Distributed flight condition data validation system and method

Claim 1

A flight condition data validation system for an aircraft having at least a first engine and a second engine, comprising: a first engine controller including means for generating an electrical signal commensurate with the first engine air inlet total pressure, means for generating an electrical signal commensurate with the first engine air inlet total temperature, means for generating an electrical signal commensurate with the ambient air pressure local to the first engine, means for generating an electrical signal commensurate with the engine turbine exhaust total pressure, means for generating an electrical signal commensurate with the rotor speed of the first engine, means for generating an electrical signal commensurate with the first engine burner absolute pressure, means for generating an electrical signal commensurate with the first engine low compressor outlet air total temperataure, means, responsive to the first engine air inlet total pressure signal, first engine air inlet total temperature signal, and the local ambient air pressure signal, for deriving a first tentative value of a critical flight condition variable selected from the group of aircraft altitude, Mach number, or total air temperature, means, responsive to the first engine burner absolute pressure signal, first engine rotor speed signal, first engine turbine exhaust total pressure signal, and first engine compressor outlet air total temperature, for synthesizing a second tentative value of the critical flight condition variable; a data bus directly connecting the first engine controller to a substantially similar second engine controller for passing a third tentative value of the critical flight condition variable determined by the second engine controller to the first engine controller; and means for determining a final, validated value of the critical flight condition variable for use in regulating a flow of fuel to the first engine, including means for comparing the magnitude and quality of the first tentative value, the second tentative value, and the third tentative value of the critical flight condition variable, and means, responsive to the comparing means, for logically selecting the final, validated value from one of the first, second, and third tentative values.

Claim 3

A system for providing a validated value of a critical flight condition variable to a first engine controller in an aircraft having a first engine and a second engine, comprising: means, local to the first engine, for measuring a plurality of physical environmental conditions; means for measuring a plurality of first engine performance parameters; means for deriving a tentative first value of the critical flight condition variable from the plurality of measured environmental conditions; means for synthesizing a tentative second value of the critical flight condition variable from the plurality of measured engine performance parameters; means, linked with the second engine, for determining a third tentative value of the critical flight condition variable from measured environmental conditions and performance parameters corresponding to the second engine; means for conveying the third tentative value from the second engine controller directly to the first engine controller; and means, responsive to the first, second and third tentative values, for determining a final, validated value of the critical flight condition variable.

Claim 4

A system for providing a validated value of a critical flight condition variable to a first engine controller in an aircraft having a first engine and a second engine, comprising: means, local to the first engine, for measuring a plurality of physical environmental conditions; means for measuring a plurality of first engine performance parameters; means for deriving a tentative first value of the critical flight condition variable from the plurality of measured environmental conditions; means for synthesizing a tentative second value of the critical flight condition variable from the plurality of measured engine performance parameters; means, linked with the second engine, for determining a third tentative value of the critical flight condition variable from measured environmental conditions and performance parameters corresponding to the second engine; means for conveying the third tentative value from the second engine controller directly to the first engine controller; and means, responsive to the first, second and third tentative values, for determining a final, validated value of the critical flight condition variable.

Claim 8

A method for providing a validated value of a critical flight condition variable to a first engine controller for controlling a first engine of an aircraft having two or more engines, comprising the steps of: measuring a first plurality of environmental conditions local to the first engine; calculating a first tentative value of the critical flight condition variable responsive to the first plurality of environmental conditions; measuring a plurality of first engine performance parameters; calculating a second tentative value of the critical flight condition variable responsive to the plurality of first engine performance parameters; determining a third tentative value of the critical flight condition variable by a data acquisition system, responsive to both a second plurality of environmental conditions local to a second engine and to a plurality of second engine performance parameters; and comparing the magnitude and quality of the first, second, and third tentative values of the critical flight condition variable and, based upon said comparing step, logically selecting from among said tentative values for determining a validated flight condition variable value for use by the first engine fuel controller.

Claim 9

A method for providing a validated value of a critical flight condition variable to a first engine controller for controlling a first engine of an aircraft having two or more engines, comprising the steps of: measuring a first plurality of environmental conditions local to the first engine; calculating a first tentative value of the critical flight condition variable responsive to the first plurality of environmental conditions; measuring a plurality of first engine performance parameters; calculating a second tentative value of the critical flight condition variable responsive to the plurality of first engine performance parameters; determining a third tentative value of the critical flight condition variable by a data acquisition system, responsive to both a second plurality of environmental conditions local to a second engine and to a plurality of second engine performance parameters; and comparing the magnitude and quality of the first, second, and third tentative values of the critical flight condition variable and, based upon said comparing step, logically selecting from among said tentative values for determining a validated flight condition variable value for use by the first engine fuel controller.