线性塞式喷管型面快速设计方法

推进技术 ›› 2004, Vol. 25 ›› Issue (2): 144-147.

线性塞式喷管型面快速设计方法

覃粒子,刘宇,王一白

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100083

发布日期:2021-08-15
基金资助:
国家"八六三"基金资助项目(863 2 1 3 1);高等学校博士学科点专项科研基金资助课题。

Rapid method for contour design of linear plug nozzle

School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China;School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China

Published:2021-08-15

摘要/Abstract

摘要： 为了发展一套快速有效的塞式喷管型面设计方法,分析了塞式喷管的总膨胀面积比、内膨胀面积比和内喷管倾角与塞式喷管膨胀能力之间的联系,采用二阶和三阶多项式来分段描述塞式喷管的所有型面曲线,并给出了确定各段型面曲线的方法。研究了膨胀面积比对外形尺寸的影响,设计了两套不同类型的实验塞式喷管型面来进行冷流实验验证。结果表明:所设计的塞式喷管具有很好的高度补偿能力。

关键词: 火箭发动机;塞式喷管;曲面;设计;高度特性

Abstract: To develop a rapid and efficient method for contour design of linear plug nozzle, the obliquity of internal nozzle and the expansion ratios of plug nozzle and internal nozzle, which are related to the expansion capability, were theoretically analyzed. Two second-degree polynomials and a third-degree polynomial were adopt to describe the contours of a linear plug nozzle, and the means in determining nozzle contours were also presented. The influence of the plug nozzle expansion ratios on its figure dimensions was studied. Two types of plug nozzles designed by the rapid method were tested with cold flow, and the experimental results demonstrate the excellent altitude compensating capability.

Key words: Rocket engine;Plug nozzle;Curved furface;Design;Altitude characteristic

覃粒子,刘宇,王一白. 线性塞式喷管型面快速设计方法[J]. 推进技术, 2004, 25(2): 144-147.