Accession Number:

AD0460198

Title:

RESULTS OF TESTING UTC XSR 57-UT-1 SOLID-PROPELLANT ROCKET MOTORS UNDER THE COMBINED EFFECTS OF SIMULATED ALTITUDE AND ROTATIONAL SPIN (PRELIMINARY FLIGHT RATING TEST)

Descriptive Note:

Technical rept.

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• White, D. W.

Report Date:

1965-03-01

Pagination or Media Count:

56.0

Abstract:

Two XSR 57-UT-1 solid-propellant rocket motors SNs 20002 and 20003 were fired at simulated altitude conditions while mounted in a spin fixture which rotated the motors about their axial centerlines at approximately 200 rpm. A third motor SN 20004 was fired in the nospin mode after having been temperature-cycled between 35 and 105 F. This firing resulted in failure in the aft dome region 2.3 sec after ignition. The major program objectives were to determine motor ballistic performance and structural integrity. Vacuum specific impulse based on the manufactuers stated propellant weight was 284.35 SN 20002 and 284.98 SN 20003 lbf-seclbm. Post-fire motor examination of motors SN 20002 and SN 20003 revealed that the uninsulated portion of each cylindrical chamber was charred, and the fiber glass filaments were essentially unbonded.

Descriptors:

• *SOLID PROPELLANT ROCKET ENGINES
• CAPTIVE TESTS
• FILAMENT WOUND CONSTRUCTION
• GLASS TEXTILES
• HIGH ALTITUDE
• IGNITION
• INSTRUMENTATION
• INTERIOR BALLISTICS
• PERFORMANCE(ENGINEERING)
• PRESSURE
• ROCKET ENGINE CASES
• ROCKET IGNITERS
• ROTATION
• SIMULATION
• SPINNING(MOTION)
• TEST EQUIPMENT
• THRUST VECTOR CONTROL SYSTEMS

Subject Categories:

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

Distribution Statement:

APPROVED FOR PUBLIC RELEASE