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 Jan 1971
TL;DR: Open cycle gas core nuclear rocket engine, considering reactor critical experiments and cold and hot flow tests as discussed by the authors, considering both nuclear critical and cold flow tests, has been proposed for the first time.
Abstract: Open cycle gas core nuclear rocket engine, considering reactor critical experiments and cold and hot flow tests
28 citations
TL;DR: In this article, a comparison of the numerical predictions of several groups modeling the reacting flow inside a gaseous methane/gaseous oxygen single-element rocket combustion chamber is conducted.
Abstract: A comparison of the numerical predictions of several groups modeling the reacting flow inside a gaseous methane/gaseous oxygen single-element rocket combustion chamber is conducted. The focus is pl...
28 citations
Patent•
14 Apr 1980TL;DR: In this paper, a rear cover for rocket launch tubes providing a seal between the tube and the rear of the rocket is presented. But the rear cover is not designed to cover the entire tube.
Abstract: A rear cover for rocket launch tubes providing a seal between the tube and the rear of the rocket. The rocket is arranged in a manner such that the exhaust of a firing rocket will produce a seal between a sealing member and the rear of the rocket and will seal off the portion of the tube adjacent to the rocket itself, thus preventing exhaust gases from entering this portion of the launch tube.
28 citations
01 Jan 1982
TL;DR: In this paper, a comprehensive model of nonlinear longitudinal combustion instability in solid rocket motors has been developed, and the two primary elements of this stability analysis are a finite difference solution of the two-phase flow in the combustion chamber and a coupled solution of a nonlinear transient propellant burning rate.
Abstract: A comprehensive model of nonlinear longitudinal combustion instability in solid rocket motors has been developed. The two primary elements of this stability analysis are a finite difference solution of the two-phase flow in the combustion chamber and a coupled solution of the nonlinear transient propellant burning rate. Although quasi-one dimensional, the model has been generalized to treat realistic variable cross-section and partial length grains. An excellent finite difference shock capturing technique—a combination of the Lax-Wendroff, Hybrid and Artificial Compression schemes—gives the analysis the ability to treat the multiple shock-wave type of instabilities that are frequently observed in reduced smoke solid rocket motors. Ad hoc velocity coupling models were also incorporated into the analysis. Solutions are presented demonstrating that pressure oscillations in unstable solid rocket motors (with metallized as well as unmetallized propellants) reach the same limit cycle (amplitude and waveform) independent of the characteristics of the initiating disturbance. Results obtained with the velocity coupling models demonstrate the ability to analytically predict triggering, DC pressure shifts, modulated amplitude limit cycle, and strongly nonlinear waveforms; phenomena that have all been observed in actual solid rocket motor firings.
28 citations