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RESEARCH ON CALIBRATION METHOD OF SAPCE-BORNE HIGH TEMPERATURE STRAIN SENSOR

机译:太空烧高温度应变传感器校准方法研究

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High temperature strain sensors are extensively used in astronautic vehicles to monitor the distribution and variation of the strain. During the re-entry capsule backing to the earth, complex thermal conditions of the outer space generate considerable unwanted thermal output, thermal sensitivity coefficient variation, creep and null shift, which greatly reduce the measurement accuracy. Therefore, thermal parameters calibration in various experiment conditions is a key technique for application of space-borne high temperature strain sensors. In this paper, a thermal parameters calibration method and device for space-borne high temperature strain sensors is proposed and demonstrated. The calibration device consists of a bidirectional strain generation mechanism, a high temperature furnace and an optical speckle measurement system. The bidirectional strain field generation mechanism is designed in the way that a equal-strength strain beam is implemented by bidirectional pulling and pressure loading using a torque motor, a force screw and a lever structure, so that the positive and negative strains are generated on the same side of the equal-strain regions on the equal-strength strain beam. The strain beam is placed in a high temperature furnace to realize temperature loading and control from room temperature to 1200 °C . The surface deformations of the linear working zone as well as the strain sensors on the strain beam surface are measured by the optical speckle measurement system through the optical window on the high temperature furnace. And the all-field strain is derived as the standard strain value according to the speckle interference map. Then the thermal parameters of the high temperature strain sensor can be calibrated under different temperature regions. During high temperature application, thermal output is much larger than null shift and creep, so the research is focused on calibration method of the thermal output and thermal sensitivity coefficient in thi
机译:高温应变传感器广泛用于宇航车辆中,以监测应变的分布和变化。在重新入口胶囊后面的胶囊在地球上,外部空间的复杂热条件产生相当大的不需要的热输出,热敏系数变化,蠕变和空换档,这大大降低了测量精度。因此,各种实验条件中的热参数校准是用于在空间高温应变传感器中应用的关键技术。本文提出并证明了热参数校准方法和用于空间高温应变传感器的装置。校准装置包括双向应变产生机构,高温炉和光学散斑测量系统。双向应变场生成机构设计成相等强度应变光束通过双向拉伸和压力负载来实现使用扭矩电动机,力螺钉和杠杆结构来实现,从而产生正和负菌株相等强度应变光束上的相等应变区域的同一侧。将应变光束放置在高温炉中,以实现温度载荷并从室温控制到1200°C。线性工作区的表面变形以及应变光束表面上的应变传感器通过高温炉上的光学窗口通过光学散斑测量系统测量。根据斑点干扰图,全场应变作为标准应变值导出。然后可以在不同的温度区域校准高温应变传感器的热参数。在高温施加期间,热输出远大于空移位和蠕变,因此研究专注于THI中热输出和热敏系数的校准方法

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