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|  MIL-L-23822C(AS)
Thrust variation. Slices as specified in 4.5.4.6.1
4.5.4.6
and 4. 5.4.6.2 shall be cut through the trace of the thrust curve
taken during the test of 4, 5. 4.1 and examined to determine that
the requirements of 3.4.8 have been demonstrated.
Boost thrust slice time. The boost thrust slice
4.5.4.6.1
shall be taken at any time during an average stabilized portion
of the interval from 20 to 40 seconds after activation of the
propellant feed line cartridge operated valves. (See Figure 2).
4.5.4.6.2
Sustainer thrust slice time. The sustainer
thrust slice shall be taken at any time during an average stabiliz-
ed portion of the interval from 170 to 230 seconds after acti-
vation of the propellant feed line cartridge operated valves.
(See Figure 2). If the sustainer chamber thrust varies more
than 5% in the interval from 80 to 339 seconds after activation
of the propellant feed line cartridge operated valves, or in
the interval from 80 seconds to the beginning of final decline,
whichever is less, a data slice shall be taken at maximum and
minimum sustainer thrust in the 170 to 230 second interval
and the average shall constitute the accepted reading. (See
Figure 2).
4.5.4.7
Operating range.
Temperature range.
4.5.4.7.1
Ten % of the sample rocket
engines, selected in accordance with 4.3.2, shall undergo the
test of 4.5.4.1 when fired at a stabilized temperature of -65 F
3 F. Ten % of the sample rocket engines, selected in accord-
ance with 4.3.2, shall undergo the test of 4.5.4.1 when fired at
a stabilized temperature of +140 F 3 F. The propellants
shall be stabilized at the same temperature that the rocket engine
has been stabilized. The rocket engines shall fire at both temp-
eratures and the propellant shall sustain burning until the end
of the firing run as calculated for the specific temperature of
firing.
4.5.4.7.2
Altitude range. Data resulting from the tests of
4.5.4.1 shall be extrapolated theoretically to the design altitude
20
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