TY - GEN
T1 - Modeling and Performance Study of Pre-cooling Air Turbo Rocket Engine in the Air-Breathing Mode
AU - Zhao, Xiaotian
AU - Mao, Hongwei
AU - Ma, Haibo
AU - Nan, Xiangyi
AU - Ma, Yuan
AU - Wang, Yunlong
AU - Liu, Jinxin
N1 - Publisher Copyright:
© The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2024.
PY - 2024
Y1 - 2024
N2 - The whole system mathematical simulation model of pre-cooling air turbo rocket engine (PATR engine) was established by the component method, the influence of the design parameters of key components on the system performance was analyzed, and the variation law of the performance parameters along the flight trajectory of the engine was calculated in the air-breathing mode. The velocity and altitude characteristics at typical operating conditions are also studied. The results indicate that the system performance (specific thrust, specific impulse) increases with higher turbo efficiency and heat transfer efficiency of the heat exchanger. The engine economy is optimal when the hydrogen flow is the design value, and both the engine economy and thrust are optimal when the helium flow is the design value. The specific impulse and thrust of core engine first increase and then decrease along the flight trajectory, and the system performance reaches a peak when Ma = 2.1. It is found that the air flow captured by inlet is the main factor affecting the engine velocity and altitude characteristics.
AB - The whole system mathematical simulation model of pre-cooling air turbo rocket engine (PATR engine) was established by the component method, the influence of the design parameters of key components on the system performance was analyzed, and the variation law of the performance parameters along the flight trajectory of the engine was calculated in the air-breathing mode. The velocity and altitude characteristics at typical operating conditions are also studied. The results indicate that the system performance (specific thrust, specific impulse) increases with higher turbo efficiency and heat transfer efficiency of the heat exchanger. The engine economy is optimal when the hydrogen flow is the design value, and both the engine economy and thrust are optimal when the helium flow is the design value. The specific impulse and thrust of core engine first increase and then decrease along the flight trajectory, and the system performance reaches a peak when Ma = 2.1. It is found that the air flow captured by inlet is the main factor affecting the engine velocity and altitude characteristics.
KW - Component-level Model
KW - Flight Trajectory
KW - PATR Engine
KW - Sensitivity Analysis
KW - Velocity and Altitude Characteristics
UR - https://www.scopus.com/pages/publications/85200476216
U2 - 10.1007/978-981-97-4010-9_79
DO - 10.1007/978-981-97-4010-9_79
M3 - 会议稿件
AN - SCOPUS:85200476216
SN - 9789819740093
T3 - Lecture Notes in Electrical Engineering
SP - 1018
EP - 1035
BT - 2023 Asia-Pacific International Symposium on Aerospace Technology, APISAT 2023, Proceedings - Volume II
A2 - Fu, Song
PB - Springer Science and Business Media Deutschland GmbH
T2 - Asia-Pacific International Symposium on Aerospace Technology, APISAT 2023
Y2 - 16 October 2023 through 18 October 2023
ER -