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|  MIL-S-18471G(AS)
APPENDIX
= 23g's
(c) Rounded GMA
UPPER
= 20g's
Rounded GMA
LOWER
(d) GMA when varied to its rounded lower limit does not
exceed the specified value at the midpoint of the 10 ms
time interval.
d.
Accelerations shall not be calculated from motion picture
data.
e. Methods of measurement and acceptable tolerance for pitch,
roll, and yaw angles to be specified in the test plan (see
3.2.2.5 and figure 5).
f. Accelerations prior to separation of the aircrewmember and
ejection seat shall be obtained from ejection seat-mounted
accelerometers. If angular motion is present, values shall be
first mathematically transferred to the seat intersect point.
g. Accelerations subsequent to separation shall be obtained from
dummy-mounted accelerometers, provided that dummy angular rates
do not exceed 1000 degrees per second. Whenever rates exceed
1000 degrees per second, then accelerations taken from a
dummy chest cavity shall be considered invalid for that
particular test ("no test" classification shall not apply).
h. Velocities and displacements shall be calculated from space
position data and not from acceleration data, except as
provided in item i.
i. For purposes of establishing compliance with the dynamic
loading limits of 3.2.2.12.1c and 3.2.2.12.2b, catapult
pressure and z axis ejection seat acceleration data, subjected
to identical filtering in accordance with either 30.3.4c or
30.3.8b, shall be used. Data processing shall consist of the
following procedure:
(1) The effects of catapult pressure shall be expressed
in suitable dimensional form using the equations:
and
where
aCAT = catapult dynamic parameter, g's
84
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