Abstract: An electromagnetic fuel injector has an orificed fuel director plate, mounted downstream of a solenoid actuated valve and an associated main orifice passage opened and closed by the valve, to receive fuel when the valve is pulled to an open position from its associated valve seat for controlling and directing flow from the injector. The upper surface of the orifice director plate is provided with a fuel distributing channel system terminating in separate pairs of cooperating injection orifices that are disposed adjacent to one another to direct adjacent jets of fuel which partially intersect one another producing discrete cones of atomized fuel accurately onto separate fuel intake valves of a piston cylinder of an internal combustion engine.

Abstract: A microwave interrogation-transponder system for controlling the airborne rendezvous and closure of two aircraft for aerial refueling and the like. The system of the invention includes a microwave interrogator mounted on the aft underfuselage of a tanker aircraft, for example, for interrogating and receiving a reply from a small microwave transponder mounted on the receiver aircraft near the aerial refueling receptacle. The angle of the received signal relative to the tanker is obtained from the angle sensing receiver portion of the microwave interrogator; whereas range is obtained from the phase of the returned modulation tone (i.e., a range tone) relative to that which was transmitted by the interrogator. The transponder sends back to the interrogator a signal which is shifted in frequency with respect to the transmitted signal and operates in an active mode with gain at long ranges and in a passive mode with no gain at shorter ranges to achieve extremely accurate guidance characteristics.

Abstract: A modulated light beam is projected from a transmitter aircraft toward a receiver aircraft and reflected back toward the receiver aircraft by a retroreflector mounted on the receiver aircraft. The reflected light beam is received by the transmitter aircraft and is focused onto the face of an image dissector tube. The location of the reflected light beam on the face of the tube defines the position of the receiver aircraft in azimuth and elevation with respect to the position of the transmitter aircraft. The range difference between the two aircraft is determined by phase comparing the transmitted light beam with the received light beam. When used for in-flight refueling, further retroreflectors are mounted on a refueling boom and a similar technique is used to determine the exact location of the boom and its associated refueling nozzle.