Abstract: Regulated pneumatic gas is supplied through a gas supply tube (14) which is welded to a pilot valve housing (18) which accommodates a solenoid valve (16). When the solenoid valve is electrically activated and opened, the pneumatic gas flows through a bifurcated channel (22) which is welded to the pilot valve housing and to a fuel valve mechanism (24A) and to an oxidizer valve mechanism (24B). The force of the pneumatic gas causes pistons (38A, 38B) to actuate respective poppets (36A, 36B). Movement of the poppets results in the dispensing of fuel propellant from a fuel outlet chamber (44A) and the dispensing of oxidizer from an oxidizer outlet chamber (44B). The fuel valve mechanism and oxidizer valve mechanism are positioned and oriented such that the exiting fuel and oxidizer are mixed in a vortex rocket engine.

Abstract: Regulated pneumatic gas is supplied through a gas supply tube (14) which is welded to a pilot valve housing (18) which accommodates a solenoid valve (16). When the solenoid valve is electrically activated and opened, the pneumatic gas flows through a bifurcated channel (22) which is welded to the pilot valve housing and to a fuel valve mechanism (24A) and to an oxidizer valve mechanism (24B). The force of the pneumatic gas causes pistons (38A, 38B) to actuate respective poppets (36A, 36B). Movement of the poppets results in the dispensing of fuel propellant from a fuel outlet chamber (44A) and the dispensing of oxidizer from an oxidizer outlet chamber (44B). The fuel valve mechanism and oxidizer valve mechanism are positioned and oriented such that the exiting fuel and oxidizer are mixed in a vortex rocket engine.

Abstract: The Rotational Canted-Joint Missile (RCJM) Control System utilizes a single or multiple body joints that rotate in planes that are not perpendicular to the missile body axis. The result is the deflection of a portion of the missile body for flight control purposes. The canted interface plane between any two adjacent movable sections of the missile body and a joint at the interface plane that allows one of the sections to be rotated by a pre-determined angle with respect to the other section comprise a rotational plane mechanism that offers an inclined bearing plane with a large mechanical advantage over typical “brute force” ball joint methods.

Abstract: The Rotational Canted-Joint Missile (RCJM) Control System utilizes a single or multiple body joints that rotate in planes that are not perpendicular to the missile body axis. The result is the deflection of a portion of the missile body for flight control purposes. The canted interface plane between any two adjacent movable sections of the missile body and a joint at the interface plane that allows one of the sections to be rotated by a pre-determined angle with respect to the other section comprise a rotational plane mechanism that offers an inclined bearing plane with a large mechanical advantage over typical “brute force” ball joint methods.

Abstract: The Magnetostrictive Missile Guidance System pivots the missile nosecone about a multi-directional joint on the missile axis to produce aerodynamic control forces for missile flight path control. The nosecone is driven by magnetostrictive materials in conjunction with displacement amplification devices. The determination of the nosecone deflection angle necessary to achieve any change in the flight path is made by a sensing device that produces position signals and a guidance computer that produces the desired flight path command signals. The sensing device senses the current position of the nosecone and this position signal is compared with the command signal by the computer to yield an error signal, which is indicative of the difference between the two input signals. Then appropriate magnetic field is applied to the magnetostrictive materials to cause them to grow in length and deflect the nosecone until the error signal is eliminated and flight path is changed.

Abstract: Apparatus for pneumatically pulling on optical filament from test bobbin and winding the optical filament onto the surface of a non-rotating spool. The filament is guided about the surface of the spool by one or more streams of fluid at supersonic flow and is wound into a groove in the cylindrical surface of the spool. The filament is wound onto the supply bobbin so that withdrawal of the filament from the supply bobbin imparts a twist to the filament as it is withdrawn and the filament is wound onto the spool in a direction which imparts a twist to said filament in the opposite direction to that the twist imparted by pulling the filament from the supply bobbin is offset by the twist imparted to the filament while winding the filament on the spool.