MIL-HDBK-244A 6 apr 90.pdf

MIL-HDBK-244A
5“.1.5.2.2 Checkout and preparation. The aircraft/weapon interface
should have adequate clearance for the applicationof any checkout or special
support equipment to be used during loading or off-loading operations. The
suspension equipment, typically, requires applicationof electrical connectors
for test or release system, weapon functional control, and a
stray-voltage check prior to connections to an electroexplosivedevice.
Where cartridge fired racks are employed, access must be provided for installation
of cartridges and functioningof appropriatemechanical safety devices.
Objectively, the store should be delivered to the aircraft as an
“all-up” weapon (any store which is completely assembled, both mechanically
and electrically, and ready for installationin or on the aircraft), however, -..
access may be required to the stores when loaded to the aircraft weapon
station for’fuze installation,actuation, and visual determination of fuze
settings, igniter connections, thermal battery status, or any functional
control that must be pre-set prior to flight.
5.1.6 Aircraft structure. When designing an aircraft intended to
carry or employ stores, the designer should provide adequate strength and
rigidity for the total weapon system (aircraft,suspension equipment, and
stores) under all conditions of intended and anticipated use. Airplane
structural strength and rigidity requirementsare specified i~t41L-A-8860,
MIL-A-8861, MIL-A-8863, and MIL-A-8865 through MIL-A-8870. Helicopter structural
strength requirements are specified in MIL-S-8698 for U.S. Army-and U.S. Air
Force helicopters, and in AR-56 for U.S. Navy helicopters. .Incomplying with
these requirements, the designer should provide adequate strength for all possible
combinations of required- arriage stores and suspension equipment.under all
conditions of taxi, field take-off, rough-fieldand catapult take-offs
(if applicable), flight, field-landing,rough-field landing (inapplicable),-and
arrested landings (if applicable). Aircraft structure should be designed so
that.loadsimposed by stores are reacted with the minimuinstructure (for example,
bomb bay supporting structure should be located near storec.g. to minimize
moments.) Primary areas of concern are discussed in 5.1.6.1 through 5.1.6;3.
5.1.6.1 Carriage loads. The aircraft should have sufficient
strength for the carriage of all specified stores and suspension equipment,
in all possiblecombinations, throughout the carriage envelope of the aircraft
or the stores, whichever is more restrictive (see MIL-A-8591). Carriage
loads imposed upon the aircraft by stores or suspension equipment include
those resulting from aerodynamic and inertia conditions, asymmetric loadings
(wing, fuselage, and rack), changes in store center-of-gravity locations,
separation conditions (ejection, employment,jettison, and g-jump).
5.1.6.2 Flutter and vibration. The’total weapons system should be
flutter-free and should meet the flutter and vibration strength and rigidity
requirements of MIL-A-8870 for airplanes, (also MIL-A-87221 for U.S. Air
Force) or MIL-S-8698 for U.S. Army and U.S. Air”Force helicopters, or AR-56
for U.S. Navy helicopters. The requirementsare applicable throughout thl
entire carriage envelope. All possible combinationsof requiredcarriage
stores and suspension equipment should be investigated,or
analyzed, and critical combinations tested;.including all hung-store cond”
tions and combinations.
35
Source: http://www.assistdocs.com -- Downloaded: 2009-07-16T13:55Z
Check the source to verify that this is the current version before use.