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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.


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Patent
30 Sep 1982
TL;DR: In this article, a three-stage rocket vehicle with a large forward tank and a small aft tank axially aligned is described, where the propellants from the forward tank are fed into the aft tank and the rocket engines are fed from the aft to parallelize the use of engines and components.
Abstract: A three stage rocket vehicle (11) having a large forward propellant tank (12) and a small aft propellant tank (13) axially aligned. Secured to the rear end of the aft propellant tank (13) is an engine mount structure (14) carrying rocket engines (15). Offset and secured to the propellant tanks (12,13) is a payload structure (18). The propellants from the large forward tank (12) are fed into the aft propellant tank (13) and the rocket engines (15) are fed propellants from the aft propellant tank (13). This arrangement enables the vehicle to parallel stage its use of engines and components.

36 citations

Journal ArticleDOI
TL;DR: In this article, an analysis of the steady flows with axial vortices in cylindrical, nonaxisymmetric cavities generated by injection from their porous walls is presented.
Abstract: An analysis of the steady flows with axial vortices in slender, cylindrical, nonaxisymmetric cavities generated by injection from their porous walls is presented. This problem is encountered in the description of the flow in slender combustion chambers of solid-propellant rocket motors associated with the gasification of the solid propellant surrounding the combustion chamber. Nonreacting flow can be described in terms of self-similar solutions of the Navier-Stokes equations and the solution, calculated numerically for noncircular grain configurations, shows strong axial vortices, with a viscous vortex core that has been analyzed asymptotically for large Reynolds numbers. It was found that the important property of the flow, namely, C 1/2 S/Π, where C is a constant determining the axial pressure gradient, S and n are the cross section area and its perimeter, respectively, becomes unexpectedly close to π/2 at large Reynolds numbers, independently on the geometry of the cross section of the cavity. One can suppose that C 1/2 S/Π = π/2 for any cavities in the invicsid limit, a conjecture that also obtained a support from numerical calculations of flows in rectangular cavities generated by injection from their porous walls.

36 citations

Journal ArticleDOI
TL;DR: In this paper, a new integral technique has been developed for the purpose of analyzing combustion test data in hybrid rocket firings, which utilizes a complete reconstruction of the regression history, and is shown to have several advantages when compared with the current endpoint technique, in which average regression rate and port mass flux are determined based on fuel grain initial and final dimensions.
Abstract: A new integral technique has been developed for the purpose of analyzing combustion test data in hybrid rocket firings. The method, which utilizes a complete reconstruction of the regression history, is shown to have several advantages when compared with the current endpoint technique, in which average regression rate and port mass flux are determined based on fuel grain initial and final dimensions. One significant advantage is that the integral method permits one to ascertain the sensitivity of regression rate to changes in mass flux in a single test. Action (burning) times greater than 5 s have been found to be preferred over shorter values more typically used to date, because this minimizes errors in action time determination and permits the fuel to reach a steady-state thermal profile.

36 citations

Journal ArticleDOI
TL;DR: In this paper, a fully reusable rocket vehicle is proposed to demonstrate good operability characteristics both on the ground and in the air, making use of clustered liquid-hydrogen rocket engines.
Abstract: A fully reusable rocket vehicle is proposed to demonstrate good operability characteristics both on the ground and in e ight. For achieving technical readiness for future space transportation systems, design considerations not only for higher-performance-related issues but also those for good operability are needed. The proposed vehicle is to be used as a sounding rocket and has the capabilities of ballistic e ight, returning to the launch site, and landing vertically, making use of clustered liquid-hydrogen rocket engines. Before the development of this type of reusable rocket was initiated, a small test vehicle with a liquid-hydrogen rocket engine was built and e ight tested. A demonstration of vertical landing and exerciseof turnaround operation forrepeated e ightsare the major objectivesof the test vehicle. Two e ightswere performed in succession, and the e ight-test operation provided many valuable experiences for designing the fully reusable rocket vehicle.

36 citations

Journal ArticleDOI
TL;DR: In this paper, a combustion model of boron particles for detailed Computational Fluid Dynamics (CFD) based simulations of ducted rocket combustion chambers is studied, which includes all main physical processes required to define an accurate particle combustion simulation.

36 citations


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