固体火箭发动机尾焰测温技术研究

Temperature Measurement Technology of Solid Rocket Motor Tail Flame

摘要:

固体火箭发动机被广泛应用于航天运载火箭、导弹武器推进以及航天器姿态和轨道控制等领域，其尾焰温度是评估推进剂燃烧性能和发动机工作效率的关键参数。由于固体火箭发动机尾焰具有高温、高压和强冲刷的特点，试验现场环境通常伴随着强振动、强杂散辐射、粉尘污染和高噪音，这对测温技术提出了挑战。本文总结了现有固体火箭发动机尾焰接触式测温和非接触式测温技术的发展状况，分析了现有测温技术的优势与不足之处，并指出多光谱辐射成像测温法及其真温反演算法是目前及今后研究热点。

Abstract:

Solid rocket motors are widely used in space launch vehicles, missile weapon propulsion, and spacecraft attitude and orbit control. Its tail flame temperature is a key parameter in evaluating propellant combustion performance and the engine efficiency. Due to the high temperature, high pressure and strong washout characteristics of the solid rocket motor exhaust flame, the test site environment is often accompanied by strong vibration, strong stray radiation, dust pollution and high noise, it's a challenge to temperature measurement techniques. In this paper, the development of contact and contactless temperature measurement techniques for solid rocket motor exhaust flame is summarized, and the advantages and disadvantages of the current techniques are analyzed. It is also pointed out that multispectral radiometric imaging thermometry and its temperature inversion algorithm are the current and future research frontiers.