Aircraft blind landing device and flight director system

Claim 1

IN AN AIRCRAFT BLIND LANDING DIRECTOR-SYSTEM, THE COMBINATION OF A SUPPORTING FRAME ATTACHED TO THE AIRCRAFT, CORRELATED MOBILE INDICIA RESPONSIVE TO AIRCRAFT ATTITUDE, AIRCRAFT TURN, AIRCRAFT LOCATION WITH RESPECT TO RADIATED ELECTRONIC SPACE PATTERNS OF ENERGY, AIRCRAFT SPEED THROUGH THE ATMOSPHERE, AIRCRAFT ALTITUDE WITH RESPECT TO THE ATMOSPHERE, AIRCRAFT ALTITUDE WITH RESPECT TO THE LANDING RUNWAY, AND AIRCRAFT DISTANCE ALONG THE RUNWAY; THE MOBILE INDICIA BEING SUPPORTED BY THE SAID FRAME AND REFERENCED TO A HORIZON LINE AND LUBBER LINE FIXEDLY POSITIONED WITHIN THE FRAME, A GYROSCOPE SPINNING ON VERTICAL AXIS, SAID GYROSCOPE BEING SUSPENDED BY GIMBALS ALLOWING FREEDOM IN ROLL AND PITCH OF 360 DEGREES, THE SAID GYROSCOPE HAVING A CASE WITH ASSOCIATED AXLES, THE AXLES SUPPORTED IN BEARINGS IN A GIMBAL, EACH AXLE TERMINATING IN GEARS WHICH ENGAGE MATING GEARS AFFIXED TO COUNTER-SHAFTS, THE SAID COUNTER-SHAFTS SUPPORTED AT ONE END IN THE SAID GIMBAL, AND SHAPED INDICIA AFFIXED TO THE OTHER END OF THE SAID COUNTER-SHAFTS, THE SAID SHAPED INDICIA BEING POSITIONED 180 DEGREES APART, EACH SHAPED INDICIA BEING VIEWABLE DURING SELECTED PHASES OF FLIGHT ATTITUDE OF THE SAID AIRCRAFT IN ORDER TO MEASURE PITCH ANGLE AND ROLL ANGLE AGAINST THE SAID FIXED HORIZON LINE, AND EACH SHAPED INDICIA ROTATING OPPOSITELY TO THE ROTATION OF THE SAID GYROSCOPE CASE AXLES, AND IN THE FIELD OF VIEW OF THE SAID CORELATED MOBILE INDICIA, A TURN DIRECTION DIAL, SAID DIAL AFFIXED TO A SYNCHRO MOTOR WHICH IS ENERGIZED BY A SYNCHRO GENERATOR AFFIXED TO DIRECTION SENSING MEANS, THE SAID DIAL MOVING IN DIRECTIONAL RATE AND DEGREE IN PROPORTION TO AIRCRAFT TURN RATES AND DEGREE AND IN DIRECTION SUCH THAT THE COMPOSITE MOVEMENT OF THE SHAPED INDICIA WITH THAT OF THE SAID DIRECTIONAL DIAL WILL PRESENT THE NORMAL VISUAL STIMULUS OF BANK, PITCH AND TURN NORMALLY SEEN BY THE PILOT DURING VISUAL CONTACT FLIGHT, AND SUPERIMPOSED UPON THE SAID INDICIA DEFINING ROLL, PITCH AND TURN, TWO CORRELATED INDICIA WHICH ARE MADE RESPONSIVE TO THE SAID RADIATED ELECTRONIC SPACE PATTERNS OF ENERGY WHICH DEFINE AIRCRAFT LOCATION IN THE VERTICAL PLANE AND IN THE HORIZONTAL PLANE RESPECTIVELY, THE SAID INDICIA WHICH ARE RESPONSIVE TO THE SAID ELECTRONIC ENERGY SPACE PATTERNS BEING POINTERS AFFIXED TO GALVANOMETERS THE SAME BEING MADE RESPONSIVE TO THE ENERGY EMANATING FROM GROUND-BASED NAVIGATIONAL TRANSMITTERS FOR IMPARTING GUIDANCE TO AN AIRCRAFT IN THE HORIZONTAL AND IN THE VERTICAL PLANE, A RADIO ALTIMETER, A GLIDE SLOPE TRANSMITTER-RECEIVER COMBINATION, AND THE SAID INDEX POINTER, HORIZONTALLY DELINEATED, WHICH SELECTIVELY RESPONDS TO SIGNALS RECEIVED FROM EITHER THE GLIDE SLOPE RECEIVER OR THE RADIO ALTIMETER, SELECTIVELY POSITIONED MARKER BEACON TRANSMITTERS ADJACENT TO AN AIRCRAFT LANDING AREA, AN AIRBORNE MARKER BEACON RECEIVER, SWITCHING MEANS MADE RESPONSIVE TO THE MARKER BEACON RECEIVER FOR SELECTIVELY SWITCHING THE HORIZONTAL POINTER INDEX TO THE OUTPUT OF THE SAID RADIO ALTIMETER AFTER DISCONNECTION FROM THE GLIDE SLOPE RECEIVER AS THE AIRCRAFT PASSES THROUGH THE ELECTRONIC ENERGY SPACE PATTERN OF THE GROUND-BASED BOUNDARY MARKER TRANSMITTER, THE SAID HORIZONTAL POINTER INDEX SO DISPOSED IN CORRELATION WITH THE SAID FIXED HORIZON LINE SO THAT THE HORIZONTAL POINTER INDEX COINCIDES WITH THE FIXED HORIZON LINE AS THE RADIO ALTIMETER SIGNALS ZERO HEIGHT, THE SAID SELECTIVELY POSITIONED MARKER BEACON TRANSMITTERS COMBINED WITH A RUNWAY TO PROVIDE MEANS FOR CONSECUTIVE RECEIPT OF THEIR RECEIVED SIGNAL BY THE AIRBORNE MARKER BEACON RECEIVER, A PLURALITY OF ILLUMINATED RUNWAY DISTANCE INDICATORS, THE SAID INDICATORS BEING CONSECUTIVELY RESPONSIVE TO ENERGIZATION BY RECEIVED MARKER