ATK-Motor-Catalog-2012

PRESSURE, psia
ASAS 21-85V
TE-M-1031-1
MOTOR DIMENSIONS
Motor diameter, in. ............................................... 20.4
Motor length, in. ................................................... 95.5
MOTOR PERFORMANCE (75°F SEA LEVEL)
Burn time/action time, sec ........................... 24.4/25.7
Ignition delay time, sec ...................................... 0.012
Burn time average chamber pressure, psia ....... 1,100
Maximum chamber pressure, psia..................... 1,350
Total impulse, lbf-sec ..................................... 347,400
Propellant specific impulse, lbf-sec/lbm ............. 240.6
Burn time average thrust, lbf............................ 14,000
Maximum thrust, lbf ......................................... 17,250
NOZZLE
Initial throat diameter, in. ....................................... 3.1
Exit diameter, in. .................................................. 11.6
Expansion ratio, initial ....................................... 13.9:1
TVC, deg ............................................................. ±4.5
The ASAS 21-85V is a solid rocket motor with a graphite-composite
case that was developed for sounding rockets and highperformance
guided booster applications. The initial 21-inch motor
static test was conducted to demonstrate application and scaling of
ASAS technology to vertical launch system-compatible large
booster designs in April 1998. The design incorporated a 4.5-
degree thrust vector control nozzle and a low-temperature capable
propellant.
Early test efforts led to a June 1999 test for the Air Force Research
Laboratory that incorporated a fixed nozzle (blast tube)
arrangement to evaluate the use of low-cost materials and design
concepts. The ASAS II version of the motor also incorporated a
new propellant (TP-H-3516A) with 20% aluminum, 88.5% total
solids, and 1% plasticizer.
WEIGHTS, LBM
Total loaded ....................................................... 1,656
Propellant ........................................................... 1,444
Case assembly ..................................................... 129
Nozzle assembly ..................................................... 33
Total inert .............................................................. 212
Propellant mass fraction ...................................... 0.87
TEMPERATURE LIMITS
Operation ..................................................-10°-130°F
Storage .....................................................-20°-130°F
PROPELLANT DESIGNATION ....... TP-H-3514A
CASE MATERIAL ..........Graphite-epoxy composite
PRODUCTION STATUS .................. Development
1800
V1098073F [413]
18000
1600
1400
F
16000
14000
1200
12000
1000
800
P
10000
8000
THRUST, lb f
600
6000
400
4000
200
2000
0
0
0
5 10 15 20 25 30
TIME, sec
Approved for Public Release
OSR No. 12-S-1902;
Dated 07 August 2012
122