Integrated aircraft air data system
First Claim
1. 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.
1 Assignment
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Accused Products
Abstract
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.
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Citations
22 Claims
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1. On an aircraft, an integrated air data system comprising:
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(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. - View Dependent Claims (2, 3, 4, 5, 6, 7)
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8. On an aircraft having at least one engine controlled by an engine control system in response to air data signals, and including an airframe air data unit for determining flight status information in response to air data signals, said air data signals being indicative of total pressure, static pressure, and total temperature, an integrated air data system comprising:
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(a) a first total pressure sensor disposed in proximity to an airframe of the aircraft, connected to provide a signal indicative of total pressure to the airframe air data unit; (b) a second total pressure sensor disposed in proximity to said at least one engine, connected to provide a signal indicative of total pressure to the engine control system; (c) a first static pressure sensor disposed in proximity to the airframe, connected to provide a signal indicative of static pressure to the airframe air data unit; (d) a second static pressure sensor disposed in proximity to said at least one engine, connected to provide a signal indicative of static pressure to the engine control system; (e) a first total temperature sensor, disposed in proximity to the airframe, connected to provide a signal indicative of total temperature to the airframe air data unit; (f) a second total temperature sensor, disposed in proximity to said at least one engine, connected to provide a signal indicative of total temperature to the engine control system, corresponding signals provided by the first total pressure, static pressure, and total temperature sensors being generally redundant to those respectively provided by the second total pressure, static pressure, and total temperature sensors; (g) means for bidirectionally conveying the signals indicative of total pressure, static pressure, and total temperature between the airframe air data unit and the engine control system; and (h) signal selection means, associated with both the airframe air data unit and the engine control system, for selecting one each of the corresponding redundant signals provided respectively by the first and second total pressure, static pressure, and total temperature sensors, for use by the airframe air data unit and the engine control system, said signal selection means including predetermined logic means for determining a preferred one of said respective redundant signals for said selection, failure of one or more of said first and second sensors having a minimal impact on the operation of the airframe air data unit and the engine control system. - View Dependent Claims (9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22)
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Specification