초록 ▼

An inertial reference unit (IRU) is described which includes a processor programmed to provide inertial data from received inertial signals, a primary sensor unit providing the inertial signals to the processor, and an input/output (I/O) unit communicatively coupled to the processor. The I/O unit pr

An inertial reference unit (IRU) is described which includes a processor programmed to provide inertial data from received inertial signals, a primary sensor unit providing the inertial signals to the processor, and an input/output (I/O) unit communicatively coupled to the processor. The I/O unit provides signals, including inertial data, to an external interface of the IRU and routes signals to and from the processor. The inertial reference unit also includes a secondary sensor unit separate from the primary sensor unit which provides inertial data independent of the inertial data provided by the processor.

대표청구항 ▼

What is claimed is: 1. An inertial reference unit (IRU) comprising: a processor programmed to provide inertial data from received inertial signals; a primary sensor unit comprising one or more gyroscopes and one or more accelerometers providing the inertial signals to said processor; an input/outpu

What is claimed is: 1. An inertial reference unit (IRU) comprising: a processor programmed to provide inertial data from received inertial signals; a primary sensor unit comprising one or more gyroscopes and one or more accelerometers providing the inertial signals to said processor; an input/output (I/O) unit communicatively coupled to said processor and providing signals, including inertial data, to an external interface of said IRU, said I/O unit routing signals to and from said processor; and a secondary sensor unit separate from said primary sensor unit, said secondary sensor unit providing inertial data independent of the inertial data provided by said processor. 2. An IRU according to claim 1 wherein said secondary sensor unit provides inertial data comprising one or more of heading, aircraft body rates, acceleration rates, and aircraft attitude. 3. An IRU according to claim 1 wherein said secondary sensor unit provides inertial data to existing aircraft interfaces and information busses through the external interface of said IRU. 4. An IRU according to claim 1 further comprising switching logic, said switching logic configured to switch between said secondary sensor unit and said I/O unit as the source of inertial data at the external interface of said IRU. 5. An IRU according to claim 4 wherein said secondary sensor unit and said switching logic are mounted on a circuit card, the circuit card configured for insertion into an expansion slot of a chassis of said IRU. 6. An IRU according to claim 1 wherein said secondary sensor unit comprises at least one micro-electromechanical systems (MEMS) device. 7. An IRU according to claim 1 further comprising a chassis, said chassis having one of a four MCU dimension and a ten MCU dimension. 8. An IRU according to claim 1 wherein said secondary sensor unit is configured to integrate GPS position into the inertial data provided by said secondary sensor unit. 9. A method for adding an additional source of inertial data to an inertial reference unit (IRU), the IRU including a primary source of inertial data, said method comprising: installing a secondary sensor unit into a chassis of the IRU; multiplexing the inertial data from the primary source of inertial data and the inertial data from the secondary sensor unit to an inertial data output of the IRU; and integrating GPS position data into the inertial data provided by the secondary sensor unit. 10. A method according to claim 9 wherein installing a secondary sensor unit comprises installing a micro-electromechanical systems (MEMS) device within the chassis of the IRU. 11. A method according to claim 9 wherein multiplexing the inertial data comprises installing switching logic in the IRU, the switching logic configured to switch between the inertial data from the primary source of inertial data and the inertial data from the secondary sensor unit as the inertial data output of the IRU. 12. A method according to claim 11 further comprising: configuring a circuit card with the secondary sensor unit and the switching logic; and installing the circuit card within the IRU. 13. A method according to claim 11 further comprising routing power for the secondary sensor unit and the switching logic through an external connector of the IRU. 14. A method according to claim 9 further comprising: configuring a circuit card with the secondary sensor unit; and installing the circuit card within the IRU. 15. A method for multiplexing sources of inertial data to existing busses and interfaces of an aircraft, said method comprising: installing a secondary sensor unit that includes at least one micro-electromechanical systems (MEMS) device into a chassis of a primary source of inertial data; and installing switching logic to multiplex the inertial data from a primary source of inertial data and the inertial data from the secondary sensor unit to an inertial data output. 16. A method according to claim 15 further comprising utilizing the switching logic to switch from the primary source of inertial data to the secondary sensor unit upon a failure of the primary source of inertial data. 17. A method according to claim 16 wherein utilizing the switching logic to switch comprises utilizing the switching logic to monitor a discrete signal from the primary source of inertial data, the discrete changing state upon a failure of the primary source of inertial data. 18. A method according to claim 15 further comprising supplying power for the switching logic and the secondary sensor unit from an external source, through connectors of the chassis of the primary source of inertial data, to the switching logic and the secondary sensor unit.