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    • 5. 发明专利
    • Flight path control system
    • GB961752A
    • 1964-06-24
    • GB2527462
    • 1962-07-02
    • THOMAS FORD KELVIN EDMISON
    • G01S1/02G01S19/15
    • 961,752. Flight path control systems. T. F. K. EDMISON. July 2, 1962 [July 5, 1961], No. 25274/62. Heading H4U. A flight path control system is characterized by a pair of elongated loops extending along and beyond the sides of the landing strip, said loops being individually rotatable about their respective longitudinal axes such that the lateral inclination of each loop to the ground varies along the length of the loop. This system is adapted to give flight path information in the final stages of touch down, use having been made of ILS or other systems for initial approach. The loops A and B (shown as 10, 11, in Fig. 2), are constructed in sections which are rotatably adjusted relative to each other to give the desired orientation to determine the flight path 23 by a series of " double null " positions 21, 21a... when the loops are respectively energized by A.C. of different low frequencies f1 and f2. Pick-up means in the aircraft comprises a horizontally stabilized loop in which is induced voltages ea and eb from loops A and B respectively, and a vertically stabilized loop for providing a constant polarity reference signal obtained on energizing both loops A and B in phase quadrature by a further higher frequency f3, amplitude modulated by both f1 and f2. In the information analysing circuit (Fig. 9) the output from vertical loop 39 is fed via filter 40, which passes only f3 and its modulation components, to detector 41 which separates f1 and f2 from f3 and then frequencies f1 and f2 are passed through filters 42 and 43 respectively to a pair of detectors 44 and 45. The output from horizontal loop 38 is fed via filter 40 which passes f1 and f2 but blocks f3 to detectors 44 and 45. Detector 44 provides an output proportional to + ea while detector 45 provides two outputs proportional respectively to +eb and - eb. These three signals are applied to summing circuit 47 providing two outputs proportional respectively to (ea+eb) and (eaeb). These signals define by their relative polarities the position of loop system 37 from the double null position at which ea = eb = O. This information may be shown visually on a cross-point indicator 50 or fed to the auto pilot mechanism. A further pair of pick-up loops may be positioned in the nose of the aircraft for use in de-crabbing operations and means for switching from this set to system 37, usually in the centre of pitch and roll, is provided.