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 published on a yearly basis
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TL;DR: In this paper, the aerodynamic principles behind the gas flow around a sounding rocket are reviewed and numerical studies are presented using the Direct Simulation Monte Carlo (DSMC) approach, which is based on a tracing of individual molecules.
Abstract: Sounding rockets are essential tools for studies of the mesosphere and lower thermosphere. However, in situ measurements from rockets are potentially subject to a number of perturbations related to the gas flow around the vehicle. This paper reviews the aerodynamic principles behind these perturbations. With respect to both data analysis and experiment design, there is a substantial need for improved understanding of aerodynamic effects. Any such analysis is complicated by the different flow regimes experienced during a rocket flight through the rarefied environment of the mesosphere and thermosphere. Numerical studies are presented using the Direct Simulation Monte Carlo (DSMC) approach, which is based on a tracing of individual molecules. Complementary experiments have been performed in a low-density wind tunnel. These experiments are crucial for the development of appropriate model parameterization. However, direct similarity between scaled wind tunnel results and arbitrary atmospheric flight conditions is usually difficult to achieve. Density, velocity, and temperature results are presented for different payload geometries and flow conditions. These illustrate a wide range of aerodynamic effects representative for rocket flights in the mesosphere and lower thermosphere.
45 citations
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TL;DR: A trade-off analysis is performed on a cooling channel system that can be of interest for rocket engines and shows the existence of an optimum channel aspect ratio that minimizes the requested pump power needed to overcome losses in the cooling circuit.
45 citations
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TL;DR: In the summer of 1959, a series of high-energy X rays accompanying three class 2+ solar flares were collected by a rocket as discussed by the authors, and the data from these flights were only partly analyzed, but many of the main conclusions can be drawn from these preliminary results.
Abstract: During the summer of 1959 rocket measurements were made of high-energy X rays accompanying three class 2+ solar flares. The rocket measurements began August 24, 1959, at 22:47 UT, August 31, 1959, at 22:53 UT, and September 1, 1959, at 17:00 UT. Four measurements were also made during times in which no flare activity occurred on the sun, but which were typical of sunspot maximum conditions. The data from these flights have been only partly analyzed, but many of the main conclusions can be drawn from these preliminary results.
45 citations
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TL;DR: A review of the history of the development of the nuclear pulse rocket can be found in this article, where the capabilities of nuclear pulse systems are examined, demonstrating the striking advantage of this system over other concepts.
Abstract: Future space exploration, and in particular rapid manned exploration, requires propulsion systems that are much more advanced than present-day systems. The paper discusses the concept of the nuclear pulse rocket and reviews some of the history of the work carried out on this concept over the last 25 years. The external system (explosion outside the vehicle) and the internal system (explosion inside the vehicle) are compared. The capabilities of nuclear pulse systems are examined, demonstrating the striking advantage of this system over other concepts. Efforts should be concentrated on a program designed to develop nuclear pulse propulsion as a tool for exploiting the solar system. Ample bibliography is included.
44 citations
07 Nov 1997
TL;DR: In this article, the authors proposed an ultra-high temperature material with temperature capabilities in the range of 2200 - 3000 deg C for liquid bi-propellant rocket engines.
Abstract: : The primary incentive for developing ultrahigh temperature materials for liquid bi-propellant rocket engines lies in the minimization and/or elimination of fuel-film and regenerative cooling of combustion chambers. Cooling is currently required because the most commonly used material for rocket combustion chambers is niobium alloy coated with disilicide with upper limit of operation up to 1450 deg C which is only approximately 50 % of the propellant combustion temperature. Therefore, by developing an ultrahigh temperature material with temperature capabilities in the range of 2200 - 3000 deg C, the fuel-film and regenerative cooling can be significantly reduced and/or eliminated resulting in cleaner burning of rocket engine. Thus fuel utilization can be vastly improved, more payload can be sent to space, higher specific impulse (Isp) can be achieved and finally the cost of the rocket engine could be reduced.
44 citations