Accession Number:

AD0328004

Title:

NOZZLE SYSTEM DEVELOPMENT FOR HYBRID PROPULSION SYSTEM (U)

Descriptive Note:

Corporate Author:

NAVAL ORDNANCE TEST STATION CHINA LAKE CA

Report Date:

1961-11-01

Pagination or Media Count:

1.0

Abstract:

Development of a hybrid propulsion concept has created the requirement for a lightweight nozzle system capable of withstanding gas temperature in excess of 6200 F with condensible soilds in excess of 25 by weight for operation longer than 30 seconds. A series of nozzle material test firings illustrated that tungsten impregnated with copper nozzle provided the best service. This led to the possibility that a transpiration effect or mass transfer cooling was being realized. A test program is now in process making use of pressure-driven liquid metal cooling through tungsten and graphite matrices subjected to a plasma-arc heat source. Tests indicate that liquid metal transpiration coolants, through a tungsten matrix coupled with nozzle inlet sacrificial materials, allow the possibility of longtime operation of a self-contained nozzle system suitable for hybrid or solid propellant rocket propulsion motors. Author

Subject Categories:

  • Metallurgy and Metallography
  • Test Facilities, Equipment and Methods
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE