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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01 Dec 2009
TL;DR: In this paper, an experimental investigation was conducted to determine the relative propulsive performance and viability of novel solid propellants comprised of ALICE using fundamental techniques such as steady-state strand experiments and applied experimentation such as labscale static fire rocket tests.
Abstract: An experimental investigation was conducted to determine the relative propulsive performance and viability of novel solid propellants comprised of ALICE using fundamental techniques such as steady-state strand experiments and applied experimentation such as labscale static fire rocket tests. Burning rates, slag accumulation, thrust, and pressure are some of the experimental parameters obtained. System scaling has been performed to examine the effect of larger systems on slag accumulation and performance parameters. The effect of pressure on the linear burning rate was examined and correlated using a Saint Roberts’s law fit. The pressure exponent for ALICE was 0.73, which is approximately a factor of two larger than Al/water mixtures. Three sizes rocket motors ranging from internal diameters of 0.75 to 3-in. Nozzle throat diameter and igniter strength were varied. It was found that ALICE propellants successfully ignited and combusted in each lab-scale rocket motor, generating thrust levels above 223 lbf for expansion ratios of 10 and center-perforated grain configurations (3-in length). For the 3-in motor, combustion efficiency was around 70%, while the specific impulse efficiency was 64%.
28 citations
Dissertation•
01 Jan 2012
TL;DR: In the high-frequency variety of combustion instability, the pressure oscillations take on the form and frequency of an acoustic resonance mode of the combustion chamber volume, and the most common mode in naturally occurring instability, and also the most destructive, is the first tangential mode, with acoustic gas oscillations oriented transversally to the direction of propellant injection.
Abstract: Self-sustaining pressure oscillations in the combustion chamber, or combustion instability, is a commonly encountered and potentially damaging phenomenon in liquid propellant rocket engines (LPREs). In the high-frequency variety of combustion instability, the pressure oscillations take on the form and frequency of an acoustic resonance mode of the combustion chamber volume. The most common mode in naturally occurring instability, and also the most destructive, is the first tangential mode, with acoustic gas oscillations oriented transversally to the direction of propellant injection. The instability is driven by the coupling between acoustic oscillations and unsteady energy release from combustion. The mechanisms through which injection and combustion firstly respond to the acoustic field, and secondly feed energy back into the acoustic field have not yet been fully characterised.
28 citations
TL;DR: In this article, the authors present results of optimisation of sounding rockets using hybrid propulsion and provide insight into the sensitivity of different design parameters on performance of hybrid sounding rockets and delve into the potential and challenges of using hybrid rocket technology for expendable suborbital applications.
28 citations