An Evaluation of the Post-ignition Unblocking Behavior of Solid Propellant Aft-end Ignition Systems Final Report PDF Download
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 128
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 128
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 298
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Author:
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ISBN:
Category : Technology
Languages : en
Pages : 1692
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Author:
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ISBN:
Category : Science
Languages : en
Pages : 268
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Author: University of Utah. Department of Chemical Engineering
Publisher:
ISBN:
Category : Solid propellants
Languages : en
Pages :
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Author: Rex C. Mitchell
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 152
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The original objective of this project was to study the ignition of composite propellants. It was broadened to encompass the study of other combustion transients, these being, so far, subjected only to exploratory investigation.
Author: Luigi De Luca
Publisher: AIAA (American Institute of Aeronautics & Astronautics)
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 924
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Author: G. Burton Northam
Publisher:
ISBN:
Category : Acceleration (Mechanics)
Languages : en
Pages : 68
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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.
Author: Leonard H. Caveny
Publisher:
ISBN:
Category :
Languages : en
Pages : 40
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The research carried out under the grant was aimed at furthering the scientific understanding of nonsteady propellant combustion behavior in rocket motor chambers. Controlled nonsteady flow and burning conditions were produced in laboratory-scale solid rocket motors by developing a device that modulated the throat area of the primary nozzle. Modulation frequencies up to 2400 Hz were obtained. The modulated throat rocket motor is being used to acquire data using AP composite propellant grains. Cold flow tests were used to study the acoustic modes and nozzle discharge characteristics. Computerized techniques were developed for conducting spectral analyses of head-end and nozzle-end pressure data. In addition, the equations describing the nonsteady one-dimensional gas dynamics and propellant combustion were formulated, and a comprehensive numerical solution was developed. The present solution takes into account the couplings among the oscillating nozzle flow, the nonsteady chamber flow, and erosive burning. Since pressure and velocity oscillations can be made to occur and decay in high loading density rocket motors with realistic grain configurations, the experiment is expected to produce propellant/chamber response functions that are relatively easy to interpret, compared to the difficult to interpret T-burner response functions.
Author: J. B. Dawes
Publisher:
ISBN:
Category : Internal combustion engines
Languages : en
Pages :
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