GB968639A - Rocket projectile - Google Patents

Abstract

968,639. Rocket projectiles. VERWALTUNGSGESELLSCHAFT DER WERKZEUGMASCHINENFABRIK OERLIKON-ZURICH. July 12, 1962 [July 19, 1961], No. 26862/62. Heading F3A. A rocket projectile provided with fins 11, which are deployed after the projectile leaves the launching tube 2, comprises a combustion chamber 1 containing a solid propellant 3 and closed at the rear by a member 4. Within the member 4 are four passages 5a shaped to form the upstream part of jet nozzles 5, which surround a cylindrical inwardly directed boss 6 housing a spring- loaded plunger 13. A carrier 7, held in abutment with the member 4 by a sleeve 8, supports the divergent ends of the nozzles 5 and has a bore 9 coaxial with the bore of cylinder 6. The fins 11, Fig. 3, are pivoted on pins 10 fixed in the carrier and abut arms 16 carried by the plunger 13, guide discs 17 for the fins being mounted on the arms 16. Spring 14 tends to drive the plunger 13 rearward to deploy the fins, but before firing a dished plate 18 holds the fins retracted. On ignition of the propellant, the gases produced dislodge the plate 18 and the fins 11 then bear against the wall of the tube 2 due to the thrust of spring 14, but while in the tube the plunger covers at least partially a duct 15 communicating with the combustion chamber. When the rocket leaves the tube 2, the fins are no longer positively held and the plunger moves so that the duct 15 is cleared. The propellent gases then enter cylinder 6 and reinforce the thrust of the spring 14 to deploy the fins 11. A second duct of smaller diameter may provide permanent communication with the combustion chamber or a groove for the same purpose may lead from the duct 15 either along the inner wall of the cylinder 6 or the outer wall of the plunger.