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UID:0-517@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20150610T163000

DTEND;TZID=Asia/Jerusalem:20150610T173000

DTSTAMP:20230603T192803Z

URL:https://aerospace.technion.ac.il/events/the-effect-of-energetic-ingred
 ients-on-the-burning-rate-of-solid-propellants/

SUMMARY:The Effect of Energetic Ingredients on the Burning Rate of Solid Pr
 opellants
DESCRIPTION:Lecturer:Hagit Greenfeld\n Faculty:Department of Aerospace Engi
 neering\n Institute:Technion – Israel Institute of Technology\n Location
 :Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstra
 ct: \n Details: \n The burning rate of a solid propellant is a fundamental
  characteristic\, which is measured for every propellant composition that 
 is aimed to be used in a rocket motor. The burning rate measuring procedur
 e in the lab requires mixing of all propellant ingredients\, casting of th
 e material into moulds\, hot curing of the material\, extracting strand sa
 mples and burning of many samples at various pressures. This procedure is 
 long and requires significant resources\, thus the motivation for developi
 ng a theoretical model\, able to predict the burning rate of a given compo
 sition is obvious.\n A solid propellant is a mixture of a polymeric binde
 r that contains a hydrocarbon fuel\, plasticizer\, surface agents\, cross 
 linking agents etc. together with crystalline oxidizer particles in two or
  three size groups. The combustion of such a mixture is very complex and i
 s affected by several combustion mechanisms and by different type of flame
 s.  The combustion mechanism depends on the pressure\, the amount of oxid
 izer particles and their size distribution. The heat transfer from the fla
 me plane to the propellant surface determines the propellant burning rate.
 \nThe well-known\, BDP model\, developed by three investigators\, Beckstea
 d\, Derr and Price\, is an analytical model that presents a set of equatio
 ns with a closed solution that provides the burning rate of a given compos
 ition as a function on pressure.\nIn the frame of the present work\, the B
 DP model was implemented in a computer code developed in Rafael. A compari
 son of the prediction to experimental data reported in literature and self
  preformed experimental data was conducted. In the second stage\, a model 
 correction was proposed in order to improve the prediction for low burning
  rate propellants.\nIn the experimental part of the research 14 "reduced s
 moke" propellant compositions were tested and about 100 experiments were c
 onducted at various pressures. The revised model that was developed in the
  present study shows a very good agreement with the tested propellants.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20150327T030000

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