Multiaxis redundant fly-by-wire primary flight control system

• US 5,493,497 A
• Filed: 06/03/1992
• Issued: 02/20/1996
• Est. Priority Date: 06/03/1992
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Buus, Henning
• Primary Examiner(s): Teska, Kevin J.
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US07/893,339
• Time in Patent Office: 1,357 Days
• Field of Search: 364/433, 364/434, 364/428, 318/564, 244/194, 91/363 A
• US Class Current: 701/4
• CPC Class Codes: G05D 1/0077 using redundant signals or controls
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A redundant, multi-channel fly-by-wire control system for use in an aircraft is disclosed. The system includes a left flight control channel (60), a center flight control channel (80) and a right flight control channel (90). Each control channel is capable of flying the aircraft in the event the other two channels fail. Included within each control channel is an actuator controller electronics unit (ACE (62, 82, 92)), which transmits a series of pilot control transducer signals to a set of primary flight computers (64, 84, and 94). The primary flight computers combine the pilot control transducer signals with data obtained from an air data and inertial reference unit (145) to generate a set of flight surface commands. Each ACE selects a set of flight surface commands to control the movement of a set of flight control surfaces on the aircraft.

Claims

1. A fly-by-wire flight control system for an aircraft that monitors the position of pilot controls and produces flight surface commands that control the movement of a plurality of flight control surfaces on the aircraft to adjust the attitude of the aircraft about roll pitch, and yaw directional axes, the system comprising:

(a) a plurality of transducers associated with the pilot controls, each of said plurality of transducers producing a signal indicative of the position of a corresponding pilot control;

(b) a plurality of isolated flight control channels, each of which includes;

(i) a plurality of servo loops assigned to one of the isolated flight control channels of the plurality of isolated flight control channels, each servo loop controlling the movement of a flight control surface on the aircraft such that the plurality of servo loops in the isolated flight control channel operate to control a set of flight control surfaces that together adjust the attitude of the aircraft in the roll, pitch and yaw directional axes;

(ii) an actuator controller electronics unit (ACE) that receives the signals from at least some of the transducers; and

(iii) a primary flight computer that is coupled to the ACE and which generates flight surface commands as a function of the signals from the transducers, the ACE for each isolated flight control channel including means for receiving the flight surface commands and for coupling the flight surface commands to the plurality of servo loops, wherein the set of flight control surfaces controlled by each isolated flight control channel is selected so that operation of a single isolated flight control channel is sufficient to fly the aircraft in the event that the remaining isolated flight control channels fail.

2. The fly-by-wire system as in claim 1, wherein the pilot controls are duplicated at both a pilot position and a copilot position, and wherein each ACE further comprises:

signal selection means for selecting the signals from the transducers associated with the pilot controls at one of the pilot and copilot positions to be transmitted by the ACE to the primary flight computer.

3. The fly-by-wire system as in claim 1, wherein each ACE further comprises:

a switch for coupling the signals from the transducers directly to the servo loops, bypassing the primary flight computer, thereby controlling the movement of the set of flight control surfaces without the flight surface commands generated by the primary flight computers.

4. The fly-by-wire system as in claim 3, wherein the switch for applying the signals from the transducers directly to the servo loops is controlled by a pilot or a copilot.

9. The fly-by-wire system as in claim 1, further comprising a plurality of isolated data busses, wherein all data transferred between the isolated flight control channels are transmitted on the data busses.

10. The fly-by-wire system as in claim 1, wherein each isolated flight control channel includes an independent hydraulic system.

11. The fly-by-wire system as in claim 1, wherein each isolated flight control channel includes an isolated power supply.

12. The fly-by-wire system as in claim 1, wherein the primary flight computer in each isolated flight control channel includes means for selecting signals transmitted by at least one of the flight control channels for use in generating the flight surface commands.

13. The fly-by-wire system as in claim 1, wherein each servo loop comprises:

(a) an electrohydraulic valve that supplies hydraulic fluid to a hydraulic actuator;

(b) a hydraulic actuator position sensor that produces a signal indicative of the position of the hydraulic actuator;

(c) a first demodulator coupled to the hydraulic actuator position sensor; and

servo loop monitoring means for determining whether a servo loop that controls the movement of a flight control surface is functioning properly, wherein the servo loop monitoring means comprises;

(i) means for producing a signal indicative of a predicted position of the electrohydraulic valve;

(ii) a sensor for producing a signal indicative of the actual position of the electrohydraulic valve;

(iii) a servo valve monitor that compares the signal indicative of the position of the electrohydraulic valve with the signal indicative of the predicted position of the electrohydraulic valve;

(iv) a common mode monitor that monitors a common mode voltage on the hydraulic actuator position sensor to determine if the position sensor is operating properly; and

(v) differential mode monitoring means for determining if the first demodulator coupled to the hydraulic actuator position sensor is operating properly.

14. The fly-by-wire system as in claim 13 wherein the differential mode monitoring means includes:

a second demodulator connected to the hydraulic actuator position sensor; and

a comparator that compares a signal from the first demodulator to a signal from the second demodulator, producing an indication of error if said signals are different.

15. The fly-by-wire system as in claim 13, wherein each servo loop further comprises:

a bypass valve that allows a hydraulic actuator to move freely when the flight control surface to which the hydraulic actuator is coupled is moved by a second hydraulic actuator while the hydraulic actuator is inoperative to move the flight control surface.

5. The fly-by-wire system as in claim 5, wherein each ACE receives flight surface commands from the primary flight computer in at least one other flight control channel and wherein each ACE further includes means for selecting the flight surface commands that are used to control the movement of the set of flight control surfaces from among those flight surface commands generated by the primary flight computer in its own flight control channel and those received from said at least one other flight control channel.

6. The fly-by-wire system as in claim 5, wherein the means for selecting the flight surface commands that are used to control the movement of the set of flight control surfaces comprises an input signal selection circuit disposed within the ACE.

7. The fly-by-wire system as in claim 6, wherein each ACE includes a digital-to-analog converter that converts the flight surface commands that are selected from a digital format to an analog format, and wherein the input signal selection circuit disposed within the ACE includes a monitor circuit that determines if the set of flight surface commands selected are being converted properly, the monitor circuit comprising:

an analog-to-digital converter that converts the analog flight surface commands back to a digital format, producing test flight surface commands; and

a comparator that compares the digital flight surface commands selected to the test flight surface commands, producing an error indication if they are different.

8. The fly-by-wire system as in claim 7, wherein the monitor circuit includes means for controlling the switch that applies the signals from the transducers directly to the servo loops such that, if the selected flight surface commands are not properly coupled to the servo loops, the movement of the flight control surfaces is controlled directly by the signals produced by the transducers associated with the pilot controls.

16. A fly-by-wire flight control system for an aircraft that monitors the position of at least one set of controls duplicated at a pilot position and at a copilot position and produces flight surface commands that control the movement of a plurality of flight control surfaces on the aircraft in response thereto, the system comprising:

(a) a plurality of transducers associated with the controls, each transducer producing a signal indicative of the position of said controls;

(b) a plurality of isolated flight control channels, each of which includes;

(i) an actuator controller electronics unit (ACE) that receives the signals indicative of the position of the controls;

(ii) a primary flight computer coupled to the ACE, which generates flight surface commands based at least in part on the signals, the ACE including means for receiving the flight surface commands and for coupling the flight surface commands to a plurality of servo loops that control the movement of a set of flight control surfaces on the aircraft; and

(c) means for selectively applying the signals directly to the servo loops, bypassing the primary flight computer, so that movement of the set of flight control surfaces is controlled without the flight surface commands generated by the primary flight computers.

17. The fly-by-wire system as in claim 16, wherein each ACE further comprises:

signal selection means for selecting the signals from the transducers associated with the controls at one of the pilot and copilot positions for transmission by the ACE to the primary flight computer.

18. The fly-by-wire system as in claim 16, wherein the means for applying the signals from the transducers directly to the servo loops comprises a direct analog mode switch disposed at one of the pilot and copilot positions.

19. The fly-by-wire system as in claim 16, wherein each ACE receives flight surface commands from the primary flight computer in its own flight control channel and from the primary flight computer in at least one other flight control channel, wherein each ACE further includes means for selecting the flight surface commands received that is used to control the movement of the set of flight control surfaces from among said sets of flight surface commands.

20. The fly-by-wire system as in claim 16, wherein each servo loop includes:

servo loop monitoring means for determining whether the servo loop that controls the movement of a flight control surface is operating correctly;

a bypass valve that is controlled by the servo loop monitoring means, which allows a hydraulic valve that moves the flight control surface to move freely when the servo loop monitoring means determines the servo loop is not operating correctly.

21. A method of controlling the position of a plurality of flight control surfaces on an aircraft comprising the steps of:

producing a plurality of transducer signals at both a pilot position and a copilot position, the transducer signals being indicative of control conditions at those positions;

selecting a different set of transducer signals from the plurality of transducer signals for each of a plurality of control channels;

transmitting each selected set of transducer signals to a separate primary flight computer associated with each control channel;

combining the sets of transducer signals in each control channel with data obtained from an air data and inertial reference system to produce a corresponding plurality of sets of flight surface commands; and

transmitting the sets of flight surface commands from the primary flight computers to a corresponding plurality of actuator controller units (ACEs);

selecting within an ACE a set of flight surface commands from among the plurality of sets; and

applying the selected set of flight surface commands to a plurality of servo loops to control a corresponding set of flight control surfaces on the aircraft.

22. The method of claim 21, further comprising the step of:

monitoring each of the servo loops to determine if each servo loop is operating properly and opening a bypass valve in a servo loop if that servo loop is not operating properly.

23. The method of claim 21, further comprising the step of:

applying the transducer signals directly to the plurality of servo loops in the event that the primary flight computers that generate the flight surface commands fail.

24. A fly-by-wire fight control system for an aircraft that monitors the position of pilot controls and produces flight surface commands that control the movement of a plurality of flight control surfaces on the aircraft for adjusting the attitude of the aircraft in a plurality of different directional axes, the system comprising:

(a) a plurality of transducers associated with the pilot controls, each of said plurality of transducers producing a signal indicative of the position of a corresponding pilot control;

(b) a plurality of isolated flight control channels, each of which includes;

(i) a plurality of servo loops assigned to the isolated flight control channel that together control the movement of a set of flight control surfaces on the aircraft;

(ii) an actuator controller electronics unit (ACE) that receives the signals from at least some of the transducers; and

(iii) a primary flight computer that is coupled to the ACE and which generates flight surface commands as a function of the signals from the transducers, the ACE for each flight control channel including means for receiving the flight surface commands from two or more primary flight computers in different isolated flight control channels, for selecting the flight surface commands that are used to control the movement of the set of flight control surfaces from those generated by the two or more primary flight computers and for coupling the selected flight surface commands to the plurality of servo loops, wherein the set of flight control surfaces controlled by each isolated flight control channel is selected so that operation of a single isolated flight control channel is sufficient to fly the aircraft in the event that the remaining isolated flight control channels fail.

25. The fly-by-wire control system of claim 24, wherein the plurality of flight control surfaces on the aircraft includes at least a rudder, a pair of elevators, a pair of ailerons, a plurality of symmetrically located spoiler surfaces and a stabilizer and wherein the set of flight control surfaces controlled by the plurality of servo loops assigned to each isolated flight control channel controls the movement of the rudder, one of the pair of elevators, one of the pair of ailerons and at least one pair of symmetrically located spoiler surfaces.

26. A fly-by-wire flight control system for an aircraft that monitors the position of pilot controls and produces flight surface commands that control the movement of a plurality of flight control surfaces on the aircraft, the system comprising:

(a) a plurality of transducers associated with the pilot controls, each of said plurality of transducers producing a signal indicative of the position of a corresponding pilot control;

(b) a plurality of isolated flight control channels, each of which includes;

(i) a plurality of servo loops assigned to one of the isolated flight control channels of the plurality of isolated flight control channels, each servo loop controlling the movement of a flight control surface on the aircraft and wherein the flight control surfaces controlled by the plurality of servo loops that are assigned to the isolated flight control channel define a set that includes at least a rudder surface, an aileron surface, and at least one pair of symmetrically located spoiler surfaces;

(ii) an actuator controller electronics unit (ACE) that receives the signals from at least some of the transducers; and

(iii) a primary flight computer that is coupled to the ACE and which generates flight surface commands as a function of the signals from the transducers, the ACE for each isolated flight control channel including means for receiving the flight surface commands and for coupling the flight surface commands to the plurality of servo loops, wherein the set of flight control surfaces controlled by each isolated flight control channel is selected so that operation of a single isolated flight control channel is sufficient to fly the aircraft in the event that the remaining isolated flight control channels fail.