A Thermal Protected Rocket Launcher, referred to herein as the launcher.

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MIL-L-85590(AS)

3.3 Characteristics.

3.3.1

Performanceo

3.3.1.1 Insulation resistance. The insulation resistance of the wiring

harness after installation in the launcher shall be not less than 20 megohms

(Mohms) at 500 +10 Volts direct current (Vdc) from conductor to conductor

and conductor to ground.

3.3.1.2 Continuity. The continuity resistance of the MK 40 firing circuit

The

after installation in the launcher shall be not greater than 0.3 ohm.

continuit;f resistance of the MK 66 firing circuit after installation in the

Continuity resistance of any

launcher shall be not greater than 0.1 ohm.

ground circuit shall be not greater than 0.1 ohm.

3.3.1.3 Rocket loading. The launcher shall require not greater than 20

pounds push or pull force exerted on the plug gage. The firing contact shall

make sufficient contact with the surface of the rocket igniter contact to

transmit a pulse which shall fire a rocket.

3.3.1.4 Detent pull. The detent shall not release before 400 +50, -0

pounds pull force is reached.

3.3.2 Functional.

With 22.0 +1.0, -0.0 Vdc applied to pin A of J1

3.3.2.1 Static firing.

or J2 (pin E grounded), the launcher shall ignite all functional rockets,

remain intact on the suspension device, and sustain no damage other than

darkening of the exposed surfaces. Upon completion of the static firing

test, the launcher shall meet the requirements of 3.3.1.1, 3.3.1.2, 3.3.1.3,

and 3.3.1.4.

3.3.2.2 Flight firing. During flight firing, the launcher shall ignite

all functional rockets, remain intact on the aircraft rack, and sustain no

damage other than darkening of the exposed surfaces. Upon completion of the

flight firing test, the launcher shall show no evidence of damage or defects,

and shall meet the requirements of 3.3.1.1, 3.3.~.2, 3.3.1.3, and 3.3.1.4.

3.4 Environmental conditions. The launcher shall not be damaged, nor

shall subsequent performance be degraded, by exposure to any natural combina-

tion of service-use environments. These shall include, but shall not be

limited to, the following environments.

3.4.1 Temperature shock. The launcher shall perform as specified in

3.3.1.3, 3.3.1.2, 3.3.1.3, and 3.3.1.4 after exposure to the temperature shock

test of 4.6.2.1.