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Discussion of rocket thrust augmentation for RBCC engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2017年01期
Page:
18-23
Research Field:
研究与设计
Publishing date:

Info

Title:
Discussion of rocket thrust augmentation for RBCC engine
Author(s):
LIU Hao; WANG Jun
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
RBCC; rocket ramjet mode; thrust augmentation
PACS:
V434-34
DOI:
-
Abstract:
In order to enhance rocket thrust augmentation of rocket-based combined-cycle (RBCC) engines in rocket ramjet mode,the flow interaction characteristics between rocket ejection and ramjet inflow are analyzed,as well as constitution of thrust augmentation is discussed on the basis of the numerical simulation result in the Maeh 4 coming flow condition of the simulated flight.Some measures for improving rocket thrust augmentation are given as follows:1) the selection of ramjet passageway and rocket ejection parameters must guarantee the flow matching between two supersonic velocity shear flows to achieve the weight transportation and momentum between high energy rocket jet flow and low energy ramjet mainstream rapidly and efficiently in the finite space of ramjet combustor,and improve the exhaust velocity and pressure of engine nozzle in maximum limit;2) the rocket with high chamber pressure should be adopted to enhance expending degree of rocket exhausted gas and reduce the thrust augmentation loss of rocket.

References:

[1] FOSTER RW, ESCHERWJ D, ROBINSON J W. Studies of an extensively axisymmetric rocket based combined cycle (RBCC) engine powered SSTO vehicle: AIAA-89- 2294[R]. USA: AIAA, 1989.
[2] HYDE E H, ESCHER W J D, RODDY J E. Marquardt's Mach 4.5 supercharged ejector ramjet high-performance aircraft engine project: AIAA-2000-3109[R]. USA: AIAA, 2000.
[3] DAINES R L, MERKLE C L. Computational fluid dynamic modeling of rocket based combined cycle engine flowfields: AIAA-94-3327[R]. USA: AIAA, 1994. [ 4] LEHMAN M, PAL S, BRODA J C, et al. Raman spectroscopy based study of RBCC ejector mode performance: AIAA-99-0090[R]. USA: AIAA, 1999.
[5] 黄生洪. 火箭基组合动力循环引射模态燃烧流动研究 [D]. 西安: 西北工业大学, 2002.

Memo

Memo:
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Last Update: 1900-01-01