TY - GEN
T1 - Design and verification of airframe/propulsion integration about air-breathing launch vehicle
AU - Bing, Chen
AU - Gong, Chun Lin
AU - Gu, Liang Xian
N1 - Publisher Copyright:
© 2015, American Institute of Aeronautics and Astronautics. All rights reserved.
PY - 2015
Y1 - 2015
N2 - Airframe/Propulsion Integrationis a key technology for air-breathing launch vehicle. This paper summaries the design constraints of RBCC (Rocket based Combined Cycle) power launch vehicle, and the performance of integration is evaluated by effective specific impulse which is a function of aerodynamic drag, engine thrust and specific impulse. The aerodynamic configuration of airframe/propulsion integration is designed, and analyzed by CFD. Considering the sizes of the vehicle are large, the inner channel is after the nose of the air frame to reduce the length of channel. Besides, the channel is behind the airframe to increase the aerodynamic lift, and the fore body is the outer compressed surface of the inlet. The analysis results show the lift-drag ratio can be up to 4.0 in subsonic and 3.5 in supersonic. The lift-drag ratio decreases when mach number is over 4. Finally, the design and analysis is verified by experiment of wind tunnel. The model of experiment is smaller than the origin configuration. The experiment is pressure test. The test results show the pressure configuration of launch vehicle which can guide the design of launch vehicle and verify the accuracy of CFD.
AB - Airframe/Propulsion Integrationis a key technology for air-breathing launch vehicle. This paper summaries the design constraints of RBCC (Rocket based Combined Cycle) power launch vehicle, and the performance of integration is evaluated by effective specific impulse which is a function of aerodynamic drag, engine thrust and specific impulse. The aerodynamic configuration of airframe/propulsion integration is designed, and analyzed by CFD. Considering the sizes of the vehicle are large, the inner channel is after the nose of the air frame to reduce the length of channel. Besides, the channel is behind the airframe to increase the aerodynamic lift, and the fore body is the outer compressed surface of the inlet. The analysis results show the lift-drag ratio can be up to 4.0 in subsonic and 3.5 in supersonic. The lift-drag ratio decreases when mach number is over 4. Finally, the design and analysis is verified by experiment of wind tunnel. The model of experiment is smaller than the origin configuration. The experiment is pressure test. The test results show the pressure configuration of launch vehicle which can guide the design of launch vehicle and verify the accuracy of CFD.
UR - http://www.scopus.com/inward/record.url?scp=84947969366&partnerID=8YFLogxK
M3 - 会议稿件
AN - SCOPUS:84947969366
SN - 9781624103209
T3 - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
BT - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
PB - AIAA American Institute of Aeronautics and Astronautics
T2 - 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
Y2 - 6 July 2015 through 9 July 2015
ER -