Continuous wave hyperbolic system for landing aircraft

Claim 1

FOR USE IN A SYSTEM FOR LANDING AIRCRAFT, A METHOD OF COORDINATING THE OPERATION OF RECEIVING EQUIPMENT CARRIED BY THE AIRCRAFT WITH TRANSMITTING EQUIPMENT LOCATED AT SPACED APART LANDING FIELDS, EACH OF SAID LANDING FIELDS BEING PROVIDED WITH TRANSMITTING EQUIPMENT FOR RADIATING POSITION INDICATING SIGNALS OF DIFFERENT FREQUENCY, FOR HETERODYNING SAID SIGNALS TO DEVELOP A BEAT SIGNAL AND FOR RADIATING A REFERENCE SIGNAL DERIVED FROM SAID BEAT SIGNAL AS A MODULATION COMPONENT UPON A SPACE RADIATED CARRIER WAVE, SAID RECEIVING EQUIPMENT INCLUDING MEANS RESPONSIVE DURING LANDING OF THE AIRCRAFT TO THE REFERENCE SIGNAL AND TO THE POSITION INDICATING SIGNALS FOR PRODUCING AN INDICATION REPRESENTATIVE OF THE LOCATION OF SAID AIRCRAFT RELATIVE TO THE TRANSMITTING EQUIPMENT AT THE LANDING FIELD BEING USED, SAID METHOD COMPRISING THE STEPS OF POSITIONING SAID RECEIVING EQUIPMENT AT A FIRST KNOWN LOCATION AT A FIRST OF SAID LANDING FIELDS, COORDINATING THE OPERATION OF THE TRANSMITTING AND RECEIVING EQUIPMENT BY ADJUSTING AT LEAST ONE OF SAID EQUIPMENTS UNTIL THE INDICATION ON SAID RECEIVING EQUIPMENT CORRESPONDS WITH THE FIRST KNOWN LOCATION, POSITIONING SAID RECEIVING EQUIPMENT AT A SECOND KNOWN LOCATION AT A SECOND OF THE LANDING FIELDS, AND ADJUSTING THE PHASE OF THE REFERENCE SIGNAL DEVELOPED AT THE SECOND LANDING FIELD PRIOR TO MODULATION UPON ITS CARRIER WAVE UNTIL THE INDICATION PROVIDED BY THE RECEIVING EQUIPMENT AGREES WITH SAID SECOND KNOWN LOCATION, THEREBY PERMITTING THE AIRCRAFT CARRYING THE RECEIVING EQUIPMENT TO USE THE TRANSMITTING EQUIPMENT AT BOTH OF THE LANDING FIELDS.