MIL-M-8555C
effect of missile propulsion exhaust and eject on aircraft engine performance,
aircraft skin and structure, canopy, wing characteristics, surface controls,
etc. Missile installations adjacent to jet engines or after burners shall be
avoided if possible. Where adjacent installations are made, proper cooling,
insulation and other techniques to limit environmental temperature and other
effects shall be used.
3.8.2.2 Surface launchinq {ground or water). The missile design shall be
coordinated with the launching equipment to assure satisfactory performance
under all the conditions encountered in operational use and shall be capable
of withstanding all motions of the launcher or undercarriage in catapult
take-off and arrested landing.
3.8.3 Strength and rigidity. Strength and rigidity shall be provided in
accordance with MIL-M-8856 except as noted for composites (see 3.8.4). Weight
variations of government furnished equipment (GFE) and government responsible
changes shall not increase or decrease the design gross weight specified
herein unless specifically stated otherwise by a contractual change. In the
event of overweight of government furnished equipment, strength shall be
provided for the actual weight of the government furnished equipment. Any
weight increase incurred by providing strength for Government furnished
equipment overweight shall be considered as government responsibility and
shall be negotiated with the acquiring activity.
3.8.4 Composite. The design and construction of the composite shall be
such as to assure that fatigue loads consistent with the planned operational
employment shall not reduce structural strength and rigidity below levels
required for adequate performance during the lifetime required for the
structure. The strength and structural reliability of adhesives shall be
substantiated for the effects of static, fatigue, and vibratory loads, and
reduced and elevated temperatures.
3.8.5 Structural sandwich composites. The fabrication of sandwich
construction shall be in accordance with provisions of MIL-HDBK-23 and shall
be such as to preclude the entrance, accumulation and entrapment of water or
other contaminants within the core structure. Perforated core (metallic or
otherwise) shall not be used.
Special working provisions shall be in
3.8.6 Special working provisions.
accordance with MIL-STD-1695.
3.8.7 Watertightness. The missile shall meet the requirements for
spraytight enclosures as defined in MIL-STD-108. If necessary, blow out plugs
shall be used in rocket motors to prevent water intrusion.
3.8.8 Jettisoning or separating of parts. The missile design shall
provide that material jettisoned or separated in flight shall be kept to a
minimum in number, size, and weight. Where necessary and practicable, means
of disintegrating such parts upon their leaving the missile shall be used.
3.8.9 Physical references. Physical references shall be provided for
measuring and leveling-each missile for weighing and assembly alignment.
Structural members which are parallel to the reference planes shall preferably
be used as jig points for taking measurements. Alternatively, leveling lugs
and jig point fittings shall be provided. If such fittings are externally
located, they shall be readilY detachable, where necessary, to prevent adverse
affects on missile performance.
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