High intensity navigation light system

Claim 1

A LIGHTING SYSTEM FOR AIRCRAFT HAVING RETRACTABLE LANDING GEAR, SAID SYSTEM COMPRISING A HIGH INTENSITY TAIL LIGHT UNIT AND A RIGHT WING AND A LEFT WING HIGH INTENSITY LIGHT UNIT, EACH OF SAID LIGHT UNITS COMPRISING A HIGH INTENSITY LIGHT SOURCE, LIGHT COLLIMATING MEANS DIRECTLY ASSOCATED WITH SAID LIGHT SOURCE FOR FORMING A BEAM OF GENERALLY PARALLEL LIGHT RAYS, REFLECTOR MEANS IN THE PATH OF SAID BEAM FOR REFLECTING LIGHT IN A PREDETERMINED PATTERN GENERALLY TRANSVERSE TO SAID BEAM, SAID REFLECTOR MEANS HAVING AT LEAST A FIRST AND A SECOND SECTION EACH OF GENERALLY CYLINDRICAL SHAPE HAVING A DIRECTRIX GENERALLY NORMAL TO SAID BEAM, SAID FIRST SECTION EXTENDING OUTWARDLY AND FORWARDLY FROM A LINE ADJACENT THE CENTER OF SAID LIGHT SOURCE TO A LINE SUBSTANTIALLY SPACED OUTWARDLY FROM THE FORWARD PERIPHERY OF SAID LIGHT SOURCE, THE PORTION OF SAID FIRST SECTION SPACED OUTWARDLY FROM THE FORWARD PERIPHERY HAVING AN ANGLE OF INCIDENCE IN THE ORDER OF 65* AND THE PORTION ADJACENT SAID CENTER HAVING AN ANGLE OF INCIDENCE LESS THAN THAT OF THE AFOREMENTIONED PORTION AND IN THE ORDER OF 45*, SAID SECOND SECTION EXTENDING OUTWARDLY AND FORWARDLY FROM A LINE ADJACENT THE REARWARD PERIPHERY OF SAID LIGHT SOURCE, THE PORTION OF SAID SECOND SECTION ADJACENT THE LIGHT SOURCE HAVING AN ANGLE OF INCIDENCE LESS THAN 45* AND THE OUTWARD PORTION THEREOF HAVING AN ANGLE OF INCIDENCE GREATER THAN THE ANGLE OF INCIDENCE OF THE AFOREMENTIONED PORTION OF THE SECOND SECTION, SAID FIRST REFLECTOR MEANS HAVING A REFLECTIVE REARWARD SURFACE WHICH RECEIVES REFLECTED LIGHT FROM SAID SECOND SECTION AND REFLECTS LIGHT THEREFROM WITH AN EFFECTIVE ANGLE OF INCIDENCE LESS THAN THAT OF SAID SECOND SECTION, AND MEANS OSCILLATING SAID REFLECTOR MEANS THROUGH AN ANGLE OF AT LEAST 120* ABOUT AN AXIS GENERALLY PARALLEL TO SAID BEAM, MEANS SYNCHRONIZING THE OSCILLATIONS OF SAID TWO WING LIGHT UNITS WHEREBY SAID UNITS MOVE TOWARD AND AWAY FROM THE LONGITUDINAL AXIS OF SUCH AN AIRCRAFT IN SYNCHRONISM, MEANS AUTOMATICALLY DIMMING SAID WING LIGHT UNITS WHENEVER SUCH LANDING GEAR ARE SUPPORTING SAID AIRCRAFT, MEANS DIMMING SAID TAIL LIGHT UNIT WHENEVER SAID LANDING GEAR ARE EXTENDED, STEADY LOW INTENSITY LIGHT ELEMENTS AT SAID TAIL, RIGHT WING AND LEFT WING, AND TRANSPARENT COVERS CONFORMING TO SAID AIRCRAFT AND ENCLOSING SAID LIGHT UNITS AND SAID LIGHT ELEMENTS.