Accession Number:

AD0861814

Title:

Evaluation of Rocket Nozzle Passive Temperature Indicators (Test Nozzle No. 2).

Descriptive Note:

Technical rept.,

Corporate Author:

AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA

Personal Author(s):

• Ellison, John R.
• Binder, Harold I.

Report Date:

1969-09-01

Pagination or Media Count:

60.0

Abstract:

The objective of this test was to demonstrate a technique for measuring subsurface nozzle material temperatures beyond the range of conventional thermocouples. The objective was achieved by designing and fabricating a 2.3-inch-throat-diameter solid rocket nozzle and instrumenting it with high-temperature indicators, the evaluation and selection of propellant ballistic properties to obtain 6500 degrees F flame temperature, 810-psig maximum chamber pressure, 21.9-sec effective firing duration, and posttest evaluation of the rocket nozzle including X-ray analysis and sectioning. Author

Descriptors:

• (*SOLID PROPELLANT ROCKET ENGINES
• ROCKET NOZZLES)
• (*TEMPERATURE SENSITIVE ELEMENTS
• REFRACTORY METALS)
• (*ROCKET NOZZLES
• CAPTIVE TESTS)
• TEST FACILITIES
• ROCKET PROPELLANT GRAINS
• NOZZLE THROATS
• NOZZLE AREA RATIO
• FLAMES
• TEMPERATURE
• EROSIVE BURNING

Subject Categories:

• Test Facilities, Equipment and Methods
• Rocket Engines
• Solid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE