Engine control system for an aircraft
US6088632A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jan 5, 1999 |
| Grant date | Jul 11, 2000 |
| Priority date | — |
| Expiry date | Jan 5, 2019 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D31/00
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An engine control system for a first aircraft belonging to a family of aircraft which includes at least a second aircraft, the first aircraft having a maximum mass which is greater, within a predetermined limit, than that of the second aircraft. For an engine of the first aircraft, a first thrust command law controls a thrust of an engine of the first aircraft during take-off phase (T), and a second thrust command law, controls a thrust of the engine to correspond with a part of the thrust command laws applicable to the second aircraft during all other flight phases (R) of the first aircraft. The transition from one flight phase to another is detected to supply the engine with a control signal corresponding to one or the other of the first thrust command law or the second thrust command law.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.