Distributed flight condition data validation system and method

• US 4,785,403 A
• Filed: 05/02/1986
• Issued: 11/15/1988
• Est. Priority Date: 05/02/1986
• Status: Expired due to Fees

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Kuhlberg, Joel F.
• Primary Examiner(s): Chin, Gary
• Application Number:
  US06/858,638
• Time in Patent Office: 928 Days
• Field of Search: 364/424, 364/550, 364/551, 364/552, 364/431.01, 364/431.02, 371/25, 371/26, 371/67, 371/68
• US Class Current: 701/14
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: G01D 3/08 with provision for safeguarding the apparatus, e.g. against abnormal operation, against breakdown

Abstract

A distributed data acquisition system for a first engine controller determines a final, validated value of a critical flight condition variable by first determining: a first tentative value based on local environmental conditions, a second tentative value based on the performance of a first engine, and a third tentative value transferred directly from a similar data acquisition system linked to a second engine on the same aircraft. The data acquisition system compares the three tentative values and selects a final, validated value for use by the controller.

Claims

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.

3. The system for providing a validated value of a critical flight condition variable as recited in claim 1, 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.

2. 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.

4. The system for providing a validated value of a critical flight condition variable as recited in claim 2, 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.

5. The system for providing a validated value of a critical flight condition variable as recited in claim 2, 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.

6. 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.

7. The method as recited in claim 6, 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.

8. The method as recited in claim 6, 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.