脉冲风洞测力系统结构动力学特性

吕金洲; 张小庆; 赵晓男; 陈光雄; 吴颖川

doi:10.3969/j.issn.0258-2724.20170737

脉冲风洞测力系统结构动力学特性

doi: 10.3969/j.issn.0258-2724.20170737

基金项目: 国家自然科学基金资助项目（51775461）

详细信息

作者简介:
吕金洲（1987—），男，博士研究生，研究方向为脉冲风洞测力技术， E-mail：shenqiuwo@126.com

通讯作者:
张小庆（1962—），男，副研究员，博士，研究方向为高超声速飞行器技术，E-mail：mukai_zhang@126.com

中图分类号: TJ760.1 V216.8
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- 被引次数: 0
出版历程
- 收稿日期: 2017-10-18
- 修回日期: 2018-08-31
- 网络出版日期: 2018-09-05
- 刊出日期: 2019-12-01

Structural Dynamic Characteristics of Force-Measurement System for Impulse Wind Tunnel

摘要

摘要: 脉冲风洞试验过程时，试验气流引起测力系统强烈振动对测试结果产生严重干扰. 为解决测力系统振动对测力结果干扰的问题，首先根据测力系统结构特点建立了相应的动力学模型；其次，对其进行了虚拟标定和模态分析；第三，对测力系统进行了瞬态分析和惯性补偿，获得了相应的瞬态输出；最后，对测力系统进行了风洞试验，分别获得了相应的弹性输出结果和惯性输出结果. 分析和试验结果表明：惯性补偿后，测力系统均值测量精度略有提高，瞬态测量精度大幅提高；惯性补偿后瞬态测量精度最低为87.4%，出现在测力系统共振时，其他状态下，瞬态测量精度超过91%；惯性补偿后的测力系统输出结果振动基本消失，说明惯性补偿方法能够消除振动对输出结果的干扰.
- 测力系统 /
- 虚拟标定 /
- 瞬态仿真 /
- 惯性补偿 /
- 测量精度
Abstract: During testing in impulse wind tunnel, vibrations of the force-measurement system (FMS) caused by airflow will greatly tamper measurement results. To solve this issue, firstly the dynamic model of the FMS was constructed according to its structural characteristics. Then, the virtual calibration and modal analysis were carried out. Thirdly, the transient analysis and inertia compensation were processed to obtain the response of the FMS. Finally, the force measurement tests was conducted in the impulse wind tunnel, and both the elastic and inertia outputs were obtained in tests. Results show that after inertia compensation, the mean measurement accuracy were improved, and the transient measurement accuracy were improved significantly. When there was resonance, the lowest transient measurement accuracy was 87.4% after inertia compensation. In the other cases, the transient measurement accuracy exceeded 91%. Vibrations on the output curves of the FMS were virtually smoothed after inertia compensation, demonstrating that inertia compensation can eliminate the disturbance in the outputs.
- FMS /
- virtual calibration /
- transient simulation /
- inertia compensation /
- measurement accuracy

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图 1 风洞测力系统

Figure 1. Force-measurement system for wind tunnel

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图 2 三分量测力天平

Figure 2. 3-component force balance

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图 3 测力系统

Figure 3. Force measuring system

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图 4 天平应变计粘贴位置

Figure 4. Strain gauge positions on force balance

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图 5 测力系统有限元模型

Figure 5. Finite element model of FMS

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图 6 试验段总压及天平测量结果

Figure 6. Total pressure of test chamber and measurement results of force balance

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图 7 测量系统振型

Figure 7. Vibration modes of FMS

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图 8 测力系统加速度测点

Figure 8. Acceleration detection points of FMS

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图 9 H-f正弦阶跃载荷加载时测力系统仿真结果

Figure 9. Simulation results of FMS under action of H-f sine step load

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图 10 N-f正弦阶跃载荷加载时测力系统仿真结果

Figure 10. Simulation results of FMS under action of N-f sine step load

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图 11 D-f正弦阶跃载荷加载时测力系统仿真结果

Figure 11. Simulation results of FMS under action of D-f sine step load

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图 12 测力系统惯性补偿前输出结果误差

Figure 12. Transient measurement errors of FMS before inertia compensation

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图 13 测力系统惯性补偿后输出结果误差

Figure 13. Transient measurement errors of FMS after inertia compensation

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图 14 风洞试验测力系统

Figure 14. FMS in wind tunnel

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图 15 风洞试验结果

Figure 15. Wind tunnel test results

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表 1 测力系统模态参数

Table 1. Mode parameters of FMS

阶数	频率	振型描述	阶数	频率	振型描述
1	80.65	绕 z 轴旋转	3	120.99	沿 x 轴振动
6	172.64	沿 y 轴振动

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表 2 测力系统各分量均值测量精度

Table 2. Mean measurement accuracy of FMS in each component %

加载频率	惯性补偿	F_x	F_y	M_z
H-f	前	99.527	99.508	99.077
H-f	后	99.653	99.71	99.195
N-f	前	99.305	99.391	99.088
N-f	后	99.69	99.775	99.319
D-f	前	99.151	99.253	98.889
D-f	后	99.724	99.787	99.450

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表 3 测力系统瞬态测量精度最小值

Table 3. Minimum values in measurement accuracy of FMS %

分量	H-f	N-f	D-f
F_x	96.136	93.284	95.004
F_y	93.462	91.678	92.292
M_z	95.644	87.388	93.616

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