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

DTSTART;TZID=Asia/Jerusalem:20260720T133000

DTEND;TZID=Asia/Jerusalem:20260720T143000

DTSTAMP:20260512T090916Z

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:Department of Aerospace Engineeri
 ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas
 sroom 240\, 1st floor\, Aerospace Eng. building\n Zoom: https://technion.z
 oom.us/j/98372598857\n Abstract: Hypergolic propellants are defined by the
 ir ability to ignite immediately upon contact\, resulting in rapid exother
 mic reactions occurring without the need for an external ignition source. 
 In hybrid rocket engines\, this spontaneous reaction simplifies thruster m
 anagement\, reduces system mass\, and enables engine re-ignition. The pres
 ent research investigates hypergolic ignition using a propellant combinati
 on of high-density polyethylene (HDPE) fuel embedded with sodium borohydri
 de (SBH) additive\, with rocket-grade hydrogen peroxide (RGHP) as the oxid
 izer. This HDPE-SBH-RGHP system offers a “green” propellant option\, w
 hich is a less toxic alternative to traditional\, highly hazardous hypergo
 lic propellants\, enhancing operational safety and reducing production cos
 ts. Our experimental framework utilizes spray ignition tests designed to e
 mulate the operational environment of a hybrid rocket motor. This approach
  provides foundational data on the interaction between multiple ignition p
 oints\, the dynamics of flame propagation\, and the fuel’s response to a
  continuous oxidizer supply. The primary focus is on the critical influenc
 e of pressure as a key condition governing the initiation and sustainment 
 of hypergolic reactions. The investigation confirms that the initial press
 ure and the O2/N2 ratio are the primary factors determining the ignition t
 hreshold. While success is consistent above 5 bar (with 2 bar marking a cr
 itical 50% probability)\, ignition at atmospheric pressure was only achiev
 ed by increasing the O2 concentration to 35%. Furthermore\, this high init
 ial pressure not only enables ignition but also promotes superior flame st
 ability\, resulting in more robust heat release compared to lower-pressure
  cases. Other operational configurations were also explored\, including sa
 mple exposure to humidity\, sample orientation with respect to oxidizer fl
 ow direction\, liquid accumulation on the fuel surface\, and potential for
  re-ignition. It is concluded that the reliability of ignition in hypergol
 ic solid fuels is a strong function of the initial conditions in the react
 or\, even for highly reactive propellant combinations.\n\nThis work is tow
 ards an M.Sc. degree under the supervision of Assoc. Prof. Joseph Lefkowit
 z\, The Stephen B. Klein Faculty of Aerospace Engineering\, Technion\n Det
 ails: \n 
CATEGORIES:Seminars
LOCATION:Classroom 240\, 1st floor\, Aerospace Eng. building

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