METHOD OF AND SYSTEM FOR CALCULATION AND CONSOLIDATION OF FLIGHT PARAMETERS OF AN AIRCRAFT
First Claim
1. A method for calculation and consolidation of a first plurality of flight parameters of an aircraft (1) including a second plurality, equal to or greater than said first plurality, of pressure sensors (S1-SN) arranged at respective locations (i1-iN) on the aircraft, each pressure sensor being configured to provide a transduced pressure value (X1-XN) on the basis of a respective detected static pressure value, the method comprising the step of acquiring (10) said transduced pressure values (X1-XN) from the pressure sensors, and being characterized by further comprising the steps of:
- defining (20) a system of equations by associating with each transduced pressure value (X1-XN) a respective non-linear mathematical model that is a function of said flight parameters and which defines a mathematical relationship between each transduced pressure value and the aerodynamic behaviour of the aircraft (1) at the location (i1-iN) of the pressure sensor (S1-SN) that has generated this transduced pressure value;
iteratively solving (20) said system of equations, obtaining a current value of each of said flight parameters at each respective location (i1-iN);
calculating (30), for each respective location (i1-iN), a respective intermediate pressure value (Y1-YN) by applying the current values of said flight parameters calculated for the respective location (i1-iN) to each mathematical model;
comparing (30, 40) each transduced pressure value (X1-XN) with the respective intermediate pressure value (Y1-YN), obtaining a result value; and
detecting (40) an operation state of said pressure sensors on the basis of said result value.
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Accused Products
Abstract
A method and system for calculation and consolidation of a first plurality of aircraft flight parameters including a second plurality of pressure sensors is provided. The pressure sensors are arranged in respective aircraft locations; each pressure sensor provides a pressure value based on a respective detected static pressure value. The method comprises: acquiring the pressure values from the pressure sensors; defining an equation system by associating with each pressure value a respective non-linear mathematical model describing the aerodynamic aircraft behaviour at the pressure sensor location, each respective mathematical model being a flight parameter function; iteratively solving the equation system, obtaining a current value of each of said flight parameters; calculating a plurality of intermediate pressure values by applying the current flight parameter values to each mathematical model; comparing each pressure value with the respective intermediate pressure value, obtaining a result value; and detecting an operation state of the pressure sensors.
12 Citations
13 Claims
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1. A method for calculation and consolidation of a first plurality of flight parameters of an aircraft (1) including a second plurality, equal to or greater than said first plurality, of pressure sensors (S1-SN) arranged at respective locations (i1-iN) on the aircraft, each pressure sensor being configured to provide a transduced pressure value (X1-XN) on the basis of a respective detected static pressure value, the method comprising the step of acquiring (10) said transduced pressure values (X1-XN) from the pressure sensors, and being characterized by further comprising the steps of:
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defining (20) a system of equations by associating with each transduced pressure value (X1-XN) a respective non-linear mathematical model that is a function of said flight parameters and which defines a mathematical relationship between each transduced pressure value and the aerodynamic behaviour of the aircraft (1) at the location (i1-iN) of the pressure sensor (S1-SN) that has generated this transduced pressure value; iteratively solving (20) said system of equations, obtaining a current value of each of said flight parameters at each respective location (i1-iN); calculating (30), for each respective location (i1-iN), a respective intermediate pressure value (Y1-YN) by applying the current values of said flight parameters calculated for the respective location (i1-iN) to each mathematical model; comparing (30, 40) each transduced pressure value (X1-XN) with the respective intermediate pressure value (Y1-YN), obtaining a result value; and detecting (40) an operation state of said pressure sensors on the basis of said result value. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 13)
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12. A calculation and consolidation system of a first plurality of flight parameters of an aircraft (1) that includes a second plurality, equal to or greater than said first plurality, of pressure sensors (S1-SN) arranged in respective locations (i1-iN) on the aircraft, each pressure sensor being configured to provide a transduced pressure value (X1-XN) on the basis of a respective detected static pressure value, the system comprising processing means (5) which acquire (10) said transduced pressure values (X1-XN) from the pressure sensors,
characterized in that the processing means (5) are configured to: -
define (20) a system of equations by associating with each transduced pressure value (X1-XN) a respective non-linear mathematical model that is a function of said flight parameters and which defines a mathematical relationship between each transduced pressure value and the aerodynamic behaviour of the aircraft (1) at the location (i1-iN) of the pressure sensor (S1-SN) that has generated this transduced pressure value; iteratively solve (20) said system of equations, obtaining a current value of each of said flight parameters at each respective location (i1-iN); calculate (30), for each respective location (i1-iN), a respective intermediate pressure value (Y1-YN) by applying the current values of said flight parameters calculated for the respective location (i1-iN) to each mathematical model; compare (30, 40) each transduced pressure value (X1-XN) with the respective intermediate pressure value (Y1-YN), obtaining a result value; and detect (40) an operation state of said pressure sensors on the basis of said result value.
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Specification