Captive Flight Vibration - Captive flight tests shall include sinu-
soidal and random vibration tests. The vibration environment shall be applied
to the launcher through the normal launcher lug attachments and sway brace lo-
cations. The launcher shall be mounted on an Aero-7A Bomb Rack. Sway braces
shall be torqued to 100 inch-pounds. The control for the vibration environment
shall be from an accelerometer located on the strongback midway between the
launcher lugs. The test unit is to be in its normal attitude during the test.
The launcher shall be tested with a full load of inert rockets, with a hlaf load
(or half load PlUS one when odd numbers of rockets are carried), and with no
load. The test times shall be divided equally between the three conditions.
The launcher shall withstand, without adverse effects, all loads induced or
resulting from flight vibration frequencies without evidence of system failure
or malfunction. The test details are as follows:
126.96.36.199.2.1 Sinusoidal - The launcher, in the Flight configuration, shall be
tested in accordance with M1L-STD-81O, Method 514, Procedure I, Curve J and "
Curve M (Parts 1, 2, and 3). Test times and sweep rates are defined in time
Schedule 1, Time Table 514-11. The launcher's electrical circuits shall be
checked (3.3.7) during each condition of resonance or complex motion. The
loaded condition portion of the test shall be conducted using Inert 2.75
inch Folding Fin Aircraft Rockets having the same weight and center of gravity
as loaded rockets.
188.8.131.52.2.2 Random Vibration with Loaded Launcher - The vibration test shall
be conducted using inert 2.75 inch Folding Fin Aircraft Rockets having the
same weight and center of gravity as loaded rockets. The launcher, in the
Flight Configuration, shall be subjected to the vibration test of MIL-sTD-81O,
Procedure II, Curve AE, except the 0.02 G2/Hz level shall be maintained over
the frequency range of 10 to 2000 Hz. The electrical circuit shall be checked
in accordance with 3.3.7 during and after the vibration test.
184.108.40.206.2.3 Random Vibration, Empty - The empty launcher, in the Flight Config-
uration, shall be subjected to the vibration test of MIL-STD-81O, Procedure II,
Part 3, Curbe AH, except the 0.1 G2/Hz level shall be extended over the frequency
range of 10 to 2000 Hz. The electrical circuit shall be checked in accordance
with 3.3.7 during and after the vibration test.
Vibration Release - There shall be no evidence of detent damage, or
release of rockets from their detents when subjected to vibration in accordance
, with 220.127.116.11.
" Shock Test - The Launcher center section, Drawing Number 30003
356AS224, shall be loaded with inert 2.75" Fold Fin Aircraft Rockets of the
correct weight and CG and shall be shock tested both forward and rearward to
verify resistance to shock loads experienced during catapult take-off and
arrested landing. The applied shock load shall be 13.5g in each longitudinal
direction as measured on the bomb rack at a point midway between the hooks
(Launcher attachment points). The duration of the applied shock load shall
be 30 milliseconds minimum to one (1) second maximum. The wave form shall
approach a half sine wave. The electrical system checks (3.3.7) shall be
performed after ths shock test.
Detent Pull Test - Detent Pull Tests shall be performed on each
tube of the launcher per 18.104.22.168.1.