Automatic flight control systems and methods

Patent metadata

Field	Value
Publication number	US-10606281-B2
Application number	US-201816202583-A
Country	US
Kind code	B2
Filing date	Nov 28, 2018
Priority date	Sep 11, 2017
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

An aircraft flight control system and method are provided. The system provides a control module that receives inertial data, sensor data, and a target airspeed. The control module processes the received data with aircraft thrust and drag models to evaluate the aircraft energy state. Based on the aircraft energy state, the control module determines (i) a maximum predicted potential flight path “max PPFP”, defined by a maximum thrust at the target airspeed, and (ii) an idle predicted potential flight path, “idle PPFP,” defined by an idle thrust at the target airspeed. The control module generates display commands for a display system to display (i) the flight path angle, (ii) the max PPFP and (iii) the idle PPFP. In addition, the control module generates and displays a predicted flight path speed indicator (PFPS) when the FPA is above the max PPFP or below the idle PPFP.

First claim

What is claimed is:

1. A method for providing flight path angle (FPA) information on a primary flight display (PFD) of an aircraft, the method comprising:
receiving, from a user interface, a target airspeed;
receiving, from a navigation system, navigation data comprising a flight path angle, attitude, and airspeed;
receiving, from on-board sensors, sensor data comprising environmental data and engine thrust status;
at a control module,
processing the navigation data, the sensor data, and the target airspeed, to determine (i) a maximum predicted potential flight path (max PPFP), defined by a maximum thrust at the target airspeed, and (ii) an idle predicted potential flight path (idle PPFP), defined by an idle thrust at the target airspeed;
commanding the PFD to render symbolic indicators for, (i) the flight path angle, and (ii) a first symbol that represents the max PPFP and a second symbol that represents the idle PPFP;
determining, when the max PPFP is greater than the FPA, and the FPA is greater than the idle PPFP, that the aircraft is in a speed controlled zone; and
commanding the PFD to display an indicator of an auto-throttle (A/T) mode in a first designated area, and a status annunciation in a second designated area, when the aircraft is in the speed controlled zone.

2. The method of claim 1 , further comprising, at the control module, when the aircraft is in the speed controlled zone:
determining that the A/T mode is active and the indicator for the A/T mode is an indication for speed; and
determining that the status annunciation is an indicator for cruise.

3. The method of claim 2 , further comprising:
at the control module,
determining when the FPA is more than a configurable predetermined upper margin above the max PPFP; and
when the FPA is more than a configurable predetermined upper margin above the max PPFP,
determining a predicted speed (PS) associated with the FPA; and
commanding the PFD to render a third symbol indicating the predicted speed (PS) on an airspeed indicator responsive thereto.

4. The method of claim 3 , further comprising:
at the control module,
commanding the PFD to display an indicator for maximum cruise in the first designated area on the PFD when the FPA is more than a configurable predetermined upper margin above the max PPFP.

5. The method of claim 4 , further comprising, at the control module, commanding the PFD to display an indicator for speed in the second designated area on the PFD when the FPA is more than a configurable predetermined upper margin above the max PPFP.

6. The method of claim 5 , further comprising, at the PFD, rendering the indicator for maximum cruise within an amber background.

7. The method of claim 1 , further comprising:
determining, by the control module, when the FPA is more than a configurable predetermined lower margin below the idle PPFP; and
when the FPA is more than a configurable predetermined lower margin below the idle PPFP,
determining a predicted speed (PS) associated with the FPA; and
commanding the PFD to render a third symbol indicating the predicted speed (PS) on an airspeed indicator responsive thereto.

8. The method of claim 7 , further comprising:
at the control module,
when the FPA is more than a configurable predetermined lower margin below the idle PPFP,

determining that the A/T mode is idle and the indicator for the A/T mode is an indication for idle; and
commanding the PFD to display the indicator for idle when the FPA is more than a configurable predetermined lower margin below the idle PPFP.

9. The method of claim 8 , further comprising, at the control module, commanding the PFD to display an indicator for speed in the second designated area on the PFD when the FPA is more than a configurable predetermined lower margin below the idle PPFP.

10. The method of claim 9 , further comprising rendering the indicator for idle within an amber background.

11. An aircraft flight control system for use with a primary flight display (PFD), the system comprising:
on-board sensors for providing sensor data comprising environmental data and sensed engine thrust data;
a navigation system for providing inertial data comprising a flight path angle, attitude, and airspeed;
a control module comprising a processor and a memory, the control module configured to:
receive the sensor data;
receive the inertial data;
receive a target airspeed;
process the inertial data, the sensor data, and the target airspeed, to determine (i) a maximum potential flight path (max PPFP), defined by a maximum thrust at the target airspeed, and an idle PPFP, defined by an idle thrust at the target airspeed; and
generate display commands for symbolic indicators of (i) the flight path angle,
(ii) the max PPFP and (iii) the idle PPFP;
determine that the aircraft is in a speed controlled zone when the max PPFP is greater than the FPA, and the FPA is greater than the idle PPFP; and
command the PFD to display an indicator of an auto-throttle (A/T) mode in a first designated area, and a status annunciation in a second designated area, when the aircraft is in the speed controlled zone; and
a primary flight display (PFD) coupled to the control module and configured to receive the display commands and render symbology and indicators responsive thereto.

12. The system of claim 11 , wherein the control module is further configured to:
when the aircraft is in the speed controlled zone,
determine that the A/T mode is active and that the indicator for the A/T mode is an indication for speed; and
determine that the status annunciation is an indicator for cruise.

13. The system of claim 12 , wherein the control module is further configured to:
when the aircraft is not in the speed control zone,
determine (a) when the FPA is more than a configurable predetermined upper margin above the max PPFP;
determine (b) when the FPA is more than a configurable predetermined lower margin below the idle PPFP;
in response to one of the conditions (a) and (b),
determine a predicted speed (PS) associated with the FPA; and
command the PFD to render a third symbol indicating the predicted speed (PS) on an airspeed indicator responsive thereto.

14. The system of claim 13 , wherein the control module is further configured to command the PFD to display an indicator for maximum cruise in the first designated area when the FPA is more than a configurable predetermined upper margin above the max PPFP.

15. The system of claim 14 , wherein the control module is further configured to command the PFD to display an indicator for speed in the second designated area when the FPA is more than a configurable predetermined upper margin above the max PPFP.

16. The system of claim 15 , wherein the control module is further configured to render the indicator for maximum cruise within an amber background.

17. The system of claim 13 , wherein the control module is further configured to command the PFD to display an indicator for idle in the first designated area when the FPA is more than a configurable predetermined lower margin below the idle PPFP.

18. The system of claim 17 , wherein the control module is further configured to render the indicator for idle within an amber background.

19. A method for an aircraft flight control system for use with a primary flight display (PFD), the method comprising:
at a control module,
receiving sensor data comprising environmental data and sensed engine thrust data, from on board sensors;
receiving navigation data comprising a flight p

Assignees

• Honeywell Int Inc

Inventors

• Wyatt Ivan Sandy
• Melendez Luis Ventura
• Koenig John
• Engels Jary

Classifications

• G01C23/005

  Flight directors (indicating arrangements specially adapted for rotary gyroscopes G01C19/32) · CPC title

• G05D1/00

  Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots (drive control systems specially adapted for autonomous road vehicles B60W60/00) · CPC title

• G05D1/0607 Primary

  specially adapted for aircraft · CPC title

• G05D1/0808 Primary

  specially adapted for aircraft · CPC title

• G05D1/101

  specially adapted for aircraft · CPC title