Aircraft glide path radius vector and altitude indicating system

Claim 1

AN AIRCRAFT LANDING STRIP GLIDE PATH, RADIUS VECTOR AND ALTITUDE INDICATING SYSTEM COMPRISING A SPACED FIRST AND A SECOND LIGHT PROJECTION UNIT SUPPORTED BY THE LANDING STRIP, A LINEAR LIGHT POLARIZING FILTER IN FRONT OF EACH OF THE LIGHT PROJECTORS, A FIRST BAND PASS FILTER IN FRONT OF THE FIRST LIGHT PROJECTOR, A SECOND BAND PASS FILTER OF DIFFERENT FREQUENCY FROM THE FIRST BAND PASS FILTER IN FRONT OF THE SECOND LIGHT PROJECTOR, MEANS TO MOVE THE LIGHT PROJECTORS AND THEIR POLARIZING FILTER THROUGH A VERTICAL SWEEP ANGLE AND SYNCHRONOUSLY ROTATE THE POLARIZING FILTERS WHEREBY THE PLANE OF POLARIZATION OF THE FILTERS BEARS A SPECIFIC RELATIONSHIP TO THE ELEVATION OF THE PROJECTED LIGHT BEAM, MEANS TO REGULATE THE RESPECTIVE SPEEDS OF THE TWO PROJECTION UNITS TO PROVIDE AN INFINITE FOCUS OF INTERSECTION POINTS OF THEIR RESPECTIVE BEAMS, A FIRST AND A SECOND PAIR OF SENSORS CARRIED BY THE AIRCRAFT TO RECEIVE THE LIGHT FROM EACH OF THE BEAMS, A LINEAR LIGHT POLARIZER IN FRONT OF EACH SENSOR IN THE SENSOR PAIRS, SAID POLARIZERS DISPOSED WITH THEIR PLANES OF POLARIZATION NORMAL TO EACH OTHER, FILTER MEANS BETWEEN THE SENSORS AND THEIR RESPECTIVE PROJECTORS TO LIMIT EACH PAIR OF SENSORS TO ONE OF THE PROJECTED BEAMS AND MEANS TO DERIVE FROM THE SENSORS THE GLIDE PATH, RADIUS VECTOR AND ALTITUDE OF THE AIRCRAFT.