Device for controlling the thrust of a multi-engine aircraft

• US 5,927,655 A
• Filed: 09/08/1997
• Issued: 07/27/1999
• Est. Priority Date: 09/09/1996
• Status: Expired due to Term

• Current Assignee: Airbus France
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Garavel, Fran.cedilla.ois, Clavel, Thierry, Zaccaria, Patrick, Larramendy, Panxika
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US08/925,605
• Time in Patent Office: 687 Days
• Field of Search: 244/76 R, 244/53 R, 244/62, 244/55, 244/194, 244/195, 701/3, 701/99, 701/100, 701/112, 701/183, 701/182, 60/702
• US Class Current: 244/195
• CPC Class Codes: B64D 31/10 for preventing asymmetric thrust
• CPC Class Codes: F02C 9/42 specially adapted for the control of two or more plants simultaneously
• CPC Class Codes: G05D 1/0072 to counteract a motor failure
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The present invention relates to a device for controlling the thrust of an aircraft, with several engines (M1, M4), comprising calculation units (UC1, UC4) that formulate first commands for controlling the engine speeds. According to the invention, said device (1) additionally comprises means (CONT1, CONT4) of controlling the two outer engines (M1, M4), calculation means that formulate second commands for controlling the speed of the outer engines (M1, M4) making it possible to obtain a reduction in thrust, and switching means which, during normal operation of the outer engines (M1, M4) send the first commands to these engines and, when one outer engine (M1) fails, send the second commands to the opposite outer engine (M4).

Claims

1. A device for controlling the thrust of an aircraft (A), this thrust being generated by a number of engines (M1 to M4) set out more or less in a line (L--L) which is orthogonal to the longitudinal axis (X--X) of the aircraft (A), and are arranged respectively so that they are symmetric with respect to said longitudinal axis (X--X), which device comprises:

calculation units (UC1, UC4) which are associated respectively with each of said engines, each of said calculation units (UC1, UC4) formulating first commands for controlling the speed of the associated engine and sending said first commands to said associated engine;

control means (CONT1, CONT4) which respectively monitor the operation of at least some of said engines (M1, M4) and which detect failures of said monitored engines (M1, M4);

calculation means (MC) which are associated respectively at least with the calculation units (UC1, UC4) associated with said monitored engines (M1, M4) and which determine second commands for controlling the speed of said monitored engines (M1, M4) making it possible to reduce the thrust of these engines relative to said first commands; and

switching means (COM) associated with said calculation means (MC) and with the corresponding calculation units (UC1, UC4) and which;

when said monitored engines (M1, M4) are operating normally send the corresponding first commands to these engines; and

which

when one of said monitored engines (M1) fails, send the corresponding second commands to at least one engine (M4) which is on the opposite side of the longitudinal axis (X--X) of the aircraft (A) to said failed engine (M1),

wherein said control means (CONT1, CONT4), said calculation means (MC) and said switching means (COM) are associated with each of the engines (M1 to M4) of the aircraft (A) and are intended, when one of the two outer engines (M1) fails, these engines being the ones furthest away from and one on either side of the longitudinal axis (X--X), to reduce the thrust of all the engines on the opposite side of the longitudinal axis (X--X) of the aircraft (A) to said failed engine.

2. The device as claimed in claim 1, wherein said calculation means (MC) formulate said second commands only when the aircraft (A) is in a defined flight envelope.

3. The device as claimed in claim 2, wherein said flight envelope is defined by the following two combined conditions:

the speed and the altitude of the aircraft are below predefined values.

4. The device as claimed in claim 1, wherein said calculation means (CAL) and said switching means (COM) are incorporated each time into the associated calculation unit (UC1).

5. The device as claimed in claim 1, wherein said control means (CONT1, CONT4) detect failure of a monitored engine when the value of a parameter characteristic of the operation of said engine lies outside an envelope of permissible predetermined values.

6. The device as claimed in claim 5, wherein said parameter characteristic of the operation of the engine represents the speed of a low-pressure module of said engine.

7. The device as claimed in claim 1, wherein said second commands for controlling the engine speed are formulated as a function of the altitude, the temperature and the speed of the aircraft.

8. The device as claimed in claim 1, wherein said second commands for controlling the engine speed are formulated in such a way as to obtain a thrust for which the aircraft can be steadied, should one of said engines fail, at a predetermined speed.

9. The device as claimed in claim 1, wherein the control means (CONT1, CONT4) associated with a pair of opposed engines are connected to each other.

10. The device as claimed in claim 1, wherein all said control means are incorporated into a central control unit.

11. A device for controlling the thrust of an aircraft (A), this thrust being generated by a number of engines (M1 to M4) set out more or less in a line (L--L) which is orthogonal to the longitudinal axis (X--X) of the aircraft (A), and are arranged respectively so that they are symmetric with respect to said longitudinal axis (X--X), which device comprises:

calculation units (UC1, UC4) which are associated respectively with each of said engines, each of said calculation units (UC1, UC4) formulating first commands for controlling the speed of the associated engine and sending said first commands to said associated engine;

control means (CONT1, CONT4) which respectively monitor the operation of at least some of said engines (M1, M4) and which detect failures of said monitored engines (M1, M4);

calculation means (MC) which are associated respectively at least with the calculation units (UC1, UC4) associated with said monitored engines (M1, M4) and which determine second commands for controlling the speed of said monitored engines (M1, M4) making it possible to reduce the thrust of these engines relative to said first commands; and

switching means (COM) associated with said calculation means (MC) and with the corresponding calculation units (UC1, UC4) and which;

when said monitored engines (M1, M4) are operating normally send the corresponding first commands to these engines; and

which

when one of said monitored engines (M1) fails, send the corresponding second commands to at least one engine (M4) which is on the opposite side of the longitudinal axis (X--X) of the aircraft (A) to said failed engine (M1),

wherein said control means, said calculation means and said switching means are associated with each of the engines (M1 to M4) of the aircraft (A) and are intended, when any one engine of the aircraft (A) fails, to reduce the thrust of all the engines on the opposite side of the longitudinal axis (X--X) of the aircraft (A) to said failed engine.

12. The device as claimed in claim 11, wherein said calculation means (MC) formulate said second commands only when the aircraft (A) is in a defined flight envelope.

13. The device as claimed in claim 12, wherein said flight envelope is defined by the following two combined conditions;

the speed and the altitude of the aircraft are below predefined values.

14. The device as claimed in claim 11, wherein said calculation means (CAL) and said switching means (COM) are incorporated each time into the associated calculation unit (UC1).

15. The device as claimed in claim 11, wherein said control means (CONT1, CONT4) detect failure of a monitored engine when the value of a parameter characteristic of the operation of said engine lies outside an envelope of permissible predetermined values.

16. The device as claimed in claim 15, wherein said parameter characteristic of the operation of the engine represents the speed of a low-pressure module of said engine.

17. The device as claimed in claim 11, wherein said second commands for controlling the engine speed are formulated as a function of the altitude, the temperature and the speed of the aircraft.

18. The device as claimed in claim 11, wherein said second commands for controlling the engine speed are formulated in such a way as to obtain a thrust for which the aircraft can be steadied, should one of said engines fail, at a predetermined speed.

19. The device as claimed in claim 11, wherein the control means (CONT1, CONT4) associated with a pair of opposed engines are connected to each other.

20. The device as claimed in claim 11, wherein all said control means are incorporated into a central control unit.