[PDF] Spectral Radiance Of Model Rocket Exhaust Plumes At High Altitudes eBook

Author : Jerry Bevans
Publisher : Elsevier
Page : 876 pages
File Size : 12,84 MB
Release : 2012-12-02
Category : Science
ISBN : 0323142117

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Progress in Astronautics and Aeronautics, Volume 21: Thermal Design Principles of Spacecraft and Entry Bodies is a collection of technical papers drawn mainly from the American Institute of Aeronautics and Astronautics Third Thermophysics Specialist Conference, held in Los Angeles, California on June 24-26, 1968 This volume is divided into three parts. The first part covers some aspects of thermal processes and design, including thermal analysis, convection, radiation, ablation, and space rocket effects. The second part surveys the remote measurements of the thermophysical and thermal radiation properties and joint conductance, which are critical criteria for space thermal design. The third part focuses on the space environmental effects on thermal coatings. This part deals first with the theory of radiative degradation, followed by a presentation of the laboratory measurements. This part also looks into the results of several flight experiments. This book will be of great value to thermophysicists, space engineers, and designers who are working in the space science fields.

Author : STANLEY A. DOLIN
Publisher :
Page : 1 pages
File Size : 22,45 MB
Release : 1961
Category :
ISBN :

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To supplement laboratory studies of infrared radiance of flames, infrared spectral emittance and absorptance of the exhaust plume of a Hydrogen-Oxygen rocket engine were measured. The engine, a tenth-scale model of the Saturn-IV, was fired in an altitude test chamber, under conditions simulating altitudes from 96,000 to 145,000 feet. Exhaust gas temperatures and emissivities were determined from the infrared spectral measurements. Laboratory measurements of hydrogen-oxygen flame emissivities were extrapolated to the case of the test rocket engine. The measured results verified the extrapolation, within the range of error determined by experiment and the limitations of the extrapolation procedure. It is concluded that the results support the extrapolation from laboratory flame measurements, and that refinement of both theory and experiment are required, to improve accuracy. The tests also demonstrated the utility of the IMRA infrared technique and instrumentation for measuring gas temperatures in rocket engines. (Author).

Author : Frederick S. Simmons
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
Page : 312 pages
File Size : 14,67 MB
Release : 2000
Category : Science
ISBN :

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This new book deals with the phenomenology of rocket exhaust plumes as the targets of space-based surveillance systems. Topics include the physical and chemical processes in rocket engines and their exhaust plumes, particularly in regard to flow properties, gas dynamics, and radiative mechanisms that are responsible for the generation of emission in rocket exhaust plumes at infrared and other wavelengths. System designers in a number of defense-related areas will be able to put the information in this book to immediate use.

Author : John T. Neu
Publisher :
Page : 16 pages
File Size : 18,76 MB
Release : 1960
Category :
ISBN :

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The results of computation of the power available from a rocket plume are given. A simplified model was used which assumes the sequential occurrence of exhaust gases expansion to ambient pressure, interaction with the atmosphere, and finally dissipation of power. It is suggested that the experimentally determined drop in radiation at about 180,000 feet is probably due to a power limitation and cessation of afterburning. Power available above about 180,000 feet is due to emission phenomena occurring before the plume equilibrates (expands, etc.) with the ambient atmosphere. It is noted that no fundamental reason exists for expecting missile thrust as a function of altitude to correlate with rocket radiance. A correlation of radiance from different missiles at a given altitude vs thrust has some theoretical justification, however, propellant flow rate is suggested as a better quantity than thrust for this correlation. (Author).

Author : Larry R. Ring
Publisher :
Page : 107 pages
File Size : 17,8 MB
Release : 1973
Category :
ISBN :

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Results are presented of a study for evaluating the applicability and accuracy of rocket motor and exhaust plume gasdynamic analytical models. Evaluation of these analytical models was based upon correlation of analytical predictions with experimental data obtained in the High Altitude Plume Radiation Program. The effects of oxidizer-to-fuel ratio gradients, combustion efficiency, combustion chamber mixing, nozzle throat expansion and chemistry model were ascertained. Non-continuum effects and closed form analytical techniques were also considered. (Modified author abstract).