A fault resilient airborne network includes a plurality of aircraft system components installed within an aircraft and at least one agent in communication with the plurality of aircraft system components during in-flight operation of the aircraft. The at least one agent is configured to monitor an aircraft system component for a fault, observe a fault within the aircraft system component, and provide reconfiguration instructions to the aircraft system component in response to the observed fault. The at least one agent is further configured to predict a life expectancy of the aircraft system component using machine learning models while monitoring the aircraft system component for a fault, and provide reconfiguration instructions to the aircraft system component when the life expectancy of the aircraft system component meets a threshold. The reconfiguration instructions are configured to cause an adjustment in at least some of the plurality of aircraft system components.

A fault resilient airborne network includes a plurality of aircraft system components installed within an aircraft and at least one agent in communication with the plurality of aircraft system components during in-flight operation of the aircraft. The at least one agent is configured to monitor an aircraft system component for a fault, observe a fault within the aircraft system component, and provide reconfiguration instructions to the aircraft system component in response to the observed fault. The at least one agent is further configured to predict a life expectancy of the aircraft system component using machine learning models while monitoring the aircraft system component for a fault, and provide reconfiguration instructions to the aircraft system component when the life expectancy of the aircraft system component meets a threshold. The reconfiguration instructions are configured to cause an adjustment in at least some of the plurality of aircraft system components.

A calibration bracket (100), comprising: a base (10); a stand component (20) connected to the base (10); a cross beam component (30, 30′) mounted to the stand component (20) and used for mounting a calibration element, which is used for calibrating an advanced driver assistant system of a vehicle; and a rotating component (40) mounted between the stand component (20) and the base (10), and used for driving the stand component (20) to pivot about a central axis of the stand component (20) relative to the base (10) so as to adjust an angle of rotation of the cross beam component (30, 30) relative to the central axis of the stand component (20). According to the structure, an angle of rotation of the cross beam component (30, 30′) relative to the central axis of the stand component (20) can be adjusted, so that the rotation of the cross beam component (30, 30′) is free from the mounting position. The calibration bracket is simple in structure, and convenient to carry.

Disclosed are a ground test system and a test method for a space-oriented multi-arm spacecraft system. A spacecraft system simulator floats on an air-floating platform through four porous air feet, a test truss is placed around the air-floating platform, a simulation auxiliary docking device, a simulation crawling truss and a satellite model are arranged in a middle of a ceiling of the test truss, and an assembly test area and a silent air compressor are arranged on sides of the test truss. The application is used to solve the problems that the prior art cannot simulate the movement and crawling of the multi-arm spacecraft system in space, assembly of large space structures, and the prior art cannot simulate the influence of assembling, catching and other actions on a base in a weightless environment.

Disclosed are a ground test system and a test method for a space-oriented multi-arm spacecraft system. A spacecraft system simulator floats on an air-floating platform through four porous air feet, a test truss is placed around the air-floating platform, a simulation auxiliary docking device, a simulation crawling truss and a satellite model are arranged in a middle of a ceiling of the test truss, and an assembly test area and a silent air compressor are arranged on sides of the test truss. The application is used to solve the problems that the prior art cannot simulate the movement and crawling of the multi-arm spacecraft system in space, assembly of large space structures, and the prior art cannot simulate the influence of assembling, catching and other actions on a base in a weightless environment.

A failure diagnosis system includes a sensor that is provided in a diagnosis target device and detects diagnosis target information of the diagnosis target device, an abnormality determination unit that determines whether or not an abnormality occurs in the diagnosis target device based on the diagnosis target information detected by the sensor, a storage unit that stores a site of the diagnosis target device where the abnormality determination is possible and a sensor installation location where a sensor needs to be installed for the abnormality determination of the site, a designation reception unit that receives designation of a site where the abnormality determination is performed, and a presentation unit that executes predetermined presentation processing. The presentation processing by the presentation unit includes processing of presenting the sensor installation location where the sensor needs to be installed to perform the abnormality determination of the designated site.

A failure diagnosis system includes a sensor that is provided in a diagnosis target device and detects diagnosis target information of the diagnosis target device, an abnormality determination unit that determines whether or not an abnormality occurs in the diagnosis target device based on the diagnosis target information detected by the sensor, a storage unit that stores a site of the diagnosis target device where the abnormality determination is possible and a sensor installation location where a sensor needs to be installed for the abnormality determination of the site, a designation reception unit that receives designation of a site where the abnormality determination is performed, and a presentation unit that executes predetermined presentation processing. The presentation processing by the presentation unit includes processing of presenting the sensor installation location where the sensor needs to be installed to perform the abnormality determination of the designated site.

A system may comprise a device. The device may be configured to receive, from one or more sensor devices of the machine, sensor data associated with wear of one or more components of an undercarriage of the machine; and predict, using a machine learning model and the sensor data, an amount wear of the one or more components based on a wear rate of the one or more components. The machine learning model is trained, using training data, to predict the wear rate of the one or more components. The training data includes two or more of: historical sensor data, historical inspection data, or simulation data, of a simulation model, from one or more third devices. The device may perform an action based on the amount of wear.

An environment association system (“EAS”) comprising: a processor and a memory; an object recognition process configured to identify objects within images, the objects including one or more of a vehicle, a vehicle lift, a vehicle repair tool, and an alignment fixture; and an EAS interface configured to communicate with a user device, the user device comprising a camera and a display; wherein the processor is configured to: determine, for at least one object in the set of objects, create a virtual overlay for the image based on the position of the at least one object within the image and a virtual marking associated with the at least one object; and provide the virtual overlay to the user device, wherein the virtual overlay is configured to cause the user device to simultaneously display the image and the virtual overlay via the display. The system provides information about the alignment of lifting points of the object with lifting members.

An indicator for monitoring temperature and wear of one or more aircraft brakes. One or more sensors are provided for sensing a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel. In addition, the sensed usage data are critical inputs for the brake controller to regulate which brakes are applied.