Hover position hold system for rotary winged aircraft
US5195039A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | May 3, 1990 |
| Grant date | Mar 16, 1993 |
| Priority date | — |
| Expiry date | May 3, 2010 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C27/57
- WIPO fieldControl
- WIPO sectorInstruments
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.