System for reducing aircraft fuel consumption

• US 4,159,088 A
• Filed: 11/04/1977
• Issued: 06/26/1979
• Est. Priority Date: 01/03/1977
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Cosley, Dennis H.
• Primary Examiner(s): Kunin, Stephen G.
• Application Number:
  US05/848,684
• Time in Patent Office: 599 Days
• Field of Search: 73/178 R, 73/178 T, 244/180-183, 244/186-188, 318/583, 318/584, 364/427, 364/428, 364/431, 364/433, 364/442
• US Class Current: 244/182
• CPC Class Codes: G05B 13/0205 not using a model or a simulator of the controlled system
• CPC Class Codes: G05D 1/0005 with arrangements to save energy

Abstract

A control system including both a method and apparatus for use on an aircraft during flight utilizes real-time data provided by sensing equipment on the aircraft to iteratively generate values for an efficiency parameter. The aircraft controls are adjusted after each iteration, and successive values of the efficiency parameter are compared until such comparison shows that the parameter has been substantially optimized. Iterations may then continue without corresponding control adjustments until comparison indicates that a current parameter value differs by a predetermined magnitude from the previously determined optimum value, at which time control adjustments resume in order to bring the efficiency parameter to a new substantially optimum parameter value.

Claims

1. A control system for improving the fuel economy of an operating aircraft during flight by sensing current values of operating parameters of said aircraft and adjusting controls of said aircraft as a function of said current values, said control system comprising:

input means for repetitively generating first, second, third, fourth, and fifth input signals representing current sensed values indicative of rate of climb, fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during cruise respectively;

computing means including a first logic circuit for receiving said first signals and generating first output command signals in response thereto, and a second logic circuit for receiving said second, third, fourth, and fifth signals and generating second output command signals in response thereto;

selection means for enabling a selected one of said first and second logic circuits in response to a selection input; and

an aircraft control including a pitch angle control for effecting incremental changes in the pitch attitude of the aircraft in response to said first output command signals, and a throttle control for effecting incremental changes in the thrust of said aircraft in response to said second output command signals,

whereby when said first logic circuit is enabled for a climb portion of said flight the rate of climb of said aircraft is substantially maximized during said climb portion, and when said second logic circuit is enabled for a cruise portion of said flight the total quantity of fuel consumed during said cruise portion is substantially minimized.

2. The control system of claim 1 including means for preventing the enabling of said first logic circuit except when said fuel flow rate for said aircraft is substantially constant.

3. The control system of claim 1 including means for preventing the enabling of said second logic circuit except when said rate of climb for said aircraft is substantially zero.

4. The control system of claim 1 wherein said computing means iteratively determines a current value of an efficiency parameter which is a function of current input signals to the selected logic circuit, and said output command signals are generated in response to differences determined by said computing means between values of said efficiency parameter.

5. The control system of claim 1 wherein said computing means iteratively determines a current value of an efficiency parameter which is a function of current input signals to the selected logic circuit, and said output command signals are generated in response to absolute-value differences determined by said computing means between values of said efficiency parameter.

6. The control system of claim 5 wherein the computing means determines the sign of the difference between said values of said efficiency parameter, and said output command signals effect said incremental changes in a direction according to said sign of said difference.

7. Apparatus for substantially maximizing the contribution of fuel consumed by an aircraft during a climb portion of a flight to overall fuel economy for the flight by sensing values indicative of the current rate of climb of said aircraft and adjusting the pitch attitude of said aircraft as a function of said sensed values, said apparatus comprising:

input means for repetitively generating input signals representative of current values of rate of climb for said aircraft,

computing means for iteratively receiving and processing said input signals and generating output command signals in response to the iterations of said computing means, and

a control for repeatedly maximizing said current rate of climb by effecting incremental changes in the pitch attitude of said aircraft in response to said output command signals.

8. The apparatus of claim 7 wherein the computing means includes a memory for storing the rate of climb value determined from one iteration, and means for determining the difference between said stored value and the rate of climb value determined during a subsequent iteration, said output command signals being generated as a function of the determined difference.

9. The apparatus of claim 8 wherein the sign of said incremental change in the pitch attitude of said aircraft depends on the sign of said determined difference.

10. The apparatus of claim 8 wherein said iterations compare successive rate of climb values, and an output command signal is generated as a result of each iteration until a comparison of successive rate of climb values indicates that the rate of climb has currently been substantially optimized.

11. Apparatus for substantially maximizing the contribution of fuel consumed by an aircraft during a climb portion of a flight to overall fuel economy for the flight by sensing values indicative of the current rate of climb of said aircraft and adjusting the pitch attitude of said aircraft as a function of said sensed values, said apparatus comprising:

input means for repetitively generating input signals representative of current values of rate of climb for said aircraft,

computing means for iteratively receiving and processing said input signals and generating output command signals in response to the iterations of said computing means, and

a control for effecting incremental changes in the pitch attitude of said aircraft in response to said output command signals,

said computing means including a memory for storing the rate of climb value determined from one iteration, and means for determining the difference between said stored value and the rate of climb value determined during a subsequent iteration, said output command signals being generated as a function of the determined difference,

said apparatus further including comparator means and means for providing a reference value to said comparator means, said comparator means comparing the absolute value of said determined difference with said reference value, and said output command signals being generated only when the absolute value of said determined difference is greater than said reference value.

12. The apparatus of claim 11 wherein said reference value is a predetermined constant.

13. The apparatus of claim 11 wherein said reference value is a function of a previous rate of climb value.

14. In an aircraft having an engine for developing thrust to propel said aircraft, a throttle control for controlling the thrust developed by said engine, a pitch axis control for controlling the pitch attitude of the aircraft, and instruments for sensing values indicative of and generating signals representing the current rate of climb of said aircraft;

a control system for substantially maximizing the contribution of fuel consumed by an aircraft during a climb portion of a flight to overall fuel economy for the flight, said control system comprising;

selection means for selectively energizing said control system;

parameter quantification means for repetitively receiving said signals from said instruments and iteratively generating a parameter value which is a function of said signals;

a memory connected to said parameter quantification means for receiving said parameter value and storing said values;

difference determining means for receiving current parameter values from said parameter quantification means and stored parameter values from said memory and determining the difference therebetween; and

comparator means, including a stored reference value, for comparing said difference with said reference value and generating a response based on said comparison, said throttle control response to said selection means for maintaining said thrust at a maximum rated value throughout said climb portion of said flight, and said pitch axis control effecting an incremental change in said pitch attitude of said aircraft as a function of said response.

15. In an aircraft as claimed in claim 14 wherein said apparatus includes synchronizing means for providing at least a predetermined time interval between successive iterations of said parameter quantification means.

16. In an aircraft as claimed in claim 14 wherein said apparatus includes synchronizing means for permitting an iteration of said parameter quantification means only when said signals representing current values of rate of climb indicate a substantially constant rate of climb.

17. In an aircraft as claimed in claim 14 wherein said apparatus includes synchronizing means for preventing a new iteration of said parameter quantification means until the immediately preceding iteration has been completed.

18. A control system for an aircraft having a pitch axis control for controlling the pitch attitude of the aircraft, and instruments for sensing values indicative of and generating signals representing the current rate of climb of said aircraft, said control system comprising:

parameter quantification logic connected to said instruments for repetitively receiving said signals therefrom and iteratively quantifying a parameter value from said signals;

a memory connected to said parameter quantification logic, said memory receiving a parameter value from said parameter quantification logic for each iteration of said parameter quantification logic and storing each said parameter value;

difference determining logic connected to said memory, said difference determining logic receiving the parameter value from the most recent iteration of said parameter quantification logic and a stored parameter value and determining the difference therebetween;

comparator logic connected to said difference determining logic, said comparator logic receiving the absolute value of the determined difference from said difference determining logic and comparing said absolute value difference to a reference value, said comparator logic providing an output signal to said difference determining logic which is a function of the comparison, said pitch axis control connected to said difference determining logic and responsive to signals from said difference determining logic which are a function of the determined differences and said output signals from said comparator logic for incrementally adjusting the pitch attitude of said aircraft and thereby maintaining a generally optimum rate of climb for said aircraft.

19. A control system as in claim 18 including synchronizing logic comprising a gate, a clock connected to said gate, and a steady-state sensor connected to said gate;

said gate connected to said difference determining logic, to said comparator logic, and to said parameter quantification logic;

said gate providing an output signal to said parameter quantification logic to initiate another iteration thereof when and only when said gate receives simultaneous input signals from said clock, said steady-state sensor, and one of said difference determining logic and said comparator logic.

20. Apparatus for substantially minimizing the total quantity of fuel consumed by an aircraft during a constant-altitude cruise by sensing values indicative of the values of current operating parameters of said aircraft and adjusting the thrust of said aircraft as a function of said sensed values, said apparatus comprising:

input means for repetitively generating input signals a, b, c, and d representative of current values of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during cruise;

computing means for iteratively receiving and processing said input signals and generating output command signals in response to the iterations of said computing means; and

a control for effecting incremental changes in the thrust of said aircraft in response to said output command signals.

21. The apparatus of claim 20 wherein the computing means during each iteration computes the value e of an efficiency parameter defined by the relationship:

space="preserve" listing-type="equation">e=d+(ac/b)

22. The apparatus of claim 21 wherein the computing means includes a memory for storing the value e determined from one iteration, and means for determining the difference between said stored value e and the value e determined during a subsequent iteration, said output command signals being generated as a function of the determined difference.

23. The apparatus of claim 22 including comparator means and means for providing a reference value to said comparator means, said comparator means comparing the absolute value of said determined difference with said reference value, and said output command signals being generated only when said absolute value of said determined difference is greater than said reference value.

24. The apparatus of claim 23 wherein said reference value is a predetermined constant.

25. The apparatus of claim 23 wherein said reference value is a function of a previously computed value e.

26. The apparatus of claim 23 wherein said reference value is a predetermined first value in each iteration where the immediately preceding iteration resulted in the generation of an output command signal and said reference value is a predetermined second value in each iteration where the immediately preceding iteration did not result in the generation of an output command signal.

27. The apparatus of claim 23 wherein said reference value is a first value while successive iterations compare successive values e and a second value while successive iterations compare a current value e with a stored value e previously determined to be a substantially optimum value.

28. The apparatus of claim 22 wherein the sign of the incremental change in the thrust of said aircraft depends on the sign of said determined difference.

29. The apparatus of claim 22 wherein said iterations compare successive values e, and an output command signal is generated as a result of each iteration until a comparison of successive values e indicates that value e has currently been substantially optimized.

30. In an aircraft having an engine for developing thrust to propel said aircraft, a control for regulating the thrust developed by said engine, and instruments for sensing values indicative of and generating signals representing current values of fuel flow rate, ground speed, distance to destination, and total fuel already consumed during cruise;

a control system for substantially minimizing the total quantity of fuel consumed during a constant-altitude cruise portion of the flight of said aircraft, said control system comprising;

selection means for selectively energizing said apparatus;

parameter quantification means for repetitively receiving said signals from said instruments and iteratively generating current values of an efficiency parameter which is a function of said signals;

a memory connected to said parameter quantification means for receiving said current efficiency parameter values and storing said values;

difference determining means for receiving current efficiency parameter values from said parameter quantification means and stored efficiency parameter values from said memory and determining the difference therebetween; and

comparator means, including a stored reference value, for comparing said difference with said reference value and generating a response based on said comparison, said control effecting an incremental change in said thrust as a function of said response.

31. In an aircraft as claimed in claim 30 wherein said parameter quantification means generates current values e of an efficiency parameter defined by the relationship

32. In an aircraft as claimed in claim 30 wherein said apparatus includes synchronizing means for providing at least a predetermined time interval between successive iterations of said parameter quantification means.

33. In an aircraft as claimed in claim 30 wherein said apparatus includes synchronizing means for permitting iterations of said parameter quantification means only when said signals representing current values of said ground speed indicate a substantially constant ground speed.

34. In an aircraft as claimed in claim 30 wherein said apparatus includes synchronizing means for preventing a new iteration of said parameter quantification means until the immediately preceding iteration has been completed.

35. A control system for an aircraft having an engine for developing thrust to propel said aircraft, a control for regulating the thrust developed by said engine, and instruments for sensing values indicative of and generating signals representing current values of fuel flow rate, ground speed, distance remaining to point of decent, and total fuel already consumed during cruise;

said control system comprising;

parameter quantification logic connected to said instruments for repetitively receiving said signals therefrom and iteratively quantifying an efficiency parameter value e from said signals in accordance with the relationship e=d+(ac/b), where a represents current fuel flow rate, b represents current ground speed, c represents the current distance remaining to point of descent, and d represents the total quantity of fuel already consumed during cruise;

a memory connected to said parameter quantification logic, said memory receiving an efficiency parameter value from said parameter quantification logic for each iteration of said parameter quantification logic and storing each said efficiency parameter value;

difference determining logic connected to said memory, said difference determining logic receiving the efficiency parameter value from the most recent iteration of said parameter quantification logic and a stored efficiency parameter value and determining the difference therebetween;

comparator logic connected to said difference determining logic, said comparator logic receiving the absolute value of the determined difference from said difference determining logic and comparing said absolute value difference to a reference value, said comparator logic providing an output signal to said difference determining logic which is a function of the comparison, said control connected to said difference determining logic and responsive to signals from said difference determining logic which are a function of said determined differences and said output signals from said comparator logic for incrementally adjusting the thrust of said aircraft.

36. A control system as in claim 35 including synchronizing logic comprising a gate, a clock connected to said gate, and a steady-state sensor connected to said gate;

said gate connected to said difference determining logic, to said comparator logic, and to said parameter quantification logic;

said gate providing an output signal to said parameter quantification logic to initiate another iteration thereof when and only when said gate receives simultaneous input signals from said clock, said steady-state sensor, and one of said difference determining logic and said comparator logic.

37. A method for substantially minimizing the total quantity of fuel consumed by an aircraft during the combined climb and cruise portions of a flight, said method comprising the steps of:

(1) setting the thrust of said aircraft at a maximum rated value and maintaining the thrust at said maximum rated value during said climb portion of said flight,

(2) repetitively sensing values indicative of current rate of climb of said aircraft,

(3) iteratively processing the current values sensed in step (2) and generating signals as a function of said processing,

(4) controlling the pitch attitude of said aircraft in response to the signals from step (3) so as to continuously maintain the aircraft at a substantially maximum rate of climb during said climb portion of said flight,

(5) bringing the aircraft to a constant-altitude cruise and maintaining the constant altitude of said aircraft during said cruise portion of said flight,

(6) repetitively sensing values indicative of current values for the aircraft of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during said cruise portion of said flight,

(7) iteratively processing the current values sensed in step (6) and generating signals as a function of said processing, and

(8) controlling the thrust of said aircraft during said cruise portion of said flight in response to the signals from step (7) so as to substantially minimize the total quantity of fuel consumed during said cruise portion of said flight.

38. A method for substantially maximizing the contribution to overall fuel economy for a flight of fuel consumed by an aircraft during a climb portion of the flight during which said aircraft is climbing to a cruising altitude, said method comprising the steps of:

(1) setting the thrust of said aircraft at a maximum rated value and maintaining the thrust at said maximum rated value during said climb portion of said flight,

(2) repetitively sensing values indicative of current rate of climb of said aircraft,

(3) iteratively processing the current values sensed in step (2) and generating signals as a function of said processing, and

(4) repeatedly maximizing the current rate of climb of said aircraft during said climb portion of said flight by controlling the pitch attitude of said aircraft in response to the signals from step (3).

39. A method for substantially minimizing the total quantity of fuel consumed by an aircraft during a cruise portion of a flight, said method comprising the steps of:

(1) bringing the aircraft to a constant-altitude cruise and maintaining the constant altitude of said aircraft during said cruise portion of said flight,

(2) repetitively sensing values indicative of current values for the aircraft of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during said cruise portion of said flight,

(3) iteratively processing the current values sensed in step (2) and generating signals as a function of said processing, and

(4) controlling the thrust of said aircraft during said cruise portion of said flight in response to the signals from step (3) so as to substantially minimize the total quantity of fuel consumed during said cruise portion of said flight.

40. A method for substantially maximizing the contribution of fuel consumed by an aircraft during a climb portion of a flight to overall fuel economy for the flight, said method comprising the steps of:

(1) setting the thrust of said aircraft at a maximum rated value and maintaining the thrust at said maximum rated value during said climb portion of said flight,

(2) sensing a value indicative of the current rate of climb of said aircraft,

(3) storing the value sensed in step (2),

(4) incrementally adjusting the pitch attitude of said aircraft,

(5) sensing a value indicative of the current rate of climb of said aircraft,

(6) storing the value sensed in step (5),

(7) determining the difference between the value sensed in the most recent iteration of step (5) and the value stored immediately prior to said most recent iteration,

(8) incrementally adjusting the pitch attitude of said aircraft as a function of the difference determined in step (7), and

(9) repeating steps (5) through (8) until a difference determined in step (7) indicates that the current rate of climb of said aircraft has been substantially maximized.

41. The method according to claim 40 including the additional steps of:

(10) continuing to sense values indicative of the current rate of climb of said aircraft,

(11) determining the absolute value difference between each newly-sensed value from step (10) and the value stored in the most recent iteration of step (6),

(12) comparing each absolute value difference determined in step (11) with a reference value until said absolute value difference exceeds said reference value, and

(13) repeating steps (4) through (13) until said climb portion of said flight is completed.

42. A method for substantially maximizing the contribution of fuel consumed by an aircraft during a climb portion of a flight to overall fuel economy for the flight, said method comprising the steps of:

(1) setting the thrust of said aircraft at a maximum rate value and maintaining the thrust at said maximum rated value during said climb portion of said flight,

(2) sensing a value indicative of the current rate of climb of said aircraft,

(3) storing the value sensed in step (2),

(4) incrementally adjusting the pitch attitude of said aircraft,

(5) sensing a value indicative of the current rate of climb of said aircraft,

(6) storing the value sensed in step (5),

(7) determining the absolute value difference between the last two stored values,

(8) comparing the difference determined from step (7) with a reference value,

(9) repeating steps (4) through (8) until a difference determined in step (7) is less than the reference value,

(10) repeating steps (5) and (6),

(11) determining the absolute value difference between the stored value from step (10) and the last stored value from step (6) just prior to proceeding with step (10),

(12) comparing the difference from step (11) with the reference value,

(13) repeating steps (10) through (12) until the difference from step (11) exceeds the reference value, and

(14) repeating steps (4) through (14) until said climb portion of said flight is completed.

43. A method for substantially minimizing the total quantity of fuel consumed by an aircraft during a cruise portion of a flight, said method comprising the steps of:

(1) bringing the aircraft to a constant-altitude cruise and maintaining the constant altitude of said aircraft during said cruise portion of said flight,

(2) sensing values indicative of current values for the aircraft of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during said cruise portion of said flight,

(3) computing the current value of an efficiency parameter which is a function of the sensed values from step (2),

(4) storing the parameter value computed in step (3),

(5) incrementally adjusting the thrust of said aircraft,

(6) sensing values indicative of current values for the aircraft of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during said cruise portion of said flight,

(7) computing the current value of said efficiency parameter based on the sensed values from step (6),

(8) storing the parameter value computed in step (7),

(9) determining the difference between the efficiency parameter value sensed in the most recent iteration of step (7) and the efficiency parameter value stored immediately prior to said most recent iteration,

(10) incrementaly adjusting the thrust of said aircraft as a function of the difference determined in step (9),

(11) repeating steps (6) through (10) until a difference determined in step (9) indicates that a substantially optimum current aircraft thrust has been attained.

44. The method according to claim 43 including the additional steps of:

(12) continuing to sense values indicative of current values for the aircraft of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during said cruise portion of said flight and continuing to compute the current values of said efficiency parameter as a function of these values,

(13) determining the absolute value difference between each newly-computed parameter value from step (12) and the parameter value stored from the most recent iteration of step (7),

(14) comparing each absolute value difference determined in step (13) with a reference value until said absolute value difference exceeds said reference value,

(15) repeating steps (6) through (10) until a difference determined in step (9) indicates that a substantially optimum current aircraft thrust has once again been attained,

(16) repeating steps (5) through (16) until said cruise portion of said flight is concluded.

45. A method for substantially minimizing the total quantity of fuel consumed by an aircraft during a cruise portion of a flight, said method comprising the steps of:

(1) bringing the aircraft to a constant-altitude cruise and maintaining the constant altitude of said aircraft during said cruise portion of said flight,

(2) sensing values indicative of current values for the aircraft of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during said cruise portion of said flight,

(3) calculating the current value of an efficiency parameter based on the values from step (2),

(4) storing the parameter value calculated in step (3),

(5) incrementally adjusting the thrust of said aircraft,

(6) sensing values indicative of current values for the aircraft of fuel flow rate, ground speed, distance remaining to destination, and total fuel already consumed during said cruise portion of said flight,

(7) calculating the current value of said efficiency parameter based on the sensed values from step (6),

(8) storing the parameter value calculated in step (7),

(9) determining the absolute value difference between the last two stored values of said efficiency parameter,

(10) comparing the difference determined from step (9) with a first reference value,

(11) repeating steps (5) through (10) until a difference determined in step (9) is less than said first reference value,

(12) repeating steps (6) through (8),

(13) determining the absolute value difference between the stored value from step (12) and the most recently stored value from step (8) just prior to proceeding with step (12),

(14) comparing the difference from step (13) with a second reference value,

(15) repeating steps (12) through (14) until the difference from step (13) exceeds the second reference value, and

(16) repeating steps (5) through (16) until said cruise portion of said flight is concluded.