Evaluation of a Heat-Flux Measurement System

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Abstract:

A solid rocket nozzle instrumented with total and radiative heat-flux transducers was test-fired on the AFRPL 36-inch Char motor. The nozzle was a conventional heavyweight test configuration. The test objective was to measure the total and radiative heat-flux components incident on the nozzle ablative liners. Thermocouple instrumented plugs of ablative material comprised the total heat-flux measurement system. Plugs were placed in the entrance cap, throat, throat extension, and exit sections of the nozzle. A narrow-view angle radiometer provided radiative heat-flux measurements at the throat. A 6500 degrees F flame temperature uncured propellant was used to provide a 1061-psig maximum chamber pressure for a 54-second total firing duration. A description of the heat-flux measurement system concept, nozzle design, motor preparation, performance, and posttest analysis is included in the report.

Author(s):
Ellison, John R. ; Binder, Harold I.
Author Organization(s):
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
Descriptive Note:
Technical rept.
Pagination:
0048

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release, Document Partially Illegible
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited. Document Partially Illegible.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFRPL-TR-69-238
Contract/Grant Number(s):
F04611-68-C-0086
Project Number(s):
AF-305903AMG
Monitor Series:
AFRPL
 Subject Terms
Joint Capability Areas:
JCA_3_Force Application; JCA_3.2_Engagement; JCA_3.2.1_Kinetic Means; JCA_8_Building Partnerships; JCA_8.2_Shape; JCA_1_Force Support; JCA_5_Command and Control; JCA_1.2_Force Preparation; JCA_5.3_Planning; JCA_8.1_Communicate; JCA_1.2.3_Educating; JCA_8.2.3_Build the Capabilities and Capacities of Partners and Institutions
Communities of Interest:
Weapons Technologies
Descriptor(s):
*RADIOMETERS, *SOLID PROPELLANT ROCKET ENGINES, *NOZZLE INSERTS, HEAT FLUX, NOZZLE THROATS, PYROLYSIS, ROCKET NOZZLES, EROSIVE BURNING, RELIABILITY, TEST METHODS, DETECTORS, THERMOCOUPLES
Field(s)/Group(s):
Test Facilities, Equipment and Methods, Thermodynamics, Solid Propellant Rocket Engines
Keyword(s):
CHAR MOTORS
Report Date:
1969 Nov 01