Integrated aircraft air data system

• US 5,001,638 A
• Filed: 04/18/1989
• Issued: 03/19/1991
• Est. Priority Date: 04/18/1989
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Zimmerman, Ward H., McIntyre, Melville D. W.
• Primary Examiner(s): Lall, Parshotam S.
• Assistant Examiner(s): Pipala, Edward J.
• Application Number:
  US07/339,675
• Time in Patent Office: 700 Days
• Field of Search: 364/424.06, 364/434, 364/131, 364/137, 364/433, 364/424.01, 364/431.01, 364/431.02, 364/431.04, 371/7, 371/11.2, 371/11.3, 371/67.1, 371/68.1-68.3, 371/8.1, 244/75 R, 244/76 R, 244/194
• US Class Current: 701/14
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

An integrated air data system for use on an aircraft. Airframe air data units (18) are connected to receive a plurality of redundant total pressure sensor inputs (20,22,24), a plurality of redundant static pressure sensor inputs (26,28,30), and a total temperature sensor input (32). Similar redundant sensor inputs are provided a first and second channel in each of two electronic engine controls (34,36). Bidirectional data buses (16) connect the airframe air data system to the electronic engine control system, so that the same sensor signals are available for each of the systems. The airframe air data unit and the primary electronic engine control channel having priority to control each engine are independently operative to select a preferred total pressure, static pressure, and total temperature value according to a common programmed logic scheme. The selection logic gives priority to the use of the same value for common parameters in each of the systems, where possible. The logic also minimizes the risk that failure of a single sensor may result in use of an incorrect value for a parameter, and that any combination of failures of different sensors, except for similar failures occurring independently on each engine, might result in an undesired effect on more than one engine.

Claims

1. On an aircraft, an integrated air data system comprising:

(a) a plurality of first sensors associated with an airframe air data unit, said first sensors each providing a signal indicative of a parameter used by the airframe air data unit to determine the flight status of the aircraft;

(b) a plurality of second sensors associated with an engine control system, said second sensors each providing a signal indicative of a parameter used by the engine control system to control the operation of an aircraft engine, the signals provided by said second sensors being redundant to the signals provided by said first sensors, the same parameter being sensed by at least one each of the first and second sensors;

(c) a bidirectional data bus connecting the airframe air data unit to the engine control system and operative to convey data bidirectionally therebetween;

(d) control means, disposed within both the airframe air data unit and the engine control system, and connected to the data bus, for selecting at least one of the redundant signals provided by the first and second sensors as a preferred signal for use by the airframe air data unit and the engine control system according to a predetermined logic that gives priority to using the same signal for both the airframe air data unit and the engine control system, and minimizes the effect of a failure of any one or more of the first and second sensors.

2. The integrated air data system of claim 1, wherein the first sensors comprise a plurality of total pressure sensors, a plurality of static pressure sensors, and a total temperature sensor.

3. The integrated air data system of claim 2, wherein the second sensors comprise a plurality of total pressure sensors, a plurality of static pressure sensors, and a plurality of total temperature sensors.

4. The integrated air data system of claim 3, wherein the engine control system includes a first and a second channel, each channel including inputs from at least one of the total pressure sensors, from at least one of the static pressure sensors, and from at least one of the total temperature sensors comprising the second sensors, one of the first and second channels having priority to control an aircraft engine in response to the selected signals.

5. The integrated air data system of claim 4, wherein the total pressure and static pressure sensors comprising one of the first sensors and the second sensors are more accurate, the logic followed by said control means giving preference to selecting signals provided by said one of the total pressure and static pressure sensors, rather than corresponding redundant signals provided by the other of said first and second sensors.

6. The integrated air data system of claim 4, wherein the logic followed by said control means gives preference to selecting one of the signals provided by the total temperture sensors rather than the other corresponding redundant signal.

7. The integrated air data system of claim 4, wherein the control means are further operative to determine differences between selected redundant signals for comparison to predetermined values in selecting which of the corresponding redundant signals indicative respectively of total pressure, static pressure, and total temperature will be used by the airframe air data unit and the engine control system.

8. On an aircraft having at least one engine controlled by an engine control system in response to air data signals, and including an airframe air data unit for determining flight status information in response to air data signals, said air data signals being indicative of total pressure, static pressure, and total temperature, an integrated air data system comprising:

(a) a first total pressure sensor disposed in proximity to an airframe of the aircraft, connected to provide a signal indicative of total pressure to the airframe air data unit;

(b) a second total pressure sensor disposed in proximity to said at least one engine, connected to provide a signal indicative of total pressure to the engine control system;

(c) a first static pressure sensor disposed in proximity to the airframe, connected to provide a signal indicative of static pressure to the airframe air data unit;

(d) a second static pressure sensor disposed in proximity to said at least one engine, connected to provide a signal indicative of static pressure to the engine control system;

(e) a first total temperature sensor, disposed in proximity to the airframe, connected to provide a signal indicative of total temperature to the airframe air data unit;

(f) a second total temperature sensor, disposed in proximity to said at least one engine, connected to provide a signal indicative of total temperature to the engine control system, corresponding signals provided by the first total pressure, static pressure, and total temperature sensors being generally redundant to those respectively provided by the second total pressure, static pressure, and total temperature sensors;

(g) means for bidirectionally conveying the signals indicative of total pressure, static pressure, and total temperature between the airframe air data unit and the engine control system; and

(h) signal selection means, associated with both the airframe air data unit and the engine control system, for selecting one each of the corresponding redundant signals provided respectively by the first and second total pressure, static pressure, and total temperature sensors, for use by the airframe air data unit and the engine control system, said signal selection means including predetermined logic means for determining a preferred one of said respective redundant signals for said selection, failure of one or more of said first and second sensors having a minimal impact on the operation of the airframe air data unit and the engine control system.

9. The integrated air data system of claim 8, wherein the aircraft includes a plurality of engines for propelling the aircraft, each engine being controlled by an engine control system.

10. The integrated air data system of claim 9, wherein the engine control system comprises a plurality of channels associated with each engine, each channel being connected to receive the signals produced by the first and the second total pressure, static pressure, and total temperature sensors, and wherein one of the channels has priority to control operation of the engine with which it is associated.

11. The integrated air data system of claim 10, further comprising a plurality of second total temperature sensors, wherein the signal selection means are further operative to determine whether the total temperatures indicated by any available second total temperature sensors agree within a predefined value in selecting said preferred one of the total temperature signals.

12. The integrated air data system of claim 11, wherein the signal selection means are further operative to use the total temperature indicated by the first total temperature sensor in selecting said preferred signal, if signals from less than all the second total temperature sensors are available.

13. The integrated air data system of claim 10, wherein the first total pressure and static pressure sensors are more accurate than the second total pressure and static pressure sensors, said signal selecting means being operative to give priority to selecting the signals produced by the first total pressure sensor and by the first static pressure sensor over signals produced by the corresponding respective second total and static pressure sensors.

14. The integrated air data system of claim 13, further comprising a plurality of first total pressure sensors, wherein if all the first total pressure sensors have failed, said signal selecting means are operative to select the second total pressure sensor signal of the channel having priority, for use in controlling the engine.

15. The integrated air data system of claim 13, further comprising a plurality of first static pressure sensors, wherein if all the first static pressure sensors have failed, said signal selecting means are operative to select the second static pressure sensor signal in controlling the engine.

16. The integrated air data system of claim 14, wherein the signal selecting means are operative to determine whether differences between the total pressures indicated by the plurality of first total pressure sensors are excessive by comparison with a predefined value in selecting said preferred total pressure signal.

17. The integrated air data system of claim 8, further comprising a plurality of first static pressure sensors, wherein the signal selecting means are operative to determine whether differences between the static pressures indicated by the plurality of first static pressure sensors are excessive by comparison with a predefined value in selecting said preferred static pressure signal.

18. The integrated air data system of claim 14, further comprising a plurality of second total pressure sensors, wherein the signal selecting means are operative to determine whether differences between the total pressures indicated by the plurality of second total pressure sensors are excessive by comparison with a predefined value in selecting said preferred total pressure signal.

19. The integrated air data system of claim 17, further comprising a plurality of second static pressure sensors, wherein the signal selecting means are operative to determine whether differences between the static pressures indicated by the plurality of second static pressure sensors are excessive by comparison with a predefined value in selecting said preferred static pressure signal.

20. The integrated air data system of claim 18, wherein the signal selecting means are operative to determine whether differences between the total pressure indicated by an available first total pressure sensor and the total pressure indicated by at least one of the second total pressure sensors are excessive by comparison with a predefined value in selecting said preferred total pressure signal.

21. The integrated air data system of claim 19, wherein the signal selecting means are operative to determine whether differences between the static pressure indicated by an available first static pressure sensor and the static pressure indicated by at least one of the second static pressure sensors are excessive by comparison with a predefined value in selecting said preferred static pressure signal.

22. The integrated air data system of claim 10, wherein the signal selecting means are operative to select different total temperature signals, total pressure signals, and static pressure signals to control each engine if the accuracy of the corresponding sensors producing the air data signals is not uncertain, so that erroneous air data signals are less likely to affect all engines.