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UID:0-355@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20181128T163000

DTEND;TZID=Asia/Jerusalem:20181128T173000

DTSTAMP:20230527T135440Z

URL:https://aerospace.technion.ac.il/events/electromechanical-system-for-s
 olid-rocket-motor-thrust-modulation/

SUMMARY:Electromechanical System for Solid Rocket Motor Thrust Modulation
DESCRIPTION:Lecturer:Yossi Zamir\n Faculty:Department of Aerospace Engineer
 ing\n Institute:Technion – Israel Institute of Technology\n Location:Cla
 ssroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstract: 
 \n Details: \n The thrust of a solid rocket motor (SRM) mainly depends on 
 the combustion chamber pressure\, nozzle geometry and propellant character
 istics. The most commonly used method for a prescribed thrust profile desi
 gn relies only on propellant grain geometry. This method is limited and do
 es not comply with all the needs and requirements of rocket motors. Real t
 ime thrust modulation can significantly extend mission versatility and per
 formance of SRM based missiles. One group of methods for real time thrust 
 modulation is based on modification of the nozzle throat area\, either dir
 ectly by moving parts\, or effectively by aerodynamic means. Another group
  of methods for thrust modulation deals with modification of the propellan
 t grain burn rate by different means. Reducing the throat area\, or increa
 sing the burn rate\, increases the pressure and thrust of the motor\, and 
 vice versa.\nThis work includes a literature survey\, description of requi
 rements\, review of concepts\, design and experimentation of an electromec
 hanical system for real time thrust modulation of a SRM. The design is bas
 ed on a movable pintle against a fixed nozzle. The system is integrated wi
 th an existing generic rocket motor employing a propellant with a relative
 ly high pressure exponent (0.5). The propellant is free of metal particles
  in order to limit the maximum chamber temperature to 3000K and avoid exte
 nsive erosion and particle accumulation on critical surfaces. The system c
 omponents are thermally insulated in order to withstand the harsh conditio
 ns of the motor operation for a sufficient amount of time. The components 
 exposed to the most challenging conditions of the nozzle area are made of 
 materials such as molybdenum and tungsten. System operation and thrust mod
 ulation are demonstrated successfully.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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