A STUDY TO INVESTIGATE TACTICAL HIGH DENSITY LANDING SYSTEM PROBLEMS FOR THE PURPOSE OF RECOMMENDING AN ADVANCED SYSTEM WHICH WILL FULFILL THE ARMY'S REQUIREMENTS IN 1965

Abstract : Effort was concentrated on establishing basic requirements of an advanced Army aircraft landing system. The system should minimize early obsolescence of components and offer maximum flexibility. The pertinent factors of an ideal Army aircraft are excellent controlability and self-contained navigation capability. The following basic types of vertical plane, landing path generation techniques represent guidance extremes demanded of an ideal Army aircraft landing system: (1) constant airspeed, high velocity landing; (2) variable velocity, constant approach angle; and (3) variable velocity, vertical let-down. Since the landing syste must provide for dynamic velocity control, the aircraft's three dimensional position relative to the intended destinations of flare and touchdown points must be obtainable throughout the landing operation. An airborne executive controller capable of performing comp tations and storing data for guidance or control of an ideal Army aircraft is defined. A hypothetical special purpose executive controller designed on a building block basis to supply instrument panel displays and conventional auto-pilot command signals is discussed. (Author)