Abstract: 1. In a guiding and propulsion system for a missile, the combination which comprises:Communication means mounted in a central portion of the missile toward the aft end thereof and effective to receive and emit radiant energy along a rearward line of view substantially axial of the missile, to guide the missile, andNozzle means mounted on said aft end to propel the missile by generally rearward discharge of fluid, said nozzle means being canted outward from said central portion to keep said line of view free from said fluid.

Abstract: A sonic flow-type carburetor having a variable area venturi defined by a conical air nozzle receiving axially within a movable matching conically-shaped plug to define a constricted annular variable area or zone between through which air flows at sonic velocity over a large portion of the operating range of the engine, the plug shape defining a diffuserless nozzle to locate the point of maximum flow velocity at the manifold edge of the plug for better atomization of the fuel and uniform distribution into the air stream for flow into the manifold, the plug having an annular fuel induction port opening into the zone and connected by conduit means to an induction-type fuel supply slot by an overlapping christmas tree-shaped slot, air also being variably supplied to the conduit means as a function of engine operation to vary the fuel induction signal and, therefore, the overall air/fuel ratio of the mixture flow to the engine.