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Altitude Qualification Test of the Aerojet SVM-6 Solid Propellant Rocket Motor

The Aerojet SVM-6 solid-propellant rocket motor was designed to provide the orbit 
insertion thrust for the 1,530-1bm NATO Ill Satellite System. The SVM-6 Qualification 
Test Requirements (Ref. l) include the firing of three motors at simulated altitude 
conditions to ensure that the motors conform to the specifications outlined in Ref. 2. 
The results of the initial qualification firing for motor SIN Q-l are contained in 
Refs. 3 and 4. The results of the second and third qualification firing are reported herein. 
Ihe motors were preconditioned to temperatures of I IOOF' (SIN Q2) and IOOF (SIN Q3) 
and successfully fired at an ignition pressure altitude in exccss of 100,000 ft while spinning 
at 110 rpm. 
Motor altitude ballistic performance , altitude ignition characteristics, temperature-time 
history, component structural integrity, and the lateral (nonaxial) thrust data are presented 
and, where applicable, compared with the motor specification requirements (Ref. 2).

2.1 TEST ARTICLE 
The Aerojet SVM-6 solid-propellant rocket motor (Fig. l) is a full-scale, flightweight 
motor with an overall length of 54 in. and diameter of 30 in. The loaded motor weight 
is nominally 800 lbm, of which 710 lbm is propellant. 
The chamber assembly consists of a glass-filament-wound pressure vessel with an 
integral aluminum attachment ring and aluminum polar bosses to which the igniter and 
nozzle are bolted. The chamber assembly is internally insulated with molded silica-filled 
Buna-N rubber. 
The case-bonded propellant grain consists of a thermally cured polybutadiene 
propellant designated ANB-3066. The internal grain configuration consists of an upstream 
cylindrical bore which diverges conically in the aft chamber. 
The contoured nozzle assembly has a nominal throat area of 6.3 in.2 and a 53:1 
expansion ratio. The throat insert is fabricated from silver-infiltrated tungsten to minimize 
erosion. 
The igniter assembly is installed in the forward dome polar boss and uses 
boron-potassium-nitrate pellets as the pyrotechnic charge. The primary charge consists of 
10 gm of pellets, and the main charge contains 210 gm of pellets. The igniter incorporates 
a safe-arm-device which provides the first element of the ignition train; two independently 
activated US Flare squibs are energized with 4.3 to 10.0 amp of direct current.