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UID:0-305@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20200205T163000

DTEND;TZID=Asia/Jerusalem:20200205T173000

DTSTAMP:20230527T131509Z

URL:https://aerospace.technion.ac.il/events/ablative-materials-screening-f
 or-solid-rocket-motors/

SUMMARY:Ablative Materials Screening for Solid Rocket Motors
DESCRIPTION:Lecturer:Igor Sapozhnikov\n Faculty:Department of Aerospace Eng
 ineering\n Institute:Technion – Israel Institute of Technology\n Locatio
 n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr
 act: \n Details: \n The research investigates the effect of insulation fib
 er spatial orientation and aluminum content in the propellant composition\
 , on particle erosion and thermochemical ablation.\nSolid propellants exhi
 bit self-sustained\, high-temperature combustion and generate large quanti
 ties of gaseous products. Composite propellants have been extensively used
  in the last 50 years. Metals such as aluminum are added to increase densi
 ty and total heat of combustion.\nIn solid rocket motors\, charring ablati
 ve materials function as heat barriers that protect the motor case through
  the mechanism of ablation. When exposed to heat\, they undergo an endothe
 rmic decomposition process. In solid rocket motor applications\, case insu
 lations based on Ethylene Propylene Diene Monomer and Kevlar are commonly 
 used.\nIn the present research\, a subscale solid motor was used\, with an
  AP/HTPB/Aluminum based solid propellant. Seven static firing tests (six w
 ith low aluminum content and a single test with high content) were  condu
 cted successfully. The tested insulations had four different Kevlar reinfo
 rcing fibers orientations\; circumferential\, longitudinal\, diagonal and 
 random. Examination and comparison of the test results enabled to reach th
 e conclusion that the longitudinal oriented fiber model had the largest ma
 ss loss.\nA numerical model of the solid motor with the ablative insulatio
 n was incorporated. The measured values of chamber pressure and motor case
  temperature in the static firing tests served as boundary conditions. The
  convective and radiative heat flux from the gases transferred to the insu
 lation were evaluated with empirical correlations. The numerical results w
 ere compared to the experimental with low Al propellant content and exhibi
 ted slight overprediction.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20191027T010000

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