초록 ▼

A method is presented for controlling thrust generated by aircraft engines. Engine thrust is controlled based on aircraft groundspeed and airspeed during the initial part of takeoff. Limiting thrust at low groundspeed during the initial phase of takeoff has significant benefits that reduce engine st

A method is presented for controlling thrust generated by aircraft engines. Engine thrust is controlled based on aircraft groundspeed and airspeed during the initial part of takeoff. Limiting thrust at low groundspeed during the initial phase of takeoff has significant benefits that reduce engine stress during this brief but critical phase leading to flight. Logical elements combine both groundspeed and airspeed in such a way that the operator perceives a smooth progressive thrust increase consistent with normal engine operation.

대표청구항 ▼

1. A method for controlling thrust generated by an engine for an aircraft, the method comprising: receiving, in a thrust control unit, a command for a selected thrust mode for the aircraft, wherein the selected thrust mode comprises at least one of: takeoff thrust, and maximum thrust;responsive to r

1. A method for controlling thrust generated by an engine for an aircraft, the method comprising: receiving, in a thrust control unit, a command for a selected thrust mode for the aircraft, wherein the selected thrust mode comprises at least one of: takeoff thrust, and maximum thrust;responsive to receiving the command, controlling a level of thrust provided by the engine for the aircraft based on factors comprising: a determination of an undesired engine parameter before the undesired engine parameter occurs, a groundspeed of the aircraft, and an airspeed of the aircraft, wherein the undesired engine parameter comprises at least one of: an engine fan blade threshold, and an engine speed limit, wherein the controlling step comprises:providing the level of thrust as a lower level of thrust set by a groundspeed limit, and an airspeed limit;determining whether a current groundspeed exceeds a first threshold; determining whether a current airspeed exceeds a second threshold; responsive to the current groundspeed exceeding the first threshold, disabling the groundspeed limit from being used to control the level of thrust; andresponsive to the current airspeed exceeding the second threshold, disabling the groundspeed limit from being used to control the level of thrust. 2. The method of claim 1, wherein the controlling step comprises: responsive to receiving the command for the selected level of thrust, using a lower limit of the thrust set by a groundspeed limit and an airspeed limit to control the level of thrust of the engine for the aircraft; andproviding the level of thrust based on the selected thrust mode and the lower limit of the thrust, wherein the level of thrust is a continuous increase in the thrust limited by the groundspeed limit and the airspeed limit. 3. The method of claim 1, wherein the groundspeed limit and the airspeed limit avoid thrust levels that increase engine fan blade vibrations above a desired level. 4. The method of claim 1, wherein the controlling step comprises: responsive to using the groundspeed limit for the thrust, providing an upper thrust limit to continuously increase the level of thrust to, as a ramp function based on the groundspeed. 5. The method of claim 4, wherein the controlling step further comprises: disabling the groundspeed limit from being used to control the level of thrust if the groundspeed is invalid. 6. The method of claim 1, wherein the controlling step further comprises: responsive to disabling the groundspeed limit above a selected speed, re-enabling the groundspeed limit for use in controlling the level of thrust if the command for a selected thrust mode is less than the groundspeed limit and the groundspeed falls below a selected groundspeed. 7. The method of claim 1, wherein the controlling step further comprises: disabling the airspeed limit from being used to control the level of thrust if the airspeed is greater than an airspeed threshold. 8. The method of claim 7, wherein the controlling step further comprises: re-enabling the airspeed limit after the airspeed limit has been disabled if the airspeed is less than a second threshold, wherein the groundspeed is valid and the command for the selected thrust mode is less than the airspeed limit. 9. The method of claim 1, wherein the groundspeed limit is selected from one of a table and a set of equations that provide the level of thrust based on the groundspeed. 10. The method of claim 1, wherein the airspeed limit is a hysteresis function. 11. The method of claim 1, wherein the groundspeed limit and the airspeed limit are only used while the aircraft is on a ground. 12. The method of claim 1 further comprising: displaying the selected thrust mode on a display device. 13. A method for controlling thrust provided to an aircraft, the method comprising: receiving, in a thrust control unit, a command for a selected thrust mode for the aircraft wherein the selected thrust mode comprises at least one of: takeoff thrust, and a maximum thrust;determining a lower thrust limit for the selected thrust mode, wherein the lower thrust limit for the selected thrust mode is based on factors comprising: a groundspeed of the aircraft, and an airspeed of the aircraft;responsive to receiving the command, controlling a level of thrust provided by an engine to the aircraft at a lesser of the selected thrust mode or the lower thrust limit for the selected thrust mode, wherein the controlling step comprises:determining whether a current groundspeed exceeds a first threshold;determining whether a current airspeed exceeds a second threshold;responsive to the current groundspeed exceeding the first threshold, disabling the groundspeed limit from being used to control the level of thrust; andresponsive to the current airspeed exceeding the second threshold, disabling the groundspeed limit from being used to control the level of thrust. 14. The method of claim 13, wherein the selected thrust mode is a percentage of maximum thrust. 15. The method of claim 14, wherein the selected thrust mode is takeoff thrust. 16. The method of claim 13, wherein the factors determining the lower thrust limit for the selected thrust mode further comprise a determination of an undesired engine parameter before the undesired engine parameter occurs. 17. A method for avoiding undesired engine blade stress in an engine of an aircraft, the method comprising: receiving, in a thrust control unit, a command to provide a selected thrust mode, wherein the selected thrust mode comprises at least one of: takeoff thrust, and a maximum thrust;determining a lower thrust limit for the selected thrust mode, wherein the determination is based on factors comprising: a determination of an undesired engine parameter before the undesired engine parameter occurs, a groundspeed of the aircraft, and an airspeed of the aircraft, wherein the undesired engine parameter comprises at least one of: an engine fan blade threshold, and an engine speed limit;responsive to receiving the command, controlling a level of thrust provided by the engine at a lesser of the selected thrust mode and the lower thrust limit for the selected thrust mode, wherein the controlling the level of thrust comprises:determining whether a current groundspeed exceeds a first threshold;determining whether a current airspeed exceeds a second threshold;responsive to the current groundspeed exceeding the first threshold, disabling the groundspeed limit from being used to control the level of thrust; andresponsive to the current airspeed exceeding the second threshold, disabling the groundspeed limit from being used to control the level of thrust. 18. The method of claim 17, wherein the selected thrust mode is takeoff thrust for the engine while the aircraft is on a takeoff roll, and wherein the lower thrust limit for the selected thrust mode is continuously determined from before the takeoff roll until the aircraft is airborne and the command for the selected thrust mode is no longer received. 19. The method of claim 18, wherein the command to provide takeoff thrust is received with an aircraft wheel brake applied.