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


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/460198.pdf


Report Date : Mar 1965


Pagination or Media Count : 56


Abstract : Two XSR 57-UT-1 solid-propellant rocket motors (S/N's 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 (S/N 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 manufactuer's stated propellant weight was 284.35 (S/N 20002) and 284.98 (S/N 20003) lbf-sec/lbm. Post-fire motor examination of motors S/N 20002 and S/N 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