MIL-DTL-82945B (OS)
3.3.1.2 Catapult grain. The catapult grain shall be loaded within 180 days of the oldest catapult
propellant mix.
3.3.2 Other explosive components. The other explosive components are the percussion primer (Drawing
8799925), the BKNO3 pellets (MIL-P-46994, Type II-A), and the BKNO3 granules (MIL-P-46944, Type
VII, 40/140 granulation).
3.3.2.1 Percussion primers. The percussion primers shall be loaded within 24 months of manufacture
and certification or within 12 months of recertification. Loaded is defined as when the external igniter
assembly (Drawing 513-174-0123) is complete.
3.3.2.2 BKNO3 pellets and granules. The BKNO3 pellets and granules shall be loaded into the rocket
motor igniter (Drawing 513-174-0107) within 12 months of the certification date. Loaded is defined as
when the rocket motor igniter is complete. The BKNO3 pellets and granules shall be loaded into the
cartridge case assembly (Drawing 513-174-0119) within 12 months of the certification date. Loaded is
defined as when the cartridge case assembly is crimped.
3.3.2.3 External igniter assembly and rocket motor igniter assembly. The external igniter assembly
(Drawing 513-174-0123) and the rocket motor igniter (Drawing 513-174-0107) shall be loaded into the
rocket catapult within 6 months of their completion. Loaded is defined as when the rocket catapult lot is
released for lot acceptance testing.
3.4 Performance and product characteristics. The rocket catapults shall meet the following
performance and product characteristics when test fired at -65F, 70F, and 165F using an ejected weight
of 347 ± 1 pounds.
3.4.1 Ballistics. The rocket catapults shall meet the ballistic performance parameters specified in table I.
3.4.1.1 Ballistic Definitions. See figure 1 for a graphical representation of some of the definitions given
below.
3.4.1.1.1 Rocket motor resultant impulse. The rocket motor resultant impulse is obtained by integrating
the resultant thrust of the rocket motor over the action time.
3.4.1.1.2 Rocket motor action time. Action time is determined from the normal thrust-time curve, and is
defined as the time interval from the 10 percent of maximum thrust on the initial rise of curve to the
corresponding 10 percent of thrust on the declining portion of the curve.
3.4.1.1.3 Rocket motor resultant thrust. The rocket motor resultant thrust is obtained by vectorially
adding the two maximum components of rocket thrust that occur at one time.
3.4.1.1.4 Rocket motor ignition delay. Rocket motor ignition time is the elapsed time from separation to
10 percent of maximum thrust, as measured on the rising portion of the normal thrust-time curve.
3.4.1.1.5 Catapult ignition delay time. Catapult ignition delay time is the elapsed time from the first
indication of shearing of the firing pins until the first indication of catapult thrust.
5
For Parts Inquires submit RFQ to Parts Hangar, Inc.
© Copyright 2015 Integrated Publishing, Inc.
A Service Disabled Veteran Owned Small Business