Multiplexed junction probe for fuel gaging system and system containing same

• US 4,872,120 A
• Filed: 04/21/1988
• Issued: 10/03/1989
• Est. Priority Date: 12/20/1984
• Status: Expired due to Term

• Current Assignee: Parker Intangibles LLC (Parker-Hannifin Corporation)
• Original Assignee: Gull, Inc. (Parker-Hannifin Corporation), Mcdonnell Douglas Corporation (The Boeing Co.)
• Inventors: Rittner, Charles H., Horowitz, Martin, Orloff, Eugene F.
• Primary Examiner(s): Lall, Parshotam S.
• Assistant Examiner(s): Dixon, Joseph L.
• Application Number:
  US07/184,271
• Time in Patent Office: 530 Days
• Field of Search: 364/509, 364/564, 364/900, 364/550, 364/558, 73/304 C, 73/304 R, 340/825.05, 340/825.15, 340/870.13, 340/945
• US Class Current: 702/52
• CPC Class Codes: B64C 17/10 Transferring fuel to adjust trim
• CPC Class Codes: B64D 37/00 Arrangements in connection with fuel supply for power plant refuelling during flight B64D39/00
• CPC Class Codes: G01F 23/263 by measuring variations in capacitance of capacitors
• CPC Class Codes: G01F 23/266 measuring circuits therefor
• CPC Class Codes: G01F 23/804 containing circuits handling parameters other than liquid level
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A true mass fuel gaging system for aircraft utilizing multiplexing of tank unit measurements in or adjacent a fuel tank for improved accuracy and fault isolation. The system provides dual equipment channels for redundancy throughout all data processing portions of the system and also uses extensive built-in testing (BIT) routines so that upon detection of a fault an alternative channel can be switched into use. Detected fault locations are displayed in the cockpit with the fuel quantity displays. The system also provides displays of center of gravity measurements derived from fuel mass and location.

Claims

1. A multiplexed junction probe fuel gaging system for aircraft having at least one fuel tank with multiple fuel sensing units comprising:

a plurality of individual elements mounted wihtin a tank for sensing fuel and providing signals corresponding to fuel measurement;

signal processing apparatus on board the aricraft for converting analog data signals to digital values corresponding to measured fuel quantity;

a junction probe installed in a tank and including circuitry separately coupled to the individual tank mounted elements, the junction probe also being coupled to the signal processing apparatus by a common signal path;

first circuit means included in the junction probe for electrically driving said elements; and

second circuit means in the junction probe for individually measuring said plurality of elements in a predetermined sequence and forming a data stream of analog signals corresponding to the sequence of signals from said elements for transmission to the signal processing apparatus over said common signal path, said data stream containing information separately representative of each individual element for processing in said signal processing apparatus to determine the fuel measurement at each individual element which is measured.

2. The system of claim 1 wherein the tank mounted elements comprise a plurality of tank units within a tank for sensing fuel level and a compensating capacitor within the tank for developing signals proportional to fuel density.

3. The system of claim 1 further including a second junction probe installed in a tank with the first-mentioned junction probe in a master/slave combination, the second junction probe including means for electrically driving a separate plurality of tank mounted elements associated with the second junction probe and measuring the associated elements in a predetermined sequence to form a data stream of analog signals corresponding to said measurements for application to the first junction probe;

the first junction probe further including a slave receiver for receiving signals from the second junction probe and incorporating them in the data stream of analog signals developed by the first junction probe for transmission to the signal processing apparatus.

4. The system of claim 1 wherein the signal processing apparatus comprises a plurality of like processing channels of which one may be selected for active operation, each channel being coupled to receive the data stream of sequential analog signals over said common signal path and including circuit means for digitizing the analog signals and storing the resultant digital values.

5. The system of claim 1 wherein the signal processing apparatus includes a standard electronic module coupled to the common signal path, display means for displaying measured fuel quantity, and an intermediate device coupled between the standard electronic module and the display means for receiving output signals from the standard electronic module and processing said signals for application to the display means.

6. The system of claim 5 wherein the standard electronic module and the intermediate device each comprise a pair of identical signal processing channels, one of each pair being selectable as an active operating channel and the other being a back-up channel.

7. The system of claim 6 wherein multiple fuel tanks are provided and including at least one junction probe in a tank and a plurality of associated tank mounted elements in each tank, and further including means coupling the common signal path from the junction probe in each tank to both of the pair of channels in the standard electronic module.

8. The system of claim 7 wherein the tank mounted elements comprise a plurality of tank units and a compensator in each tank and further including a densitometer in at least one of the fuel tanks and means coupling the densitometer of each tank to both of the pair of channels in the standard electronic module.

9. The system of claim 8 further including means in the standard electronic module for calculating true mass of measured fuel from signals indicative of fuel volume in a given tank and signals from the densitometer in that tank.

10. The system of claim 9 further including means in the standard electronic module for calculating center of gravity from separate signals derived from the individual tank mounted elements and from predetermined signals indicative of selected aircraft parameters.

11. The system of claim 10 wherein each channel in the standard electronic module includes bus means for transmitting signals indicating true mass and center of gravity to the intermediate device.

12. The system of claim 11 wherein each channel in the intermediate device includes means for receiving said bus means signals from the standard electronic module and separating the true mass and center of gravity signals for display in corresponding display means.

13. The system of claim 12 further including a plurality of input means at an operator'"'"'s panel in the aircraft for selectively inputting settable modes to the intermediate device for transmission to the standard electronic module.

14. The system of claim 13 wherein the intermediate device and standard electronic module further include means for storing input means states corresponding to said settable modes and wherein said module includes means for combining the fuel center of gravity measurements with corresponding zero fuel center of gravity signals from the operator'"'"'s panel to develop a display of aircraft center of gravity corresponding to fuel distribution.

15. The system of claim 14 wherein the display means includes a first display unit having means for displaying aircraft center of gravity as a percentage of mean aerodynamic chord derived from zero fuel center of gravity condition input from the operator'"'"'s panel and distribution of fuel mass as calculated in the standard electronic module.

16. The system of claim 15 wherein the first display unit also includes an analog bar graph display of percentage of mean aerodynamic chord between forward and aft limits.

17. The system of claim 16 wherein the first display unit also includes a display for indicating total onboard fuel as calculated in the standard electronic module.

18. The system of claim 17 wherein the first display unit also includes separate potentiometers accessible to an operator for manually inputting to the intermediate device signals corresponding to zero fuel center of gravity and zero fuel weight.

19. The system of claim 15 wherein the display means further include a plurality of second display units, one for each tank, for displaying the fuel mass in a corresponding tank as calculated in the standard electronic module.

20. The system of claim 19 wherein all of the tank display units are constructed in a common configuration, each tank display unit being externally programmed to operate with the tank to which it corresponds.

21. The system of claim 19 wherein each tank display unit includes means for displaying fuel mass, fuel specific gravity, and capacitance of individual tank mounted units, as selected by an operator, in accordance with signals from the standard electronic module transmitted via the intermediate device.

22. The system of claim 19 wherein each tank display unit includes annunciator means for indicating the detection of faults and the location of a detected fault in any one of the following parts of the system:

junction probe, master or slave;

compensator, right or left;

densitometer;

standard electronic module, A or B channel;

intermediate device, A or B channel or common circuitry;

tank display unit;

power supply voltage display unit; and

any one of the tank mounted units in the corresponding fuel tank.

23. The system of claim 19 wherein each tank display unit includes an annunciator for providing a warning of lateral unbalance in the center of gravity due to fuel distribution as calculated in the standard electronic module.

24. The system of claim 19 further including built-in test equipment for testing each of the channels in the standard electronic module, the intermediate device, the load selector display unit and each of the components in the first and second display units upon the application of power to the system and in response to signals developed upon initiation of system test by an operator.

25. The system of claim 24 wherein the built-in test equipment includes means for applying simulated tank mounted element and densitometer signals to each channel of the standard electronic module in turn and comparing the corresponding test readings as calculated in the respective channels for detecting faults in the true mass and center of gravity calculating portions of the standard electronic module.

26. The system of claim 25 wherein the built-in test equipment further includes means for comparing received tank compensator signals with predetermined allowable limits for said signals and providing a fault indication signal at a corresponding tank display unit upon detection of a tank compensator signal outside said allowable limits.

27. The system of claim 26 further including means for substituting a fixed compensator value for the signal from a tank compensator in which a fault is detected so that fuel quantity measurement is not disabled by a detected fault in a tank compensator.

28. The system of claim 24 wherein the built-in test equipment includes means in the standard electronic module for storing a running average of signals from the respective tank mounted elements and comparing the individual signals with said running average to detect an abrupt change in measured signals and provide a corresponding fault display.

29. The system of claim 25 further including means for individually testing the tank units in succession and, upon detection of a faulty tank unit, substituting a predetermined signal value derived from a height vs. volume curve for that tank as the signal to be used in calculating fuel mass.

30. The system of claim 25 wherein the standard electronic module and the intermediate device include non-volatile memory for storing indications of equipment failure detected during testing without loss of said stored failure indications upon removal of system power.

31. The system of claim 19 wherein each of the first and second display units includes means for storing fuel quantity data and fault indication data and means coupled to the storing means for activating corresponding displays of the display unit.

32. The system of claim 31 further including return bus means extending between each display unit and the intermediate device for transmitting sequentially stored data back to the intermediate device for comparison with the data previously sent by the intermediate device in order to detect discrepancies between the compared data.

33. The system of claim 16 wherein said forward and aft limits are variable in accordance with aircraft gross weight data input from the operator'"'"'s panel, as determined by the standard electronic module.

34. The system of claim 9 further including a load select display unit for receiving signals from the standard electronic module and providing a display of fuel quantity at a refueling panel.

35. The system of claim 34 wherein the load select display unit includes a plurality of display modules, one for each tank;

each module including a fuel quantity display and a settable fuel select display for controlling the amount of fuel to be added to the corresponding tank.

36. The system of claim 35 wherein the load select display unit includes a pair of like data processing channels and a cross over switch for selecting the channel to be activated.

37. The system of claim 12 further including redundant return bus means between the standard electronic module and the intermediate device for returning signals from the intermediate device corresponding to those sent to the intermediate device from the standard electronic module and means in the standard electronic module for comparing the returned signals with corresponding signals stored therein to detect any discrepancy between the two sets of signals and provide a fault detection signal when a discrepancy is detected.

38. The system of claim 37 further including return bus means extending between the display means and the intermediate device and means within the intermediate device for comparing the returned signals with corresponding signals stored therein to detect any discrepancy between the two sets of signals and provide a fault detection signal when a discrepancy is detected.

39. The system of claim 5 wherein the first circuit means in the junction probe include timing and control circuitry responsive to synchronizing signals from the standard electronic module for developing the data stream of analog signals in a predetermined sequence.

40. The system of claim 39 wherein said timing and control circuitry includes means for injecting calibration signals in the sequence of tank mounted element signals for use in detecting drift in analog signal reference level due to variations in circuit parameters with use.

41. The system of claim 40 wherein the standard electronic module includes means for monitoring the calibration signals and automatically adjusting analog signal reference levels to compensate for detected drift thereof.

42. The system of claim 26 wherein the standard electronic module includes clock synchronizing means for providing said synchronizing signals to the timing and control circuitry in the junction probe.

43. A multiplexed junction probe for use in the system of claim 1, the probe being adapted for installation in an aircraft fuel tank and comprising:

circuitry for separately coupling to each individual tank mounted element of said plurality and for coupling to the common signal paths leading to the signal processing apparatus;

first circuit means for electrically driving the tank mounted elements sequentially; and

second circuit means for individually measuring said plurality of elements in a predetermined sequence and forming a data stream of analog signals corresponding to the sequence of signals from said elements for transmission to the signal processing apparatus over said common signal path, said data stream containing information separately representative of each individual element for processing in said signal processing apparatus to determine the fuel measurement at each individual element which is measured.

44. The probe of claim 43 further including a second multiplexed junction probe intercoupled with the first-mentioned junction probe in a master/slave combination, the second junction probe including means for electrically driving a separate plurality of tank mounted elements associated with the second junction probe and measuring said associated elements individually in a predetermined sequence to form a data stream of analog signals corresponding to said measurements for application to the first junction probe;

the first junction probe further including a slave receiver for receiving signals from the second junction probe and interspersing them in the data stream of analog signals developed by the first junction probe for transmission to the signal processing apparatus.

45. The probe of claim 43 wherein the first circuit means include timing and control circuitry responsive to synchronizing signals from the signal processing apparatus for developing the data stream of analog signals in a predetermined sequence and time separation.

46. The probe of claim 45 wherein said timing and control circuitry includes means for injecting calibration signals in the sequence of tank mounted element signals for use in detecting drift in analog signal reference level due to variations in circuit parameters with use.

47. A junction probe for installation in the fuel tank of an aircraft to develop signals for measurement of fuel quantity in the tank comprising:

means for individually coupling to a plurality of fuel sensing elements mounted within the tank;

means for electrically driving the tank mounted elements over a common connection to one side of each of said elements; and

a multiplexer coupled to individual leads from the other side of each of said elements, said multiplexer being adapted to measure individually the signal level on each of said individual leads in a predetermined sequence and to develop a corresponding data stream of analog signals in a corresponding sequence at an output thereof, said data stream containing information separately representative of the signal level sensed by each individual element for determining the individual fuel measurements at the locations of said elements.

48. The junction probe of claim 47 further including timing and control circuitry for driving the multiplexer to measure said signals in said predetermined sequence in response to an applied synchronizing signal.

49. The junction probe of claim 48 further including a transmission line driver stage coupled to receive the data stream output of the multiplexer and apply a corresponding analog data stream to a common output signal path.

50. The combination of a pair of junction probes in accordance with claim 49 interconnected in a master/slave configuration for installation in the same fuel tank, the second junction probe of said pair being configured to operate as a slave probe and being connected to a separate set of tank mounted elements to develop a multiplexed signal data stream according to individual analog signals from the second set of elements measured in sequence and apply the analog data stream to the first junction probe of said pair, said first junction probe being configured to operate as a master junction probe and further including a slave receiver for receiving the analog data stream from the slave junction probe and applying said data stream to the transmission line driver of the master junction probe for combining with the data stream from the master junction probe multiplexer, whereby the transmission line driver provides an analog data stream output including the analog data streams from both junction probes in series with each other.

51. The junction probe of claim 48 wherein said timing and control circuitry includes means for injecting calibration signals in the sequence of tank mounted element signals for use in detecting drift in analog signal reference level due to variations in circuit parameters with time.

52. A multiplexed fuel gaging system for aircraft having at least one fuel tank with multiple fuel sensing units comprising:

a plurality of elements mounted within a tank for sensing fuel and providing separate individual signals corresponding to fuel measurement;

signal processing apparatus on board the aircraft for converting analog data signals to digital values corresponding to measured fuel quantity;

a multiplexer associated with a tank and including circuitry separately coupled to the individual tank mounted elements, the multiplexer also being coupled to the signal processing apparatus by a common signal path;

first circuit means included in the multiplexer for electrically driving said elements; and

second circuit means in the multiplexer for individually measuring said plurality of elements in a predetermined sequence and forming a data stream of analog signals corresponding to the sequence of signals from said elements for transmission to the signal processing apparatus over said common signal path, said data stream containing information separately representative of each individual element for processing in said signal processing apparatus to determine the fuel measurement at each individual element which is measured.