Experimental study of the thermal erosion in a subscale solid-propellant launcher

Yeu Pin Yeh, Kenneth K. Kuo, F. Bill Cheung, Thomas A. Litzinger

Research output: Contribution to conferencePaper

Abstract

A one-sixteenth subscale solid-propellant launcher has been tested to closely simulate the highly transient pressure and the material erosion characteristics of the prototype vertical launching system (VLS). The highly transient pressure responses measured in the rocket motor were verified by the lumped-parameter approach using the fourth-order Runge-Kutta method. The transient pressure responses in other components of the launcher were similar to the behavior of the rocket motor. The two-hole and four*hole nozzles, which simulated a cluster of nozzles in the prototype VLS, were separately tested to investigate the pressure responses and material erosion affected by the nozzle configuration. A small total throat area of the nozzle resulted in a shorter firing duration and higher mass efflux issuing from the rocket motor into the plenum chamber. The erosion depth contour of an ablative material repeatedly tested indicated that the charred material with previous eroded surface contour could provide better insulation than the flat surface of a virgin material. The erosion of the ablative material mainly depends on the mass efflux from the nozzle and the structure of the ablative material.

Original languageEnglish (US)
StatePublished - Jan 1 1992
EventAIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 - Nashville, United States
Duration: Jul 6 1992Jul 8 1992

Other

OtherAIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992
CountryUnited States
CityNashville
Period7/6/927/8/92

Fingerprint

Solid propellants
Ablative materials
Erosion
Nozzles
Rocket engines
Launching
Runge Kutta methods
Insulation
Hot Temperature

All Science Journal Classification (ASJC) codes

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

Cite this

Yeh, Y. P., Kuo, K. K., Cheung, F. B., & Litzinger, T. A. (1992). Experimental study of the thermal erosion in a subscale solid-propellant launcher. Paper presented at AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992, Nashville, United States.
Yeh, Yeu Pin ; Kuo, Kenneth K. ; Cheung, F. Bill ; Litzinger, Thomas A. / Experimental study of the thermal erosion in a subscale solid-propellant launcher. Paper presented at AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992, Nashville, United States.
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Yeh, YP, Kuo, KK, Cheung, FB & Litzinger, TA 1992, 'Experimental study of the thermal erosion in a subscale solid-propellant launcher', Paper presented at AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992, Nashville, United States, 7/6/92 - 7/8/92.

Experimental study of the thermal erosion in a subscale solid-propellant launcher. / Yeh, Yeu Pin; Kuo, Kenneth K.; Cheung, F. Bill; Litzinger, Thomas A.

1992. Paper presented at AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992, Nashville, United States.

Research output: Contribution to conferencePaper

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N2 - A one-sixteenth subscale solid-propellant launcher has been tested to closely simulate the highly transient pressure and the material erosion characteristics of the prototype vertical launching system (VLS). The highly transient pressure responses measured in the rocket motor were verified by the lumped-parameter approach using the fourth-order Runge-Kutta method. The transient pressure responses in other components of the launcher were similar to the behavior of the rocket motor. The two-hole and four*hole nozzles, which simulated a cluster of nozzles in the prototype VLS, were separately tested to investigate the pressure responses and material erosion affected by the nozzle configuration. A small total throat area of the nozzle resulted in a shorter firing duration and higher mass efflux issuing from the rocket motor into the plenum chamber. The erosion depth contour of an ablative material repeatedly tested indicated that the charred material with previous eroded surface contour could provide better insulation than the flat surface of a virgin material. The erosion of the ablative material mainly depends on the mass efflux from the nozzle and the structure of the ablative material.

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Yeh YP, Kuo KK, Cheung FB, Litzinger TA. Experimental study of the thermal erosion in a subscale solid-propellant launcher. 1992. Paper presented at AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992, Nashville, United States.