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

1990-05-03

1993-03-16

Chin, Gary

Boots, shoes, and leggings

244 1713, 244181, B64C 1316

Patent

active

051950391

ABSTRACT:
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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