NDLI: Effects of normal acceleration on transient burning rate augmentation of an aluminized solid propellant

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Effects of normal acceleration on transient burning rate augmentation of an aluminized solid propellant

Content Provider	NASA Technical Reports Server (NTRS)
Author	Northam, G. B.
Copyright Year	1972
Description	Instantaneous burning rate data for a polybutadiene acrylic acid propellant, containing 16 weight percent aluminum, were calculated from the pressure histories of a test motor with 96.77 sq cm of burning area and a 5.08-cm-thick propellant web. Additional acceleration tests were conducted with reduced propellant web thicknesses of 3.81, 2.54, and 1.27 cm. The metallic residue collected from the various web thickness tests was characterized by weight and shape and correlated with the instantaneous burning rate measurements. Rapid depressurization extinction tests were conducted in order that surface pitting characteristics due to localized increased burning rate could be correlated with the residue analysis and the instantaneous burning rate data. The acceleration-induced burning rate augmentation was strongly dependent on propellant distance burned, or burning time, and thus was transient in nature. The results from the extinction tests and the residue analyses indicate that the transient rate augmentation was highly dependent on local enhancement of the combustion zone heat feedback to the surface by the growth of molten residue particles on or just above the burning surface. The size, shape, and number density of molten residue particles, rather than the total residue weight, determined the acceleration-induced burning rate augmentation.
File Size	2299978
Page Count	59
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19720013273
Archival Resource Key	ark:/13960/t3nw4780g
Language	English
Publisher Date	1972-04-01
Access Restriction	Open
Subject Keyword	Thermodynamics And Combustion Residues Aluminum Solid Rocket Propellants Acrylic Acid Acceleration Physics Polybutadiene Spin Stabilization Pressure Burning Rate 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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