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A method, apparatus, and computer program product are present for operating an aircraft. Responsive to a command to hold an altitude of the aircraft, an adjustment to a pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft is identified using a lift for the aircra

A method, apparatus, and computer program product are present for operating an aircraft. Responsive to a command to hold an altitude of the aircraft, an adjustment to a pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft is identified using a lift for the aircraft to form an identified adjustment to the pitch angle to reduce altitude deviations from at least one of a change in configuration of a number of flight surfaces and changes in wind. The pitch angle of the aircraft is adjusted using the identified adjustment during flight.

대표청구항 ▼

1. A method for operating an aircraft, the method comprising: determining an output from a roll in logic based upon an OR gate processing outputs from dual AND gates processing logic unit outputs based upon inputs comprising: a roll rate, and a limited roll angle, for the aircraft;selecting, using t

1. A method for operating an aircraft, the method comprising: determining an output from a roll in logic based upon an OR gate processing outputs from dual AND gates processing logic unit outputs based upon inputs comprising: a roll rate, and a limited roll angle, for the aircraft;selecting, using the output from the roll in logic, at least one of: a roll in gain and a roll out gain;deriving a current lift for the aircraft, using a pitch angle adjustment system comprising at least one of: the roll in gain, and the roll out gain;responsive to a turning of the aircraft when holding an altitude, identifying, using the current lift for the aircraft, an identified adjustment to a pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft during the turning of the aircraft; andperforming the turning of the aircraft using the identified adjustment. 2. The method of claim 1, wherein the step of identifying the identified adjustment comprises: identifying a corrected coefficient of lift for the aircraft from the current lift for the aircraft;identifying a number of conversion values from a control surface configuration of the aircraft to form a number of identified conversion values; andapplying the number of identified conversion values to the corrected coefficient of lift to identify the adjustment to the pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft during the turning of the aircraft, using a coefficient of lift and a number of values for the aircraft to form the identified adjustment to the pitch angle from the coefficient of lift for the aircraft. 3. The method of claim 2, wherein the step of identifying the corrected coefficient of lift for the aircraft from the current lift for the aircraft comprises: identifying the corrected coefficient of lift using the roll rate, a roll angle of the aircraft, a weight of the aircraft, and a dynamic pressure on the aircraft during the turning of the aircraft. 4. The method of claim 3, wherein the roll rate is used to identify a roll trim lift and the roll angle is used to identify a wing lift during the turning of the aircraft. 5. The method of claim 2, wherein the number of conversion values comprises a slope and a y-intercept. 6. The method of claim 2, wherein the number of conversion values is a number of values representing a ratio of the pitch angle to the coefficient of lift. 7. The method of claim 2, wherein the current lift comprises: a lift loss component, from using control surfaces for the turning of the aircraft, and current lift component inputs to the pitch angle adjustment system, the components based upon a lift equation, L=0.7*2116*Delta*Mach*Mach*CL*S, comprising: an aircraft weight, a static air pressure, a sea level pressure, a mach number, and a wing area; wherein “S” comprises the wing area, “Mach” comprises the mach number, “Delta” comprises an atmospheric pressure ratio derived from the static air pressure and the sea level pressure, and “CL” comprises the coefficient of lift calculated from the aircraft weight. 8. The method of claim 6, further comprising, the roll in logic determining whether the aircraft is rolling into a turn or rolling out of the turn and then selecting a corresponding gain adjustment depending on an amount of change to the current lift, wherein a lift loss component from using control surfaces for the turning of the aircraft comprises the roll rate and a roll trim lift. 9. The method of claim 2, wherein the corrected coefficient of lift is as follows: corrected coefficient of lift=(weight of aircraft+roll trim lift+turning wing lift)/(cosine(roll angle)*dynamic pressure*wing area). 10. The method of claim 1, wherein the identifying step is performed dynamically during the turning of the aircraft. 11. The method of claim 1, wherein the identifying step is performed continuously during the turning of the aircraft. 12. The method of claim 1 further comprising: responsive to holding the altitude of the aircraft, identifying the adjustment to the pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft, using the current lift for the aircraft to form the identified adjustment to the pitch angle to reduce altitude deviations from at least one of a change in configuration of a number of flight surfaces and changes in wind; andadjusting the pitch angle of the aircraft using the identified adjustment during flight. 13. A method for operating an aircraft, the method comprising: responsive to a command to hold an altitude of the aircraft, reducing an altitude deviation of the aircraft by identifying an adjustment to a pitch angle of the aircraft,-using a pitch roll compensation for the aircraft;deriving, using a pitch angle adjustment system, a corrected coefficient of lift from inputs comprising a roll rate and a limited roll angle processed through a roll in logic selecting at least one of: a roll in gain, and a roll out gain, such that the roll in logic comprises an OR gate processing outputs from dual AND gates;deriving the pitch roll compensation, from inputs comprising: the corrected coefficient of lift, and at least one of: a configuration of a flap, a slat, a spoiler, a landing gear, and a landing gear door, of the aircraft; andadjusting the pitch angle of the aircraft using the adjustment during flight. 14. An apparatus comprising: processor unit configured to:identify, in response to a command to hold an altitude of an aircraft, an identified adjustment to a pitch angle of the aircraft;generate a limited roll angle;select at least one of: a roll in gain, and a roll out gain, based upon a roll rate and the limited roll angle processed through a roll in logic comprising an OR gate configured to process outputs from dual AND gates configured to process outputs from logic units configured to receive the roll rate and limited roll angle;derive a corrected coefficient of lift from inputs comprising: the roll rate, and the limited roll angle;form the identified adjustment based upon the corrected coefficient of lift for the aircraft;reduce altitude deviations caused by at least one of: a change in configuration of at least one of: a flap, a slat, a spoiler, a landing gear, and a landing gear door, of the aircraft; and change in a wind; andadjust, using the identified adjustment during flight, the pitch angle of the aircraft; anda computer configured to store and execute instructions for software on the processor unit. 15. An apparatus comprising: a processor unit configured to identify an adjustment, to a pitch angle during a turning of an aircraft, needed to substantially maintain an altitude of the aircraft, using a change in a current lift for the aircraft, such that the current lift is derived, in a pitch angle adjustment system, from inputs comprising: a roll rate, and a limited roll angle, to from an identified adjustment, such that the identified adjustment is identified, by the processor unit during the turning of the aircraft, from inputs comprising a pitch roll compensation, and such that the processor comprises a roll in logic configured to generate an output configured to select at least one of: a roll in gain, and a roll out gain based upon the roll rate and the limited roll angle, such that the roll in logic comprises logic units connected to AND gates connected to an OR gate; anda processor unit configured to perform the turning of the aircraft using the adjustment to the pitch angle of the aircraft. 16. The apparatus of claim 15, wherein in identifying the adjustment, to the pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft during the turning of the aircraft, using the current lift for the aircraft to form the identified adjustment to the pitch angle, the process is configured to identify a corrected coefficient of lift for the aircraft from the current lift for the aircraft; identifying a number of conversion values from a control surface configuration of the aircraft to form a number of identified conversion values; and applying the number of identified conversion values to a coefficient of lift to identify the adjustment to the pitch angle of the aircraft needed to substantially maintain the altitude of the aircraft during the turning of the aircraft, using the coefficient of lift and a number of values for the aircraft to form the identified adjustment to the pitch angle from the coefficient of lift for the aircraft. 17. The apparatus of claim 16, wherein in identifying the corrected coefficient of lift for the aircraft from the current lift for the aircraft, the process is capable of identifying the corrected coefficient of lift using the roll rate, a roll angle of the aircraft, a weight of the aircraft, and a dynamic pressure on the aircraft during the turning of the aircraft. 18. The apparatus of claim 17, wherein the roll rate is used to identify a roll trim lift and the roll angle is used to identify a turning wing lift. 19. The apparatus of claim 16, wherein the number of conversion values is a number of values representing a ratio of the pitch angle to the coefficient of lift. 20. The apparatus of claim 16, wherein the current lift comprises: a lift loss component from using control surfaces for the turning of the aircraft and current lift component inputs to the pitch angle adjustment system, the components based a lift equation, L=0.7*2116*Delta*Mach*Mach*CL*S, comprising: an aircraft weight, a static air pressure, a sea level pressure, a mach number, and a wing area; wherein “S” comprises the wing area, “Mach” comprises the mach number, “Delta” comprises an atmospheric pressure ratio derived from the static air pressure and the sea level pressure, and “CL” comprises the coefficient of lift calculated from the aircraft weight. 21. The apparatus of claim 20, wherein the lift loss component from using control surfaces for the turning of the aircraft comprises the roll rate and a roll trim lift. 22. The apparatus of claim 16, wherein the corrected coefficient of lift is as follows: corrected coefficient of lift=(weight of aircraft+roll trim lift+turning wing lift)/(cosine(roll angle)*dynamic pressure*wing area). 23. A computer program product for operating an aircraft, the computer program product comprising: a non-transitory computer recordable storage medium;a program code, stored on the non-transitory computer recordable storage medium, configured to identify an adjustment, to a pitch angle of the aircraft needed to substantially maintain an altitude of the aircraft during a turning of the aircraft, using a current lift for the aircraft, such that the current lift is derived by the computer program product from inputs comprising: a roll rate, and a limited roll angle, to form, from inputs comprising a pitch roll compensation, the adjustment to the pitch angle, in response to the turning of the aircraft when holding the altitude such that the program code comprises a roll in logic configured to generate an output configured to select at least one of: a roll in gain, and a roll out gain based upon the roll rate and the limited roll angle, such that the roll in logic comprises logic units connected to AND gates connected to an OR gate; andprogram code, stored on the computer recordable storage medium, for performing the turning of the aircraft using the adjustment to the pitch angle of the aircraft.