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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 article, a one-formula surrogate fuel formulation and its quasi-global combustion kinetics model are developed to support the design of injectors and thrust chambers of kerosene-fueled rocket engines.
Abstract: A one-formula surrogate fuel formulation and its quasi-global combustion kinetics model are developed to support the design of injectors and thrust chambers of kerosene-fueled rocket engines. This surrogate fuel model depicts a fuel blend that properly represents the general physical and chemical properties of kerosene. The accompanying gaseous-phase thermodynamics of the surrogate fuel is anchored with the heat of formation of kerosene and verified by comparing a series of one-dimensional rocket thrust chamber calculations. The quasi-global combustion kinetics model consists of several global steps for parent fuel decomposition, soot formation, and soot oxidation and a detailed wet-CO mechanism to complete the combustion process. The final thermophysics formulations are incorporated with a computational fluid dynamics model for prediction of the combustion efficiency of an unielement, tripropellant combustor and the radiation of a kerosene-fueled thruster plume. The model predictions agreed reasonably well with those of the tests.

118 citations

Journal Article
TL;DR: The twin benefits of cost savings and better weld properties have led Boeing to switch to friction stir welding for use on its Delta rocket programm. as discussed by the authors, which has been used for the launch of the Space Station.
Abstract: The twin benefits of cost savings and better weld properties have led Boeing to switch to friction stir welding for use on its Delta rocket programm.

114 citations

Proceedings ArticleDOI
Gordon A. Dressler1, J. Bauer1
24 Jul 2000
TL;DR: Pintle Injectors have been used extensively in the development of a variety of different types of rocket engines, such as the Pintle-Injector Engine (PIE) as discussed by the authors, which employs a series of separate propellant injection orifices distributed across the diameter of the head end of the combustion chamber.
Abstract: The pintle injector rocket engine is fundamentally different from other rocket engines, which nearly universally employ a series of separate propellant injection orifices distributed across the diameter of the headend of the combustion chamber. The pintle’s central, singular injection geometry results in a combustion chamber flowfield that varies greatly from that of conventional rocket engines. These differences result in certain operational characteristics of great benefit to rocket engine design, performance, stability, and test flexibility. The mid-1950’s origin of the pintle injector concept and the subsequent early development work and applications in rocket engines are reviewed. The pintle engine’s key design and operational features are compared to conventional rocket engines. Pintle injector design refinements and associated recent applications are discussed. The presentation includes photographs and summaries of many different rocket engines that TRW has developed and successfully flown, each of which used the pintle injector.

113 citations

01 Dec 1953
TL;DR: In this article, the closed-cycle gas-turbine power plant is described and the closed cycle gas turbine and centrifugal compressors for natural gas pipe-lines are discussed.
Abstract: Mech. Eng. 74, 234. T. R. Rhea and .. S. Quill. Gas turbine and centrifugal compressors for natural gas pipe-lines. ASME M. P. No. 52-A-157. S. T. Robinson, The closed-cycle gas-turbine-power plant. Abstract: Mech. Eng. 175, 328. P. R. Sidler, Operating experiences with stationary gas turbines. Mech. Eng. 74,

112 citations

Journal ArticleDOI
TL;DR: The present paper shows that an active debris removal mission capable of de-orbiting 35 large objects in 7 years is technically feasible, and the resulting propellant mass budget is compatible with many existing platforms.

112 citations


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