Instrumentation and control circuit having multiple, dissimilar sources for supplying warnings, indications, and controls and an integrated cabin pressure control system valve incorporating the same

• US 6,737,988 B2
• Filed: 02/21/2002
• Issued: 05/18/2004
• Est. Priority Date: 02/21/2002
• Status: Expired due to Term

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Horner, Darrell W., Rabon, Joaquin P., Bunn, Andrew D.
• Primary Examiner(s): TRIEU, VAN THANH
• Application Number:
  US10/080,107
• Publication Number:
  US 20030157875A1
• Time in Patent Office: 817 Days
• Field of Search: 340/963, 340/967, 340/970, 340/974, 340/977, 454/72, 454/74, 454/71
• US Class Current: 340/970
• CPC Class Codes: B64D 13/02 the air being pressurised
• CPC Class Codes: B64D 13/04 Automatic control of pressure
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

An integrated cabin pressure control system valve that uses a dual, redundant channel electronic control unit for both control of the valve and to supply alarm, indication, and control signals to the aircraft'"'"'s avionics system. Each channel in the electronic control unit includes an instrumentation and control circuit that uses multiple, dissimilar sensors and signals for warnings, indications, and controls. This configuration reduces the likelihood for a common mode failure that could result in a postulated gradual decompression without indication event.

Claims

1. An aircraft cabin pressure control valve, comprising:

a valve body;

a valve mounted in the valve body and moveable between a closed position and an open position;

at least two controller circuits mounted on the valve body, each controller circuit operable to sense the cabin pressure and supply a valve actuation signal; and

a valve actuator mounted on the valve body and operable, in response to one or more of the valve actuation signals, to position the valve to a predetermined position,

wherein each of the controller circuits includes;

a first pressure sensor operable to sense aircraft cabin pressure and supply a first pressure signal representative thereof,

a second pressure sensor dissimilar from the first pressure sensor and operable to sense aircraft cabin pressure and supply a second pressure signal representative thereof,

a digital signal conditioning circuit coupled to receive the first pressure signal and operable, in response thereto, to supply a digital pressure signal,

an analog signal conditioning circuit coupled to receive the second pressure signal and operable, in response thereto, to supply an analog pressure signal, and

a processor coupled to receive the analog pressure signal and the digital pressure signal and operable, in response thereto, to supply (i) a signal in a first data transmission format that is representative of cabin pressure altitude and (ii) the valve actuation signal.

2. The valve of claim 1, wherein in the processor is further operable to supply a signal in the first data transmission format that is representative of a rate of change of cabin pressure altitude.

3. The valve of claim 1, wherein:

the processor is further coupled to receive a signal representative of ambient pressure outside of the aircraft; and

the processor is further operable to supply a signal in the first data transmission format that is representative of a differential pressure between the aircraft cabin pressure and the ambient pressure.

4. The valve of claim 1, wherein the processor is further operable to supply at least one warning/control signal in the first data transmission format when the signal representative of cabin pressure altitude is at or above at least one predetermined set point.

5. The valve of claim 4, wherein the processor is further operable to supply at least one warning/control signal in a second data transmission format when the signal representative of cabin pressure altitude is at or above at least one predetermined set point.

6. The valve of claim 5, wherein the warning/control signals supplied by the processor include at least a high altitude warning signal and an oxygen deployment control signal.

7. The valve of claim 6, wherein the warning/control signals supplied by the processor further include an altitude limit control signal.

8. The valve of claim 5, further comprising:

a discrete signal processing circuit coupled to receive (i) the warning/control signals in the second data transmission format and (ii) the analog pressure signal, and operable to supply at least one discrete logic signal when one of the analog pressure signal and the processed warning/control signals is at or below at least one predetermined set point.

9. The valve of claim 8, wherein the discrete signal processing circuit comprises:

at least one comparator circuit having a first input terminal coupled to a reference voltage magnitude representative of a warning/control set point and a second input terminal coupled to receive the analog pressure signal, each comparator circuit operable to supply an analog warning/control signal when the analog pressure signal is at or below the reference voltage magnitude; and

at least one logic OR circuit having a first input terminal coupled to receive one of the analog warning/control signals and a second input terminal coupled to receive one of the warning/control signals in the second data transmission format, and operable to supply a discrete logic signal upon receipt of one of the analog warning/control signals and processed warning/control signals.

10. The valve of claim 1, further comprising:

an analog-to-digital converter circuit coupled between the second signal conditioning circuit and the processor and operable to convert the analog pressure signal into a second digital pressure signal.

11. A circuit for supplying one or more signals representative of an aircraft cabin environment, comprising:

a first pressure sensor operable to sense aircraft cabin pressure and supply a first pressure signal representative thereof;

a second pressure sensor dissimilar from the first pressure sensor and operable to sense aircraft cabin pressure and supply a second pressure signal representative thereof;

a digital signal conditioning circuit coupled to receive the first pressure signal and operable, in response thereto, to supply a first digital pressure signal;

an analog signal conditioning circuit coupled to receive the second pressure signal and operable, in response thereto, to supply an analog pressure signal; and

a processor coupled to receive the analog pressure signal and the digital pressure signal and operable, in response thereto, to supply a signal in a first data transmission format that is representative of cabin pressure altitude.

12. The circuit of claim 11, wherein the processor is further operable to supply a signal in the first data transmission format that is representative of a rate of change of cabin pressure altitude.

13. The circuit of claim 11, wherein:

the processor is further coupled to receive a signal representative of ambient pressure outside of the aircraft; and

the processor is further operable to supply a signal in the first data transmission format that is representative of a differential pressure between the aircraft cabin pressure and the ambient pressure.

14. The circuit of claim 11, wherein the processor is further operable to supply at least one warning/control signal in the first data transmission format when the signal representative of cabin pressure altitude is at or above at least one predetermined set point.

15. The circuit of claim 14, wherein the processor is further operable to supply at least one warning/control signal in a second data transmission format when the signal representative of cabin pressure altitude is at or above at least one predetermined set point.

16. The circuit of claim 15, wherein the warning/control signals supplied by the processor include at least a high altitude warning signal and an oxygen deployment control signal.

17. The circuit of claim 16, wherein the warning/control signals further include an altitude limit control signal.

18. The circuit of claim 15, further comprising:

a discrete signal processing circuit coupled to receive (i) the processed warning/control signals in the second data transmission format and (ii) the analog pressure signal and operable to supply at least one discrete logic signal when one of the analog pressure signal and the processed warning/control signals is at or below at least one predetermined set point.

19. The circuit of claim 18, wherein the discrete signal processing circuit comprises:

at least one comparator circuit having a first input terminal coupled to a reference voltage magnitude representative of a warning/control set point and a second input terminal coupled to receive the analog pressure signal, each comparator circuit operable to supply an analog warning/control signal when the analog pressure signal is at or below the reference voltage magnitude; and

at least one logic OR circuit having a first input terminal coupled to receive one of the analog warning/control signals and a second input terminal coupled to receive one of the warning/control signals in the second data transmission format, and operable to supply a discrete logic signal upon receipt of one of the analog warning/control signals and processed warning/control signals.

20. The circuit of claim 11, further comprising:

an analog-to-digital converter circuit coupled between the second signal conditioning circuit and the processor and operable to convert the analog pressure signal into a second digital pressure signal.

21. The circuit of claim 11, wherein the processor is further operable to supply a valve actuation signal for positioning an outflow valve.

22. A controller circuit for controlling the position of a valve to thereby control cabin pressure in an aircraft, the controller circuit comprising:

a first pressure sensor operable to sense aircraft cabin pressure and supply a first pressure signal representative thereof,

a second pressure sensor dissimilar from the first pressure sensor and operable to sense aircraft cabin pressure and supply a second pressure signal representative thereof,

a digital signal conditioning circuit coupled to receive the first pressure signal and operable, in response thereto, to supply a first digital pressure signal;

an analog signal conditioning circuit coupled to receive the second pressure signal and operable, in response thereto, to supply an analog pressure signal; and

a processor coupled to receive the analog pressure signal and the digital pressure signal and operable, in response thereto, to supply (i) a signal in a first data transmission format that is representative of cabin pressure altitude and (ii) the valve actuation signal.

23. The circuit of claim 22, wherein the processor is further operable to supply a signal in the first data transmission format that is representative of a rate of change of cabin pressure altitude.

24. The circuit of claim 22, wherein:

the processor is further coupled to receive a signal representative of ambient pressure outside of the aircraft; and

the processor is further operable to supply a signal in the first data transmission format that is representative of a differential pressure between the aircraft cabin pressure and the ambient pressure.

25. The circuit of claim 22, wherein the processor is further operable to supply at least one warning/control signal in the first data transmission format when the signal representative of cabin pressure altitude is at or above at least one predetermined set point.

26. The circuit of claim 25, wherein the processor is further operable to supply at least one warning/control signal in a second data transmission format when the signal representative of cabin pressure altitude is at or above at least one predetermined set point.

27. The circuit of claim 26, wherein the warning/control signals supplied by the processor include at least a high altitude warning signal and an oxygen deployment control signal.

28. The circuit of claim 27, wherein the warning/control signals further include an altitude limit control signal.

29. The circuit of claim 26, further comprising:

a discrete signal processing circuit coupled to receive (i) the processed warning/control signals in the second data transmission format and (ii) the analog pressure signal and operable to supply at least one discrete logic signal when one of the analog pressure signal and the processed warning/control signals is at or below at least one predetermined set point.

30. The circuit of claim 29, wherein the discrete signal processing circuit comprises:

at least one comparator circuit having a first input terminal coupled to a reference voltage magnitude representative of a warning/control set point and a second input terminal coupled to receive the analog pressure signal, each comparator circuit operable to supply an analog warning/control signal when the analog pressure signal is at or below the reference voltage magnitude; and

at least one logic OR circuit having a first input terminal coupled to receive one of the analog warning/control signals and a second input terminal coupled to receive one of the warning/control signals in the second data transmission format, and operable to supply a discrete logic signal upon receipt of one of the analog warning/control signals and processed warning/control signals.

31. The circuit of claim 22, further comprising:

an analog-to-digital converter circuit coupled between the second signal conditioning circuit and the processor and operable to convert the analog pressure signal into a second digital pressure signal.

32. A method of determining cabin pressure altitude in an aircraft cabin, comprising:

determining cabin pressure using a first pressure determination method;

determining cabin pressure using a second pressure determination method that is different from the first pressure determination method; and

determining cabin pressure altitude based on the cabin pressure determined using at least one of the first and the second pressure determination methods.

33. The method of claim 32, further comprising:

supplying a signal in a first data transmission format that is representative of the determined cabin pressure altitude.

34. The method of claim 32, further comprising determining a rate of change of cabin pressure altitude based on the cabin pressure determined using at least one of the first and the second pressure determination methods.

35. The method of claim 34, further comprising:

supplying a signal in a first data transmission format that is representative of the determined rate of change of cabin pressure altitude.

36. The method of claim 32, further comprising:

determining ambient pressure outside of the aircraft; and

determining a differential pressure between the aircraft cabin pressure and the ambient pressure based on the determined ambient pressure and the cabin pressure determined using at least one of the first and the second pressure determination methods.

37. The method of claim 36, further comprising:

supplying a signal in a first data transmission format that is representative of the determined differential pressure.

38. The method of claim 32, further comprising:

supplying at least one warning/control signal in a first data transmission format when the determined cabin pressure altitude is at or above at least one predetermined set point.

39. The method of claim 38, further comprising:

supplying at least one warning/control signal in a second data transmission format when the determined cabin pressure altitude is at or above at least one predetermined set point.

40. The method of claim 39, wherein the supplied warning/control signals include at least a high altitude warning signal and an oxygen deployment control signal.

41. The method of claim 40, wherein the supplied warning/control signals further include an altitude limit control signal.

42. The method of claim 32, further comprising:

supplying a signal in a second data transmission format that is representative of the cabin pressure determined using the first pressure sensor according to a first data transmission format.

43. The method of claim 32, further comprising:

positioning a cabin pressure control system outflow valve based on the determined cabin pressure altitude.

44. In an aircraft cabin pressure control system having an outflow valve that is used to control cabin pressure in an aircraft, a method of controlling outflow valve position, comprising:

determining the cabin pressure using a first pressure determination method;

determining the cabin pressure using a second pressure determination method that is different from the first pressure determination method;

determining cabin pressure altitude based on the cabin pressure determined using at least one of the first and the second pressure determination methods; and

controlling the position of the outflow valve based on the determined cabin pressure altitude.

45. The method of claim 44, further comprising:

supplying a signal in a first data transmission format that is representative of the determined cabin pressure altitude.

46. The method of claim 44, further comprising determining a rate of change of cabin pressure altitude based on the cabin pressure determined using at least one of the first and the second pressure determination methods.

47. The method of claim 46, further comprising:

supplying a signal in a first data transmission format that is representative of the determined rate of change of cabin pressure altitude.

48. The method of claim 44, further comprising:

determining ambient pressure outside of the aircraft; and

determining a differential pressure between the aircraft cabin pressure and the ambient pressure based on the determined ambient pressure and the cabin pressure determined using at least one of the first and the second pressure determination methods.

49. The method of claim 48, further comprising:

supplying a signal in a first data transmission format that is representative of the determined differential pressure.

50. The method of claim 44, further comprising:

supplying at least one warning/control signal in a first data transmission format when the determined cabin pressure altitude is at or above at least one predetermined set point.

51. The method of claim 50, further comprising:

supplying at least one warning/control signal in a second data transmission format when the determined cabin pressure altitude is at or above at least one predetermined set point.

52. The method of claim 51, wherein the supplied warning/control signals include at least a high altitude warning signal and an oxygen deployment control signal.

53. The method of claim 51, wherein the supplied warning/control signals further include an altitude limit control signal.

54. The method of claim 44, further comprising:

supplying a signal in a second data transmission format that is representative of the cabin pressure determined using the first pressure sensor according to a first data transmission format.