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|  MIL-L-23822-C(AS)
3
REQUIREMENTS
3.1
Description. The LR64 Liquid Propellant Rocket Engine,
consists of a propulsion unit, a cartridge actuated multipurpose nitrogen
valve, a cartridge actuated oxidizer valve and shear fitting, a cartridge
actuated fuel valve and shear fitting, and two nitrogen check valves.
Propulsion Unit. The propulsion unit consists of a
3.1.1
booster thrust chamber, a sustainer thrust chamber, a propellant flow
selector valve, a cartridge actuated booster shut-off valve, a thrust
mount, and miscellaneous fittings and tubing.
3.1.2
Associated Equipment. Associated with the LR64 Rocket
Engine (but not a Part of it) are a fuel tank, an oxidizer tank, a nitrogen
tank, impulse cartridges, burst diaphragms and holders, engine section
structure. air launch structure, lines, and fittings.
Operation. The LR64 Rocket Engine is prepared for flight
3.1.3
by installation of impulse cartridges in the nitrogen, oxidizer, fuel and
booster shut off valves. The nitrogen tank is charged to 3, 000 psig and
the desired engine thrust level is selected on the propellant flow selector
valve, The engine. start sequence is initiated shortly after launch by
action of the target's programmer. The nitrogen valve is opened and
the stored gas flows through the nitrogen pressure regulator to pres-
surize the propellant tanks. Upon actuation of the shear fittings in the
propellant valves, the pressurized propellants flow from the propellant
tanks through the propellant flow selector valve into the thrust chambers.
The hypergolic propellents ignite on contact. Propellant flow to the booster
thrust chamber is shut off by energizing the impulse cartridge in the
booster shut off valve as a function of missile target velocity.
Preproduction sample. Unless otherwise specified in the
3.2
contract or purhase order, each contractor who has not previously been
approved as a qualified producer of the rocket engine shall manufacture
a sample lot of 15 rocket engines (or a greater number when a design
proposed in the opinion of the Government requires a Preflight Rating Test
(PFRT) and Qualification Program) using the methods, processes and
equipment proposed for production. The preproduction engines shall meet
the requirements of 3.3.3.4 and 3.5 of this specification when tested in
4
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