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UID:0-296@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20200115T163000

DTEND;TZID=Asia/Jerusalem:20200115T173000

DTSTAMP:20230527T131140Z

URL:https://aerospace.technion.ac.il/events/electric-control-of-the-burnin
 g-rate-of-a-solid-propellant/

SUMMARY:Electric Control of the Burning Rate of a Solid Propellant
DESCRIPTION:Lecturer:Inna Zamir\n Faculty:Department of Aerospace Engineeri
 ng\n Institute:Technion – Israel Institute of Technology\n Location:Clas
 sroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: \
 n Details: \n Solid propellant rocket motors are simple\, easy for handlin
 g\, and ready for immediate operation. That is why they are the preferred 
 rocket motors in multiple applications and missions. However\, in practice
 \, solid propellant motor thrust cannot be controlled once the propellant 
 has been ignited. The thrust developed during operation depends on the pro
 pellant burning surface and burning rate. The burning surface may change a
 ccording to a predesigned geometry of the propellant grain\, but cannot be
  actively controlled during the propellant combustion. This research inves
 tigates the possibility of controlling the burning rate by applying electr
 ic field/voltage.\nCommon ammonium perchlorate (AP) based propellant were 
 found to be insensitive to electric field. However\, the research revealed
  that ammonium nitrate (AN) based propellants are sensitive to electric ef
 fect\, and their burning rate can be controlled by applying voltage on the
  propellant. These findings are promising for better managing the energy a
 nd maneuverability of tactical motors\, as well as for small space motors\
 , where such electric controlled solid motors may replace the traditional 
 hydrazine motors\, whose use is projected to diminish and even to be banne
 d due to the hydrazine carcinogenic and toxic properties.\nAn experimental
  system has been designed\, constructed and tested. The experiments invest
 igated the effect of voltage (up to 250V) for different values of oxidizer
  mass fraction\, strand thickness\, storage condition\, and pressure\, dem
 onstrating 3-5 fold increase of the burning rate when increasing the volta
 ge from 70 to 200V. A theoretical model showed good agreement with the exp
 eriments.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20191027T010000

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