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UID:0-394@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20180117T163000

DTEND;TZID=Asia/Jerusalem:20180117T173000

DTSTAMP:20230527T141055Z

URL:https://aerospace.technion.ac.il/events/experimental-investigation-of-
 a-hypergolic-hybrid-motor/

SUMMARY:Experimental Investigation of a Hypergolic Hybrid Motor
DESCRIPTION:Lecturer:David Andres Castaneda\n Faculty:Department of Aerospa
 ce Engineering\n Institute:Technion – Israel Institute of Technology\n L
 ocation:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n
  Abstract: \n Details: \n Hybrid rocket systems have the potential to high
  performance and wide operational capabilities\, as well as throttling and
  shutdown. An essential component in any rocket system is the ignition mec
 hanism. This can allow the motor to initiate proper burning\, as well as p
 rovide ignition - shutdown- re-ignition capabilities. Currently\, the igni
 tion of hybrid motors is generally achieved by the addition of external ga
 s or liquid systems\, or by a consumable catalytic bed (CCB)\, resulting i
 n more complex and heavy systems.\nIn the present work\, a hypergolic hybr
 id rocket motor is proposed to obtain a more efficient hybrid propulsion s
 ystem. The hypergolic ignition proposed\, i.e.\, ignition of the fuel upon
  contact with the oxidizer\, allows very short ignition delay times and sh
 utdown – re-ignition capabilities without any need of external systems t
 hat add weight\, length and complexity to the system. The hypergolic ignit
 ion is achieved by embedding a catalyst\, or promoter\, which is hypergoli
 c with the liquid oxidizer\, into the solid grain. The hypergolic reaction
  between catalyst and oxidizer is highly exothermic\, and enough\, to caus
 e the ignition and combustion of the solid fuel together with the liquid o
 xidizer. In the present work\, different catalysts and fuels were tested w
 ith high concentration hydrogen peroxide via drop-on-solid tests and radia
 l injection\, to prove the feasibility of such ignition.\nThe idea of hype
 rgolic ignition between a solid fuel and a liquid oxidizer was proven unde
 r different ambient conditions for different fuels. Average ignition delay
  times in the tests performed were always less than 10 ms\, depending on 
 the fuel and catalyst load in the solid grain.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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