Methodology for simplification of aircraft harnessing in multi-redundant control systems
AssigneeHamilton Sundstrand Corporation
InventorsJeffrey A. Eldridge, Steven A. Avritch
Life of this patent
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Abstract
A method and control system that implements a particular aircraft harnessing for an aircraft is provided. The control system includes an effector Line-Replaceable Unit (LRU) including a first connection port, a second connection port, and a first interconnect wire internally connecting the first connection port and the second connection port, a first control LRU connected using a first harnessing to the effector LRU, and a second control LRU connected using a second harnessing to the effector LRU, wherein the first control LRU and the second control LRU are configured to communicate using the first interconnect wire in the effector LRU.
Claims20
A control system with aircraft harnessing for an aircraft, the control system comprising:
- an effector Line-Replaceable Unit (LRU) comprising a first connection port, a second connection port, and a first interconnect wire internally connecting the first connection port and the second connection port;
- a first control LRU connected using a first harnessing to the effector LRU;
- and
- a second control LRU connected using a second harnessing to the effector LRU,
- wherein the first control LRU and the second control LRU are configured to communicate using the first interconnect wire in the effector LRU.
An effector Line-Replaceable Unit (LRU) for an aircraft comprising:
- a first connection port configured to connect to a first control LRU using a first harnessing that includes a first communication cable;
- a second connection port configured to connect to a second control LRU using a second harnessing that includes a second communication cable;
- a third connection port configured to connect to a third control LRU using a third harnessing that includes a third communication cable;
- a first interconnect wire internally connecting the first connection port and the second connection port;
- a second interconnect wire internally connecting the first connection port and the third connection port;
- and
- a third interconnect wire internally connecting the second connection port and the third connection port,
- wherein the first control LRU, the second control LRU, and the third control LRU are configured to communicate with each other using the first interconnect wire, the second interconnect wire, and the third interconnect wire in the effector LRU.
A method of implementing a control system for controlling an aircraft, the method comprising:
- providing an effector Line-Replaceable Unit (LRU);
- connecting a first connection port of the effector LRU to a second connection port of the LRU internally using a first interconnect wire;
- connecting the first connection port to a third connection port of the LRU internally using a second interconnect wire;
- connecting the second connection port and the third connection port using a third interconnect wire;
- providing a first control LRU, a second control LRU, and a third control LRU that are connected to the first connection port, the second connection port, and the third connection port respectively;
- transmitting signals between the first control LRU, the second control LRU, and the third control LRU using the first interconnect wire, the second interconnect wire, and the third interconnect wire.
Dependencies are inferred from the claim text.