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UID:0-392@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20180129T163000

DTEND;TZID=Asia/Jerusalem:20180129T173000

DTSTAMP:20230527T141017Z

URL:https://aerospace.technion.ac.il/events/investigation-of-the-burning-r
 ate-of-solid-propellants-composed-of-nano-aluminum-and-water/

SUMMARY:Investigation of the Burning Rate of Solid Propellants Composed of 
 Nano-Aluminum and Water
DESCRIPTION:Lecturer:Shahar Wollmark\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 Solid propellants comprised of aluminum and water show 
 high theoretical energetic performance and are considered environmentally 
 friendly\, since the burning products contain non-toxic and carbon-free ma
 terials (aluminum oxide – Al2O3\, and hydrogen gas – H2). These prope
 llants may be attractive for different types of propulsion systems (for ex
 ample: in-space\, under-water)\, and could also be used in other applicati
 ons\, such as hydrogen production\, power generation etc. Thermochemical a
 nalysis shows that stoichiometric combustion of aluminum-water propellant 
 can yield high performance parameters that exceed those of the highly toxi
 c hydrazine at similar conditions\, and are on par with commonly used soli
 d propellants (AP/HTPB\, NG/NC and others).\nIn the present research\, sol
 id propellants containing distilled water and different nano‑aluminum po
 wders were filled into consumable strands\, and ignited inside a pressure 
 chamber for burning rate measurements at pressures up to 70 bar. Three typ
 es of nano aluminum powders were tested: ALEX – uncoated particles\; V
 ‑ALEX – Viton coated particles\; and L‑ALEX – stearic acid coated 
 particles. All tested compositions presented burning rates similar to thos
 e of conventional solid propellants\, and the obtained pressure exponents 
 suggest that the combustion of aluminum-water solid propellants will be st
 able during pressure fluctuations. In addition to burning rate experiments
 \, selected compositions were tested inside a small rocket motor where the
  operating pressure and the developed thrust were measured\, to receive th
 e key performance parameters of the propellant.\nThe entire process of the
  research will be covered in the presentation: starting from the powder an
 alysis using TEM/TGA techniques\; followed by the preparation process of t
 he different propellant mixtures\; description of the experimental setup c
 onstructed for the burning rate measurements and the static firing experim
 ents\; and the results obtained including the performance parameters for t
 he different propellant compositions.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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