02602cam a2200313Ma 4500011444998MiAaHDL20141009010000.0m d cr bn ---auaua030910s1972 dcua b f000 0 eng dsdr-uiuc6403934(OCoLC)643055977EGMSTFUIUUNAS 1.14:D-6625NASA-TN-D-6625Northam, G. Burton.Effects of normal acceleration on transient burning-rate augmentation of an aluminized solid propellant /G. Burton Northam.NASA TN D-6625Washington, D.C. :National Aeronautics and Space Administration :[For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151],1972.56 p. :ill. ;27 cm.NASA technical note ;D-6625Includes bibliographical references (p. 16-17).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.Mode of access: Internet.Acceleration (Mechanics)Solid propellant rockets.Solid propellants.Langley Research Center.United States.National Aeronautics and Space Administration.01144499820101110145806.020141009010000.020141112165512.02025-01-02T19:12:33Z2025-01-02T18:30:02ZSDR-UIUCUNKNOWNloader.pl-003-020BKsdr-uiuc6403934uiugSDRUIUCuiug.30112106883058UIU6403934UIUUIUC20250102googleuiug.301121068830581972pdbibUS fed doc