Aircraft flight envelope protection and recovery autopilot

• US 10,228,692 B2
• Filed: 03/27/2017
• Issued: 03/12/2019
• Est. Priority Date: 03/27/2017
• Status: Active Grant

• Current Assignee: Gulfstream Aerospace Corporation (General Dynamics Corporation)
• Original Assignee: Gulfstream Aerospace Corporation (General Dynamics Corporation)
• Inventors: Prosser, Kevin
• Primary Examiner(s): Kan, Yuri
• Application Number:
  US15/470,776
• Publication Number:
  US 20180275651A1
• Time in Patent Office: 715 Days
• CPC Class Codes: B64C 13/18 using automatic pilot
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa
• CPC Class Codes: G05D 1/0825 using mathematical models
• CPC Class Codes: G05D 1/81 Handing over between on-board automatic and on-board manual control
• CPC Class Codes: G06N 3/00 Computing arrangements based on biological models
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0086 for monitoring terrain radar or analogous systems specially adapted for terrain avoidance G01S13/935
• CPC Class Codes: G08G 5/0091 for monitoring atmospheric conditions radar or analogous systems specially adapted for meteorological use G01S13/95; meteorology G01W
• CPC Class Codes: G08G 5/025 Navigation or guidance aids radar or analogous systems specially adapted for landing purposes G01S13/913
• CPC Class Codes: G08G 5/045 Navigation or guidance aids, e.g. determination of anti-collision manoeuvers radar or analogous systems specially adapted for anti-collision between aircraft G01S13/933

Abstract

Systems and aircraft are provided. An avionics system for an aircraft includes: a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition; a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path; a limit comparison module configured to determine whether the modeled flight condition violates aircraft limits; and a violation indicator module configured to generate an indication of impending violation.

Claims

1. An avionics system for an aircraft, the avionics system comprising:

a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;

a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path, wherein the trajectory flight condition module comprises;

a vertical velocity module configured to calculate a vertical velocity of the aircraft on the potential aircraft path;

an energy state module configured to calculate an energy state of the aircraft on the potential aircraft path; and

an airspeed prediction module configured to estimate an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state;

a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit; and

a violation indicator module configured to generate an indication of impending violation.

2. The avionics system of claim 1, wherein the energy state module is further configured to calculate the energy state based on a rate of climb of the aircraft at full power and on a rate of descent of the aircraft at idle power.

3. The avionics system of claim 2, wherein the energy state module is further configured to calculate the energy state based on a current power setting of the aircraft, a current power capability of the aircraft, a speedbrake position on the aircraft, a landing gear setting, a flap setting, and an engine health of the aircraft.

8. The avionics system of claim 1, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit.

9. The avionics system of claim 1, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a capability limit as the aircraft limit.

10. The avionics system of claim 1, further comprising a terrain conflict module configured to determine whether the potential aircraft path indicates a terrain conflict, and wherein the violation indication module is further configured to generate the indication of impending violation based on the terrain conflict.

4. An avionics system for an aircraft, the avionics system comprising:

a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;

a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path;

a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit;

a violation indicator module configured to generate an indication of impending violation; and

a potential path generation module configured to generate a plurality of trajectories from which the trajectory selection module selects the potential aircraft path, wherein the trajectory selection module is configured to select a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path.

5. The avionics system of claim 4, wherein the potential path generation module is further configured to generate the plurality of trajectories to cover at least six different directions for a potential escape recovery.

6. The avionics system of claim 4, wherein the potential path generation module is further configured to generate a landing path of the plurality of trajectories in response to a potential landing indicator, wherein the limit comparison module is configured to determine whether the aircraft will violate the aircraft limit by following the landing path.

7. The avionics system of claim 6, further comprising a recovery autopilot configured to guide the aircraft along the potential aircraft path in response to the potential aircraft path being a last trajectory of the plurality of trajectories to lack a violation indication.

20. The avionics system of claim 4, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit.

21. The avionics system of claim 4, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a capability limit as the aircraft limit.

22. The avionics system of claim 4, further comprising a terrain conflict module configured to determine whether the potential aircraft path indicates a terrain conflict, and wherein the violation indication module is further configured to generate the indication of impending violation based on the terrain conflict.

11. An aircraft comprising:

a sensor system configured to provide aircraft flight condition data;

an actuator system configured to manipulate control surfaces of the aircraft; and

a control system comprising;

a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;

a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path, wherein the trajectory flight condition module comprises;

a vertical velocity module configured to calculate a vertical velocity of the aircraft on the potential aircraft path;

an energy state module configured to calculate an energy state of the aircraft on the potential aircraft path; and

an airspeed prediction module configured to estimate an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state;

a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit; and

a violation indicator module configured to generate an indication of impending violation.

12. The aircraft of claim 11, wherein the energy state module is further configured to calculate the energy state based on a rate of climb of the aircraft at full power and on a rate of descent of the aircraft at idle power.

13. The aircraft of claim 12, wherein the energy state module is further configured to calculate the energy state based on a current power setting of the aircraft, a current power capability of the aircraft, a speedbrake position on the aircraft, a landing gear setting, a flap setting, and an engine health of the aircraft.

18. The aircraft of claim 11, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit.

14. An aircraft comprising:

a sensor system configured to provide aircraft flight condition data;

an actuator system configured to manipulate control surfaces of the aircraft; and

a control system comprising;

a trajectory selection module configured to select a potential aircraft path relative to a current aircraft flight condition;

a trajectory flight condition module configured to estimate a modeled flight condition of the aircraft along the potential aircraft path;

a limit comparison module configured to determine whether the modeled flight condition violates an aircraft limit;

a violation indicator module configured to generate an indication of impending violation; and

a potential path generation module configured to generate a plurality of trajectories from which the trajectory selection module selects the potential aircraft path, wherein the trajectory selection module is configured to select a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path.

15. The aircraft of claim 14, wherein the potential path generation module is further configured to generate the plurality of trajectories to cover at least six different directions for a potential escape recovery.

16. The aircraft of claim 14, wherein the potential path generation module is further configured to generate a landing path of the plurality of trajectories in response to a potential landing indicator, wherein the limit comparison module is configured to determine whether the aircraft will violate the aircraft limit by following the landing path.

17. The aircraft of claim 16, wherein the control system further comprises a recovery autopilot configured to guide the aircraft along the potential aircraft path in response to the potential aircraft path being a last trajectory of the plurality of trajectories to lack a violation indication.

19. The aircraft of claim 14, wherein the limit comparison module is configured to determine whether the modeled flight condition violates a predetermined passenger comfort limit as the aircraft limit.

23. An avionics system for an aircraft, the avionics system comprising:

means for selecting a potential aircraft path relative to a current aircraft flight condition;

means for estimating a modeled flight condition of the aircraft along the potential aircraft path, wherein the means for estimating a modeled flight condition of the aircraft along the potential path comprises;

means for calculating a vertical velocity of the aircraft on the potential aircraft path;

means for calculating an energy state of the aircraft on the potential aircraft path; and

means for estimating an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state; and

means for determining whether the modeled flight condition violates an aircraft limit; and

means for generating an indication of impending violation.

24. An avionics system for an aircraft, the avionics system comprising:

means for selecting a potential aircraft path relative to a current aircraft flight condition;

means for estimating a modeled flight condition of the aircraft along the potential aircraft path;

means for determining whether the modeled flight condition violates an aircraft limit;

means for generating an indication of impending violation; and

means for generating a plurality of trajectories from which to select the potential aircraft path, wherein the means for generating a plurality of trajectories is configured to select a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path.

25. An aircraft comprising:

means for providing aircraft flight condition data;

means for manipulating control surfaces of the aircraft; and

means for;

selecting a potential aircraft path relative to a current aircraft flight condition;

estimating a modeled flight condition of the aircraft along the potential aircraft path, comprising;

calculating a vertical velocity of the aircraft on the potential aircraft path;

calculating an energy state of the aircraft on the potential aircraft path; and

estimating an airspeed of the aircraft on the potential aircraft path based on the vertical velocity and the energy state;

determining whether the modeled flight condition violates an aircraft limit; and

generating an indication of impending violation.

26. An aircraft comprising:

means for providing aircraft flight condition data;

means for manipulating control surfaces of the aircraft; and

means for;

selecting a potential aircraft path relative to a current aircraft flight condition;

estimating a modeled flight condition of the aircraft along the potential aircraft path;

determining whether the modeled flight condition violates an aircraft limit;

generating an indication of impending violation; and

generating a plurality of trajectories from which to select the potential aircraft path, wherein generating a plurality of trajectories includes selecting a next consecutive trajectory of the plurality of trajectories as the potential aircraft path upon a completed evaluation of a previous potential path.