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一种根据羽流扩张角判断火箭发动机海平面排气速度的方法

A Determination Method for Rocket Motor Sea-Level Exhaust Velocity According to Plume Expansion Angle

摘要:近年,火箭发动机的非接触式测量研究受到各国的关注,但是主要关注点为火箭发动机的羽流温度场或振动力学研究,并未用于测量火箭发动机的排气速度。传统排气速度测量方法设备复杂,且长期没有其他方法作为参照。因此本文提出了一种利用羽流图像中扩张角测量结果,估算火箭发动机海平面排气速度的方法,该方法结合一维可压缩绝热流模型、大气背景下的普朗特-迈耶函数和布伦特算法。本文利用该方法得到羽流扩张角-海平面排气速度关系,并将其与传统方法测量结果进行对比,验证该方法的精度。估算结果显示海平面排气速度和羽流扩张角呈线性关系,与传统方法之间的相对误差小于2%,因此,结果说明该估算方法具有较高精确度。近年,火箭发动机的非接触式测量研究受到各国的关注,但是主要关注点为火箭发动机的羽流温度场或振动力学研究,并未用于测量火箭发动机的排气速度。传统排气速度测量方法设备复杂,且长期没有其他方法作为参照。因此本文提出了一种利用羽流图像中扩张角测量结果,估算火箭发动机海平面排气速度的方法,该方法结合一维可压缩绝热流模型、大气背景下的普朗特-迈耶函数和布伦特算法。本文利用该方法得到羽流扩张角-海平面排气速度关系,并将其与传统方法测量结果进行对比,验证该方法的精度。估算结果显示海平面排气速度和羽流扩张角呈线性关系,与传统方法之间的相对误差小于2%,因此,结果说明该估算方法具有较高精确度。

英文摘要:Global researchers have recently become interested in non-contact measurements of rocket motors, but the primary focus is on the rocket motor's temperature field or mechanical vibration. As a result, non-contact methods were seldom used to measure the exhaust velocity of the rocket motor. Traditional exhaust velocity measurements need complex equipment and have had few references for a lengthy time. Thus, a method for estimating the rocket motor sea-level exhaust velocity was offered, which makes use of the plume expansion angle measured in its image by integrating a one-dimensional compressible adiabatic flow model, the Prandtl-Mayer function in the ambient atmosphere, and the Brent algorithm. The relationship between the plume expansion angle and the sea-level exhaust velocity was determined in this study, and the results were compared to those obtained using the traditional method to verify the new method's accuracy. The estimation results showed that there was a linear relation between the sea-level exhaust velocity and the plume expansion angle, and the relative error compared to the tradition method is less than 2%. Therefore, it was shown this estimation method has a fairly good accuracy.

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[V1] 2022-03-17 10:33:14 chinaXiv:202203.00044V1 下载全文
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