Flight performance data computer system

• US 4,312,041 A
• Filed: 02/22/1978
• Issued: 01/19/1982
• Est. Priority Date: 02/22/1978
• Status: Expired due to Term

• Current Assignee: Lear Siegler, Inc. (LSS Holdings LLC)
• Original Assignee: Lear Siegler, Inc. (LSS Holdings LLC)
• Inventors: DeJonge, Michael K.
• Primary Examiner(s): Smith, Jerry
• Application Number:
  US05/880,219
• Time in Patent Office: 1,427 Days
• Field of Search: 364/427, 364/430, 364/431, 364/442, 364/444, 340/27 R, 340/27 NA
• US Class Current: 701/123
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G05D 1/0005 with arrangements to save energy

Abstract

A flight performance data system comprises a control and display unit operably connected to a computer. The computer has input means responsive to real air mass parameters and real aircraft dynamic measurements. The computer is programmed to respond to the incoming signals and automatically generate various output signals representing flight profile data. A mode selector is operably connected to the computer to direct the computer in different modes to determine the different flight profile data for the climb, cruise, descent and other modes of the aircraft. For various modes, a different flight schedule can be determined corresponding to the most fuel efficient flight, a long-range cruise flight, or the most economical flight. In addition, the computer produces output signals corresponding to the maximum rate of climb and the maximum rate of descent in the climb and descent modes, respectively. A display screen selectively displays the desired flight profile data. In addition, given desired variables can be supplied by the pilot to the computer and the computer automatically generates an output signal corresponding to the flight profile data consistent with the desired variables.

Claims

1. An on-board aircraft computer system for use with jet engine powered aircraft, the computer system comprising:

input means mounted to the aircraft for generating signals representative of real flight parameters, including the ambient altitude pressure, the total air temperature, the combined weight of the plane, cargo, fuel and passengers, and the actual mach of the aircraft;

computer means coupled to the input means and responding to the real parameter signals received from the input means for producing output signals representing flight profile data for maximum fuel efficiency of the aircraft for the real parameters;

the computer means further produces signals corresponding to the theoretical and actual engine pressure ratios of the aircraft jet engine and produces a degraded performance factor signal proportional to the ratio of the actual and theoretical engine pressure ratios as an indication of a degraded performance of the aircraft;

the computer means responds to the degraded performance factor signal to modify the output signals representing flight profile data for maximum fuel efficiency, taking into account the degrading performance of the aircraft; and

indicating means coupled to the computer means responsive to the output signals for displaying the flight profile data within the aircraft.

2. On on-board aircraft computer as defined in claim 1 wherein:

the computer means includes a filter means for comparing actual engine pressure ratio and theoretical engine pressure ratio values only when the aircraft is in a steady state with minimum fluctuation in the actual engine pressure ratio, mach, and altitude over a predetermined period of time to assure an accurate degrade performance factor;

the computer means taking all ratios of the actual and theoretical engine pressure ratios and averaging them together with any previously determined degraded performance factor, such that the computer means responds to a degraded performance factor that is accurate under the present existing conditions of the aircraft.

3. An on-board computer as defined in claim 1 wherein:

the input means further generates a signal representing a cost index factor which represents the time dependent costs in flight compared to fuel costs during flight; and

the computer means further responds to the cost index factor signal to produce output signals representing a most economical flight profile schedule taking into account both the time dependent costs and the extra costs of fuel consumed at faster speeds.

4. An on-board aircraft computer system for use with jet engine powered aircraft, the computer system comprising:

input means mounted to the aircraft for generating signals representative of real flight parameters, including ambient altitude pressure, the total air temperature, the combined weight of the plane, cargo, fuel and passengers;

computer means coupled to the input means and responsive to the real flight parameter signals received from the input means for producing output signals representing flight profile data for maximum fuel efficiency of the aircraft for the real parameters;

indicating means coupled to the computer means responsive to the output signals for displaying and flight profile data within the aircraft; and

an altitude performance selector actuably coupled to the computer means such that the computer means becomes responsive to the flight parameter input signals representing the actual real time altitude and a selected second altitude for producing an output signal representing a change in the wind component needed at a selected altitude to obtain a flight profile which is as efficient as the flight profile at the real time altitude.

5. An on-board aircraft computer system for use with jet engine powered aircraft, the computer system comprising:

input means mounted to the aircraft for generating signals representative of real flight parameters, including ambient altitude pressure, the total air temperature, the combined weight of the plane, cargo, fuel and passengers;

computer means coupled to the input means and responding to the real flight parameter signals received from the input means for producing output signals representing flight profile data for maximum fuel efficiency of the aircraft for the real parameters;

indicating means coupled to the computer means responsive to the output signals for displaying the flight profile data within the aircraft;

a mode selector having climb, cruise and descent mode positions and operably coupled to the computer means;

the computer means is responsive to the input signals for producing output signals representing optimum mach, optimum altitude, and engine pressure ratios when the mode selector is in the cruise position;

the computer means is responsive to the input signals for producing output signals representing the engine pressure ratio limits and optimum speed when the mode selector is in the climb position; and

the computer means utilizes the input signals for producing output signals indicating an optimum descent when the mode selector is in the descent position, the output signals representing the distance from the destination that descent should commence, the time it takes for descent at the optimum air speed.

6. An on-board computer as defined in claim 5 wherein:

the computer means responds to the input signals representing the real flight parameters to produce output signals corresponding to a long range cruise flight profile of the aircraft wherein the fuel mileage of the aircraft is approximately 99% of the maximum possible;

a schedule selector is coupled to the computer means and is actuable between a long range cruise schedule and most economical cruise schedules when the first mode selector is positioned so that the computer means is in the cruise mode; and

the indicating means are operably connected to the schedule selector such that only one of the long range cruise profiles and the most economical cruise profile is indicated depending on which schedule is actuated by the schedule selector.

7. An on-board computer as defined in claim 6 wherein the computer means is responsive to the input signals representing the real flight parameters to produce output signals corresponding to the maximum rate of climb of the aircraft;

the schedule selector is operable between a most economical schedule and maximum rate of climb schedule when the first mode selector is positioned so that the computer means is in the climb mode and the schedule selector is in the maximum rate position; and

the indicating means is operably connected to the schedule selector such that only one of the maximum rate of climb profiles and the most economical climb profile is indicated depending on which schedule is actuated by the schedule selector.

8. An on-board computer as defined in claim 5 wherein:

the computer means is responsive to input signals representing the actual real time altitude and a selected second altitude to produce output signals representing the time and distance required to achieve the selected second altitude.

9. An on-board aircraft computer system for use with jet engine powered aircraft, the computer system comprising:

input means mounted to the aircraft for generating signals representative of real flight parameters, including real air mass measurements and real aircraft dynamic measurements;

computer means coupled to the input means and responding to the real parameter signals received from the input means for producing output signals representing flight profile data for maximum fuel efficiency of the aircraft for the real parameters;

the computer means is further responsive to the real parameter input signals to generate signals corresponding to the maximum altitude for a given mach and the maximum mach for a given altitude without exceeding the engine pressure ratio limits of the jet engines for the altitudes and machs;

the computer means produces output signals representing the maximum safe mach by responding to an arbitrary target mach, the weight, altitude, pressure and total air temperature inputs to produce an engine pressure ratio output signal for the target mach;

the computer means is responsive to the input means signals to produce an engine pressure ratio output signal for the target mach and compares the engine pressure ratio signal with the engine pressure ratio limit;

the computer means adds or subtracts an increment to the target mach to obtain a modified target mach, depending on whether the engine pressure ratio output signal was less or greater than the engine pressure ratio limit;

the computer means responds to the added or subtracted increment and produces an engine pressure ratio output signal and engine pressure limit signal for the modified target mach, a subsequent increment being subtracted or added until the engine pressure ratio signal equals the engine pressure ratio limit;

the computer means is responsive to the maximum safe mach output signal and a selected mach input signal to produce a warning output signal if the selected mach input signal represents a mach higher than the maximum safe mach represented by the corresponding output signal; and

visual indicating means coupled to the computer means responsive to the output signals for displaying the flight profile data within the computer, the visual indicating means displaying a warning indication responsive to the warning output signal produced by the computer means.

10. An on-board aircraft computer system for use with aircraft powered by jet engines, the computer system comprising:

input means mounted to the aircraft for producing signals representative of real flight parameters of the aircraft and producing signals representative of the time dependent costs of the aircraft;

computer means coupled to the input means and responding to the real parameter and time dependent costs signals received from the input means for producing output signals representing flight profile data for total minimum costs of the flight; and

indicating means coupled to the computer means for receiving the output signals and displaying the flight profile data within the aircraft.

11. An on-board aircraft computer as defined in claim 10 wherein:

the computer means further produces signals corresponding to the theoretical and actual engine pressure ratios of the aircraft jet engine and produces a degraded performance factor signals proportional to the ratio of the actual and theoretical engine pressure ratios as an indication of a degraded performance of the aircraft; and

the computer means responds to the degraded performance factor signal to modify the output signals representing flight profile data for total minimum costs, taking into account the degraded performance of the aircraft.

12. An on-board computer system as defined in claim 10 further comprising an altitude performance selector actuably coupled to the computer means such that the computer means becomes responsive to the flight parameter input signals representing the actual real time altitude and a selected second altitude for producing an output signal representing a change in the wind component needed at the selected altitude to obtain a flight profile which is as efficient as the flight profile at the present altitude.

13. An on-board computer system defined in claim 10 and further comprising a mode selector having climb, cruise and descent mode positions and operably coupled to the computer means whereby:

the computer means is responsive to the input signals for producing output signals representing optimum mach, optimum altitude, and engine pressure ratios when the mode selector is in the cruise position;

the computer means is responsive to the input signals for producing output signals representing the engine pressure ratio limits and optimum speed when the mode selector is in the climb position; and

the computer means utilizes the input signals for producing output signals indicating an optimum descent when the mode selector is in the descent position, the output signals representing the distance from the destination descent should commence, the time it takes for descent and the optimum air speed.

14. An on-board computer as defined in claim 13 wherein:

the computer means is responsive to input signals representing the actual real time altitude and a selected second altitude to produce output signals representing the time and distance required to achieve the selected second altitude.

15. An on-board computer as defined in claim 10 wherein:

the computer means is responsive to the real parameter input signals to generate signals corresponding to the maximum altitude for a given mach and the maximum mach for a given altitude without exceeding the engine pressure ratio limits of the jet engines for said altitudes and machs.

16. An on-board aircraft computer system as defined in claim 15 wherein:

the computer means produces output signals representing the maximum safe mach by responding to an arbitrary target mach, the weight, altitude pressure and total air temperature inputs to produce an engine pressure ratio output signal for the target mach;

the computer means is responsive to the input to produce the engine pressure ratio limit output signal for the target mach and compares the engine pressure ratio readout with the engine pressure ratio limit;

the computer means adds or subtracts an increment to the target mach, obtaining a modified target mach, depending on whether the engine pressure ratio readout was less or greater than the engine pressure ratio limit;

the computer means responds to the added or subtracted increment and produces an engine pressure ratio output signal and engine pressure ratio limit signal for the modified target mach;

a subsequent increment being subtracted or added until the engine pressure ratio readout equals the engine pressure ratio limit;

the computer means is responsive to the maximum safe mach output signal and a selected mach input signal to produce a warning output signal if the selected mach input signal represents a mach higher than the maximum safe mach represented by the corresponding output signal; and

the visual indicating means displays a warning indication responsive to the warning output signal produced by the computer means.

17. An on-board aircraft computer system for use with jet engine powered aircraft, the computer system comprising:

input means mounted to the aircraft for generating signals representative of real flight parameters, including real air mass measurements and real aircraft dynamic measurements;

computer means coupled to the input means and responding to the real parameter signals received from the input means for producing output signals representing flight profile data for maximum fuel efficiency of the aircraft for the real parameters;

the computer means modifies the output signals representing flight profile data and the computer further modifies the output signals such that the fuel mileage of the aircraft is reduced to approximately 99% of the maximum possible fuel efficiency; and

visual indicating means coupled to the computer means responsive to the output signals for displaying the flight profile data within the aircraft.

18. An on-board aircraft computer as defined in claim 17 wherein:

the computer means further produces signals corresponding to the theoretical and actual engine pressure ratios of the aircraft jet engine and produces a degraded performance factor signal proportional to the ratio of the actual and theoretical engine pressure ratios as an indication of a degraded performance of the aircraft; and

the computer means responds to the degraded performance factor signal to modify the output signals corresponding to a long-range cruise flight schedule, taking into account the degraded performance of the aircraft.

19. An on-board computer system as defined in claim 17 further comprising an altitude performance selector actuably coupled to the computer means such that the computer means becomes responsive to the flight parameter input signals representing the actual real time altitude and a selected second altitude for producing an output signal representing a change in the wind component needed at the selected altitude to obtain a flight profile which is as efficient as the flight profile at the present altitude.

20. An on-board computer system defined in claim 17 and further comprising a mode selector having climb, cruise and descent mode positions and operably coupled to the computer means wherein:

the computer means is responsive to the input signals for producing output signals representing optimum mach, optimum altitude, and engine pressure ratios when the mode selector is in the cruise position;

the computer means is responsive to the input signals for producing output signals representing the engine pressure ratio limits and optimum speed when the mode selector is in the climb position; and

the computer means utilizes the input signals for producing output signals indicating an optimum descent when the mode selector is in the descent position, the output signals representing the distance from the destination descent should commence, the time it takes for descent and the optimum air speed.

21. An on-board computer as defined in claim 20 wherein:

the computer means is responsive to input signals representing the actual real time altitude and a selected second altitude to produce output signals representing the time and distance required to achieve the selected second altitude.

22. An on-board computer as defined in claim 17 wherein:

the computer means is responsive to the real parameter input signals to generate signals corresponding to the maximum altitude for a given mach and the maximum mach for a given altitude without exceeding the engine pressure ratio limits of the jet engines for said altitudes and machs.

23. An on-board aircraft computer system as defined in claim 22 wherein:

the computer means produces output signals representing the maximum safe mach by responding to an arbitrary target mach, the weight, altitude pressure and total air temperature inputs to produce an engine pressure ratio output signal for the target mach;

the computer means is responsive to the input to produce the engine pressure ratio limit output signal for the target mach and compares the engine pressure ratio readout with the engine pressure ratio limit;

the computer means adds or subtracts an increment to the target mach obtaining a modified target mach, depending on whether the engine pressure ratio readout was less or greater than the engine pressure ratio limit;

the computer means responds to the added or subtracted increment and produces an engine pressure ratio output signal and engine pressure ratio limit signal for the modified target mach;

a subsequent increment being subtracted or added until the engine pressure ratio readout equals the engine pressure ratio limit;

the computer means is responsive to the maximum safe mach output signal and a selected mach input signal to produce a warning output signal if the selected mach input signal represents a mach higher than the maximum safe mach represented by the corresponding output signal; and

the visual indicating means displays a warning indication responsive to the warning output signal produced by the computer means.

24. An on-board aircraft computer system for use with jet powered aircraft, the computer system comprising:

input means for providing signals indicating real flight parameters including the ambient altitude pressure, the total air temperature, and the combined weight of the plane, cargo, fuel and passengers;

computer means coupled to the input means and responding to the real parameter signals for producing output signals corresponding to the maximum altitude for a given mach or the maximum mach for a given altitude without exceeding engine pressure ratio limits of the jet engine;

the computer means produces output signals representing maximum safe mach by responding to an arbitrary target mach, the weight, altitude pressure and total air temperature inputs to produce an engine pressure ratio output signal for the target mach;

the computer means is responsive to the input means to produce the engine pressure ratio limit output signal for the target mach and compares the engine pressure ratio output signal with the engine pressure ratio limit signal;

the computer means adds or subtracts an increment to the target mach, obtaining modified target mach, depending on whether the engine pressure ratio readout is less or greater than the engine pressure ratio limit;

the computer means responds to the added or subtracted increment and produces an engine pressure ratio output signal and engine pressure ratio limit signal for the modified target mach, a subsequent increment being subtracted or added until the engine pressure ratio signal equals the engine pressure ratio limit signal;

the computer means is responsive to the maximum safe mach output signal and a selected mach input signal to produce a warning output signal if the selected mach input signal represents a mach higher than the maximum safe mach represented by the corresponding output signal; and

visual indicating means responsive to the output signals for displaying the maximum altitude and maximum mach for a given altitude, and the visual indicating means displays a warning indication responsive to the warning output signal produced by the computer means.

25. An on-board aircraft computer system for use with a jet powered aircraft, the computer system comprising:

input means for providing signals indicating real flight parameters including air mass parameters and real aircraft dynamic measurements and the actual mach of the aircraft;

computer means coupled to the input means and responding to the real parameter signals for producing output signals corresponding to the maximum altitude for a given mach or the maximum mach for a given altitude without exceeding engine pressure ratio limits of the jet engine;

the computer means further produces signals corresponding to the theoretical and actual engine pressure ratios of the aircraft jet engine and produces a degraded performance factor signal proportional to the ratio of the actual and theoretical engine pressure ratios as an indication of a degraded performance of the aircraft;

the computer means responds to the degraded performance factor signal to modify the output signals corresponding to the maximum altitude for a given mach and the maximum mach for a given altitude, taking into account the degraded performance of the aircraft; and

visual indicating means responsive to the output signals for displaying the maximum altitude and maximum mach for the given altitude within the aircraft.