Extinguishment of a solid rocket motor by rapid depressurization after nozzle detachment

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2023-1-20

Author

Yılmaz, Rüştü Görkem

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In order to estimate the performance of a solid rocket motor with the nozzle detachment ability and to estimate the propellant extinguishment by rapid depressurization after detachment, a zero dimensional internal ballistic solver is developed, utilizing a transient burn rate model, which is to calculate the actual propellant burn rate at the rapid depressurization phase by solving the 1-D heat transfer equation within the propellant. As the detachable nozzle moves axially away from the motor by means of the ejecting force created by the chamber pressure, the solver also calculates the position of the detachable nozzle at every time instant, incrementing the effective gas discharge area of the motor, which is the cause of the rapid depressurization. For validation, static firings have been performed in which propellant extinguishment has been observed as estimated by the solver while the pressure transients calculated by the solver agreed well with the test results.

Subject Keywords

Solid rocket motor, Transient burning rate, Extinguishment, Thrust termination, Nozzle detachment

URI

https://hdl.handle.net/11511/102585

Collections

Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

R. G. Yılmaz, “Extinguishment of a solid rocket motor by rapid depressurization after nozzle detachment,” M.S. - Master of Science, Middle East Technical University, 2023.