| 摘要 |
<p>The present invention is directed to a non-normalized aircraft angle-of-attack indicating system. An angle-of-attack vane produces a signal alpha ' indicative of raw aircraft angle-of-attack. A pitot-static system (68) produces output signals representative of aircraft static pressure and total pressure, Ps and Pt, respectively. The signals alpha ', Ps and Pt are fed to an air data computer (66) which correspondingly produces an aircraft actual angle-of-attack value alpha and a calculated Mach number, M. Configuration sensors (80) produce output signals representative of gear position, g, flap position, f, and speed brake position, sb. The signals alpha , M, g, f and sb are fed to a display computer (76). The display computer includes a submodule (90) which utilizes a lookup table to determine a value of angle-of-attack stick shaker, alpha ss from the values of M, g, f and sb. A second submodule (92) utilizes a lookup table to produce a second angle-of-attack reference value alpha ref from the values g, f and sb. The display computer (76) feeds the alpha , alpha ss, alpha ref signals to an angle-of-attack indicator which includes a pointer (102) which is moveable with respect to a fixed gauge (104). The alpha signal is used to drive the pointer (102) to indicate the aircraft's actual angle-of-attack. Bug drivers are utilized to position the first bug alpha ss and the second bug, alpha ref, at their appropriate positions on the opposite side of the gauge. <IMAGE></p> |
