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Page Title:
Table I Engine Performance Requirements |
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|  MIL-L-238220C (AS)
TABLE I
Upon delivery of the specified impulse in paragraph 1 the booster shutoff
valve shall be used to shut down the booster chamber. The sustainer chamber
shall continue operation and shall meet the following requirements:
Sustainer chamber operating
2.
Booster #4, Sustainer #2
Orifice selection
a.
106 Ibs +l0%
Sustain thrust
b.
-5%
(Extrapolated to 70,000 ft. )
262 Ibf-see. /lbm, nominal,
Specific impulse, Isp
c.
instantaneous
0.405 lb/see. , nominal
d.
Total flow rate
3.0 nominal
Propellant weight mixture
e.
ratio (0/F)
280 sec. , m i n i m u m
Run duration
f.
28, 296 lbf-sec. /lbm + 10%
Impulse, Total
g.
*
Engine performance shall be contingent upon propellants being supplied
to the propellant flow selector valve at the following pressures:
Fuel
Oxidizer
407 psia + 3. 5%
380 psia + 3. 57%
Boost phase
1.
448 psia + 3. 5%
448 psia + 3. 5%
Sustainer phase
2.
I
Engine performance shall normally be verified by conducting
NOTE :
engine tests at the test site conditions and extrapolating the data
theoretically to specified altitudes based on atmosphere of NACA
Report No. 1235. Actual altitude tests may be conducted at the
I
discretion of the Government.
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