[미국특허]
Methods and systems to detect and alert a dynamic rollover condition for an aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-045/08
G08G-005/00
B64C-027/00
G05D-001/00
G01S-019/13
B64D-045/00
출원번호
US-0431997
(2017-02-14)
등록번호
US-10099802
(2018-10-16)
발명자
/ 주소
Reddy, Mahipal
Songa, Anil Kumar
출원인 / 주소
HONEYWELL INTERNATIONAL INC.
대리인 / 주소
Lorenz & Kopf, LLP
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
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 positi
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.
대표청구항▼
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 compon
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; andwhen 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; andpresenting 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; andpresenting 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; andwhen 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; andwhen 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; andwhen 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; andpresenting 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; andpresenting 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; andat 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; andwhen 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; andpresent 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; andpresenting 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; andwhen 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; andwhen 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; andwhen 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; andpresenting 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; andpresenting 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; andwhen 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; andpresenting 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; andwhen 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; andwhen 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; andwhen the one or more ground contact components is secured to ground, determining existence of the potential dynamic rollover condition.
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