DESCRIPTION. The 8.6-cm R.Spgr L5.5 rocket has a longer motor and a smaller payload than the Spgr L/4.5. (See fig. 221.) The details of construction of the motor are similar to the Spgr L/4.5 in that the motor closure is not fixed permanently to the motor tube. A KlAZ 40 impact firing nose fuze is employed.

The propellant grain consists of two concentric cylinders of a diglycol propellant, exten-ded to different diameters than for the other grains. The length is 220 mm and the dia-meter are 66/41 and 32/71, with a total weight of 1,000 grams. The forward igniter is a 40-mm disk of incendiary material.

Propellant: Diglycol.
Nozzles: 10.
Throat diameter: 5.25.
Cant angle: 17°.
Nozzle K: 495.

Thrust: 57°.
Burning time: 0.52.
Impulse: 185.
Velocity (maximum): 300 m/sec.
Range: 4,500 m.

REMARKS. This rocket has the same design factors as shown for the 8.6 cm RLg 1000 rockets execpt for the throat diameter and uses the same type launcher.

Figure 221 – 8.6-cm R.Spgr L/5.5 Rocket