Cruise airspeed control of aircraft altitude capture
AssigneeSperry Corporation
InventorTerry L. Zweifel
Life of this patent
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Abstract
An aircraft speed control system for use with an automatic throttle position control system and automatic flight control system permits capturing and maintaining a commanded airspeed during the capturing of a desired altitude from either climbing or descending flight. The system manipulates the throttles at a variable rate dependent on the difference between the actual thrust of the aircraft and the desired cruising thrust at the selected airspeed and inversely proportional to the actual altitude rate. A signal derived from thrust error and altitude rate signals is utilized to generate a limiter control signal which is combined with an engine pressure ratio signal to generate a drive signal for urging the aircraft to capture precisely the commanded airspeed.
Claims13
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.
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:
- .DELTA..tau.=K.vertline..DELTA.EPR/h.sub.1 .vertline.
- where .delta..tau. is the required throttle rate to maintain a commanded speed during said altitude capture maneuver, .DELTA.EPR is the difference between engine pressure ratios at two distinct throttle positions, h.sub.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 .DELTA.EPR, the combination further comprising:
- means for providing a signal proportional to said altitude rate h.sub.1,
- means for providing a signal proportional to said engine pressure ratio difference .DELTA.EPR,
- 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.
Dependencies are inferred from the claim text.