초록 ▼

An integrated air data system for use on an aircraft. Airframe air data units (18) are connected to receive a plurality of redundant total pressure sensor inputs (20,22,24), a plurality of redundant static pressure sensor inputs (26,28,30), and a total temperature sensor input (32). Similar redundan

An integrated air data system for use on an aircraft. Airframe air data units (18) are connected to receive a plurality of redundant total pressure sensor inputs (20,22,24), a plurality of redundant static pressure sensor inputs (26,28,30), and a total temperature sensor input (32). Similar redundant sensor inputs are provided a first and second channel in each of two electronic engine controls (34,36). Bidirectional data buses (16) connect the airframe air data system to the electronic engine control system, so that the same sensor signals are available for each of the systems. The airframe air data unit and the primary electronic engine control channel having priority to control each engine are independently operative to select a preferred total pressure, static pressure, and total temperature value according to a common programmed logic scheme. The selection logic gives priority to the use of the same value for common parameters in each of the systems, where possible. The logic also minimizes the risk that failure of a single sensor may result in use of an incorrect value for a parameter, and that any combination of failures of different sensors, except for similar failures occurring independently on each engine, might result in an undesired effect on more than one engine.

대표청구항 ▼

On an aircraft, an integrated air data system comprising: (a) a plurality of first sensors associated with an airframe air data unit, said first sensors each providing a signal indicative of a parameter used by the airframe air data unit to determine the flight status of the aircraft; (b) a pluralit

On an aircraft, an integrated air data system comprising: (a) a plurality of first sensors associated with an airframe air data unit, said first sensors each providing a signal indicative of a parameter used by the airframe air data unit to determine the flight status of the aircraft; (b) a plurality of second sensors associated with an engine control system, said second sensors each providing a signal indicative of a parameter used by the engine control system to control the operation of an aircraft engine, the signals provided by said second sensors being redundant to the signals provided by said first sensors, the same parameter being sensed by at least one each of the first and second sensors; (c) a bidirectional data bus connecting the airframe air data unit to the engine control system and operative to convey data bidirectionally therebetween; (d) control means, disposed within both the airframe air data unit and the engine control system, and connected to the data bus, for selecting at least one of the redundant signals provided by the first and second sensors as a preferred signal for use by the airframe air data unit and the engine control system according to a predetermined logic that gives priority to using the same signal for both the airframe air data unit and the engine control system, and minimizes the effect of a failure of any one or more of the first and second sensors.