三组元液体火箭发动机综述
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- 论文作者：王伟良 ; 孛涛 ; 李娜 ; 魏祥庚 ; 秦飞
- 年：2016
- 作者机构：西北工业大学;
- 论文关键词：三组元 ; 系统方案 ; 关键技术
- 会议召开时间：2016-08-17
- 会议录名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议论文集
- 语种：中文
- 分类号：V434
- 学会代码：HTDZ
- 会议名称：中国航天第三专业信息网第三十七届技术交流会暨第一届空天动力联合会议
- 会议地点：中国陕西西安
- 主办单位：中国航天第三专业信息网、中国航天科技集团公司科技委、中国航天科工集团公司科技委
- 学会名称：中国航天第三专业信息网
- 页数：7
- 文件大小：916k
- 原文格式：D
- 会议级别：全国
摘要
双组元液体火箭发动机的发展已经进入成熟阶段,想要进一步提高其性能已十分困难。为了满足人们对空间探索的需求,就需要探索液体火箭发动机发展的新途径。美国和俄罗斯都十分重视三组元发动机的技术研究,我国近年来也做了一定的研究工作。本文针对三组元发动机的背景需求、系统方案、技术发展和关键技术等进行概述。
引文
[1]Bekey,L,"SSTO Rockets:A Practical Possibility,"Aerospace America,July 1994,pp.32-37.
[2]Martin,J.A.,"History of Propulsion for SSTO and Multiple Stage Vehicles,"AIAA Paper93-1942,June 1993.
[3]Salkeld,R.,"Mixed-Mode Propulsion for the Space Shuttle,"Astronautics and Aeronautics,Vol.9,No.8,1971,pp.52-58.
[4]Wilhite,A.W.,"Optimization of Rocket Propulsion Systems for Advanced Earth-to-orbit Shuttles,"Journal of Spacecraft and Rockets,Vol.17,No.2,1980,pp.99-104.
[5]Martin,J.A.,"A Method for Determining Optimum Phasing of a Multiphase Propulsion System for a Single-Stage Vehicle with Linearized Inert Weight,"NASA TN-7792,1974.
[6]Colasurdo,G.,Pastrone,D.,and Casalino,L.,"Optimal Performance of a Dual-Fuel Single-Stage Rocket,"Journal of Spacecraft and Rockets,Vol.35,No.5,1998,pp.667-671.
[7]James A.Martin.Effects of Tripropellant Concept.NASA Technical Paper 2602,1986,6.
[8]钟家强、胡平信,三组元系统方案研究.推进技术,1997、6:18(3).
[9]Roger A.Lepsch Jr.Douglas O.Stanley,and Resit Unal.Dual-Fuel Propulsion in Single-Stage Advanced Manned Launch System Vehicle.Journal of Spacecraft and Rockets,1995:32(3).
[10]Henry,B.V.,and Decker,J.P.,"Future Earth Orbit Transportation Systems/Technology Implications,"Astronautics and Aeronautics,Vol.14,No.9,1976,pp.18-28.
[11]Wilhite,A.W.,"Advanced Rocket Propulsion Technology Assessment for Future Space Transportation,"Journal of Spacecraft and Rockets,Vol.19,No.4,1982,pp.314-319.
[12]Martin,J.A.,"Hydrocarbon Rocket Engines for Earth-to-Orbit Vehicles,"Journal of Spacecraft and Rockets,Vol.20,No.3,1983,pp.249-256.
[13]Martin,J.A.,"Selecting Hydrocarbon Rocket Propulsion Technology,"IAF-86-167,37th Congress of the International Astronautical Federation,Innsbruck,Austria,1986.
[14]Lepsch,R.A.,Jr.,Stanley,D.O.,and Unal,R.,"Dual-fuel Propulsion in Single-Stage Advanced Manned Launch System Vehicle,"Journal of Spacecraft and Rockets,Vol.32,No.3,1995,pp.417-425.
[15]宁建华、杨瑞亭.双喷管发动机.China Academic Journal Electronic Publishing House.
[16]谭建国,王振国.三组元液体火箭发动机系统方案设计与比较.推进技术.2003,10:24(5).
[17]B.David Goracke.Tripropellant Engine Drive Cycle Consideration for the SSTO Application.AIAA 95-2950.
[18]N.S.Gontcharov.Tripropellant Engine Technology for Reusable Launch Vehicles.AIAA.
[19]旷武岳.俄罗斯三组元发动机在单级入轨(SSTO)中的应用主.China Academic Journal Electronic Publishing House.
[20]Thongsay Vongpaseuth,G.Venkatasubramanyam and James A.Martin,Russian Tripropellant Engines for SSTO,AIAA95一2952.
[21]James A.Martin,Thongsay Vongpaseuth and.G.Venkaatsubramanyam.Russian RD一704for Single一Stage Vehieles.University of Alabama,Tusealoosa,Alabama35487一0280.
[22]John O.Vilja and James R.Lobitz,Bell Annular Tripropellant Engine concept,AIAA94一46180.
[23]M.G.Schmidt and M.M.Micci.Combustion Performance of RP-1/O2/H2 Tripropellants.Propulsion Engineering Research Center,The Pennsylvania State University.AIAA 98-3686.
[24]王振国,周进等.三组元双模式喷注器与燃烧室技术研究(四):数值仿真研究报告.国防科学技术报告,2003、1.
[25]王振国,周进等.液氧/煤油/气氢三组元燃烧室技术研究(二):系统分析与仿真研究报告.国防科学技术报告,2004、10.
[26]李清廉,田章福,王振国.模型三组元喷嘴流量特性实验,推进技术,2002,23(4).
[27]田章福,李消廉,沈赤兵,周进,王振国.三组元喷嘴结构参数对棍合腔中两相流的影响,推进技术,2002,23(4).
[28]李大鹏.黄玉辉.沈赤兵.王振国三组元液体火箭发动机燃烧不稳定性实验研究[会议论文]2001.
[29]Rudis,M.A.,Orlov,V.A.,Rachuk,V.S.,Nikitin,L.N.,and Campbell,W.E.,"A Universal Methodology for Predicting Liquid Rocket Engine Durability Based on Russian RD-0120 Engine Operating Experience,"AIAA Paper 95-2963,1995.
[30]Lauston,M.F.,Rousar,D.C.,and Bucella,S.,"Carbon Deposition with LOX/RP-1Propellants,"AIAA Paper 85-1164,1985.
[31]张学和.国外三组元液体火箭发动机研制概况分析.世界导弹与航天.1989,3.
[32]黄艳斐,朱岳麟,熊常健,潘英杰.航空发动机喷嘴结焦积碳的性质.北京航空航天大学学报.2011,6:37(6).
[33]贾春燕,王洪铭.航空发动机燃烧室喷嘴内部燃油结焦研究.航空发动机.2011,10:37(5).
[34]李大鹏.三组元火箭发动机推力室工作过程实验研究与数值仿真[工学硕士学位论文].长沙:国防科技大学研究生院,2002,1
[35]沈赤兵,周进,王振国,李麦亮,李清廉.三组元喷嘴雾化特性的试验研究.推进技术.1999,10:20(5).
[36]沈赤兵,童荣瑜,周进,王振国.三组元喷嘴流量特性的试验研究.中国空间科学技术.1999,6:3.
[2]Martin,J.A.,"History of Propulsion for SSTO and Multiple Stage Vehicles,"AIAA Paper93-1942,June 1993.
[3]Salkeld,R.,"Mixed-Mode Propulsion for the Space Shuttle,"Astronautics and Aeronautics,Vol.9,No.8,1971,pp.52-58.
[4]Wilhite,A.W.,"Optimization of Rocket Propulsion Systems for Advanced Earth-to-orbit Shuttles,"Journal of Spacecraft and Rockets,Vol.17,No.2,1980,pp.99-104.
[5]Martin,J.A.,"A Method for Determining Optimum Phasing of a Multiphase Propulsion System for a Single-Stage Vehicle with Linearized Inert Weight,"NASA TN-7792,1974.
[6]Colasurdo,G.,Pastrone,D.,and Casalino,L.,"Optimal Performance of a Dual-Fuel Single-Stage Rocket,"Journal of Spacecraft and Rockets,Vol.35,No.5,1998,pp.667-671.
[7]James A.Martin.Effects of Tripropellant Concept.NASA Technical Paper 2602,1986,6.
[8]钟家强、胡平信,三组元系统方案研究.推进技术,1997、6:18(3).
[9]Roger A.Lepsch Jr.Douglas O.Stanley,and Resit Unal.Dual-Fuel Propulsion in Single-Stage Advanced Manned Launch System Vehicle.Journal of Spacecraft and Rockets,1995:32(3).
[10]Henry,B.V.,and Decker,J.P.,"Future Earth Orbit Transportation Systems/Technology Implications,"Astronautics and Aeronautics,Vol.14,No.9,1976,pp.18-28.
[11]Wilhite,A.W.,"Advanced Rocket Propulsion Technology Assessment for Future Space Transportation,"Journal of Spacecraft and Rockets,Vol.19,No.4,1982,pp.314-319.
[12]Martin,J.A.,"Hydrocarbon Rocket Engines for Earth-to-Orbit Vehicles,"Journal of Spacecraft and Rockets,Vol.20,No.3,1983,pp.249-256.
[13]Martin,J.A.,"Selecting Hydrocarbon Rocket Propulsion Technology,"IAF-86-167,37th Congress of the International Astronautical Federation,Innsbruck,Austria,1986.
[14]Lepsch,R.A.,Jr.,Stanley,D.O.,and Unal,R.,"Dual-fuel Propulsion in Single-Stage Advanced Manned Launch System Vehicle,"Journal of Spacecraft and Rockets,Vol.32,No.3,1995,pp.417-425.
[15]宁建华、杨瑞亭.双喷管发动机.China Academic Journal Electronic Publishing House.
[16]谭建国,王振国.三组元液体火箭发动机系统方案设计与比较.推进技术.2003,10:24(5).
[17]B.David Goracke.Tripropellant Engine Drive Cycle Consideration for the SSTO Application.AIAA 95-2950.
[18]N.S.Gontcharov.Tripropellant Engine Technology for Reusable Launch Vehicles.AIAA.
[19]旷武岳.俄罗斯三组元发动机在单级入轨(SSTO)中的应用主.China Academic Journal Electronic Publishing House.
[20]Thongsay Vongpaseuth,G.Venkatasubramanyam and James A.Martin,Russian Tripropellant Engines for SSTO,AIAA95一2952.
[21]James A.Martin,Thongsay Vongpaseuth and.G.Venkaatsubramanyam.Russian RD一704for Single一Stage Vehieles.University of Alabama,Tusealoosa,Alabama35487一0280.
[22]John O.Vilja and James R.Lobitz,Bell Annular Tripropellant Engine concept,AIAA94一46180.
[23]M.G.Schmidt and M.M.Micci.Combustion Performance of RP-1/O2/H2 Tripropellants.Propulsion Engineering Research Center,The Pennsylvania State University.AIAA 98-3686.
[24]王振国,周进等.三组元双模式喷注器与燃烧室技术研究(四):数值仿真研究报告.国防科学技术报告,2003、1.
[25]王振国,周进等.液氧/煤油/气氢三组元燃烧室技术研究(二):系统分析与仿真研究报告.国防科学技术报告,2004、10.
[26]李清廉,田章福,王振国.模型三组元喷嘴流量特性实验,推进技术,2002,23(4).
[27]田章福,李消廉,沈赤兵,周进,王振国.三组元喷嘴结构参数对棍合腔中两相流的影响,推进技术,2002,23(4).
[28]李大鹏.黄玉辉.沈赤兵.王振国三组元液体火箭发动机燃烧不稳定性实验研究[会议论文]2001.
[29]Rudis,M.A.,Orlov,V.A.,Rachuk,V.S.,Nikitin,L.N.,and Campbell,W.E.,"A Universal Methodology for Predicting Liquid Rocket Engine Durability Based on Russian RD-0120 Engine Operating Experience,"AIAA Paper 95-2963,1995.
[30]Lauston,M.F.,Rousar,D.C.,and Bucella,S.,"Carbon Deposition with LOX/RP-1Propellants,"AIAA Paper 85-1164,1985.
[31]张学和.国外三组元液体火箭发动机研制概况分析.世界导弹与航天.1989,3.
[32]黄艳斐,朱岳麟,熊常健,潘英杰.航空发动机喷嘴结焦积碳的性质.北京航空航天大学学报.2011,6:37(6).
[33]贾春燕,王洪铭.航空发动机燃烧室喷嘴内部燃油结焦研究.航空发动机.2011,10:37(5).
[34]李大鹏.三组元火箭发动机推力室工作过程实验研究与数值仿真[工学硕士学位论文].长沙:国防科技大学研究生院,2002,1
[35]沈赤兵,周进,王振国,李麦亮,李清廉.三组元喷嘴雾化特性的试验研究.推进技术.1999,10:20(5).
[36]沈赤兵,童荣瑜,周进,王振国.三组元喷嘴流量特性的试验研究.中国空间科学技术.1999,6:3.
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