Coordinated engine autothrottle
US4912642A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 3, 1987 |
| Grant date | Mar 27, 1990 |
| Priority date | — |
| Expiry date | Sep 3, 2007 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/051
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An integrated engine control-autothrottle control system for controlling changes in the thrust of a jet aircraft engine during transients (i.e., changes in speed) in a manner that prevents throttle lead and overshoot (i.e., exceeds the response capability of the engine) is disclosed. The system uses the engine control to continuously monitor current fuel flow (WF), burner pressure (PB), high rotor speed (N2) and engine thrust (EPR), manipulates the signals and produces limiting fuel flow transient error (WFPBERR) and rotor speed transient error (N2DOTERR) signals for both acceleration and deceleration. The lower parameter transient error signal is selected as the controlling limit signal during acceleration and the higher parameter transient error signal is selected as the controlling limit signal during deceleration. The controlling limit signals are used to produce limiting throttle lever angle rate of change signals--+TRADOT for acceleration and -TRADOT for deceleration. The throttle lever angle rate of change signals denote the maximum rate at which the throttle can be advanced (+TRADOT) or retarded (-TRADOT) without exceeding the response capabilities of the engines. The TRADO…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.