Aircraft lift control system with acceleration and attitude limiting
US4485446A · kind A · utility
9Cited by
9References
5Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Sep 8, 1981 |
| Grant date | Nov 27, 1984 |
| Priority date | — |
| Expiry date | Sep 8, 2001 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG05D1/0607
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
An aircraft vertical lift guidance signal is developed for providing optimum aircraft lift with limiting to avoid excessive acceleration and attitude. A lift computer produces an angle of attack signal as a function of aircraft altitude rate minus longitudinal acceleration such that demand increases in acceleration result in an increased angle of attack, thereby limiting acceleration. Attitude limiting is achieved by limiting the longitudinal signal to a constant value in response to aircraft acceleration exceeding a reference level.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.