Dynamic combustion of AP composite propellents: Ignition pressure spike

K. C. Tang, M Quinn Brewster

Research output: Contribution to conferencePaper

Abstract

Nonlinear, pressurization-rate dependent combustion during initial pressurization in solid propellant rockets is simulated computationally. The "ignition" spike commonly observed in motors with small L* and usually attributed to erosive burning or igniter mass flux is simulated for a tactical motor with AP composite propellant, similar to what has been previously demonstrated for homogeneous propellant. A mechanism for bulk-mode, nonlinear limit cycle behavior (amplitude-limited oscillations) is also presented.

Original languageEnglish (US)
StatePublished - Dec 1 2001
Event37th Joint Propulsion Conference and Exhibit 2001 - Salt Lake City, UT, United States
Duration: Jul 8 2001Jul 11 2001

Other

Other37th Joint Propulsion Conference and Exhibit 2001
CountryUnited States
CitySalt Lake City, UT
Period7/8/017/11/01

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering

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  • Cite this

    Tang, K. C., & Brewster, M. Q. (2001). Dynamic combustion of AP composite propellents: Ignition pressure spike. Paper presented at 37th Joint Propulsion Conference and Exhibit 2001, Salt Lake City, UT, United States.