NDLI: Laser-heated rocket studies

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Laser-heated rocket studies

Content Provider	NASA Technical Reports Server (NTRS)
Author	Wu ,. P. K. S. Caledonia, G. E. Root, R. G. Kemp, N. H. Pirri, A. N.
Copyright Year	1976
Description	CW laser heated rocket propulsion was investigated in both the flowing core and stationary core configurations. The laser radiation considered was 10.6 micrometers, and the working gas was unseeded hydrogen. The areas investigated included initiation of a hydrogen plasma capable of absorbing laser radiation, the radiation emission properties of hot, ionized hydrogen, the flow of hot hydrogen while absorbing and radiating, the heat losses from the gas and the rocket performance. The stationary core configuration was investigated qualitatively and semi-quantitatively. It was found that the flowing core rockets can have specific impulses between 1,500 and 3,300 sec. They are small devices, whose heating zone is only a millimeter to a few centimeters long, and millimeters to centimeters in radius, for laser power levels varying from 10 to 5,000 kW, and pressure levels of 3 to 10 atm. Heat protection of the walls is a vital necessity, though the fraction of laser power lost to the walls can be as low as 10% for larger powers, making the rockets thermally efficient.
File Size	4971315
Page Count	127
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19770007254
Archival Resource Key	ark:/13960/t6f23r63j
Language	English
Publisher Date	1976-05-01
Access Restriction	Open
Subject Keyword	Spacecraft Propulsion And Power Hydrogen Fuels Thermal Protection Hydrogen Plasma Laser Heating Plasma Propulsion Rocket Propellants Nozzle Flow Ion Propulsion Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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