BR-102016023997-B1 - A computer-implemented method for displaying aircraft engine information, and a system for indicating aircraft engine information on board an aircraft.

BR102016023997B1BR 102016023997 B1BR102016023997 B1BR 102016023997B1BR-102016023997-B1

Abstract

COMPUTER-IMPLEMENTED METHOD FOR DISPLAYING AIRCRAFT ENGINE, SYSTEM, AND AIRCRAFT INFORMATION. Systems and methods for displaying N1 airspeed on a cockpit display in a manner that provides increased resolution at the upper end of the operating range. This is accomplished by variable scale(s) that enhance(s) the functionality of the N1 indicator (serving as a thrust indication) in the desired region. Also, there is visual indication to provide pilots with the ability to discern whether the current thrust is within a specific tolerance for the desired value within the takeoff region. This additional indication is based on color changes associated with the N1 display structure.

Inventors

CHRISTOPHER M. HODGES
KEVIN S. BROWN

Assignees

THE BOEING COMPANY

Dates

Publication Date: 20260317
Application Date: 20161014
Priority Date: 20151026

Claims (13)

1. A computer-implemented method for displaying aircraft engine information, characterized in that it comprises: obtaining a value of an engine control parameter during the operation of an aircraft engine, wherein the engine control parameter has a non-linear relationship with thrust, and wherein the engine control parameter is a fan speed (N1); displaying a scale in a display unit (20); and displaying first symbology (8) having a position relative to the scale using a non-linear scaling function in the region from zero fan speed to maximum nominal fan speed (N1Max), wherein the sensitivity is reduced at zero fan speed and the sensitivity is increased at maximum nominal fan speed, the first symbology (8) representing the obtained value of the fan speed; and displaying second symbology (6) representing a target fan speed (N1Targ).
2. Method according to claim 1, characterized in that the nonlinear scaling function is a polynomial function.
3. Method according to any one of claims 1 or 2, characterized in that it further comprises retrieving the position of the first symbol (8) in relation to the scale from a lookup table comprising fan speed values (N1) and corresponding symbol positions of the first symbol (8) in relation to the scale.
4. Method according to any one of claims 1 to 3, characterized in that the scale is a circular arc and the first symbol (8) is a radial line that originates at a center of, and intersects, the circular arc at an angular position.
5. Method according to claim 4, characterized in that it further comprises retrieving the angular position of the radial line relative to the circular arc from a lookup table comprising fan speed values (N1) and corresponding angular positions relative to the circular arc.
6. A method according to any one of claims 1 to 5, characterized in that it further comprises displaying a discreet indication that the thrust has been adjusted to a takeoff thrust value that is within a specified tolerance of a desired takeoff thrust value.
7. Method according to claim 6, characterized in that it further comprises displaying a third symbol (10) on the display unit (20), wherein the display of a discrete indication comprises changing the color of the third symbol, wherein the third symbol comprises a rectangle, the method comprising displaying a numerical value within said rectangle, said numerical value being a magnitude of the fan speed (N1).
8. System for displaying aircraft engine information on board an aircraft, the system characterized in that it comprises: a display unit (20) that can be electronically controlled to generate symbology and colors; and a display control processor configured to control said display unit (20) to generate indicators that show the current fan speed of an operating aircraft engine, wherein said display control processor is configured to perform the following operations: obtain a value of an engine control parameter during engine operation, wherein the engine control parameter has a non-linear relationship with thrust, and wherein the engine control parameter is a fan speed (N1); control the display unit (20) to display a scale; control the display unit (20) to display first symbol (8) having a position relative to the scale using a non-linear scaling function in the region from zero fan speed to maximum nominal fan speed (N1Max), where sensitivity is reduced at zero fan speed and sensitivity is increased at maximum nominal fan speed, the first symbol (8) representing the obtained fan speed value (N1); control the display unit (20) to display second symbol (6) representing a target fan speed (N1Targ).
9. System according to claim 8, characterized in that the nonlinear scaling function is a polynomial function.
10. System according to any one of claims 8 or 9, characterized in that it further comprises computer memory (18) having a lookup table stored therein, wherein said lookup table comprises fan speed values (N1) and corresponding symbol positions of the first symbol (8) relative to the scale, and the display control processor is configured to retrieve the position of the first symbol (8) relative to the scale from said lookup table.
11. System according to any one of claims 8 or 9, characterized in that the scale is a circular arc and the first symbol (8) is a radial line that originates at a center of, and intersects, the circular arc at an angular position.
12. System according to claim 11, characterized in that it further comprises computer memory (18) having a lookup table stored therein, wherein said lookup table comprises fan speed values (N1) and corresponding symbol positions of said radial line relative to the scale, and said display control processor is configured to retrieve the angular position of the radial line relative to the circular arc from a lookup table.
13. System according to any one of claims 8 to 12, characterized in that the display control processor is further configured to control said display unit (20) to display a discrete indication that thrust has been adjusted to a takeoff thrust value that is within a specified tolerance of a desired takeoff thrust value, wherein said display control processor is configured to control said display unit (20) to display third symbology (10), and wherein the display of a discrete indication comprises changing the color of the third symbology.

Description

FUNDAMENTALS [001] The technology described herein generally refers to systems and methods for displaying aircraft engine characteristics, such as engine operating states, to the flight crew of an aircraft. In particular, the technology described herein refers to display systems and methods for use in indicating the thrust and fan speed of an aircraft turboprop engine. [002] In controlling the thrust of a turboprop engine, and especially when causing selected changes in the thrust output of such an engine, it is important that a thrust control system provide both an accurate and stable indication of thrust. In addition, aircraft are required to provide tachometer indications of engine rotor speeds, including fan speed (N1). Some commercial transport aircraft with turboprop engines use N1 itself as the thrust adjustment parameter. Providing acceptable accuracy and stability in displaying N1, serving as both the tachometer and the thrust adjustment parameter, has long been a problem in the art. This is mainly because the relationship between N1 and thrust is non-linear, resulting in loss of resolution at the upper end (near maximum or takeoff thrust) of the scale. Small changes in N1 at the upper end of the range correspond to large changes in thrust (greater than the same change in N1 at the lower end of the fan speed range). This can make it difficult for the pilot to determine a target thrust setting due to the low resolution of the display. As a result, a pilot may have difficulty detecting or adjusting small increments of thrust at high thrust. [003] It would be advantageous to provide a means of increasing the resolution at the upper end of the N1 scale as well as other visual indications to show the pilot that the engine is providing the desired thrust. SUMMARY [004] The matter described in detail below is directed to systems and methods for displaying the N1 fan speed in a manner that provides increased resolution at the upper end of the operating range. This is achieved by variable scale(s) that improve(s) the functionality of the N1 indicator (as a thrust indicator) in the desired region. Also, there is visual indication to provide pilots with the ability to discern whether the current thrust is within a specific tolerance for the desired value within the takeoff region. This additional indication is obtained by color changes associated with the N1 display structure. [005] The display described in detail below provides increased performance of the N1 display parameter and can support a reduction in the number of engine displays required in the cockpit (e.g., N1 only, instead of N1 and a different dedicated thrust setting parameter, such as engine pressure ratio (EPR)). The display described here can also increase the pilot's ability to determine the thrust setting. [006] One aspect of the matter described in detail below is a computer-implemented method for displaying aircraft engine information, comprising: obtaining a value of an engine control parameter during the operation of an aircraft engine, wherein the engine control parameter has a non-linear relationship with thrust; displaying in a display unit (20) symbology representing the engine control parameter at positions relative to the scale using a non-linear scaling function. In the embodiments described, the engine control parameter is the fan speed (N1). The non-linear scaling function may be an algebraic function (e.g., a polynomial) or a lookup table, providing the desired symbology positions on the scale corresponding to each possible value of the fan speed. In the embodiments described, the scale is a circular arc and the symbology is a radial line originating at a center of, and intersecting, the circular arc at an angular position. The method may further comprise displaying a discreet indication that thrust has been adjusted to a takeoff thrust value that is within a specified tolerance of a desired takeoff thrust value. [007] Another aspect of the matter described in detail below is a system for indicating aircraft engine information on board an aircraft, comprising: a display unit (20) that can be electronically controlled to generate symbology and colors; and a display control processor configured to control the display unit (20) to generate indicators that show the current fan speed of an operating aircraft engine, wherein the display control processor is configured to perform the following operations: obtain a value of an engine control parameter during engine operation, wherein the engine control parameter has a non-linear relationship with thrust; control the display unit (20) to display a scale; and control the display unit (20) to display symbology having the position relative to the scale using a non-linear scaling function, the symbology representing the value obtained from the engine control parameter. In the embodiments described, the engine control parameter is the fan speed. The non-linear scaling function may be a poly