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MIL-T-18232B(AS]
3.3.2.2
(cont)
The design ultimate factor of safety, by which the limit loads resulting from
the above conditions are multiplied to obtain ultimate loads, shall be 1.25.
3.3.2.2.1
MALFUNCTION. - For air launched targets, ultimate strength
shall be provided to preclude breakup in way of the launching
aircraft in the event of a functional failure of any part of the target.
3.3.2.3
CAPTIVE FLIGHT CONDITIONS. - For captive flight loads, Speci-
fication MIL-A-8591 shall apply. The limit speeds for captive
flight shall be as required by the detail specification. The design ultimate
factor of safety shall be 1.5.
3.3.2.4
LAUNCHING LOADS* - For booster launches, a forward acting
load equal to two times the rated thrust of the booster shall
act separately and in combination with inertial loads. Inertial loads shall be
based on the weight of the fully loaded booster unit(s). The loads shall include
side loads due to misalignment and orthogonal components due to use of canted
nozzles. For catapult launches, the limit loads shall be based on the peak
accelerations deliverable by the catapult. The ultimate factor of safety shall
be 1.5.
3.3.2.5
HANDLING LOADS, - The limit load factor for hoisting shall be
2.67. For shipping by rail or truck, the maximum horizontal
load factor shall be + 7.0. The ultimate factor of safety shall be 1.5.
3.3.2.6
PROPERTIES OF MATERIAL. - Handbook MIL-HDBK-5 shall be used
for determination of material properties of structural elements.
MASS BALANCE OF CONTROL SURFACES. - Flutter safety substantia-
3.3.3
tion of the vehicle shall be consistent with the applicable
requirements of Specification MIL-A-8870(ASG).
3.4
WING GROUP
3.4.1
DESCRIPTION. - The wing group includes wings, ailerons, slats,
tabs, spoilers and high-drag and high-life devices.
3.4.2
CONSTRUCTION. - Separable center sections are preferred to
integral center sections to facilitate overhaul and repair.
26

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