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. An aircraft recovery control unit, the aircraft recovery control unit comprising: a processor and communication circuitry, wherein the processor is configured to connect via the communication circuitry to a flight display and a plurality of data instruments that obtain respective in-flight parame
1. An aircraft recovery control unit, the aircraft recovery control unit comprising: a processor and communication circuitry, wherein the processor is configured to connect via the communication circuitry to a flight display and a plurality of data instruments that obtain respective in-flight parameters associated with an aircraft, and the processor is further configured to: receive flight data from the plurality of data instruments, the flight data indicative of at least a speed of the aircraft and a position of the aircraft, the position defining a pitch and roll of the aircraft;retrieve a 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;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 the flight envelope that is defined by a manufacturer of the aircraft, so as to place the aircraft in a recovery state; andduring the recovery state, cause an aircraft reference representative of a current flight condition, and an overlay of a moving target immediately over the aircraft reference, to be displayed on the flight display, the overlay defining 1) an area indicative of the unstable condition and 2) the moving target separated from the area, the moving target representative of the aircraft returning to a level flight condition from the current flight condition at a constant rate of change,wherein the moving target and the aircraft reference are continuously updated responsive to the speed of the aircraft, the pitch of the aircraft, and the roll of the aircraft, and the aircraft transitions out of the recovery state when a pilot controls the speed of aircraft, the pitch of the aircraft, and the roll of the aircraft, so as to place the aircraft reference within the moving target. 2. The aircraft recovery control unit of claim 1, wherein the moving target includes a box, and the aircraft reference is within the box when aircraft returns to the level flight condition. 3. The aircraft recovery control unit of claim 2, wherein the box is a first color, and an area outside the box is a second color that is different than the first color. 4. The aircraft recovery control unit of claim 1, wherein, during the recovery state, the processor is further configured to display text indicating that thrust of the aircraft should be increased or decreased. 5. The aircraft recovery control unit of claim 1, wherein the processor is further configured to, when the recovery sequence is triggered, render one or more aural commands indicating that thrust of the aircraft should be increased or decreased. 6. The aircraft recovery control unit of claim 1, wherein the processor is further configured to be operable in a plurality of aircrafts, each aircraft associated with a respective flight envelope. 7. An aircraft comprising: a plurality of data instruments that obtain respective in-flight parameters associated with the aircrafta flight display configured to display flight guidance to a pilot of the aircraft; andan aircraft control unit communicatively connected to the flight display and the plurality of data instruments, the aircraft control unit configured to: receive flight data from the plurality of data instruments, the flight data indicative of at least a speed of the aircraft and a position of the aircraft, the position defining a pitch and roll of the aircraft;retrieve a 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;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 the flight envelope that is defined by a manufacturer of the aircraft, so as to place the aircraft in a recovery state; andduring the recovery state cause an aircraft reference representative of a current flight condition, and an overlay of a moving target immediately over the aircraft reference, to be displayed on the flight display, the overlay defining 1) an area indicative of the unstable condition and 2) the moving target separated from the area, the moving target representative of the aircraft returning to a level flight condition from the current flight condition at a constant rate of change,wherein the moving target and the aircraft reference are continuously updated responsive to the speed of the aircraft, the pitch of the aircraft, and the roll of the aircraft, and the aircraft transitions out of the recovery state when the pilot controls the speed of aircraft, the pitch of the aircraft, and the roll of the aircraft, so as to place the aircraft reference within the moving target. 8. The aircraft of claim 7, wherein the plurality of data instruments comprise an attitude system and an air data computer. 9. The aircraft of claim 7, 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, an 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. 10. A method performed by an aircraft, wherein the aircraft comprises a processor, a flight display, and a plurality of data instruments that obtain respective in-flight parameters associated with the aircraft, the method comprising: obtaining, by ones of the plurality of data instruments, flight data indicative of at least a speed of the aircraft and a position of the aircraft, the position defining a pitch and roll of the aircraft;storing a 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;based on the flight data and the flight envelope, determining, by the processor, that the aircraft will enter an unstable condition;in response to determining that the aircraft will enter the unstable condition, triggering, by the processor, a recovery sequence before the aircraft enters the unstable condition and before the aircraft exits a recovery perimeter within the flight envelope that is defined by a manufacturer of the aircraft, so as to place the aircraft in a recovery state; andduring the recovery state, causing an aircraft reference representative of a current flight condition, and an overlay of a moving target immediately over the aircraft reference, to be displayed on the flight display, the overlay defining 1) an area indicative of the unstable condition and 2) the moving target separated from the area, the moving target representative of the aircraft returning to a level flight condition from the current flight condition at a constant rate of change,wherein the moving target and the aircraft reference are continuously updated responsive to the speed of the aircraft, the pitch of the aircraft, and the roll of the aircraft, and the aircraft transitions out of the recovery state when a pilot controls the speed of aircraft, the pitch of the aircraft, and the roll of the aircraft, so as to place the aircraft reference within the moving target. 11. The method of claim 10, wherein the moving target includes a box, and the aircraft reference is within the box when the aircraft returns to the level flight condition. 12. The method of claim 11, wherein the box is a first color, and an area outside the box is a second color that is different than the first color. 13. The method of claim 10, the method further comprising: during the recovery state, displaying text indicating that thrust of the aircraft should be increased or decreased. 14. The method of claim 10, wherein triggering the recovery sequence comprises rendering one or more aural commands indicating that thrust of the aircraft should be increased or decreased. 15. The method of claim 10, wherein triggering the recovery comprises changing an operation of the aircraft at a constant rate until the aircraft operates within the recovery perimeter. 16. The method of claim 10, wherein triggering the recovery comprises rendering an audible alarm. 17. The method of claim 10, wherein the plurality of data instruments comprise an attitude system and an air data computer.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (10)
Bateman,Charles D.; Gover,John H.; Johnson,Steven C., Aircraft autorecovery systems and methods.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.