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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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Journal ArticleDOI
TL;DR: In this paper, the authors examined a multistage rocket-scramjet-rocket system for low-Earth-orbit insertion, which includes a solid rocket boost to Mach 6, a near-term Mach 6-12 hydrogen-fueled scramjet engine to propel a reusable second stage, and a liquid-fused final-stage rocket.
Abstract: Scramjet engines promise significantly higher specific impulse than rockets during the hypersonic phase of low- Earth-orbit insertion trajectories. Despite this, scramjets are not used on any current systems due to the difficulty of operating over the large Mach number envelope required by this accelerating trajectory. The key to taking advantage of airbreathing hypersonic engines for low-Earth-orbit insertion is to develop a multistage system that makes use of the scramjet only within its high-performance regime. Amultistage rocket-scramjet-rocket system that accepts this limitation has therefore been examined. This system includes a solid rocket boost to Mach 6, a near-term Mach 6–12 hydrogen-fueled scramjet engine to propel a reusable second stage, and a liquid-fueled final-stage rocket. Trajectory calculations for a system scaled to deliver approximately 100 kg to a 200 km equatorial orbit indicate payload mass fractions of approximately 1.5% with the use of a scramjet stage designed for low drag and efficient packaging. The goal of this work is to guide the future development of scramjets by identifying the areas that will make the most significant improvement to their use for space access.

91 citations

Journal ArticleDOI
TL;DR: In this paper, the erosion behavior of graphite nozzles in hybrid engines at different operating conditions and compare results with those obtained for solid motors was studied. But the main distinctive feature of hybrid engine operating conditions is a greater concentration of oxygen-containing combustion products than solid motors.
Abstract: Ablative materials are commonly used to protect the nozzle metallic housing and to provide the internal contour to expand the exhaust gases in both solid and hybrid rockets. Because of interaction with hot gas, these materials are chemically eroded during rocket firing, with a resulting nominal performance reduction. The objective of the present work is to study the erosion behavior of graphite nozzles in hybrid engines at different operating conditions and compare results with those obtained for solid motors. A main distinctive feature of hybrid engine operating conditions is, in fact, a greater concentration of oxygen-containing combustion products than solid motors. The adopted approach relies on a validated full Navier–Stokes flow solver coupled with a thermochemical ablation model that takes into account heterogeneous chemical reactions at the nozzle surface, rate of diffusion of the species through the boundary layer, ablation species injection in the boundary layer, heat conduction inside the nozzl...

91 citations

Journal ArticleDOI
TL;DR: In this paper, the characterization of several differently sized aluminium powders, by BET (specific surface), EM (electron microscopy), XRD (x-ray diffraction), and XPS (xray photoelectron spectroscopy), was performed in order to evaluate their application in solid rocket propellant compositions.
Abstract: The characterization of several differently sized aluminium powders, by BET (specific surface), EM (electron microscopy), XRD (x-ray diffraction), and XPS (x-ray photoelectron spectroscopy), was performed in order to evaluate their application in solid rocket propellant compositions. These aluminium powders were used in manufacturing several laboratory composite solid rocket propellants, based on ammonium perchlorate (AP) as oxidizer and hydroxil-terminated polybutadiene (HTPB) as binder. The reference formulation was an AP/HTPB/Al composition with 68/17/15% mass fractions respectively. The ballistic characterization of the propellants, in terms of steady burning rates, shows better performance for propellant compositions employing nano-aluminium when compared to micro-aluminium. Results obtained in the pressure range 1-70 bar show that by increasing the nano-Al mass fraction or decreasing the nano-Al size, larger steady burning rates are measured with essentially the same pressure sensitivity.

91 citations

Journal ArticleDOI
01 Jan 2014-Fuel
TL;DR: In this article, the effects of metal-based high-energy matter (Aluminum) into the content of the propellant produced within the scope of development project were investigated, and it was found that the burning rates and burning heat of new fuels manufactured by adding aluminum to the contents of the standard double base fuel (DB-1) increased.

91 citations

Journal ArticleDOI
TL;DR: In this article, the aerodynamic control and propulsion should be coordinated to realize fuel-optimal precise landing for a reusable rocket returning back to Earth, where aerodynamic forces are not negligible.
Abstract: Aerodynamic forces are not negligible for a reusable rocket returning back to Earth. How the aerodynamic controls and propulsion should be coordinated to realize fuel-optimal precise landing is add...

91 citations


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