Flight control system with alternate control path

• US 8,935,015 B2
• Filed: 12/01/2011
• Issued: 01/13/2015
• Est. Priority Date: 05/09/2011
• Status: Active Grant

• Current Assignee: Parker Intangibles LLC (Parker-Hannifin Corporation)
• Original Assignee: Parker-Hannifin Corporation
• Inventors: Olsoe, Jonathan S., McLaughlin, David, Hartin, Charles B., Cyrot, Luc, Streeter, Bruce, Wanchu, Stephane
• Primary Examiner(s): Nguyen, John Q
• Assistant Examiner(s): KERRIGAN, MICHAEL V
• Application Number:
  US13/308,818
• Publication Number:
  US 20120290153A1
• Time in Patent Office: 1,139 Days
• Field of Search: 244/194
• US Class Current: 701/3
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions
• CPC Class Codes: G05D 1/0077 using redundant signals or controls

Abstract

A flight control system and method including a primary flight control path between one or more pilot controls and control surface actuators on an associated aircraft, wherein the primary control path includes one or more flight control computers and one or more first data concentrators; and a secondary flight control path between the one or more pilot controls and the control surface actuators, wherein the secondary flight control path utilizes direct mode control laws to control the control surface actuators; wherein the primary flight control path and the secondary flight control path are independent from each other and the secondary flight control path is operative upon detection of a fault in the primary flight control path.

Claims

1. A flight control system comprising:

a primary flight control path from one or more pilot controls to control surface actuators on an associated aircraft, wherein the primary control path includes one or more flight control computers and one or more first data concentrators; and

a secondary flight control path from the one or more pilot controls to the control surface actuators, wherein the secondary flight control path utilizes direct mode control laws to control the control surface actuators;

wherein the primary control path includes remote electronic units operatively coupled to the one or more data concentrators, and wherein the secondary control path bypasses all remote electronic units, and wherein the primary flight control path and the secondary flight control path are independent from each other over the control paths from the one or more pilot controls to the control surface actuators, and the secondary flight control path is operative upon detection of a fault in the primary flight control path.

2. The system of claim 1, wherein the one or more first data concentrators are coupled between the one or more pilot controls and the one or more flight control computers, wherein the data concentrators monitor the one or more pilot controls and transmit control information to the one or more flight control computers.

3. The system of claim 2, wherein at least one of the one or more first data concentrators is an inceptor interface module.

4. The system of claim 2, further including one or more remote electronic units coupled to the one or more flight control computers and the one or more data concentrators.

5. The system of claim 1, wherein the one or more flight control computers is configured to receive pilot commands from at least one of the first data concentrators, and further including an alternate flight control unit, wherein the alternate flight control unit is operable once the alternate flight control unit is enabled and armed.

6. The system of claim 5, wherein the alternate flight control unit is configured to receive discrete inputs from one or more remote electronic units to facilitate enabling the alternate flight control unit.

7. The system of claim 6, wherein the alternate flight control unit is configured to receive discrete inputs from the one or more flight control computers to facilitate arming the alternate flight control unit.

8. The system of claim 6, wherein the alternate flight control unit is configured to receive additional discrete inputs from the one or more flight control computers to facilitate arming the alternate flight control unit.

9. The system of claim 1, further including one or more time triggered protocol busses coupled between the one or more flight control computers and one or more remote electronic units to facilitate movement of one or more control surfaces via an analog signal path.

10. The system of claim 1, further including one or more remote electronic units operatively coupled to the one or more data concentrators, wherein the one or more data concentrators are operatively coupled between the one or more flight control computers and the one or more remote electronic units.

11. The system of claim 1, further including a tertiary flight control path from one or more pilot controls to control surface actuators, wherein the tertiary control path includes the one or more first data concentrators and bypasses all flight control computers.

12. The system of claim 11, wherein the primary flight control path includes one or more remote electronic units operatively coupled between the one or more flight control computers and the control surface actuators, and wherein the tertiary flight control path includes the one or more remote electronic units operatively coupled between the one or more first data concentrators and the control surface actuators.

13. The system of claim 12, wherein a first data bus operatively couples the one or more remote electronic units to the one or more flight control computers and a second data bus operatively couples the one or more remote electronic units to the one or more first data concentrators, and wherein the first and second data busses have dissimilar hardware and/or firmware.