초록 ▼

Systems and methods for asynchronous multi-channel data communications are provided. In one embodiment, a system in accordance with the invention includes a plurality of redundant pairs of computer systems, a plurality of actuators, and a plurality of line replaceable units. Each of the line replace

Systems and methods for asynchronous multi-channel data communications are provided. In one embodiment, a system in accordance with the invention includes a plurality of redundant pairs of computer systems, a plurality of actuators, and a plurality of line replaceable units. Each of the line replaceable units is coupled to one of the actuators, and each of the line replaceable units is configured to receive synchronous digital control data from each pair of computer systems of the plurality of redundant pairs of computer systems. The plurality of redundant pairs of computer systems includes at least three redundant pairs of computer systems, and the plurality of line replaceable units includes three or more line replaceable units.

대표청구항 ▼

What is claimed is: 1. A system comprising: a plurality of redundant pairs of computer systems; a plurality of actuators; and a plurality of line replaceable units with dual-dissimilar processing lanes, each of the plurality of line replaceable units being coupled to one of the plurality of actuato

What is claimed is: 1. A system comprising: a plurality of redundant pairs of computer systems; a plurality of actuators; and a plurality of line replaceable units with dual-dissimilar processing lanes, each of the plurality of line replaceable units being coupled to one of the plurality of actuators, each of the plurality of line replaceable units being configured to receive synchronous digital control data from each pair of computer systems of the plurality of redundant pairs of computer systems, wherein the plurality of redundant pairs of computer systems includes at least three redundant pairs of computer systems and wherein the plurality of line replaceable units includes three or more line replaceable units, wherein each line replaceable unit is configured to perform a validity check of each redundant pair of computer systems, wherein each line replaceable unit performs the validity check by determining if a freshness invalid signal and an error condition exists based on a corresponding digital control data and the freshness invalid signal, wherein each line replaceable unit determines if an error condition exists for each of the pairs of plurality of redundant pairs of computer systems by determining: if a difference between the digital control data of each computer system of a pair is greater than a threshold value, then a first constant value is added to an error value; if the difference between the digital control data from the computer systems of a pair of computer systems is less than the first threshold value, then a second constant value is subtracted from the error value; if the error value is greater than a second threshold value, then a line replaceable unit indicates that an error condition exists with respect to the pair of computer systems; and if the error value is at least equal to a third threshold value, then the line replaceable unit indicates that an error condition does not exist. 2. A system comprising: a plurality of redundant pairs of computer systems; a plurality of actuators; and a plurality of line replaceable units with dual-dissimilar processing lanes, each of the plurality of line replaceable units being coupled to one of the plurality of actuators, each of the plurality of line replaceable units being configured to receive synchronous digital control data from each pair of computer systems of the plurality of redundant pairs of computer systems, wherein the plurality of line replaceable units are configured to select the digital control data of one of the computer systems of a pair of the plurality of redundant pairs of computer systems, wherein each of the plurality of line replaceable units converts the selected digital control data into an analog signal and sends the analog signal to the corresponding actuator, wherein the digital control data is one of discrete or continuous variable data, wherein each line replaceable unit is configured to perform a validity check of each redundant pair of computer systems, wherein each line replaceable unit performs the validity check by determining if a freshness invalid signal and an error condition exists based on a corresponding digital control data and the freshness invalid signal, wherein each line replaceable unit determines if an error condition exists for each of the pairs of plurality of redundant pairs of computer systems by determining: if a difference between the digital control data of each computer system of a pair is greater than a threshold value, then a first constant value is added to an error value; if the difference between the digital control data from the computer systems of a pair of computer systems is less than the first threshold value, then a second constant value is subtracted from the error value; if the error value is greater than a second threshold value, then a line replaceable unit indicates that an error condition exists with respect to the pair of computer systems; and if the error value is at least equal to a third threshold value, then the line replaceable unit indicates that an error condition does not exist. 3. The system of claim 2, wherein the line replaceable units repeat the determination of whether an error condition exists at a periodic rate. 4. The system of claim 2, wherein the line replaceable units are configured to disable one or more of the redundant pairs of computer systems based on the determination of whether an error condition exists. 5. The system of claim 2 wherein the plurality of redundant pairs of computer systems, the plurality of actuators, and the plurality of line replaceable units are included within an aircraft. 6. The system of claim 5, wherein the aircraft includes control surfaces that a couple to one or more of the plurality of actuators. 7. A flight control system, comprising: at least three pairs of flight computer systems; a plurality of actuators; and at least three actuation control modules, each of the actuation control modules being coupled to at least one of the plurality of actuators and being configured to receive synchronous digital control data from one or more pairs of the at least three pairs of flight computer systems, wherein each actuation control module is configured to perform a validity check of one or more pairs of the at least three pairs of flight computer systems, wherein each actuation control module performs the validity check by determining if a freshness invalid signal and an error condition exists based on a corresponding digital control data and the freshness invalid signal, wherein each actuation control module is configured to select at least a portion of the digital control data, and to convert the selected portion of the digital control data, wherein each actuation control module determines if an error exists for each of the pairs of plurality of redundant pairs of computer systems by determining: if a difference between the digital control data of each computer system of a pair is greater than a threshold value, then a first constant value is added to an error value; if the difference between the digital control data from the computer systems of a pair of computer systems is less than the first threshold value, then a second constant value is subtracted from the error value; if the error value is greater than a second threshold value, an actuation control module indicates that an error condition exists with respect to the pair of computer systems; and if the error value is at least equal to a third threshold value, then the actuation control module indicates that an error condition does not exist. 8. The system of claim 7, wherein the actuation control modules repeat the determination of whether an error condition exists at a periodic rate. 9. The system of claim 7, wherein the actuation control modules are configured to disable one or more of the pairs of flight computer systems based on a determination that an error condition exists. 10. The system of claim 7 wherein at least some of the plurality of actuators are operatively coupled to one or more control surfaces of an aircraft.