Fault tolerant actuation system for flight control actuators
US5806805A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 7, 1996 |
| Grant date | Sep 15, 1998 |
| Priority date | — |
| Expiry date | Aug 7, 2016 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C13/42
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A fault tolerant actuation system (12) for flight control systems is provided. The fault tolerant actuation system (12) includes a plurality of primary flight computers (14a, 14b, and 14c) with corresponding power control units (24a, 24b, and 24c). Each power control unit includes a remote electronic unit (18a, 18b, and 18c), an electro-hydraulic servo valve (26a, 26b, and 26c), and an actuator (28a, 28b, and 28c). The actuators are linked to a flight control surface (30) to control its position. The electro-hydraulic servo valves (26a, 26b, and 26c) and the actuators (28a, 28b, and 28c) include sensors that monitor their operation. Each RE (18a, 18b, and 18c) generates a control current (i.sub.1, i.sub.2, and i.sub.3) based upon commands of the corresponding primary flight computer as well as feedback data transmitted from the sensors of the corresponding electro-hydraulic servo valve and actuator only. The feedback data is transmitted along separate servo loops having separate compensations (66a, 70a). A current equalization control (34a, 34b, and 34c) equalizes the control currents with one another. A force fight equalization control (36a, 36b, and 36c) equalizes the forces of t…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.