|Table of Contents|

Analysis on transportation capacity of DRBCC-powered two-stage-to-orbit launch vehicle(PDF)

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

Issue:
2023年05期
Page:
32-38
Research Field:
目次
Publishing date:

Info

Title:
Analysis on transportation capacity of DRBCC-powered two-stage-to-orbit launch vehicle
Author(s):
ZHANG Fan1;  ZHANG Huiqiang2
(1.China Academy of Launch Vehicle Technology, Beijing 100076, China; 2. School of Aerospace Engineering,Tsinghua University, Beijing 100084, China)
Keywords:
DRBCC propulsion system;  propulsion performance;  transportation capacity;  two-stage-to-orbit
PACS:
V412
DOI:
-
Abstract:
In order to provide a suggestion for developing rocket-based-combined-cycle(RBCC)system, as well as researching the influence of propulsion performance on payload, the transportation capacity of dual-rocket-based-combined-cycle(DRBCC)powered two-stage-to-orbit(TSTO)launch vehicle was studied. The configuration of the TSTO launch vehicle was designed, and the flight profile was given. Then the TSTO transportation capacity to low-earth-orbit at 180 km was calculated. Results show the 150 t-weight TSTO launch vehicle can achieve payload of 4.773 t for equatorial mission to low-earth-orbit at 180 km with a DRBCC-powered first stage and a rocket engine powered second stage. The propulsion performance of DRBCC is tightly coupled to flight states of the launch vehicle. DRBCC works in hybrid mode under 2.5 Ma and then directly turns into ramjet mode. In ramjet and scramjet mode, specific impulse changes gently along with Mach number, but thrust fluctuates, especially in ramjet mode. During orbit-injecting process, hybrid mode is mainly used to raise height, ramjet mode is used to raise both height and speed, and scramjet mode is mainly used to raise speed.

References:

[1] 张蒙正,李斌,李光熙.组合动力:现状、问题与对策[J].火箭推进,2021,47(6):1-10.
ZHANG M Z,LI B,LI G X.Combined cycle propulsion:Current status,problems and solutions[J].Journal of Rocket Propulsion,2021,47(6):1-10.
[2] 李斌,张蒙正,黄道琼,等.组合发动机研究中若干问题探讨[J].火箭推进,2022,48(6):1-8.
LI B,ZHANG M Z,HUANG D Q,et al.Discussion on some problems in combined engine research[J].Journal of Rocket Propulsion,2022,48(6):1-8.
[3] 刘佩进.RBCC引射火箭模态性能与影响因素研究[D].西安:西北工业大学,2001.
[4] 刘洋,何国强,刘佩进,等.RBCC组合循环推进系统研究现状和进展[J].固体火箭技术,2009,32(3):288-293.
[5] 张帆,张会强.RBCC引射性能对飞行器入轨运载特性影响分析[J].火箭推进,2020,46(5):42-47.
ZHANG F,ZHANG H Q.Influence analysis of RBCC ejector mode performance on transportation capacity of launch vehicle[J].Journal of Rocket Propulsion,2020,46(5):42-47.
[6] SEGAL C.The scramjet engine:Processes and characteristics[M].Cambridge:Cambridge University Press,2009.
[7] 刘昊,王春民.不同燃料RBCC发动机性能分析[J].火箭推进,2021,47(6):33-38.
LIU H,WANG C M.Analysis of RBCC engine performance with different fuel[J].Journal of Rocket Propulsion,2021,47(6):33-38.
[8] ZHANG F,ZHANG H Q,WANG B.Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle[J].Proceedings of the Institution of Mechanical Engineers,Part G:Journal of Aerospace Engineering,2018,232(5):944-957.
[9] OLDS J,BELLINI P.Argus,a highly reusable SSTO rocket-based combined cycle launch vehicle with maglifter launch assist[C]//8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virigina:AIAA,1998.
[10] OLDS J,BRADFORD J,CHARANIA A,et al.Hyperion:An SSTO vision vehicle concept utilizing rocket-based combined cycle propulsion[C]//9th International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virigina:AIAA,1999.
[11] BLOCKER W,KOMAR D,BRADLEY M.NGLT systems assessment of the boeing FASST TSTO airbreathing vehicle concept[C]//39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virigina:AIAA,2003.
[12] KANDA T,KUDO K.Conceptual study of a combined-cycle engine for an aerospace plane[J].Journal of Propulsion and Power,2003,19(5):859-867.
[13] 佘文学,刘晓鹏,刘凯.桑格尔空天飞行器技术途径分析与思考[J].火箭推进,2021,47(6):11-20.
SHE W X,LIU X P,LIU K.Analysis and thinking on technical approach of Sanger aerospace vehicle[J].Journal of Rocket Propulsion,2021,47(6):11-20.
[14] ZHOU J X,XIAO Y T,LIU K,et al.Preliminary analysis for a two-stage-to-orbit reusable launch vehicle[C]//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virginia:AIAA,2015.
[15] PHILIP T H,LOWELL C K,ANTHONY C,et al.X43A vehicle dedign and manufacture[C]//13th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virigina:AIAA,2005.
[16] 张洪倩.基于高斯伪谱法的弹道优化设计与实现[D].南京:南京理工大学,2014.

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