底排-火箭复合发动机底排临界面喉比的确定

周俊祥; 周海清; 粱增友

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底排-火箭复合发动机底排临界面喉比的确定

更新时间：2026-09-14

- 底排-火箭复合发动机底排临界面喉比的确定
- 底排-火箭复合发动机底排临界面喉比的确定
- Issue 3, (2001)
- 作者机构：
  
  华北工学院机械电子工程系,山西,太原,030051
- 作者简介：
- 基金信息：
- DOI：
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- Published：2001
- 稿件说明：
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周俊祥, 周海清, 粱增友. 底排-火箭复合发动机底排临界面喉比的确定[J]. 2001, (3).
DOI：

周俊祥, 周海清, 粱增友. 底排-火箭复合发动机底排临界面喉比的确定[J]. 2001, (3). DOI：

摘要

目的　确定整体式底排 -火箭复合发动机合理的底排临界面喉比 .方法　根据复合增程装置的工作原理和主要设计参数

通过理论分析确定了理论临界面喉比

并通过试验对临界面喉比进行了验证 .结果理论分析获得的临界面喉比与试验结果吻合的较好 .结论　所获得的临界面喉比对复合增程装置关键参数的设计具有重要的指导意义和参考价值

Abstract

Aim\ To acquired a reasonable critical exhaust throat area ratio used for integrative base bleed and compound rocket engine. Methods\ According to the working principle and primary design parameter

an area ratio is obtained by theoretical analysis. A proof test is executed for the obtained ratio. Results\ The experiment results well accord with the calculated results. Conclusion\ The decided critical change exhaust throat area ratio has an important guidance and reference value on critical parameter design of compound rocket assistant device.

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