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

DTSTART;TZID=Asia/Jerusalem:20260824T133000

DTEND;TZID=Asia/Jerusalem:20260824T143000

DTSTAMP:20260701T121950Z

URL:https://aerospace.technion.ac.il/events/seminar-saar-levi-24-8-2026/

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:Auditorium 235\, The Faculty of Aerospace Engineering\, Tech
 nion\n Zoom: https://technion.zoom.us/j/98372598857\n Abstract: Hypergolic
  propellants are defined by their ability to ignite immediately upon conta
 ct\, resulting in rapid exothermic reactions occurring without the need fo
 r an external ignition source. In hybrid rocket engines\, this spontaneous
  reaction simplifies thruster management\, reduces system mass\, and enabl
 es engine re-ignition. The present research investigates hypergolic igniti
 on using a propellant combination of high-density polyethylene (HDPE) fuel
  embedded with sodium borohydride (SBH) additive\, with rocket-grade hydro
 gen peroxide (RGHP) as the oxidizer. This HDPE-SBH-RGHP system offers a 
 “green” propellant option\, which is a less toxic alternative to tradi
 tional\, highly hazardous hypergolic propellants\, enhancing operational s
 afety and reducing production costs. Our experimental framework utilizes s
 pray ignition tests designed to emulate the operational environment of a h
 ybrid rocket motor. This approach provides foundational data on the intera
 ction between multiple 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 governin
 g the initiation and sustainment of hypergolic reactions. The investigatio
 n confirms that the initial pressure and the O2/N2 ratio are the primary f
 actors determining the ignition threshold. While success is consistent abo
 ve 5 bar (with 2 bar marking a critical 50% probability)\, ignition at atm
 ospheric pressure was only achieved by increasing the O2 concentration to 
 35%. Furthermore\, this high initial pressure not only enables ignition bu
 t also promotes superior flame stability\, resulting in more robust heat r
 elease compared to lower-pressure cases. Other operational configurations 
 were also explored\, including sample exposure to humidity\, sample orient
 ation with respect to oxidizer flow direction\, liquid accumulation on the
  fuel surface\, and potential for re-ignition. It is concluded that the re
 liability of ignition in hypergolic solid fuels is a strong function of th
 e initial conditions in the reactor\, even for highly reactive propellant 
 combinations.\n\nThis work is towards an M.Sc. degree under the supervisio
 n of Assoc. Prof. Joseph Lefkowitz\, The Stephen B. Klein Faculty of Aeros
 pace Engineering\, Technion\n Details: \n 
CATEGORIES:Seminars
LOCATION:Auditorium 235\, The Faculty of Aerospace Engineering\, Technion

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