Abstract
Methods and results in the design and evaluation of a digital flight control system (DFCS) for a CH-47B helicopter are presented. The DFCS employs proportional-integral control logic to provide rapid, precise response to automatic or manual guidance commands while following conventional or spiral-descent approach paths. It contains attitude - and velocity - command modes, and it adapts to varying flight conditions through gain scheduling. Extensive use is made of linear systems analysis technques - the DFCS is designed using linear-optimal estimation and control theory, and the effects of gain scheduling are assessed by examination of closed-loop eigenvalues and time responses. The pre-flight-test evaluation described provides a direct comparison of alternate navigation, guidance, and control philosophies; confirms the practical merits of the DFCS design approach; and demonstrates techniques which will aid in the development of future guidance and control systems.
Original language | English (US) |
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Pages | 18. 1-18. 21 |
State | Published - 1977 |
Event | Pap Presented at the Guid and Control Panel Symp - Dayton, OH, USA Duration: Oct 17 1977 → Oct 20 1977 |
Other
Other | Pap Presented at the Guid and Control Panel Symp |
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City | Dayton, OH, USA |
Period | 10/17/77 → 10/20/77 |
All Science Journal Classification (ASJC) codes
- General Engineering