Aircraft non-normalized angle-of-attack indicating system

Abstract

Abstract The present invention is directed to a non-normalized aircraft angle-of-attack indicating system. An angle-of-attack vane produces a signal α' indicative of raw aircraft angle-of-attack. A pitot-static system (68) produces output signals representative of aircraft static pressure and total pressure, P s and P t , respectively. The signals α', P s and P t are fed to an air data computer (66) which correspondingly produces an aircraft actual angle-of-attack value α 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 α, 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, α 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 α ref from the values g, f and sb. The display computer (76) feeds the α, α ss , α ref signals to an angle-of-attack indicator which includes a pointer (102) which is moveable with respect to a fixed gauge (104). The α 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 α ss and the second bug, α ref , at their appropriate positions on the opposite side of the gauge.

Inventors

• 👤 Nicholas J. M. Patrick

Bibliographic Details