Results 311 to 320 of about 892,130 (360)

Thrust Performance of Converging Rotating Detonation Engine Compared with Steady Rocket Engine

Journal of Propulsion and Power, 2023
Rotating detonation engines (RDEs) have been actively researched around the world for application to next-generation aerospace propulsion systems because detonation combustion has theoretically higher thermal efficiency than conventional combustion ...
K. Ishihara, Kentaro Yoneyama, H. Watanabe, N. Itouyama, A. Kawasaki, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki, K. Higashino   +9 more
semanticscholar   +1 more source

Development of a Liquid-Propellant Rocket Powered by a Rotating Detonation Engine

Journal of Propulsion and Power, 2023
This paper presents work on a demonstrator rocket powered by a rotating detonation engine (RDE) fed by liquid propellants. Key to the success of the project was the development of a suitably efficient and lightweight RDE. After selecting the propellants:
M. Kawalec, P. Wolański, W. Perkowski, A. Bilar   +3 more
semanticscholar   +1 more source

Unsupervised Multimodal Anomaly Detection With Missing Sources for Liquid Rocket Engine

IEEE Transactions on Neural Networks and Learning Systems, 2022
To achieve reliable and automatic anomaly detection (AD) for large equipment such as liquid rocket engine (LRE), multisource data are commonly manipulated in deep learning pipelines.
Yong Feng, Zijun Liu, Jinglong Chen, Haixin Lv, Jun Wang, Xinwei Zhang   +5 more
semanticscholar   +1 more source

A Supervised Framework for Recognition of Liquid Rocket Engine Health State Under Steady-State Process Without Fault Samples

IEEE Transactions on Instrumentation and Measurement, 2021
Data-driven intelligent models have received more and more attention in liquid rocket engine (LRE) state recognition. However, due to practical limitations, the fault data are rare for model training, which results in poor testing results.
Haixin Lv, Jinglong Chen, Jun Wang, Junshe Yuan, Zijun Liu   +4 more
semanticscholar   +1 more source

A Review Towards the Design Optimization of High Performance Additively Manufactured Rotating Detonation Rocket Engine Injectors

AIAA Propulsion and Energy 2021 Forum, 2021
Rotating Detonation Rocket Engines (RDRE) have been marketed primarily for their higher specific impulse potential over constant pressure (CP) liquid rocket engines. However, several other performance advantages exist such as heat transfer advantages for
Thomas W. Teasley, C. Protz, Andrew P. Larkey, Benjamin B. Williams, P. Gradl   +4 more
semanticscholar   +1 more source

Formation mechanism of high-frequency combustion oscillations in a model rocket engine combustor

The Physics of Fluids, 2021
We study the formation mechanism of high-frequency combustion oscillations in a model rocket combustor from the viewpoints of symbolic dynamics and complex networks.
Satomi Shima, Kosuke Nakamura, H. Gotoda, Y. Ohmichi, S. Matsuyama   +4 more
semanticscholar   +1 more source

Thrust Validation of Rotating Detonation Engine System by Moving Rocket Sled Test

Journal of Propulsion and Power, 2021
This Paper presents the results of a rotating detonation engine rocket sled test demonstration on a 127 mm gauge rail at 100 m long high-speed running track test equipment to evaluate the thrust pe...
Keisuke Goto, Y. Kato, K. Ishihara, K. Matsuoka, J. Kasahara, A. Matsuo, I. Funaki, D. Nakata, K. Higashino, N. Tanatsugu   +9 more
semanticscholar   +1 more source

A Simple Model for Rotating Detonation Rocket Engine Sizing and Performance Estimates

AIAA Scitech 2021 Forum, 2020
A Rotating Detonation Rocket Engine (RDRE) model is described which characterizes the device as an essentially infinite number of circumferentially arranged, sequentially firing pulse detonation engine (PDE) tubes.
D. Paxson, H. D. Perkins
semanticscholar   +1 more source

Performance of a Rotating Detonation Rocket Engine with Various Convergent Nozzles and Chamber Lengths

Energies, 2019
A rotating detonation rocket engine (RDRE) with various convergent nozzles and chamber lengths is investigated. Three hundred hot-fire tests are performed using methane and oxygen ranging from equivalence ratio equaling 0.5–2.5 and total propellant flow ...
J. Bennewitz, Blaine Bigler, M. Ross, S. Danczyk, W. Hargus, Richard D. Smith   +5 more
semanticscholar   +1 more source