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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37 citations
TL;DR: In this article, a large eddy simulation with liquid kerosene sprayed and vaporized is used to study the intrinsic unsteadiness of combustion in a rocket-based combined-cycle engine combustor operating at ramjet mode numerically.
37 citations
TL;DR: In this article, high frequency waves in two frequency bands above the electron gyro frequency (1.6 MHz and 2.3 MHz) were observed by radio receivers carried on a sounding rocket as it passed over a strong aurora.
Abstract: High frequency waves in two frequency bands above the electron gyro frequency (1.6 MHz and 2.3 MHz) were observed by radio receivers carried on a sounding rocket as it passed over a strong aurora. Only the line at 2.3 MHz has a large magnetic component. Both 0.4s and 4s periods are present in much of the emissions. Good correlation is seen for a short time between the 2.3 MHz waves and 1.9 keV electrons detected on board the rocket.
37 citations
TL;DR: In this paper, a couplednite elementuid -structure interaction analysis of regeneratively cooled rocket combustion cham- bers is presented, which allows the computation of the coolant and the heat conduction between the cooling and combustion chamber structure, and the resulting elasto-plastic deformation of the combus- tion chamber under cyclic thermal and mechanical loading is analyzed.
Abstract: A couplednite elementuid -structure interaction analysis of regeneratively cooled rocket combustion cham- bers, which allows the computation of the coolantow and the heat conduction between the coolant and the combustion chamber structure, is presented. Furthermore, the resulting elasto-plastic deformation of the combus- tion chamber under cyclic thermal and mechanical loading is analyzed. The developed solution strategy is applied to the prediction of the heat transfer and thermomechanical load-induced deformation process of the European rocket engine Vulcain. Based on the results, the failure mechanism of the combustion chamber and its governing parameters are identied. It is demonstrated that this mechanism signicantly reduces the lifetime of the rocket engine. Besides the conceptual design by the engineer, a mathematical optimization procedure based on thenite element model of the combustion chamber is investigated. This optimization method allows the improvement of an initial design with respect to anite number of design variables such that the stress, plastic strain, or temperature levels are decreased, and accordingly, the lifetime will be increased.
37 citations