Cruise airspeed control of aircraft altitude capture

Claim 2

Engine control apparatus for an automatic flight control system including a throttle position controller for urging an aircraft to capture a commanded airspeed during an altitude capture maneuver comprising: means responsive to an operational characteristic of said engine for generating a signal representing actual engine thrust, means for generating a signal representing a predetermined engine thrust at said commanded airspeed and a predetermined altitude, means for generating a signal representing an actual rate of change in altitude, means for combining said actual engine thrust signal, said predetermined engine thrust signal and said altitude rate signal for generating a command signal to drive said throttle position controller for urging said aircraft to capture said airspeed.

Claim 3

Apparatus as set forth in claim 1, wherein: said means for generating said signal representing actual engine thrust comprises means for providing a signal proportional to actual engine pressure ratio.

Claim 4

Apparatus as set forth in claim 2, wherein: said means for generating a signal representing said predetermined engine thrust comprises means for providing a signal proportional to the desired engine pressure ratio required to maintain said commanded speed in a level flight path at said predetermined altitude.

Claim 5

Apparatus as set forth in claim 3, wherein said means for combining said actual engine thrust signal, said predetermined engine thrust signal, and said altitude rate signal further comprises: means for providing a drive signal proportional to the algebraic difference between said actual engine pressure ratio signal and said desired engine pressure ratio signal, and means for providing a control signal proportional to the ratio between said drive signal and said altitude rate signal.

Claim 6

Apparatus as set forth in claim 4, wherein the value of said command signal does not exceed a predetermined maximum value governed by said control signal.

Claim 7

The apparatus as set forth in claim 5, further including amplitude limiter means for limiting said drive signal to said maximum value.

Claim 8

The apparatus as set forth in claim 6, said limiter means further comprising variable limiter means responsive to said control signal.

Claim 9

The apparatus as set forth in claim 7, further comprising absolute value detector means for receiving said control signal and for providing a unipolar output to said variable limiter means.

Claim 10

Apparatus as set forth in claim 8, wherein said throttle position controller further comprises: a manual throttle control, and closed-loop servo means coupled to a linkage for driving said manual throttle control, responsive to said command signal, said manual throttle control coupled to said engine for controlling said actual engine pressure ratio.

Claim 11

Apparatus as set forth in claim 1, wherein said command signal for urging said aircraft to capture said commanded airspeed varies in accordance with a control law comprising: δτ=KΔEPR/h.sub.1 where δτ is the throttle rate required to maintain said commanded airspeed during said altitude capture maneuver, ΔEPR is the difference between engine pressure ratios at two distinct throttle positions, h 1 is the actual rate of change of altitude of the aircraft, and K is a constant of proportionality relating the maximum allowable acceleration normal to the aircraft flight path during said altitude capture maneuver and the slope of the ratio of said throttle controller position to engine pressure in the region of ΔEPR.

Claim 12

Apparatus as set forth in claim 10, wherein said two throttle positions comprise a first actual position during the course of said altitude capture maneuver and a desired position at the completion of said maneuver.

Claim 13

Apparatus as set forth in claim 11, wherein said constant K has a value of 4000.

Claim 14

Apparatus for controlling an engine through a throttle linkage including an automatic flight control system and an automatic throttle position controller to provide airspeed control of an aircraft during an altitude capture maneuver, wherein: said linkage is responsive to a command signal that varies in accordance with: Δτ=K|ΔEPR/h.sub.1 | where δτ is the required throttle rate to maintain a commanded speed during said altitude capture maneuver, ΔEPR is the difference between engine pressure ratios at two distinct throttle positions, h 1 is the actual rate of change of altitude of said aircraft, and K is a constant of proportionality relating the maximum allowable acceleration normal to the aircraft flight path and the slope of the throttle controller position vs engine pressure ratio in the region of ΔEPR, the combination further comprising: means for providing a signal proportional to said altitude rate h 1 , means for providing a signal proportional to said engine pressure ratio difference ΔEPR, divider means responsive to said engine pressure ratio difference and said altitude rate signal for providing a signal proportional to the ratio thereof, means responsive to said divider signal for providing a further signal proportional to the absolute value thereof, gain means responsive to said absolute value signal for providing a control signal, variable amplitude limiter means responsive to said control signal and said engine pressure ratio difference signal, for reducing a limit imposed on the value of said command signal when said ratio signal is at a low value and for increasing the value of the limit imposed on said command signal when said ratio signal is at a high value, and for limiting said command signal to a predetermined maximum value, and means for driving said linkage, responsive to said command signal.

Claim 15

Apparatus for controlling an engine through a throttle linkage including an automatic flight control system and an automatic throttle position controller to provide airspeed control of an aircraft during an altitude capture maneuver, wherein: said linkage is responsive to a command signal that varies in accordance with: Δτ=K|ΔEPR/h.sub.1 | where δτ is the required throttle rate to maintain a commanded speed during said altitude capture maneuver, ΔEPR is the difference between engine pressure ratios at two distinct throttle positions, h 1 is the actual rate of change of altitude of said aircraft, and K is a constant of proportionality relating the maximum allowable acceleration normal to the aircraft flight path and the slope of the throttle controller position vs engine pressure ratio in the region of ΔEPR, the combination further comprising: means for providing a signal proportional to said altitude rate h 1 , means for providing a signal proportional to said engine pressure ratio difference ΔEPR, divider means responsive to said engine pressure ratio difference and said altitude rate signal for providing a signal proportional to the ratio thereof, means responsive to said divider signal for providing a further signal proportional to the absolute value thereof, gain means responsive to said absolute value signal for providing a control signal, variable amplitude limiter means responsive to said control signal and said engine pressure ratio difference signal, for reducing a limit imposed on the value of said command signal when said ratio signal is at a low value and for increasing the value of the limit imposed on said command signal when said ratio signal is at a high value, and for limiting said command signal to a predetermined maximum value, and means for driving said linkage, responsive to said command signal.