One Thiokol Chemical Corporation TE-M-616-01 solid-propellant rocket motor was successfully fired at an average simulated altitude of 103,000 ft while spinning at 105 rpm after being temperature conditioned at 5 plus or minus 5F for a minimum of 34 hr. In addition, the aft six inches of the nozzle exit cone was cooled to about -195F immediately prior to ignition. The program objectives were to determine vacuum ballistic performance, altitude ignition characteristics, motor temperature-time histories, structural integrity of motor components, and the lateral (nonaxial) thrust vector. The applicable data were used to demonstrate compliance of the motor with requirements set forth in Communication Research Centre Specification SS09-04. (Author)
Development Test of the Thiokol TE-M-616-01 Solid-Propellant Rocket Motor
1973
47 pages
Report
No indication
English
Rocket Engines & Motors , Rocket motors(Solid propellant) , Captive tests , Rocket cases , Solid rocket propellants , Rocket motor nozzles , Nozzle area ratio , Specific impulse , Ignition , Statistical data , Spacecraft components , Communication satellites(Active) , TE-M616-01 motors , Altitude simulation , AF
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