|Table of Contents|

An analysis of RBCC realizability scheme: DRBCC(PDF)

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

Issue:
2014年05期
Page:
1-7
Research Field:
专论与综述
Publishing date:

Info

Title:
An analysis of RBCC realizability scheme: DRBCC
Author(s):
ZHANG Qian;  WANG Bing;  ZHANG Yun-long;  ZHANG Hui-qiang
School of Aerospace, Tsinghua University, Beijing 100084, China
Keywords:
-
PACS:
V434-34
DOI:
-
Abstract:
A dual rocket-based combined cycle (DRBCC) propulsion system with LOX/air/methane as propellants is proposed in this paper. In this system, the LOX/methane staged combustion cycle system is adopted for both the ejecctor and pure rocket modes. For the rocket-ejector and scramjet modes, the LOX/methane staged cycle runs at the half working-condition, where only the fuel-rich LOX/methane pre-combustion process works. In the rocket-ejector mode, the fuel-rich burned hot gas functions as the ejecting source, and thus reburns with air. In the scramjet mode, such fuel-rich hot gas can be used to enhance the supersonic combustion or as fuel, which is helpful to reduce the technical difficulty of scramjet mode. In the pure rocket mode, the closed-cycle system of Lox/methane staged combustion rocket cycle works at full load state. The ejector-rocket, scramjet and pure rocket modes in DRBCC are therefore highly integrated based on the half-load or full-load state of the LOX/methane staged rocket cycle, and single fuel of methane is adopted in whole process of DRBCC. Such

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