Methods and systems to detect and alert a dynamic rollover condition for an aircraft

• US 10,099,802 B2
• Filed: 02/14/2017
• Issued: 10/16/2018
• Est. Priority Date: 02/14/2017
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Reddy, Mahipal, Songa, Anil Kumar
• Primary Examiner(s): Frejd, Russell
• Application Number:
  US15/431,997
• Publication Number:
  US 20180229857A1
• Time in Patent Office: 609 Days
• CPC Class Codes: B64C 27/006 Safety devices
• 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 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64D 45/04 Landing aids; Safety measures to prevent collision with earth's surface
• CPC Class Codes: B64D 45/08 optical
• CPC Class Codes: G01S 19/13 Receivers
• CPC Class Codes: G05D 1/0055 with safety arrangements
• 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

Abstract

A method for providing data associated with rollover of an aircraft is provided. The method detects a potential dynamic rollover condition for the aircraft based on at least one of a current rotor thrust, a slope of terrain surrounding the aircraft, a state of ground contact components, and a position of a lateral center of gravity, by at least one processor onboard the aircraft, wherein the potential dynamic rollover condition indicates imminent rollover of the aircraft occurring within a predetermined period of time; and presents an alert associated with the potential dynamic rollover condition via an aircraft onboard display communicatively coupled to the at least one processor.

Claims

1. A method for providing data associated with rollover of an aircraft, the method comprising:

detecting a potential dynamic rollover condition for the aircraft based a state of ground contact components, by at least one processor onboard the aircraft, by;

detecting whether the ground contact components associated with one lateral side of the aircraft are currently contacting ground, wherein the ground contact components comprise at least one of aircraft skids and aircraft wheels; and

when the ground contact components associated with one lateral side of the aircraft are currently contacting ground, determining existence of the potential dynamic rollover condition;

wherein the potential dynamic rollover condition indicates imminent rollover of the aircraft occurring within a predetermined period of time; and

presenting an alert associated with the potential dynamic rollover condition via an aircraft onboard display communicatively coupled to the at least one processor, by;

presenting a set of graphical elements representing a collective cue and bracket, via a display device communicatively coupled to the at least one processor; and

presenting an alert graphical element in proximity to the set of graphical elements, wherein the alert graphical element comprises distinguishing visual characteristics distinct from the set of graphical elements, and wherein the alert graphical element indicates a collective input limit for avoiding the potential dynamic rollover condition.

2. The method of claim 1, wherein detecting the potential dynamic rollover condition further comprises:

detecting a total weight of the aircraft at time of door closing;

comparing the total weight to the current rotor thrust of the aircraft; and

when the current rotor thrust of the aircraft is within a first predetermined threshold of the total weight of the aircraft, determining existence of the potential dynamic rollover condition.

3. The method of claim 1, wherein detecting the potential dynamic rollover condition further comprises:

during takeoff or landing, detecting the slope of terrain surrounding the aircraft, wherein the slope is detected using at least one of a terrain analyzer, a terrain database, and aircraft sensors communicatively coupled to the at least one processor; and

when the slope exceeds a predetermined slope threshold, determining existence of the potential dynamic rollover condition.

4. The method of claim 1, wherein detecting the potential dynamic rollover condition further comprises:

detecting whether a shift in the lateral center of gravity for the aircraft around a pivot point of the aircraft has occurred, based on aircraft critical parameters including at least a roll angle, wind speed, yaw rate, cross wind parameters, altitude, and attitude; and

when the lateral center of gravity of the aircraft has passed the pivot point of the aircraft, determining existence of the potential dynamic rollover condition.

5. The method of claim 1, wherein presenting the alert further comprises:

presenting a set of graphical elements representing cyclic control of the aircraft, wherein the set of graphical elements comprise at least a forward indicator, an aft indicator, a left indicator, and a right indicator; and

presenting one of the set of graphical elements using distinguishing visual characteristics to indicate a cyclic control input limit for avoiding the potential dynamic rollover condition.

6. The method of claim 1, wherein presenting the alert further comprises:

presenting a set of graphical elements representing a pedals control of the aircraft, wherein the set of graphical elements comprise at least a left indicator and a right indicator; and

presenting one of the set of graphical elements using distinguishing visual characteristics to indicate a pedals control input limit for avoiding the potential dynamic rollover condition.

7. A system for providing data associated with rollover of an aircraft, the system comprising:

a system memory element;

a display device, configured to present alerts onboard the aircraft;

a plurality of aircraft sensors communicatively coupled to the at least one processor, the plurality of aircraft sensors configured to detect positioning of ground contact components of the aircraft, wherein the ground contact components comprise at least one of aircraft skids and aircraft wheels; and

at least one processor communicatively coupled to the system memory element and the display device, the at least one processor configured to;

detect a potential dynamic rollover condition for the aircraft based on a state of the ground contact components by;

detecting whether the ground contact components associated with one lateral side of the aircraft are currently contacting ground, based on the detected positioning; and

when the ground contact components associated with one lateral side of the aircraft are currently contacting ground, determining existence of the potential dynamic rollover condition;

wherein the potential dynamic rollover condition indicates imminent rollover of the aircraft occurring within a predetermined period of time; and

present an alert associated with the potential dynamic rollover condition via the display device, by;

presenting a set of graphical elements representing a collective cue and bracket, via the display device; and

presenting an alert graphical element in proximity to the set of graphical elements, wherein the alert graphical element comprises distinguishing visual characteristics distinct from the set of graphical elements, and wherein the alert graphical element indicates a collective input limit for avoiding the potential dynamic rollover condition.

8. The system of claim 7, wherein the system further comprises a plurality of aircraft onboard sensors communicatively coupled to the at least one processor, the plurality of aircraft onboard sensors configured to detect a total weight of the aircraft and the current rotor thrust of the aircraft;

and

wherein the at least one processor is further configured to detect the potential dynamic rollover condition by;

comparing the total weight to the current rotor thrust of the aircraft; and

when the current rotor thrust of the aircraft is within a first predetermined threshold of the total weight of the aircraft, determining existence of the potential dynamic rollover condition.

9. The system of claim 7, wherein the system further comprises a terrain device comprising at least one of a terrain analyzer, a terrain database, and aircraft sensors communicatively coupled to the at least one processor, wherein the terrain device is configured to detect the slope of terrain surrounding the aircraft during takeoff or landing;

and

wherein the at least one processor is further configured to detect the potential dynamic rollover condition by;

determining whether the slope of terrain exceeds a predetermined slope threshold; and

when the slope exceeds the predetermined slope threshold, determining existence of the potential dynamic rollover condition.

10. The system of claim 7, wherein the system further comprises a plurality of aircraft sensors communicatively coupled to the at least one processor, the plurality of aircraft sensors configured to detect aircraft critical parameters including at least a roll angle, wind speed, yaw rate, cross wind parameters, altitude, and attitude;

and

wherein the at least one processor is further configured to detect the potential dynamic rollover condition by;

detecting whether a shift in the lateral center of gravity for the aircraft around a pivot point of the aircraft has occurred, based on the aircraft critical parameters; and

when the lateral center of gravity of the aircraft has passed the pivot point of the aircraft, detecting existence of the potential dynamic rollover condition.

11. The system of claim 7, wherein the at least one processor is further configured to present the alert by:

presenting a set of graphical elements representing cyclic control of the aircraft, wherein the set of graphical elements comprise at least a forward indicator, an aft indicator, a left indicator, and a right indicator; and

presenting one of the set of graphical elements using distinguishing visual characteristics to indicate a cyclic control input limit for avoiding the potential dynamic rollover condition.

12. The system of claim 7, wherein the at least one processor is further configured to present the alert by:

presenting a set of graphical elements representing a pedals control of the aircraft, wherein the set of graphical elements comprise at least a left indicator and a right indicator; and

presenting one of the set of graphical elements using distinguishing visual characteristics to indicate a pedals control input limit for avoiding the potential dynamic rollover condition.

13. A non-transitory, computer-readable medium containing instructions thereon, which, when executed by a processor, perform a method comprising:

identifying, onboard an aircraft, a condition indicating imminent dynamic rollover of the aircraft based on at least one of a current rotor thrust, a slope of terrain surrounding the aircraft, a state of ground contact components, and a position of a lateral center of gravity, by;

detecting whether the ground contact components associated with one lateral side of the aircraft are currently contacting ground, wherein the ground contact components comprise at least one of aircraft skids and aircraft wheels; and

when the ground contact components associated with one lateral side of the aircraft are currently contacting ground, determining existence of the imminent dynamic rollover of the aircraft; and

presenting a notification of a corrective action, by a display device onboard the aircraft, wherein the corrective action mitigates factors associated with the imminent dynamic rollover.

14. The non-transitory, computer-readable medium of claim 13, wherein identifying the condition further comprises:

detecting a total weight of the aircraft, by one or more aircraft onboard sensors;

comparing the total weight to the current rotor thrust of the aircraft; and

when the current rotor thrust of the aircraft is within a first predetermined threshold of the total weight of the aircraft, determining existence of the potential dynamic rollover condition.

15. The non-transitory, computer-readable medium of claim 13, wherein identifying the condition further comprises:

during takeoff or landing, detecting the slope of terrain surrounding the aircraft, wherein the slope is detected using at least one of a terrain analyzer, a terrain database, and aircraft sensors communicatively coupled to the at least one processor; and

when the slope exceeds a predetermined slope threshold, determining existence of the potential dynamic rollover condition.

16. The non-transitory, computer-readable medium of claim 13, wherein identifying the condition further comprises:

identifying a takeoff condition of the aircraft;

detecting whether one or more ground contact components of the aircraft is secured to ground; and

when the one or more ground contact components is secured to ground, determining existence of the potential dynamic rollover condition.