Despite pilot training and current safety systems, aircraft accidents continue to occur. It is recognized herein that existing approaches to preventing aircraft accidents lack capabilities. A predictive aircraft recovery control unit can receive flight data from the plurality of data nodes. The flig
Despite pilot training and current safety systems, aircraft accidents continue to occur. It is recognized herein that existing approaches to preventing aircraft accidents lack capabilities. A predictive aircraft recovery control unit can receive flight data from the plurality of data nodes. The flight data can be indicative of at least a speed of the aircraft and a position of the aircraft. In some cases, based on the flight data, the predictive aircraft recovery control unit can determine that the aircraft will enter a stall condition. Furthermore, based on the flight data, the predictive aircraft recovery control unit can determine a time period that will elapse before the aircraft enters the stall condition. In response to determining that the aircraft will enter the stall condition after the time period elapses, the predictive aircraft recovery control until can trigger a recovery sequence before the aircraft enters the stall condition.
대표청구항▼
1. A predictive aircraft recovery control unit, comprising: a processor;a memory; andcommunication circuitry,wherein the processor is configured to connect via the communication circuitry to a plurality of data nodes that obtain respective in-flight parameters associated with an aircraft that includ
1. A predictive aircraft recovery control unit, comprising: a processor;a memory; andcommunication circuitry,wherein the processor is configured to connect via the communication circuitry to a plurality of data nodes that obtain respective in-flight parameters associated with an aircraft that includes a control column configured to shake based on an angle of attack of the aircraft, and the processor is further configured to: receive flight data from the plurality of data nodes, the flight data indicative of at least a speed of the aircraft and a position of the aircraft,based on the flight data, determine that the aircraft will enter a stall condition,based on the flight data, determine a time period that will elapse before the aircraft enters the stall condition,in response to determining that the aircraft will enter the stall condition after the time period elapses, trigger a recovery sequence before the aircraft enters the stall condition and before the aircraft exits a recovery perimeter within a flight envelope that is defined by a manufacturer of the aircraft, andtrigger the recovery sequence 1 to 30 seconds before the control column of the aircraft begins to shake based on the angle of attack of the aircraft to alert a pilot of the aircraft before the aircraft enters the stall condition. 2. The predictive aircraft recovery control unit of claim 1, wherein the flight data comprises the respective in-flight parameters that are indicative of at least one of an altitude of the aircraft, an airspeed of the aircraft, a vertical speed of the aircraft, the angle of attack of the aircraft, a thrust lever angle of the aircraft, an engine speed of the aircraft, a bank angle of the aircraft, a critical angle of attack of the aircraft, a flap position of the aircraft, and a landing gear position of the aircraft. 3. The predictive aircraft recovery control unit of claim 2, wherein the determining that the aircraft will enter the stall condition further comprises: computing a trend based on the flight data received over time, the trend predicting the respective in-flight parameters after the time period elapses;comparing the trend to predetermined values of the respective in-flight parameters, each predetermined value of the respective in-flight parameter representative of a respective tolerance; andbased on the comparison, determining that at least one of the respective in-flight parameters will be outside the respective tolerance when the time period elapses. 4. The predictive aircraft recovery control unit of claim 3, wherein computing the trend further comprises: computing a rate in which the angle of attack is increasing; andbased on the rate of increase, determining the angle of attack when the time period elapses, such that the angle of attack is greater than the critical angle of attack required to avoid the stall condition when the time period elapses. 5. The predictive aircraft recovery control unit of claim 4, wherein the time period is 1 to 30 seconds. 6. The predictive aircraft recovery control unit of claim 5, wherein the time period is 3 to 10 seconds. 7. The predictive aircraft recovery control unit of claim 1, wherein the processor is further configured to: retrieve the flight envelope associated with the aircraft, the flight envelope defining an operational boundary between a stable condition of the aircraft within the flight envelope and an unstable condition of the aircraft outside the flight envelope. 8. The predictive aircraft recovery control unit of claim 1, wherein the processor is further configured to: trigger the recovery sequence from 3 to 10 seconds before the aircraft exits the flight envelope. 9. The predictive aircraft recovery control unit of claim 1, wherein the processor is further configured to: trigger the recovery sequence from 3 to 10 seconds before the control column of the aircraft begins to shake. 10. The predictive aircraft recovery control unit of claim 1, wherein the triggering of the recovery sequence comprises: rendering an audible alarm. 11. The predictive aircraft recovery control unit of claim 1, wherein the triggering of the recovery sequence comprises: rendering a visual depiction representative of a corrective action, such that, when an auto flight system or the pilot of the aircraft complies with the corrective action, an operation of the aircraft is altered so as to avoid the stall condition. 12. The predictive aircraft recovery control unit of claim 11, wherein the visual depiction of the corrective action includes a box and an aircraft reference, and the aircraft reference is within the box when the auto flight system or the pilot of the aircraft complies with the corrective action. 13. The predictive aircraft recovery control unit of claim 12, wherein the corrective action includes increasing the airspeed of the aircraft and decreasing a pitch attitude of the aircraft so as to avoid the stall condition. 14. The predictive aircraft recovery control unit of claim 12, wherein the box is a first color, and an area outside the box is a second color that is different than the first color. 15. The predictive aircraft recovery control unit of claim 14, wherein the first color is green, and the second color is red. 16. The predictive aircraft recovery control unit of claim 11, wherein the visual depiction of correction action includes text indicating that thrust of the aircraft should be increased or decreased. 17. The predictive aircraft recovery control unit of claim 1, wherein the triggering of the recovery sequence comprises: rendering one or more aural commands indicating that thrust of the aircraft should be increased or decreased. 18. The predictive aircraft recovery control unit of claim 1, wherein the processor of aircraft recovery control unit is configured to be operable in a plurality of aircrafts, each aircraft associated with a respective flight envelope. 19. The predictive aircraft recovery control unit of claim 1, wherein the plurality of data nodes comprise an attitude system and an air data computer. 20. A method for predicting an unstable condition corresponding to flight of an aircraft and triggering a recovery sequence for the aircraft, wherein the aircraft comprises a control column configured to shake based on an angle of attack of the aircraft, the method comprising: receiving, by a processor, flight data from a plurality of data nodes, the flight data indicative of at least a speed of the aircraft and a position of the aircraft;based on the flight data, determining, by the processor, that the aircraft will enter a stall condition and determining a time period that will elapse before the aircraft enters the stall condition; andin response to determining that the aircraft will enter the stall condition after the time period elapses, triggering, by the processor, the recovery sequence before the aircraft enters the stall condition and before the aircraft exits a recovery perimeter within a flight envelope that is defined by a manufacturer of the aircraft; andtriggering the recovery sequence 1 to 30 seconds before the control column of the aircraft begins to shake based on the angle of attack of the aircraft to alert a pilot of the aircraft before the aircraft enters the stall condition. 21. The method of claim 20, wherein the flight data comprises in-flight parameters that are indicative of at least one of an altitude of the aircraft, an airspeed of the aircraft, a vertical speed of the aircraft, the angle of attack of the aircraft, a thrust lever angle of the aircraft, an engine speed of the aircraft, a bank angle of the aircraft, a critical angle of attack of the aircraft, a flap position of the aircraft, and a landing gear position of the aircraft. 22. A predictive aircraft recovery control unit, comprising: a processor;a memory; andcommunication circuitry, wherein the processor of the aircraft recovery control unit is configured to connect via the communication circuitry to a plurality of data nodes that obtain respective in-flight parameters associated with an aircraft that includes a control column configured to shake based on an angle of attack of the aircraft, and the processor is further configured to: receive flight data from the plurality of data nodes, the flight data comprising the respective in-flight parameters that are indicative of at least one of an altitude of the aircraft, an airspeed of the aircraft, a vertical speed of the aircraft, the angle of attack of the aircraft, a thrust lever angle of the aircraft, an engine speed of the aircraft, a bank angle of the aircraft, a critical angle of attack of the aircraft, a flap position of the aircraft, and a landing gear position of the aircraft;based on the flight data, determine that the aircraft will enter an unstable condition;in response to determining that the aircraft will enter the unstable condition, trigger a recovery sequence before the aircraft enters the unstable condition and before the aircraft exits a recovery perimeter within a flight envelope defined by a manufacturer of the aircraft, andtrigger the recovery sequence 1 to 30 seconds before the control column of the aircraft begins to shake based on the angle of attack of the aircraft to alert a pilot of the aircraft before the aircraft enters the unstable condition,wherein the triggering of the recovery sequence comprises rendering a visual depiction representative of a corrective action, such that, when the pilot of the aircraft complies with the corrective action, an operation of the aircraft is altered so as to avoid the unstable condition. 23. The predictive aircraft recovery unit of claim 22, wherein the visual depiction of the corrective action includes a box and an aircraft reference, wherein the aircraft reference is within the box when the pilot of the aircraft complies with the corrective action. 24. The aircraft recovery control unit of claim 23, wherein the corrective action includes increasing the airspeed of the aircraft and decreasing the attitude of the aircraft so as to avoid the unstable condition. 25. A method for predicting an unstable condition corresponding to flight of an aircraft and triggering a recovery sequence for the aircraft, wherein the aircraft comprises a control column configured to shake based on an angle of attack of the aircraft, the method comprising: receiving, by a processor, flight data from the plurality of data nodes, the flight data indicative of at least one of an altitude of the aircraft, an airspeed of the aircraft, a vertical speed of the aircraft, the angle of attack of the aircraft, a thrust lever angle of the aircraft, an engine speed of the aircraft, a bank angle of the aircraft, a critical angle of attack of the aircraft, a flap position of the aircraft, and a landing gear position of the aircraft;based on the flight data, determining, by the processor, that the aircraft will enter an unstable condition; andin response to determining that the aircraft will enter the unstable condition, triggering, by the processor, the recovery sequence before the aircraft enters the unstable condition and before the aircraft exits a recovery perimeter within a flight envelope defined by a manufacturer of the aircraft; andtriggering the recovery sequence 1 to 30 seconds before the control column of the aircraft begins to shake based on the angle of attack of the aircraft to alert a pilot of the aircraft before the aircraft enters the unstable condition,wherein the triggering of the recovery sequence comprises rendering a visual depiction representative of a corrective action, such that, when the pilot of the aircraft complies with the corrective action, an operation of the aircraft is altered so as to avoid the unstable condition. 26. The method of claim 25, wherein the visual depiction of the corrective action includes a box and an aircraft reference, and the aircraft reference is within the box when the pilot of the aircraft complies with the corrective action. 27. The method of claim 26, wherein the corrective action includes increasing the airspeed of the aircraft and decreasing a pitch attitude of the aircraft so as to avoid the unstable condition.
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이 특허에 인용된 특허 (10)
Bateman,Charles D.; Gover,John H.; Johnson,Steven C., Aircraft autorecovery systems and methods.
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