多目标多光谱辐射高速高温计的研制

固体火箭羽焰是一种特殊的火焰，固体火箭发动机喷管羽流沿径向和轴向的温度是研究固体推进剂燃烧状况和发动机燃烧流场的基本参数。针对固体火箭发动机尾喷焰温度及其空间分布测量的需要，继1999年采用多光谱辐射测温方法和技术实现航天某型号固体火箭发动机测量后，研制了新型的多目标多光谱辐射高速高温计用于固体火箭发动机地面搭载试验。仪器使用组合棱镜和光电二极管阵列实现目标0.4~1.1μm光谱的热辐射测量，在主光路设计中首次使用光纤技术，实现一台仪器同时测量空间分布6个目标点的温度和发射率，每个点的空间位置由光阑上的通光孔精确确定，且每个目标测点均有8个工作光谱，研制的同步高速数据采集系统完成48个测量通道的数据同步时间小于10 ns。

Development of Multi-Target Multi-Spectral High-Speed Pyrometer

The plume temperature of a solid propellant rocket engine (SPRE) is a fundamental parameter in denoting combustion status. It is necessary to measure the temperature along both the axis and the radius of the engine. In order to measure the plume temperature distribution of a solid propellant rocket engine, the multi-spectral thermometry has been approved. Previously the pyrometer was developed in the Harbin Institute of Technology of China in 1999, which completed the measurement of SPRE plume temperature and its distribution with multi-spectral technique in aerospace model development for the first time. Following this experience, a new type of multi-target multi-spectral high-speed pyrometer used in the ground experiments of SPRE plume temperature measurement was developed. The main features of the instrument include the use of a dispersing prism and a photodiode array to cover the entire spectral band of 0.4 to 1.1 μm. The optic fibers are used in order to collect and transmit the thermal radiation fluxes. The instrument can measure simultaneously the temperature and emissivity of eight spectra for six uniformly distributed points on the target surface, which are well defined by the hole on the field stop lens. A specially designed S/H (Sample/Hold) circuit, with 48 sample and hold units that were triggered with a signal, measures the multi-spectral and multi-target outputs. It can sample 48 signals with a less than 10ns time difference which is most important for the temperature calculation.