calibration on a low aspect-ratio wing structure at elevented temperature: NASA TP-2921[R]. Washton, D. C. : National Aeronautics and Space Administration, 1989. [8] JENKINS J M, QUINN R D. A historical perspective of the YF-12A thermal loads and structures program: ASA TM-104317[R]. Washton, D. C. : National Aeronautics and Space Administration, 1996. [9] 李俊. 飞机结构载荷测量应变电桥热输出修正方法[J]. 空军工程大学学报(自然科学版), 2022, 23(1): 64-69.LI J. A thermal output correction method of strain-gage bridge for load measurement of aircraft structure[J]. Journal of Air Force Engineering University (Natural Science Edition), 2022, 23(1): 64-69(in Chinese). [10] 朱江辉. 复合材料翼面结构载荷测量及温度修正技术研究[J]. 中国测试, 2023, 49(7): 101-111.ZHU J H. Study on load measurement and temperature correction technology of composite wing structure[J]. China Measurement & Test, 2023, 49(7): 101-111(in Chinese). [11] 李文龙, 李俊, 刘敬礼, 等. 考虑温度影响的复合材料结构载荷测量方法[J]. 空军工程大学学报, 2024, 25(1): 47-51.LI W L, LI J, LIU J L, et al. A load measurement method for composite structure considering the effect of temperature[J]. Journal of Air Force Engineering University, 2024, 25(1): 47-51(in Chinese). [12] 丁冬, 濮兴庭. 利用Origin处理测金属电阻温度系数实验数据[J]. 大学物理实验, 2011, 24(6): 59-60.DING D, PU X T. Processing the experiment data of measuring temperature coefficient of metallic resistance with origin[J]. Physical Experiment of College, 2011, 24(6): 59-60(in Chinese). [13] 陆集平. 碳-环氧复合材料的热物理和热冲击性能[J]. 宇航材料工艺, 1983, 13(6): 7-10.LU J P. Thermophysical and thermal shock properties of carbon-epoxy composites[J]. Aerospace Materials & Technology, 1983, 13(6): 7-10(in Chinese). [14] ALAN B, STUART D, DONALD K. 飞机结构复合材料技术[M]. 2版. 柴亚南, 丁惠梁, 译. 北京: 航空工业出版社, 2015: 140-156.ALAN B, STUART D, DONALD K. Composite materials for aircraft structures[M]. 2nd ed. CHAI Y N, DING H L, translated. Beijing: Aviation Industry Press, 2015: 140-156(in Chinese). [15] 谢伟, 窦鹏鹏, 薛展. 湿热环境下复合材料层合板本构模型研究及其应用[J]. 航空工程进展, 2019, 10(1): 62-72.XIE W, DOU P P, XUE Z. Research and application of the constitutive model of composite laminates in hydrothermal environments[J]. Advances in Aeronautical Science and Engineering, 2019, 10(1): 62-72(in Chinese). -
下载:
点击查看大图
计量
- 文章访问数: 199
- HTML全文浏览量: 66
- PDF下载量: 12
- 被引次数: 0
