Built-in test system for aircraft indication switches

Details Built-in test system for aircraft indication switches Built-in test system for aircraft indication switches

G - Physics

01

R

G01R 31/327 (2006.01) B64D 43/00 (2006.01) F02K 1/76 (2006.01) H01H 9/16 (2006.01)

Patent

CA 2454808

A built-in test system (10) for aircraft indication switches comprises a plurality of aircraft indication switches (11, 12, 13) and a first resistor adding network having input resistors (20, 21, 22) individually connected to first contacts of different ones of the indication switches. The test system further includes a second resistor adding network having input resistors (30, 31, 32) individually connected to second contacts of different ones of the indication switches. Output circuitry is provided for coupling outputs of the first and second resistor adding networks to an electronic control unit for the aircraft.

L'invention concerne un système d'essai intégré (10) pour des commutateurs d'indication d'un aéronef. Ce système comprend plusieurs commutateurs d'indication d'un aéronef (11, 12, 13) et un premier réseau d'addition à résistances possédant des résistances d'entrée (20, 21, 22) reliées individuellement aux premiers contacts de différents commutateurs d'indication. Ce système d'essai comprend également un second réseau d'addition à résistances possédant des résistances d'entrée (30, 31, 32) reliées individuellement aux seconds contacts de différents commutateurs d'indication. Des circuits de sortie permettent de coupler les sorties des premier et second réseaux d'addition à une unité de commande électronique de l'aéronef.

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