Distributed flight condition data validation system and method

Claim 3

The method as recited in Claim 1, wherein the step of measuring the first plurality of physical environmental conditions at the inlet of the first engine comprises the steps of: measuring the ambient air pressure; measuring the total pressure of the air entering the first engine inlet; and measuring the total temperature of the air entering the first engine inlet.

Claim 4

The method as recited in Claim 1, wherein the step of measuring the plurality of first engine performance parameters includes the steps of: measuring the first engine turbine exhaust total pressure; measuring the speed of at least one rotor of the first engine; measuring the absolute pressure in the burner section of the first engine; and measuring the air total temperature at the outlet of the low compressor section of the first engine.

Claim 5

A flight condition data validation system for an aircraft having at least a first engine and a second engine for providing a validated value of a critical flight condition variable to the first engine controller, 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, informationally 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 6

A flight condition data validation system for an aircraft having at least a first engine and a second engine for providing a validated value of a critical flight condition variable to the first engine controller, 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, informationally 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 7

The flight condition data validation system as recited in Claim 4, wherein the critical flight condition variable is selected from the group of variables consisting of aircraft altitude, Mach number and first engine air inlet total temperature.

Claim 8

The flight condition data validation system as recited in Claim 4 or 5, wherein the plurality of environmental conditions measured local to the first engine includes one or more variables selected from the group of variables consisting of first engine air inlet total temperature, first engine air inlet total pressure, and ambient air pressure.

Claim 9

The flight condition data validation system as recited in anyone of the Claims 4 to 6, wherein the plurality of first engine performance parameters includes one or more parameters selected from the group of parameters consisting of first engine turbine exhaust total pressure, first engine rotor speed, first engine burner absolute pressure, and first engine low compressor outlet air total temperature.

Claim 10

The flight condition data validation system as recited in Claim 4, the 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 elecrical signal commensurate with the first engine low compressor outlet air total temperature, 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 said first tentative value of the 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 said second tentative value of the critical flight condition variable, and further comprising a data bus directly connecting the first engine controller to a substantially similar second engine controller for passing said third tentative value of the critical flight condition variable determined by the second engine controller to the first engine controller; and means for comparing the first tentative value, the second tentative value, and the third tentative value of the critical flight condition variable and determining said final, validated value of the critical flight condition variable for use in regulating a flow of fuel to the first engine.