高速风洞微型测量系统研制及应用

Development and Application of Micro Measurement System in High Speed Wind Tunnel

为满足高速风洞试验现场日益复杂的采集需求,研制了一种高速风洞微型测量系统,由电气接口模块、增益控制模块、低通滤波模块、扫描采集模块、主控模块、LAN总线接口模块组成,实现了电压信号放大、低通滤波、模数转换、数据处理与分析等功能;静态校准结果线性度及误差限小于0.03%,与风洞常规测量系统相当,将该系统成功应用于2.4米跨声速风洞标模测力试验,开展了与常规测量系统的对比试验以及测量精度试验,马赫数0.40、0.78、0.85对应的C Lα差量分别为0.0009、0.0004和0.0020,差异在2.0%以内,C m CL差量分别为0.0039、0.0003和0.0011,对应焦点位置变化均小于0.5%气动弦长,重复性精度指标绝大部分均在国军标合格指标以内,部分达到先进指标;结果表明微型测量系统精度和稳定性满足高速风洞试验要求。

In order to meet the increasingly complex requirements of high speed wind tunnel test,a micro measurement system for high speed wind tunnel is developed,which composed of electrical interface module,gain control module,low-pass filter module,scan acquisition module,master control module and LAN bus interface module,realizing voltage signal amplification,low-pass filter,analog digital conversion and data processing and analysis.The linearity and error limit of static calibration results are less than 0.03%,which are equivalent to the conventional wind tunnel measurement system.The system was successfully applied to the standard model’s force test in 2.4 meter transonic wind tunnel,and the comparison test and measurement accuracy test were carried out.The differences of C Lαbetween micro measurement system and conventional measurement system are 0.0009、0.0004 and 0.0020 at Mach number 0.40,0.78 and 0.85,which is within 2.0%.The differences of C m CL are 0.0039、0.0003 and 0.0011,and the corresponding change of focus position is less than 0.5%of the aerodynamic chord length.Most of the repeatability precision indexes are within the qualified indexes of national military standards,some of them reach advanced indexes.The results showed that the precision and stability of the micro measurement system meet the high speed wind tunnel test requirements.