scispace - formally typeset
Search or ask a question
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.


Papers
More filters
Patent
13 Mar 1989
TL;DR: In this article, a combined air-hydrogen turbo-rocket engine is described, in which the hydrogen driven turbine is formed integrally with the rotor wheel of the axial air compressor stages.
Abstract: A combined air-hydrogen turbo-rocket engine is disclosed having a simplified construction in which the hydrogen driven turbine is formed integrally with the rotor wheel of the axial air compressor stages. The rotor stages are located downstream of a stator vane structure and are driven by gaseous hydrogen passing across the turbine blades. The hydrogen is subsequently injected into an air duct surrounding the axial air compressor and defining an airflow path having an air inlet. The hydrogen-air mixture is ignited and the burned gases are expanded through a converging-diverging exhaust nozzle.

63 citations

Journal ArticleDOI
TL;DR: In this article, the authors estimate global ozone depletion from rockets as a function of payload launch rate and relative mix of SRM and LRE rocket emissions, and propose to limit the number of kilotons per year of launch to several tens of kiloton per year, comparable to the launch requirements of proposed space planes, space solar power, and space reflectors.
Abstract: Solid rocket motors (SRMs) and liquid rocket engines (LREs) deplete the global ozone layer in various capacities. We estimate global ozone depletion from rockets as a function of payload launch rate and relative mix of SRM and LRE rocket emissions. Currently, global rocket launches deplete the ozone layer ∼0.03%, an insignificant fraction of the depletion caused by other ozone depletion substances (ODSs). As the space industry grows and ODSs fade from the stratosphere, ozone depletion from rockets could become significant. This raises the possibility of regulation of space launch systems in the name of ozone protection. Large uncertainties in our understanding of ozone loss caused by rocket engines leave open the possibility that launch systems might be limited to as little as several tens of kilotons per year, comparable to the launch requirements of proposed space systems such as spaceplanes, space solar power, and space reflectors to mitigate climate change. The potential for limitations on launch syst...

63 citations

Journal ArticleDOI
TL;DR: In this article, numerical simulations of three-dimensional flow of a gas mixture with chemical reactions over a flat thermally destructing material surface are presented, and two ways of determining the heat removal are considered, and a comparison with the analytical solution obtained within the frame of the boundary layer approximation is represented.

62 citations

Journal ArticleDOI
TL;DR: In this article, the mechanisms responsible for the separation of the nozzle from the wall are demonstrated, and the theory for a new solution of the separation location is presented, also correlated with historical rocket data, a new approximate solution, and an empirical curve e t that has been in use for 35 years.
Abstract: During the sea-level ignition process of rocket motors, the nozzle is subjected to an overexpanded e ow condition that can cause high side loads. Prediction of the symmetrical separation location is the e rst key step to a determination of the range of possible side-load magnitudes. The mechanisms responsible for causing the e ow to separate from the nozzle wall are demonstrated, and the theory for a new solution of the separation location is presented. The model is also correlated with historical rocket data, a new approximate solution, and an empirical curve e t that has been in use for 35 years. Nomenclature A = cross-sectional area of nozzle B = constant in approximate solution C = constant in Schilling curve e t CD = discharge coefe cient E = exponent in Schilling curve e t F = thrust M = Mach number P m = mass e ow rate p = pressure V = velocity ® = ratio of Mach disk area to nozzle area at separation point AMd=A3

62 citations


Network Information
Related Topics (5)
Boundary layer
64.9K papers, 1.4M citations
77% related
Nozzle
158.6K papers, 893K citations
76% related
Turbulence
112.1K papers, 2.7M citations
75% related
Solar wind
26.1K papers, 780.2K citations
75% related
Combustion
172.3K papers, 1.9M citations
75% related
Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202211
2021373
2020480
2019624
2018537
2017493