TY - GEN
T1 - Design and ground test of An RBCC based two-stage-to-orbit reusable launch vehicle
AU - Gong, Chun Lin
AU - Chen, Bing
AU - Gu, Liang Xian
AU - Tang, Shuo
N1 - Publisher Copyright:
Copyright © 2017 by the International Astronautical Federation (IAF). All rights reserved.
PY - 2017
Y1 - 2017
N2 - In response to a demand for fast access to near space, a horizontal take-off and horizontal landing TSTO airbreathing reusable launch vehicle (RLV) concept is proposed. The introduced RLV is designed to deliver a maximum 2,000 kg payload to 200km circular orbit. The first stage is powered by Carbon-Hydrogen Rocket Based Combined Cycle (RBCC) engines, and has capability of flying back to the launch site. The second stage is an aircraft-like Hydrogen-Oxygen rocket piggybacked on first stage. This paper put focus on the first stage and describe system concept, design methodologies, and preliminary ground test results. Firstly, the system concept, including propulsion and fuel selection, airframe/propulsion integrated configuration, separation condition, variable geometric inlet & nozzle, is proposed. Balancing several alternatives, the configuration of lift-body aerodynamic shape with six-module RBCC engine located under airframe is selected. The optimal separation velocity and altitude are chosen by sensitivity analysis. Then, the Multidisciplinary Design Optimization methodology and tools developed to resolve tight-coupled system design challenge is introduced. The methods and tools used include: 1) a weight & sizing tool, 2) a multi-point optimizer for aerodynamic shape design over wide-range speeds, 3) a multi-point optimizer for RBCC engine design to meet requirements of all working modes, 4) an integrated aerodynamic/propulsion performance computation tool, 5) a gauss-pseudo spectral based optimizer, 6) a structural design and sizing method, 7) an thermal protection system concept selection and sizing tool, and 8) a surrogate model based system optimizer. After that, the preliminary design results, including configuration, RBCC engine, structure, TPS, and control, is described. Lastly, the test plan for the critical technology of RBCC engine integrated on airframe is described, and recent integrated airframe/propulsion ground test carried out is reported.
AB - In response to a demand for fast access to near space, a horizontal take-off and horizontal landing TSTO airbreathing reusable launch vehicle (RLV) concept is proposed. The introduced RLV is designed to deliver a maximum 2,000 kg payload to 200km circular orbit. The first stage is powered by Carbon-Hydrogen Rocket Based Combined Cycle (RBCC) engines, and has capability of flying back to the launch site. The second stage is an aircraft-like Hydrogen-Oxygen rocket piggybacked on first stage. This paper put focus on the first stage and describe system concept, design methodologies, and preliminary ground test results. Firstly, the system concept, including propulsion and fuel selection, airframe/propulsion integrated configuration, separation condition, variable geometric inlet & nozzle, is proposed. Balancing several alternatives, the configuration of lift-body aerodynamic shape with six-module RBCC engine located under airframe is selected. The optimal separation velocity and altitude are chosen by sensitivity analysis. Then, the Multidisciplinary Design Optimization methodology and tools developed to resolve tight-coupled system design challenge is introduced. The methods and tools used include: 1) a weight & sizing tool, 2) a multi-point optimizer for aerodynamic shape design over wide-range speeds, 3) a multi-point optimizer for RBCC engine design to meet requirements of all working modes, 4) an integrated aerodynamic/propulsion performance computation tool, 5) a gauss-pseudo spectral based optimizer, 6) a structural design and sizing method, 7) an thermal protection system concept selection and sizing tool, and 8) a surrogate model based system optimizer. After that, the preliminary design results, including configuration, RBCC engine, structure, TPS, and control, is described. Lastly, the test plan for the critical technology of RBCC engine integrated on airframe is described, and recent integrated airframe/propulsion ground test carried out is reported.
KW - Ground test
KW - MDO
KW - RBCC
KW - Reusable launch vehicle
KW - Space transportation
KW - Two stage to orbit
UR - http://www.scopus.com/inward/record.url?scp=85051379347&partnerID=8YFLogxK
M3 - 会议稿件
AN - SCOPUS:85051379347
SN - 9781510855373
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 9945
EP - 9957
BT - 68th International Astronautical Congress, IAC 2017
PB - International Astronautical Federation, IAF
T2 - 68th International Astronautical Congress: Unlocking Imagination, Fostering Innovation and Strengthening Security, IAC 2017
Y2 - 25 September 2017 through 29 September 2017
ER -