| 摘要 |
PCT No. PCT/US82/00825 Sec. 371 Date Jun. 16, 1982 Sec. 102(e) Date Jun. 16, 1982 PCT Filed Jun. 16, 1982 PCT Pub. No. WO84/00071 PCT Pub. Date Jan. 5, 1984.Each of three redundant sensor sets (16, 18, 20) provides flight status data to a corresponding one of three flight control computers (22, 24, 26). Each of the computers shares sensor data as well as computed control surface command signals with all other system computers. The command signal outputs from two computers are transduced (34, 36) to mechanical commands which are combined and applied to the appropriate aircraft control surface. The remaining computer output is a mathematical model of the mechanical outputs of the other channels. Fault detection and isolation is accomplished by cross channel comparing sensor data, command signals, model/surface position information and by incorporating channel monitors for detecting generic or common mode flight control computer failures.
|
