三目标六波长高温计的研制
发布时间：2018-11-18 11:01
【摘要】：火箭发动机羽焰温度是表征固体推进剂燃烧特性一个重要参数,对导弹武器研制和发射平台设计起着关键的作用。由于固体火箭发动机羽焰流场具有高温、高压和强冲击的特点,使得对其进行温度测量存在一定的难度。根据航天X院项目要求,研制出一套3目标6波长高温计,利用多光谱辐射测温技术实现羽焰真温和发射率的测量,温度测量范围在900-3000K,整体测温精度优于3%。本文主要完成了高温计装置的研制工作:包括高温计的方案设计,软、硬件研制和调试,仪器的标定和测试等。光学系统采用组合棱镜分光的设计方案,增强了光学部分的稳定性;利用光纤完成取样系统和分光系统间光能量的传输;探测器采用硅光电二极管,实现近似线性的输出;电路系统有针对性地设计了多级放大电路,保证高温计在整个测温范围内具有足够的信噪比;最后采用高速数据采集卡来实现信号的快速获取。软件系统设计采用C#语言,结合ADO.NET数据库访问技术,实现数据的管理和操作。根据项目要求完成了标定程序、测量和处理程序的编写和调试。最后利用单色仪和标准黑体炉对高温计进行了PWF标定和亮温方程标定;并对标定好的高温计进行测试实验。此高温计具有3套独立的光学取样系统、光纤传输、棱镜分光系统以及多级放大电路,可以满足任意3个目标点的同时测量。而且通过优化结构设计,此高温计还具有体积小,便携式,稳定性高的优点。
[Abstract]:The plume temperature of rocket engine is an important parameter to characterize the combustion characteristics of solid propellant. It plays a key role in the development of missile weapon and the design of launch platform. Because the plume flow field of solid rocket motor has the characteristics of high temperature, high pressure and strong impact, it is difficult to measure the temperature of solid rocket motor. According to the requirements of the space X institute project, a set of 3 target 6 wavelength pyrometer is developed. The plume flame true mild emissivity is measured by multispectral radiation temperature measurement technique. The temperature measurement range is 900-3000K, and the whole temperature measurement precision is better than 3. In this paper, the development of pyrometer device is mainly completed, including the design of pyrometer scheme, the development and debugging of hardware and software, the calibration and testing of the instrument, etc. The optical system adopts the design scheme of combination prism to enhance the stability of the optical part; the optical energy is transmitted between the sampling system and the light splitting system by using optical fiber; the detector uses silicon photodiode to achieve approximately linear output. The multistage amplifier circuit is designed to ensure that the pyrometer has enough signal-to-noise ratio in the whole temperature measurement range. Finally, the high-speed data acquisition card is used to achieve the fast signal acquisition. The software system is designed with C # language and ADO.NET database access technology to realize data management and operation. According to the project requirements, the calibration program, measurement and processing procedures are written and debugged. Finally, the PWF calibration and bright temperature equation calibration of the pyrometer are carried out by using Monochromator and standard blackbody furnace, and the calibrated pyrometer is tested. The pyrometer has three sets of independent optical sampling system, optical fiber transmission, prism splitting system and multistage amplifier circuit, which can be used for simultaneous measurement of any three target points. By optimizing the structure, the pyrometer has the advantages of small volume, portable and high stability.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V435
本文编号：2339849
[Abstract]:The plume temperature of rocket engine is an important parameter to characterize the combustion characteristics of solid propellant. It plays a key role in the development of missile weapon and the design of launch platform. Because the plume flow field of solid rocket motor has the characteristics of high temperature, high pressure and strong impact, it is difficult to measure the temperature of solid rocket motor. According to the requirements of the space X institute project, a set of 3 target 6 wavelength pyrometer is developed. The plume flame true mild emissivity is measured by multispectral radiation temperature measurement technique. The temperature measurement range is 900-3000K, and the whole temperature measurement precision is better than 3. In this paper, the development of pyrometer device is mainly completed, including the design of pyrometer scheme, the development and debugging of hardware and software, the calibration and testing of the instrument, etc. The optical system adopts the design scheme of combination prism to enhance the stability of the optical part; the optical energy is transmitted between the sampling system and the light splitting system by using optical fiber; the detector uses silicon photodiode to achieve approximately linear output. The multistage amplifier circuit is designed to ensure that the pyrometer has enough signal-to-noise ratio in the whole temperature measurement range. Finally, the high-speed data acquisition card is used to achieve the fast signal acquisition. The software system is designed with C # language and ADO.NET database access technology to realize data management and operation. According to the project requirements, the calibration program, measurement and processing procedures are written and debugged. Finally, the PWF calibration and bright temperature equation calibration of the pyrometer are carried out by using Monochromator and standard blackbody furnace, and the calibrated pyrometer is tested. The pyrometer has three sets of independent optical sampling system, optical fiber transmission, prism splitting system and multistage amplifier circuit, which can be used for simultaneous measurement of any three target points. By optimizing the structure, the pyrometer has the advantages of small volume, portable and high stability.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V435
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