Topic
Rocket
About: Rocket is a research topic. Over the lifetime, 14018 publications have been published within this topic receiving 95852 citations. The topic is also known as: rockets.
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TL;DR: In this article, the authors analyzed the aspect ratio effect on methane flow and compared it with supercritical methane flow fields in an asymmetrically heated rectangular channel with high aspect ratio and strong wall temperature differences.
Abstract: The knowledge of the flow behavior inside cooling channels is of great importance to improve design and performance of regeneratively cooled rocket engines. The modeling of the coolant flow is a challenging task because of its particular features, such as the high wall temperature gradient, the high Reynolds number and the three-dimensional geometry of the passages. In case of methane as coolant, a further complication is the transcritical operating condition of the fluid. In this thermodynamic regime large changes of the fluid properties can greatly influence the coolant flow-field and the heat transfer. Numerical simulations of transcritical methane flow-field in asymmetrically heated rectangular channel with high aspect ratio and strong wall temperature differences are carried out by a suitable CFD solver. Results are discussed in detail and compared with supercritical methane flow-fields. Finally the aspect ratio effect on methane flow is analyzed by comparison of four different rectangular cooling channel geometries with fixed hydraulic diameter and coolant flows with the same mass flow-rate per unit area. Emphasis is given to the comparison of fluid cooling performance and pressure loss.
60 citations
TL;DR: In this paper, the authors describe the measurement program and rationale, the mean state observed during the rocket salvoes, and evidence that the mean-state structure during 2002 differed in important respects from previous years.
Abstract: [1] The MaCWAVE/MIDAS collaborative rocket and ground-based measurement programs were performed at the Andoya Rocket Range and the nearby ALOMAR observatory in northern Norway during July 2002 The summer component of the MaCWAVE (Mountain and Convective Waves Ascending Vertically) program was focused on gravity wave propagation, instability, and wave-wave and wave-mean flow interaction dynamics contributing to summer mesopause structure and variability The MIDAS (Middle Atmosphere Dynamics and Structure) program concentrated on small-scale dynamical and microphysical processes near the summer mesopause Our merged program yielded a comprehensive data set comprising two ∼12-hour rocket salvoes, including 25 MET rockets and 5 sounding rockets, ground-based lidar, radar, and balloon data, and coordinated overpasses of the TIMED satellite This paper describes the measurement program and rationale, the mean state observed during the rocket salvoes, and evidence that the mean state structure during 2002 differed in important respects from previous years
60 citations
TL;DR: In this article, the authors proposed a new fuel grain design to accelerate the gasification rate of solid fuel, designated as CAMUI as an abbreviation of "cascaded multistage impinging-jet".
59 citations
TL;DR: In this article, the authors present the methodology and results of a numerical study aimed at the investigation and optimisation of different means of fuel and oxidizer injection adapted to rocket engines operating in the rotating detonation mode.
59 citations
TL;DR: In this paper, a model PDE system with increased specific impulse by partial fill was made and the performance predicted by this model was then confirmed experimentally, and the thrust can be calculated by using the simplified PDE model of Endo et al and the partial filling effect models of Sato et al.
Abstract: A pulse detonation engine (PDE) can be operated even if there are no compression mechanisms such as compressors or pistons, and a rocket engine with an extremely low combustor fill pressure (pulse detonation rocket, PDR) thus becomes possible. In this research, we made a model PDR system with increased specific impulse by partial fill. The performance predicted by this model was then confirmed experimentally. The thrust can be calculated by using the simplified PDE model of Endo et al. and the partial filling effect models of Sato et al. The mass flow rate of the propellant supplied from the pressurized cylinders is considered in this calculation. As a result, the thrust performance can be determined by the kind of propellant, the initial conditions of the gas in the cylinders, the supply-valve orifice and PDE-tube volume, and the operation frequencies. We fabricated a pulse detonation rocket (PDR) named “TODOROKI” and verified the thrust calculation model via a horizontal sliding test. We confirmed that the stability of the PDE operation depends on the ratio between the purge-gas thickness and the tube diameter. The thrust predicted by the model was identical to experimental results within 4%.
59 citations