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UID:0-1576@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20260720T133000

DTEND;TZID=Asia/Jerusalem:20260720T143000

DTSTAMP:20260524T092017Z

URL:https://aerospace.technion.ac.il/events/seminar-saar-levi-20july2026/

SUMMARY:COMBUSTION OF HYPERGOLIC HYBRID ROCKET FUEL IN HYDROGEN PEROXIDE SP
 RAY ENVIRONMENT
DESCRIPTION:Lecturer:Saar Levi \n Faculty:The Stephen B. Klein Faculty of A
 erospace Engineering\n Institute:Technion – Israel Institute of Technolo
 gy\n Location:Classroom 240\, 1st floor\, Aerospace Eng. building\n Zoom: 
 https://technion.zoom.us/j/98372598857\n Abstract: Hypergolic propellants 
 are defined by their ability to ignite immediately upon contact\, resultin
 g in rapid exothermic reactions occurring without the need for an external
  ignition source. In hybrid rocket engines\, this spontaneous reaction sim
 plifies thruster management\, reduces system mass\, and enables engine re-
 ignition. The present research investigates hypergolic ignition using a pr
 opellant combination of high-density polyethylene (HDPE) fuel embedded wit
 h sodium borohydride (SBH) additive\, with rocket-grade hydrogen peroxide 
 (RGHP) as the oxidizer. This HDPE-SBH-RGHP system offers a “green” pro
 pellant option\, which is a less toxic alternative to traditional\, highly
  hazardous hypergolic propellants\, enhancing operational safety and reduc
 ing production costs. Our experimental framework utilizes spray ignition t
 ests designed to emulate the operational environment of a hybrid rocket mo
 tor. This approach provides foundational data on the interaction between m
 ultiple ignition points\, the dynamics of flame propagation\, and the fuel
 ’s response to a continuous oxidizer supply. The primary focus is on the
  critical influence of pressure as a key condition governing the initiatio
 n and sustainment of hypergolic reactions. The investigation confirms that
  the initial pressure and the O2/N2 ratio are the primary factors determin
 ing the ignition threshold. While success is consistent above 5 bar (with 
 2 bar marking a critical 50% probability)\, ignition at atmospheric pressu
 re was only achieved by increasing the O2 concentration to 35%. Furthermor
 e\, this high initial pressure not only enables ignition but also promotes
  superior flame stability\, resulting in more robust heat release compared
  to lower-pressure cases. Other operational configurations were also explo
 red\, including sample exposure to humidity\, sample orientation with resp
 ect to oxidizer flow direction\, liquid accumulation on the fuel surface\,
  and potential for re-ignition. It is concluded that the reliability of ig
 nition in hypergolic solid fuels is a strong function of the initial condi
 tions in the reactor\, even for highly reactive propellant combinations.\n
 \nThis work is towards an M.Sc. degree under the supervision of Assoc. Pro
 f. Joseph Lefkowitz\, The Stephen B. Klein Faculty of Aerospace Engineerin
 g\, Technion\n Details: \n 
CATEGORIES:Seminars
LOCATION:Classroom 240\, 1st floor\, Aerospace Eng. building

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