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[1]陈宏．何国强.RBCC和TBCC组合发动机在RLV上的应用[J].火箭推进,2008,34(03):39-43.
　Chen Hong,He Guoqiang.Application of RBCC and TBCC engines to RLVs[J].Journal of Rocket Propulsion,2008,34(03):39-43.
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RBCC和TBCC组合发动机在RLV上的应用

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 34 期数: 2008年03期 页码: 39-43 栏目: 燃料与推进剂 出版日期: 2008-06-30
Title:
Application of RBCC and TBCC engines to RLVs
作者:
陈宏1．何国强2
1中国航天科技集团公司第四研究院第四十一所，陕西西安710025； 2西北工业大学航天学院，陕西西安710072
Author(s):
Chen Hong1; He Guoqiang2
1 The 41st Institute of the Fourth Academy of CASC，National Key Lab of Combustion， Flow and Thermo—Structure，Xi7an 7 10025，China； 2 College of Astronautics，Noahwestem Polytechnical University，Xi'an 7 10072，China
关键词:
两相反应; 燃烧室; 有限速率; EDC; PDF; 燃烧模型
Keywords:
two-phase reacting flow; combustion chamber; finite rate; EDC; PDF; combustion model
分类号:
V438
文献标志码:
A
摘要:
论述了吸气式组合发动机在新一代可重复使用运载器上的使用现状，分析了各 种组合方案的优势和特点。着重介绍了RBCC、TBCC的应用对飞行器总体性能的影响，并提 出了两种较优的飞行器组合结构方案。
Abstract:
The application of combined airbreathing engines used for the next generation reusable launch vehicle(RLV)was presented．Two-Stage-To—Orbit RLV configurations using corn— bined propulsion systems for both stages were described，and a comparison was made between RBCC and TBCC to analyze their effects on the general performances of RLV．Two recommended RLV configurations were shown consequently．

参考文献/References:

[1]陈宏．高超飞行器推进系统概念研究[D]．西安：西北工业 大学．2005．
[2]Wagner A，Bouchez M．Integration of a Combined Engine Propulsion System into a SSTO Launcher[R]．AIAA一95— 6044．
[3]Roche J M．Structural Sizing of A 250001b Payload Air— Breathing Launch Vehicle for Single-Stage-To—Orbit． JANNF 25th airbreathing propulsion subcommittee[C]． 37th combustion subcommittee and 1st modeling＆ simulation subcommittee joint meeting，vol(1)．
[4]Roche J M．Preliminary Sizing of Vertical Take-Off Rocket- Based Combined—Cycle Powered Launch Vehicles[C]． JANNF 25th airbreathing propulsion subcommittee，37th combustion subcommittee and 1st modeling＆simulation subcommittee joint meeting，vol(1)．
[5]Hank J M，Franke M E．TSTO Reusable Launch Vehicles Using Airbreathing Propulsion[R]．AIAA 2006--4962．
[6]Caldwell R A，Franke M E．Weight Analysis of Two— Stage-To-Orbit Reusable Launch Vehicles[R]．AIAA 2005—4365．
[7]Kokan T，Olds J R．Aztec：A TSTO Hypersonic Vehicle Concept Utilizing TBCC and HEDM Propulsion Techno— logies[R]．AIAA2004—3728．
[8]8 Andrew M Crocker,Jeffery H Cannon，Dana G Andrews． A Comparison of Horizontal Takeoff RLVS for Next Generation Space Transportation[R]．AIAA 2003—5037．
[9]Culver G．Probabilistic Performance Comparison of RBCC and TBCC—Based Reusable Launch Vehicles with Enhan— eing Technologies[R]．AIAA 2003-5035．

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备注/Memo

收稿日期：2008—02—22；修回日期：2008一05—13， 作者简介：陈宏(1974一)，女，硕士，研究领域为固体火箭发动机装药设计。

更新日期/Last Update: 1900-01-01