TY - GEN
T1 - Effect of secondary injection reaction heat on thrust vector control in divergent section
AU - Cheng, Yang
AU - Xie, Kan
AU - Wang, Ningfei
AU - Jiang, Chen
N1 - Publisher Copyright:
© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - Compared to mechanical adjustment process, using secondary injection to control the thrust vector of solid rocket engine is a better method. Under the condition that the secondary injection can control the thrust vector, this paper tries to use other methods to make the thrust vector control have a better effect. This paper will explore that the effect of secondary injection reaction heat on thrust vector control. The main method used in this paper is the numerical simulation technology of computational fluid dynamics and the simulation model adopts an experimental model. Through CFD simulation, the parameters affecting the effect of the thrust vector control and their influence are explored. The chemical reaction will increase the side control force and the thrust vector angle, and have some positive influence on the thrust vector control.
AB - Compared to mechanical adjustment process, using secondary injection to control the thrust vector of solid rocket engine is a better method. Under the condition that the secondary injection can control the thrust vector, this paper tries to use other methods to make the thrust vector control have a better effect. This paper will explore that the effect of secondary injection reaction heat on thrust vector control. The main method used in this paper is the numerical simulation technology of computational fluid dynamics and the simulation model adopts an experimental model. Through CFD simulation, the parameters affecting the effect of the thrust vector control and their influence are explored. The chemical reaction will increase the side control force and the thrust vector angle, and have some positive influence on the thrust vector control.
UR - http://www.scopus.com/inward/record.url?scp=85066494048&partnerID=8YFLogxK
U2 - 10.2514/6.2018-4485
DO - 10.2514/6.2018-4485
M3 - Conference contribution
AN - SCOPUS:85066494048
SN - 9781624105708
T3 - 2018 Joint Propulsion Conference
BT - 2018 Joint Propulsion Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018
Y2 - 9 July 2018 through 11 July 2018
ER -