Evaluation of the Thiokol TE-M-640 Solid-Propellant Rocket Motor Under the Combined Effects of Simulated Altitude and Rotational Spin

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Abstract:

Three Thiokol, Inc., TE-M-640 solid-propellant rocket motors were tested at average pressure altitudes of 100,000 ft, 111,000 ft, and 105,000 ft, respectively, while spinning about their axial centerlines at 180 rpm. Test objectives were to evaluate altitude ballistic performance and lateral nonaxial force and to demonstrate structural integrity of the motor case and nozzle. The first two motors failed 27 and 8 sec, respectively, after ignition. After modifications to the motor manufacturing procedures, the third motor was tested and performed satisfactorily. Test results for the three motors are presented and discussed herein.

Author(s):
Brooksbank, R. M.
Author Organization(s):
ARO INC ARNOLD AFS TN
Descriptive Note:
Final rept. 11 Jul 1973-30 Jul 1974
Supplementary Note:
Prepared in cooperation with ARO, Inc., Tullahoma, TN, Rept. no. ARO-ETF-TR-74-102.
Pagination:
0061

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release
Distribution Statement:
Approved For Public Release; Distribution Is Unlimited.

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AEDC-TR-74-125
Task Number(s):
5
Project Number(s):
AF-921E, ARO-RA307
Monitor Series:
TR-74-125, NASA
 Subject Terms
Joint Capability Areas:
JCA_5_Command and Control; JCA_5.3_Planning; JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means; JCA_5.3.3_Develop Strategy; JCA_5.3.4_Develop Courses of Action; JCA_5.3.5_Analyze Courses of Action
Modernization Areas:
Quantum Science and Computing
Communities of Interest:
Weapons Technologies
Descriptor(s):
*SOLID PROPELLANT ROCKET ENGINES, CASE BONDING, COMPOSITE MATERIALS, FAILURE(MECHANICS), FOURTH STAGE ENGINES, GRAPHITE, HIGH ALTITUDE, IGNITION LAG, INTERIOR BALLISTICS, LAUNCH VEHICLES, NOZZLE INSERTS, PERFORMANCE(ENGINEERING), PHENOLIC PLASTICS, ROCKET ENGINE CASES, ROCKET IGNITERS, ROCKET NOZZLES, ROCKET PROPELLANT GRAINS, SILICON DIOXIDE, SPECIFIC IMPULSE, SPINNING(MOTION), STRESSES, TEST METHODS, THRUST
Field(s)/Group(s):
Solid Propellant Rocket Engines, Solid Rocket Propellants
Keyword(s):
*TE M 640 MOTORS, SCOUT, RESEARCH ROCKETS
Report Date:
1974 Nov 01