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| MIL-T-18232B(AS)
3.10.1
DESCRIPTION. - The propulsion system includes propulsion
units, booster units, air induction system, exhaust system,
cooling system, lubricating system, fuel system, propulsion system controls,
starting system and propeller as applicable. The choice and design of the system
shall take into consideration such factors as type or vehicle, space availability,
weight restrictions, specific fuel consumption, specific impulse, variable load
range, altitude performance, velocity, maneuverability, target accuracy, and
operating characteristics at other than optimum design conditions.
3.10.1.1
INSTALLATIONS. - The propulsion system design shall be such
as to facilitate installation and removal and/or replacement
with a minimum disturbance of fittings and connections.
BOOSTERS. - Necessary provisions shall be made for attachment
3.10.1.2
of auxiliary power plant or booster unit(s) as required. The
requirements of the integrated propulsion system shall be analyzed to assure
compatibility of the auxiliary power plant, or accelerating device, with the
operational chacteristics of the main power plant.
3.10.1.2.1
THRUST ALIGNMENT. - Target design shall prevent exceed-
ing the specified permissible thrust misalignment.
Provisions shall include means for automatic release and jettisoning of the
auxiliary units, unless otherwise specified.
3.10.1.2.2
SAFETY FEATURES. - The unit shall have easy access for installa-
tion and removal of all components, as necessary, and shall
be provided with effective, approved weather seals in the thrust chamber opening,
if required. Any solid propellant pressurizing charge, as maybe utilized, shall
be mounted in the unit to prevent damage due to adverse handling and environmental
conditions. Solid propellant pressurizing charge(s) and igniter booster charge(s),
if utilized, shall be stored and shipped as an integral part of the thrust unit.
3.10.2
PROPULSION UNIT. - Propulsion units shall be as required by
the detail specification.
3.10.2.1
RESIDUAL OIL AND GREASE. - The weight of each engine shall
include an allowance for residual oil and grease as specified
in the engine model specification.
3.10.3
Propellants - Propellants having suitable specific impulse,
density and energy release rate shall be used. These shall
be chemically stable, capable of withstanding long periods (minimum of 5 years)
of storage and or withstanding the shock and vibrations encountered in handling,
shipping, launching and flight, without any degradation in safety, reliability
or performance~
3.10.3.1
LIQUID ROCKET PROPELLANTS. - Liquid propellants selected shall
be capable of being packaged and hermetically sealed at the
contractor's facility. Appropriate structural material shall be selected to
provide compatibility between the propellants and tankage for storage periods as
approved by the procuring activity.
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