Technique for developing thin slab strain gauge balance based on rectangular beam
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摘要: 在飞行器铰链力矩测力和部件测力风洞试验中，常采用片式应变天平测量。受模型结构限制，传统片式天平连接端刚度相对天平元件不足，测量精准度偏低。将片式天平元件分解为多个柱梁元件，通过多个柱梁元件组成一台新型结构的片式天平，可以有效提高片式天平的测量精准度。传统力学分析和有限元软件仿真分析结果均表明该方法具有可行性。基于该技术研制了验证天平，校准结果表明该技术具有很高的应用价值。目前该片式天平研制技术已在中国空气动力研究与发展中心高速所成功应用于多个试验项目。Abstract: The thin slab strain gauge balance is often used in hinge moment force test and parts force test for aircraft in wind tunnel. Limited by the structure of the aircraft model, the stiffness of the conventional thin slab strain gauge balance at the connections is insufficient as compared with that of the balance elements, leading to low accuracy. In this study, each element of the thin slab balance is divided into multiple rectangular beams which together compose a new element. Using the new thin slab strain gauge balance can improve the accuracy of measurement. By traditional mechanical analysis, FEA, and tests the feasibility of the technique is shown, and it has already been used in several wind tunnel tests in China Aerodynamics Research and Development Center.
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Key words:
- thin slab balance /
- thin slab beam /
- rectangular beam /
- high accuracy
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图 2 通过不同位置施加同一法向力时传统片式天平的应变差异
Figure 2. Strain difference of a conventional thin slab balance under the same normal force acting on different positions
图 5 2种结构应变差异对比
Figure 5. Contrast of strain between conventional structure balance and new structure balance
图 8 某飞机外翼部件测力Ma=1.05重复性
Figure 8. Repeatability of outer wing force test for an aircraft (Ma=1.05)
表 1 5种不同孔组合的加载位置
Table 1. Five loading positions based different groups of holes
加载位置 一 二 三 四 五 对应孔
的编号1, 2, 3, 4,
5, 6, 7, 81, 3, 5,
6, 81, 2, 3,
6, 73, 4, 5,
7, 82, 4, 7 
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表 2 2种结构天平通过不同位置施加同一法向力时的测量应变
Table 2. Strain measured of two structure balances under the same normal force on different positions
加载位置 一 二 三 四 五 测量应变
(×10-6)传统结构 1991.71 2006.82 1987.65 1789.53 1788.71 新结构 2420.46 2424.04 2420.13 2412.46 2412.54
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表 3 2种结构天平通过不同位置施加同一弯矩时的测量应变
Table 3. Strain measured of two structure balances under the same moment on different positions
加载位置 一 二 三 四 五 测量应变
(×10-6)传统结构 9001.12 9021 8994.71 8973.35 8972.65 新结构 9375.53 9375.87 9375.53 9375.80 9373.67
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表 4 某型飞机升降舵新型片式天平校准结果
Table 4. Calibration results of the new type thin slab balance for an aircraft elevator
测量分量 Y Mx Mj 设计载荷/(N、N·m) 500 25 15 主项 +Y向/(N·mV-1) 95.6147 5.5914 2.0143 系数 -Y向/(N·mV-1) 95.6373 5.5763 2.0146 差异 相对差异/% 0.024 0.27 0.015 综合加载误差/(%FS) 0.057 0.10 0.14 法向力模拟加载相对误差/% ＜0.3
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表 5 某型飞机副翼新型片式天平校准结果
Table 5. Calibiation results of the new type thin slab balance for an aircraft aileron
测量分量 Y Mx Mj 设计载荷/(N、N·m) 910 30 25 主项 +Y向/(N·mV-1) 69.0955 3.6151 1.1941 系数 -Y向/(N·mV-1) 69.0589 3.6143 1.1909 差异 相对差异/% 0.053 0.022 0.27 综合加载误差/(%FS) 0.015 0.3 0.09 法向力模拟加载相对误差/% ＜0.5
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