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 deadline for reviewed and approved manuscripts is August 17, 2017 and all submitted manuscripts should be submitted to Meetings Manager, American Rocket Society, 500 Fifth Avenue, New York 36, N.Y.
Abstract: s should be submitted to Meetings Manager, American Rocket Society, 500 Fifth Avenue, New York 36, N.Y. They will be for- warded to the appropriate Technical Committee. Deadline date for reviewed and approved manuscripts is August 17.
66 citations
TL;DR: In this paper, a cylindrical stack of G-5 nuclear emulsions was used in the payload section of a four-stage research rocket to fly into the northern edge of the inner Van Allen belt on September 19, 1960.
Abstract: A cylindrical stack of G-5 nuclear emulsions housed in the payload section of a four-stage research rocket was flown into the northern edge of the inner Van Allen belt on September 19, 1960. The experimental design permitted, for the first time, measurements of the particle fluxes and energy spectra as functions of position along the rocket trajectory. Eight points along the trajectory have been selected for analysis. Results are presented herein for three of these points, and they are discussed in the light of various theories on the trapped radiation.
66 citations
08 Jul 2001
TL;DR: In this article, a more complete representation of the linearized motor aeroacoustics is utilized to determine the growth or decay of the system energy with rotational e ow effects accounted for already.
Abstract: Current solid-propellant rocket instability calculations (e.g., Standard Stability Prediction Program ) account only for the evolution of acoustic energy with time. However, the acoustic component represents only part of the total unsteady system energy; additional kinetic energy resides in the shear waves that naturally accompany the acousticoscillations. Becausemost solid-rocketmotor combustion chambercone gurationssupport gas oscillations parallel to the propellant grain, an acoustic representation of the e ow does not satisfy physically correct boundary conditions. It is necessary to incorporate corrections to the acoustic wave structure arising from generation of vorticity at the chamber boundaries. Modie cations of the classical acoustic stability analysis have been proposed that partially correct this defect by incorporating energy source/sink terms arising from rotational e ow effects. One of these is Culick’ s e ow-turning stability integral; related terms that are not found in the acoustic stability algorithm appear. A more complete representation of the linearized motor aeroacoustics is utilized to determine the growth or decay of the system energy with rotational e ow effects accounted for already. Signie cant changes in the motor energy gain/loss balance result; these help to explain experimental e ndings that are not accounted for in the present acoustic stability assessment methodology.
66 citations
20 Jun 1999
66 citations
TL;DR: In this paper, the authors examined existing test data, theories and procedures, frequently used for evaluating the maximum pressure in closed ended cylindrical vessels, and examined their application in the development of a solid rocket motor case, pressure vessel for a launch vehicle or a missile system.
66 citations