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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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Journal ArticleDOI
TL;DR: In this paper, a theoretical similarity analysis is presented to derive proper scaling rules in hybrid rocket motors, and tests are conducted on different-size polymethylmethacrylate/gaseous oxygen hybrid-rocket motors.

24 citations

Journal ArticleDOI
TL;DR: In this paper, a gigawatt pulse line called Godzilla is adapted for experimental development to produce the power levels associated with such systems, a megajoule-level energy available is electromagnetically deposited in cold helium gas to simulate the fusion-heated, low-molecular-weight propellant.
Abstract: Optimum travel duration for manned interplanetary missions requires propulsion systems that deliver very high thrust, on the order of a thousand Newtons, in conjunction with specific impulse capabilities that exceed 10,000 s. Theoretically, rocket propellants consisting of fusion reactants intermixed with large masses of low-molecular-weight fuels can be expanded within a magnetic nozzle to meet these requirements. To produce the power levels associated with such systems, a gigawatt pulse line called Godzilla is adapted for experimental development. The megajoule-level energy available is electromagnetically deposited in cold helium gas to simulate the fusion-heated, low-molecular-weight propellant. The magnetohydrodynamic computer code, MACH2, is employed to provide guidelines in the design of this magnetoplasmadynamic plasma source. The numerical results specify the geometric configuration and operation conditions required to overcome destructive effects associated with these power levels within experimental limitations.

24 citations

Proceedings ArticleDOI
01 Jun 2013
TL;DR: In this paper, the turbulent wake flow of generic rocket configurations is investigated experimentally and numerically at a freestream Mach number of 6.0 and a unit Reynolds number of 10 · 10 6.
Abstract: The turbulent wake flow of generic rocket configurations is investigated experimentally and numerically at a freestream Mach number of 6.0 and a unit Reynolds number of 10 · 10 6 .T heflow condition is based on the trajectory of Ariane V at an altitude of 50km, which is used as baseline to address the overarchingtasks of wakeflows in the hypersonicregimelikefluid-structuralcoupling,reversehot jets and base heating. Experiments using pressure transducers and high-speed schlieren measurement technique were conducted to gain insight into the local pressure fluctuations on the base and the oscillations of the recompression shock. This experimental configuration features a wedge-profiled strut orthogonally mounted to the main body. Additionally, the influence of cylindrical nozzle extensions attached to the base of the rocket is investigated, which is the link to the numerical investigations. Here, the axisymmetric model possesses a cylindrical sting support of the same diameter as the nozzle extensions. The sting supportallows investigationsof a undisturbedwakeflow. A time-accurate zonal RANS/LES approachwas applied to identify shocks, expansion waves, and the highly unsteady recompression region numerically. Subsequently,experimentaland numericalresults in the strut-avertedregionare opposed with regardto the wall pressure and recompression shock frequency spectra. For the compared configurations, experimental pressure spectra exhibit dominant Strouhal numbers at about SrD = 0.03 and 0.27 and the recompression shock oscillates at 0.2. In general, the numerical pressure and recompression shock fluctuations agree satisfactorily to the experimental results. The experiments with a blunt base reveal base-pressure spectra with dominant Strouhal numbers at 0.08 at the center position and 0.145, 0.21 − 0.22 and 0.31 − 0.33 at the outskirts of the base.

24 citations

Journal ArticleDOI
TL;DR: In this article, two rockets, one from Andoya Rocket Range, Norway and one from Esrange, Sweden, each carrying a liquid helium cooled infrared spectrometer, were simultaneously launched as part of salvo B. The launches occurred during the recovery phase of the last of four auroral magnetic events after a Joule heating criteria was exceeded.

24 citations

Patent
23 Oct 1989
TL;DR: In this article, metal filaments for use as fuel additives for rocket propellants, explosives, and other pyrotechnic devices are described, such as zirconium, niobium and titanium.
Abstract: The present invention relates to metal filaments for use as fuel additives for rocket propellants, explosives, and other pyrotechnic devices. Preferred filaments are those such as zirconium, niobium and titanium (and alloys thereof) which have very high heat of combustion.

24 citations


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