Ignition of composite propellants in a stagnation region under rapid pressure loading

M. Kumar, J. E. Wills, Anil Kamalakant Kulkarni, K. K. Kuo

Research output: Contribution to journalArticle

5 Citations (Scopus)

Abstract

Ignition of AP-based composite solid propellants located at the tip of an inert crack wasinvestigated both experimentally and theoretically. The ignition process was observed by simultaneously using a high-speed (≈40,000 pictures/s) camera and a fast-response photodiode system. Heat flux to the propellant surface was measured with a thin-film heat-flux gage. Effects of pressurization rate, crack-gap width, and igniter flame temperature on the ignition process were studied experimentally. Experimental results indicate that the ignition-delay time decreases and the heat flux to the propellant surface increases as the pressurization rate is increased. Results of the theoretical analysis which employed separate solid-phase energy equations for fuel and oxidizer and the measured heat flux to the propellant surface are in good agreement with experimental data. The decrease in ignition delay with increasing pressurization rate is caused by enhanced heat feedback to the propellant surface at higher pressurization rates. This augmentation in heat feedback to the propellant at higher pressurization is believed to be a result of a combination of the following mechanisms: heating due to compression-wave reflection at the closed end; heat release due to burning of unreacted igniter species near the tip, behind the compression wave; and enhanced heat transfer due to recirculating hot gases near the tip.

Original languageEnglish (US)
Pages (from-to)757-767
Number of pages11
JournalSymposium (International) on Combustion
Volume19
Issue number1
DOIs
StatePublished - Jan 1 1982

Fingerprint

composite propellants
Composite propellants
Pressurization
stagnation point
propellants
Propellants
ignition
Ignition
Heat flux
heat flux
igniters
compression waves
heat
cracks
Cracks
Feedback
solid propellants
flame temperature
Solid propellants
wave reflection

All Science Journal Classification (ASJC) codes

  • Chemical Engineering(all)
  • Fuel Technology
  • Energy Engineering and Power Technology
  • Mechanical Engineering
  • Physical and Theoretical Chemistry
  • Fluid Flow and Transfer Processes

Cite this

@article{dea6029fe91241a3a55b107ad26603e1,
title = "Ignition of composite propellants in a stagnation region under rapid pressure loading",
abstract = "Ignition of AP-based composite solid propellants located at the tip of an inert crack wasinvestigated both experimentally and theoretically. The ignition process was observed by simultaneously using a high-speed (≈40,000 pictures/s) camera and a fast-response photodiode system. Heat flux to the propellant surface was measured with a thin-film heat-flux gage. Effects of pressurization rate, crack-gap width, and igniter flame temperature on the ignition process were studied experimentally. Experimental results indicate that the ignition-delay time decreases and the heat flux to the propellant surface increases as the pressurization rate is increased. Results of the theoretical analysis which employed separate solid-phase energy equations for fuel and oxidizer and the measured heat flux to the propellant surface are in good agreement with experimental data. The decrease in ignition delay with increasing pressurization rate is caused by enhanced heat feedback to the propellant surface at higher pressurization rates. This augmentation in heat feedback to the propellant at higher pressurization is believed to be a result of a combination of the following mechanisms: heating due to compression-wave reflection at the closed end; heat release due to burning of unreacted igniter species near the tip, behind the compression wave; and enhanced heat transfer due to recirculating hot gases near the tip.",
author = "M. Kumar and Wills, {J. E.} and Kulkarni, {Anil Kamalakant} and Kuo, {K. K.}",
year = "1982",
month = "1",
day = "1",
doi = "10.1016/S0082-0784(82)80251-8",
language = "English (US)",
volume = "19",
pages = "757--767",
journal = "Proceedings of the Combustion Institute",
issn = "1540-7489",
publisher = "Elsevier Limited",
number = "1",

}

Ignition of composite propellants in a stagnation region under rapid pressure loading. / Kumar, M.; Wills, J. E.; Kulkarni, Anil Kamalakant; Kuo, K. K.

In: Symposium (International) on Combustion, Vol. 19, No. 1, 01.01.1982, p. 757-767.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Ignition of composite propellants in a stagnation region under rapid pressure loading

AU - Kumar, M.

AU - Wills, J. E.

AU - Kulkarni, Anil Kamalakant

AU - Kuo, K. K.

PY - 1982/1/1

Y1 - 1982/1/1

N2 - Ignition of AP-based composite solid propellants located at the tip of an inert crack wasinvestigated both experimentally and theoretically. The ignition process was observed by simultaneously using a high-speed (≈40,000 pictures/s) camera and a fast-response photodiode system. Heat flux to the propellant surface was measured with a thin-film heat-flux gage. Effects of pressurization rate, crack-gap width, and igniter flame temperature on the ignition process were studied experimentally. Experimental results indicate that the ignition-delay time decreases and the heat flux to the propellant surface increases as the pressurization rate is increased. Results of the theoretical analysis which employed separate solid-phase energy equations for fuel and oxidizer and the measured heat flux to the propellant surface are in good agreement with experimental data. The decrease in ignition delay with increasing pressurization rate is caused by enhanced heat feedback to the propellant surface at higher pressurization rates. This augmentation in heat feedback to the propellant at higher pressurization is believed to be a result of a combination of the following mechanisms: heating due to compression-wave reflection at the closed end; heat release due to burning of unreacted igniter species near the tip, behind the compression wave; and enhanced heat transfer due to recirculating hot gases near the tip.

AB - Ignition of AP-based composite solid propellants located at the tip of an inert crack wasinvestigated both experimentally and theoretically. The ignition process was observed by simultaneously using a high-speed (≈40,000 pictures/s) camera and a fast-response photodiode system. Heat flux to the propellant surface was measured with a thin-film heat-flux gage. Effects of pressurization rate, crack-gap width, and igniter flame temperature on the ignition process were studied experimentally. Experimental results indicate that the ignition-delay time decreases and the heat flux to the propellant surface increases as the pressurization rate is increased. Results of the theoretical analysis which employed separate solid-phase energy equations for fuel and oxidizer and the measured heat flux to the propellant surface are in good agreement with experimental data. The decrease in ignition delay with increasing pressurization rate is caused by enhanced heat feedback to the propellant surface at higher pressurization rates. This augmentation in heat feedback to the propellant at higher pressurization is believed to be a result of a combination of the following mechanisms: heating due to compression-wave reflection at the closed end; heat release due to burning of unreacted igniter species near the tip, behind the compression wave; and enhanced heat transfer due to recirculating hot gases near the tip.

UR - http://www.scopus.com/inward/record.url?scp=0020278408&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0020278408&partnerID=8YFLogxK

U2 - 10.1016/S0082-0784(82)80251-8

DO - 10.1016/S0082-0784(82)80251-8

M3 - Article

VL - 19

SP - 757

EP - 767

JO - Proceedings of the Combustion Institute

JF - Proceedings of the Combustion Institute

SN - 1540-7489

IS - 1

ER -