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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.


Papers
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Book ChapterDOI
Angelo Miele1
01 Jan 1959
TL;DR: In this article, general equations for analyzing the optimum flight paths of rocket-powered aircraft, missiles and satellites are presented for spherical Earth and the variability of the acceleration of gravity with the altitude is accounted for.
Abstract: General equations are presented for analyzing the optimum flight paths of rocket-powered aircraft, missiles and satellites. The Earth is assumed spherical; the variability of the acceleration of gravity with the altitude is accounted for.

37 citations

Journal ArticleDOI
TL;DR: In this paper, a low-order analytical performance model for the rocket-mode rotating detonation engine was developed, starting from the general form of the continuity, momentum, and energy equations and integrati...
Abstract: A low-order analytical performance model for the rocket-mode rotating detonation engine was developed. Starting from the general form of the continuity, momentum, and energy equations and integrati...

37 citations

01 Aug 1959
TL;DR: In this paper, a 1,500-pound-thrust engine and several 5,000-pistons-per-cycle engines for which the nozzle exit pressure was changed systematically in order to study its effects on the noise level and spectra.
Abstract: Measurements of near- and far-field noise pressures are presented for a 1,500-pound-thrust engine and for several 5,000-pound-thrust engines for which the nozzle exit pressure was changed systematically in order to study its effects on the noise level and spectra. Near-field surveys indicated that the highest noise pressure occurred at about 20 exit diameters downstream if the nozzle near the transition from super-sonic to subsonic flow. The acoustical power radiated from all engines averaged about 0.5 percent of the mechanical power of the exhaust stream, the least noise being radiated by the nozzle having an exit pressure less than atmospheric. The rocket engines of these tests radiate more power per cycle at the lower frequencies than arte reported for subsonic jets in other related studies.

37 citations

Journal ArticleDOI
TL;DR: The main result of this work is the successful integration and real-time demonstration of model-based fault detection with a reconfigurable control as a new technique for valve fault accommodation on a reusable rocket engine.
Abstract: An intelligent control system for reusable rocket engines is under development at the NASA Lewis Research Center. The primary objective is to extend the useful life of a reusable rocket propulsion system while minimizing flight maintenance and maximizing engine life and performance through improved control and monitoring algorithms and additional sensing and actuation. The main result of this work is the successful integration and real-time demonstration of model-based fault detection with a reconfigurable control as a new technique for valve fault accommodation on a reusable rocket engine. The focus here is on detecting and accommodating a frozen (stuck in a fixed position) oxidizer valve during a down-thrust and up-thrust manoeuvre by examining fault parameters produced by the algorithm. The detection scheme estimates the position of the frozen valve as a function of the fault parameters. Real-time simulation results demonstrate the effectiveness of the approach for two fault scenarios during a typical throttling manoeuvre.

36 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202211
2021373
2020480
2019624
2018537
2017493