60 results about "Integrated modular avionics" patented technology

A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and / or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

A robotic system includes a plurality of robotic elements, each having at least one processing component, at least one memory component, and an I / O interface; and a virtual backplane coupling the plurality of robotic elements.

An integrated modular avionics (IMA) cabinet for housing printed circuit board (PCB) modules includes a chassis configured with slots for receiving the PCB modules. The chassis of the IMA cabinet also includes a rear panel configured for connecting to connectors, wire harnesses, and the like. Additionally, the PCB modules include a front panel configured with screws for securing the PCB modules to the chassis of the IMA cabinet. The PCB modules also include retractable handles for transporting the PCB modules. The chassis of the IMA cabinet is also configured with ventilation holes for cooling the PCB modules. The IMA cabinet is further configured to be EMI / RFI resistant. In an exemplary embodiment, the IMA cabinet is configure such that substantially all of the electronic and / or computer components are disposed on the PCB modules and not in the IMA cabinet, thus reducing the overall cost of the IMA cabinet and facilitating easier and quicker reconfiguration, repair, and replacement of the PCB modules.

The invention discloses a distributed integrated modular avionic system hybrid dynamic reconfiguration system and method. The distributed integrated modular avionic system hybrid dynamic reconfiguration system at least comprises a first operation module, a second operation module, a third operation module, a fourth operation module, a fifth operation module, a first TTE exchanger and a second TTE exchanger, wherein the first operation module, the second operation module, the third operation module, the fourth operation module and the fifth operation module are connected through the first TTE exchanger and the second TTE exchanger, and the first TTE exchanger and the second TTE exchanger execute the TTE protocol. According to the protocol, in the communication process, a global clock is adopted for starting data receiving and transmitting, and the operation of each TTE exchanger and each operation module is only related with the global time. One operation module is set as the main reconfiguration management module to manage the remote reconfiguration work of the whole system in a uniform mode, and another operation module is set as the backup module.

An integrated modular avionics (IMA) cabinet for housing printed circuit board (PCB) modules includes a chassis configured with slots for receiving the PCB modules. The chassis of the IMA cabinet also includes a rear panel configured for connecting to connectors, wire harnesses, and the like. Additionally, the PCB modules include a front panel configured with screws for securing the PCB modules to the chassis of the IMA cabinet. The PCB modules also include retractable handles for transporting the PCB modules. The chassis of the IMA cabinet is also configured with ventilation holes for cooling the PCB modules. The IMA cabinet is further configured to be EMI / RFI resistant. In an exemplary embodiment, the IMA cabinet is configure such that substantially all of the electronic and / or computer components are disposed on the PCB modules and not in the IMA cabinet, thus reducing the overall cost of the IMA cabinet and facilitating easier and quicker reconfiguration, repair, and replacement of the PCB modules.

A multi-core processor system including a main processor, an internal EPON bus, and a plurality of secondary core processors. The main processor includes a processing unit; an offload engine operatively connected to the processing unit for routing data to and from the processing unit; a plurality of main processor optical network units (ONU's) operatively connected to the offload engine; and, a dual optical line terminal (OLT) operatively connected to the offload engine. The internal EPON bus is operatively connected to the OLT. The plurality of secondary core processors are located physically separate from the main processor, each secondary core processor having a respective secondary core processor ONU being operatively connected to the main processor via the internal EPON bus. A number of the multi-core processor systems can be used to form an integrated modular avionics (IMA) system when operatively connected to remote data concentration components via an external EPON bus connected to the dual OLTs of the multi-core processor systems.

A remote concentration system includes at least one avionics computing resource module; and, a plurality of remote wireless data concentration components. The avionics computing resource module and the wireless data concentration components are operably connected via a wireless (Ultra-Wideband) UWB network. The wireless data concentration components may be operably connected with multiple data paths via the wireless UWB network to enhance communication availability.

The present invention provides an electronic system mounted on an aircraft which can effectively reduce electronic devices and wires by integration of control systems. Specifically, a fuselage (80) of an aircraft (100) is divided into a nose part (80a), a center part (80b), and an aft part (80c), and two IMAs (integrated modular avionics units) (50a to 50c) are provided in each of these parts. The IMA units (50a to 50c) are interconnected via an integrated data bus (53) to construct an integrated electronic system mounted on the aircraft. The system is suitably used for integrating utility systems except for avionics systems, among a plurality of control systems mounted on the aircraft, and is also applicable to integration of the avionics systems.

A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and / or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

The invention discloses a scheduling optimization method based on time-triggered communication service. The method combines the distributed integrated modular avionics system, based on the service characteristics thereof, with a time trigger mechanism to enable the system to support both time-triggered service and event-triggered service, thereby improving the timeliness and stability of the system. In order to further improve the utilization rate of system resources, the scheme provides a static scheduling table generation algorithm for time-triggered service, and the optimization goal is toarrange the time-triggered service in a dispersed way as much as possible, so as to obtain the largest number of idle time slots and provide uniform time resources for subsequent event-triggered service to improve the stability of the system. The invention provides a new two-dimensional packing algorithm and introduces constraints to achieve the goal of optimizing uniform and dispersed arrangementof the time-triggered service, thus improving the time delay performance of the system.

The invention relates to a multichannel controller module for integrated modular avionics, having at least two channels, wherein for each of the channels at least one first interface for communicating with a control computer, a processor, at least one second interface for communicating with a peripheral device, and a first memory having an operating system are all connected to each other for data exchange, wherein a second memory is provided for selectively storing at least one application program for communicating with the peripheral device, wherein a selecting means is provided by means of which the application program can selectively be associated with a first or a second operating mode, wherein the first operating mode is a redundant duplex operating mode, wherein both channels are used for executing the application program and the two channels, in this case, are connected to each other by means of data exchange and error monitoring means, and wherein the second operating mode is a non-redundant simplex operating mode, wherein only one of the two channels is used for executing the application program and, in this case, the data exchange and error monitoring means is deactivated.

The embodiment of the invention discloses a new integrated modular avionics system architecture, belonging to the technical field of avionics. The architecture comprises an avionics core resource subsystem, an avionics information platform subsystem, an avionics data network subsystem and a data conversion subsystem, wherein the avionics core resource subsystem is used for providing calculation resources for a resident application of an aircraft control domain system; the avionics information platform subsystem is used for providing calculation resources for a resident application of an aircraft information service domain system; the avionics data network subsystem is respectively connected with the avionics core resource subsystem and the avionics information platform subsystem, and is used for transmitting interactive data between the avionics core resource subsystem and the avionics information platform subsystem; and the data conversion subsystem is connected with the avionics data network subsystem and is used for providing signal conversion functions for an aircraft system so as to realize the inter-conversion between non-ARINC664 signals and ARINC664 signals. According to the embodiment of the invention, the function residence is carried out in different ways according to different functional domains to which each resident function belongs, so that the comprehensiveness and integration degree of the aircraft system can be increased, and meanwhile, the system performance can be improved.

The invention provides an integrated modular avionics system service capability assessment method which includes the steps of identifying and classifying resources provided by an IMA (Integrated Modular Avionics) platform, performing independence identification and quantification on resources of the IMA (Integrated Modular Avionics) platform, setting up an IMA (Integrated Modular Avionics) platform resource matrix, obtaining the maximum service capability of the IMA (Integrated Modular Avionics) platform from the IMA (Integrated Modular Avionics) platform matrix, determining whether an IMA (Integrated Modular Avionics) system satisfies the service capability demands of avionics system functions, resetting elements in a corresponding resource matrix to zero when resource failure occurs or reducing values according to the degradation of resources, repeating the determination process, and assessing the service capabilities of the IMA (Integrated Modular Avionics) platform after resource failure. The integrated modular avionic system service capability assessment method is capable of assessing the service capabilities of the IMA (Integrated Modular Avionics) platform with resource sharing characteristics by quantifying the service capabilities of the system, thereby helping to maximize the resource utilization of the system. Furthermore, the integrated modular avionic system service capability assessment method helps system integrators reasonably plan the variety and quantity of residence functions of the IMA (Integrated Modular Avionics) platform, thereby enhancing the 'failure-safety' capability of the avionics system.

Input / output interfaces of avionic modules of IMA type in a device including several modules is tested. A system includes at least one application employed by a set of computer modules. This set includes the computer module (a first module), and at least one other computer modul (at least one second module). A system test is associated with the at least one system for functionally testing the set of computer modules according to the system. The system test includes at least one elementary system test for functionally testing at least one input / output interface of the first module. The execution of the at least one elementary system test is independent of the at least one second module. At least one result of execution of the at least one elementary system test is transmitted to a maintenance computer distinct from the computer modules of the plurality of computer modules.

The invention discloses a system-level reconstruction management application software master-slave switching method, which is applied to a secondary management and control based IMA (integrated modular avionics) system. The method comprises the steps that 1) two pieces of system-level reconstruction management application software are deployed on two different general processing modules respectively according to pre-settings after the IMA system is powered on, and a master-slave relation is set according to ID numbers; 2) system reconstruction is carried out after the system-level reconstruction management master application software SYSRC_M breaks down, the ID number of the reconstructed system-level reconstruction management master application software SYSRC_M is the sum of an original ID number of the original system-level reconstruction management slave application software SYSRC_S and an original ID number of the original system-level reconstruction management master application software SYSRC_M, and the ID number of the reconstructed system-level reconstruction management slave application software SYSRC_S is the ID number of the original system-level reconstruction management master application software SYSRC_M. The master-slave relation of the system-level reconstruction management application software is determined according to the ID numbers, when the system-level reconstruction management master application software SYSRC_M breaks down, the system-level reconstruction management slave application software SYSRC_S switches into a master control mode automatically, and a normal management mode of the system is recovered, thereby ensuring normal operations of the system, and improving the overall security of the system.

A robotic system includes a plurality of robotic elements, each having at least one processing component, at least one memory component, and an I / O interface; and a virtual backplane coupling the plurality of robotic elements.

Fault-tolerant synchronization of real-time equipment connected to a computer network of several tens of meters with an option of including or not including such equipment in the synchronization device is disclosed. Global scheduling of the real-time computer platform in the form of minor and major cycles is provided in order to reduce latency during sensor acquisition. The associated calculation and preparation of output to the actuator is provided in an integrated modular avionic (IMA) architecture. To achieve the foregoing, a synchronization bus separate from the data transfer network and circuits interfacing with this specific bus for processing the local real-time clocks in each piece of equipment in a fault-tolerant, decentralized manner is provided.

A line replaceable unit (LRU) for an integrated modular avionics (IMA) architecture, the LRU comprising at least one input / output interface and a plurality of connectors, wherein each connector includes at least one pin and each connector is adapted for connection to a single segregated wire route bundle, and wherein hardware of one interface is electrically connected within the LRU to one or more pins of each of at least two of the connectors. Also, an IMA architecture including the LRU, and an aircraft including the LRU or the IMA architecture.

The invention discloses a distributed integrated modular avionics system reconfiguration parameter selection system and method. The system comprises a running parameter database, a parameter selection module and a parameter output check module, wherein the running parameter database is connected with an external DIMA reconfiguration management system; the parameter selection module is connected with the running parameter database and the parameter output check module, and is also connected with the DIMA reconfiguration management system; and the parameter check module is externally connected with the DIMA reconfiguration management system. The reconfiguration parameter selection system and method havethe advantages that (1) the transmission of harmful / invalid parameters in a reconfiguration process is considered, and reconfiguration parameters are judged, so that the robustness of a reconfigured system is improved and the system security is improved; and (2) during reconfiguration parameter selection, different parameter selection and backup modes are provided, so that different system frameworks can be effectively adapted and the reconfiguration parameter selection system and method have higher practicality.

An integrated modular system for managing plurality of medical devices in an interventional procedure room and usable in conjunction with a patient positioner having an articulating tabletop is disclosed. The integrated modular system comprises a wheeled base; an upwardly extended support structure mounted on the wheeled base; two or more device integration modules removably mounted on the upwardly extended support structure; one or more coupling devices arranged in a linearly guided fashion with the upwardly extended support structure; wherein the one or more coupling devices couples the articulating tabletop of a patient positioner and the upwardly extended support structure.

The invention discloses an integrated modular avionics system two-stage scheduling model and a prototype platform, and belongs to the technical field of avionics. The two-stage scheduling model is divided into three categories of combination ways according to whether process time is continuous and according to a partition scheduling strategy and a process scheduling strategy, the optimization of unknown parameters is independently finished by aiming at each category of combination ways, and finally, a reasonable scheduling scheme and a reasonable scheduling Gantt chart are generated. On the basis of a classical partition and process scheduling model, an IMA (Integrated Modular Avionics) system two-stage scheduling model is expanded, the prototype platform has the advantages of complete structure and function, various two-stage scheduling models and any partitioning and process parameter can be conveniently verified, and a platform is provided for researching an efficient IMA two-stagescheduling strategy; and the prototype platform adopts a modular structure to support to add a new scheduling strategy and a new scheduling algorithm, each module can be conveniently replaced, and themodel exhibits good expandability.

The invention provides an IMA (Integrated Modular Avionics) system performance degradation modeling and simulation method, and relates to the field of aircraft avionics. The IMA system performance degradation modeling and simulation method comprises the step of regarding performance of a soft fault in a whole IMA life cycle as representation of IMA system performance degradation to accordingly build an IMA system performance degradation model. The IMA system performance degradation modeling and simulation method avoids the dilemma that data driving based modeling cannot be carried out by utilizing original data due to insufficient IMA system performance degradation, provides a new idea for the IMA performance degradation modeling and describes an IMA system performance change course by combining a resource reliability function with the fact whether soft faults such as an intermittent fault and a transient fault occurs in the whole IMA period; as the IMA system performance degradation course is expressed by a probability model, the cost is low and a foundation for condition-based maintenance is laid.

A system and method for enhanced dispatch of an operationally critical system is disclosed. The method receives a minimum equipment list associated with the system including a plurality of dispatch critical applications with at least one dispatch critical application instance. A rules set determines a plurality of schedules of the dispatch critical application instances in compliance with the minimum equipment list, each schedule associates a specific processing resource with a specific dispatch critical application instance. A monitor tracks the availability of each dispatch critical application instance and, should one or more instanced become unavailable, the method implements an alternate schedule of dispatch critical application instances in accordance with the rules set and the minimum equipment list.

The invention discloses a high-integrity system-on-chip for a comprehensive modular avionics system, which comprises a first area and a second area which are the same, and the first area and the second area both comprise functional modules including a universal processor core, a CoreNet-based on-chip interconnection bus, a delay module and an independent bus monitoring module; the delay module inserts bus delay of a clock period when the general processor core sends various signals on the on-chip interconnection bus to the bus monitoring module; the bus monitoring module compares the received signals of the first area and the second area one by one in clock cycles, and triggers a synchronous interrupt signal once an error is found; and the configuration, the read-write access state and the input and output addresses / data of the on-chip interconnection bus when the comparison fails are used as synchronous interruption information to be sent to the general processor core for processing. According to the invention, the internal synchronization of the dual-processor core is realized, and the data integrity is improved.

Methods and systems are provided for authorizing a command of an integrated modular environment in which a plurality of partitions control actions of a plurality of effectors is provided. A first identifier, a second identifier, and a third identifier are determined. The first identifier identifies a first partition of the plurality of partitions from which the command originated. The second identifier identifies a first effector of the plurality of effectors for which the command is intended. The third identifier identifies a second partition of the plurality of partitions that is responsible for controlling the first effector. The first identifier and the third identifier are compared to determine whether the first partition is the same as the second partition for authorization of the command.

The invention discloses an information delay time analysis and distribution method for an integrated modular avionics system. The method comprises the steps of (a), obtaining operation time or a partition scheduling period of each node; (b), determining an information stream, determining information passing nodes and analyzing to obtain information maximum allowed delay time according to system architecture; (c), obtaining a demand of a terminal node for an input information update period through analysis of a function performance demand of the terminal node; (d), starting from the demand of the terminal node for the input information update period, calculating an information collection period of a front end node; (e), distributing system delay time to each node according to the information maximum allowed delay time; and (f), distributing an output information update period and network maximum allowed delay time to each node. According to the method, whether the system architecture is reasonable or not can be determined, and whether a high-time-sensitivity function can be realized or not can be determined. Moreover, the basis is provided for determination of parameter demands such as the information collection period, and platform and subsystem performance.

The present invention provides an electronic system mounted on an aircraft which can effectively reduce electronic devices and wires by integration of control systems. Specifically, a fuselage (80) of an aircraft (100) is divided into a nose part (80a), a center part (80b), and an aft part (80c), and two IMAs (integrated modular avionics units) (50a to 50c) are provided in each of these parts. The IMA units (50a to 50c) are interconnected via an integrated data bus (53) to construct an integrated electronic system mounted on the aircraft. The system is suitably used for integrating utility systems except for avionics systems, among a plurality of control systems mounted on the aircraft, and is also applicable to integration of the avionics systems.

Methods and systems are provided for authorizing a command of an integrated modular environment in which a plurality of partitions control actions of a plurality of effectors is provided. A first identifier, a second identifier, and a third identifier are determined. The first identifier identifies a first partition of the plurality of partitions from which the command originated. The second identifier identifies a first effector of the plurality of effectors for which the command is intended. The third identifier identifies a second partition of the plurality of partitions that is responsible for controlling the first effector. The first identifier and the third identifier are compared to determine whether the first partition is the same as the second partition for authorization of the command.