Hover position hold system for rotary winged aircraft

Details Hover position hold system for rotary winged aircraft Hover position hold system for rotary winged aircraft

G - Physics

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G05D 1/10 (2006.01) B64C 27/57 (2006.01) G05D 1/08 (2006.01)

Patent

CA 2035407

A ground-plane-referenced, acceleration signal (2) and Doppler velocity signal (56) are utilized by a complementary filter (6) to provide a complementary velocity signal (8) which is transformed (60) to an inertial coordinate referenced velocity signal (62) utilized in combination with a GPS position signal (56) by a complementary filter (68) to provide a complementary, position error signal (130) that is transformed to a ground-plane-referenced, position error signal (168) and summed with a wind speed signal (196) calculated from the difference between air speed (200) and the aforementioned complementary velocity signal (8) to provide a pitch command signal (202). A similar system is utilized to provide a roll command signal. The system is gated by signals (100, 176) which are determinative of the aircraft meeting predetermined flight conditions (250-262).

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