A robotic applique assembly for incorporation into a manually controlled vehicle to provide unmanned operational capability to the vehicle includes an assembly body configured to be positioned into the vehicle in substantially the same area occupied by a user of the vehicle. The assembly body can have a series of segments including a torso segment, a bench segment and a leg segment. The segments are pivotally coupled one to another to allow adjustment of position of the segments relative to one another.

An analyzer and diagnostic system can include one or more sensors that are operable to generate combustion condition data relating to the performance of an associated combustion system. An analysis module can be operable to analyze at least a portion of the combustion condition data and determine a state of the associated combustion system. A diagnostic module can be operable to identify one or more recommended corrective actions for a combustion system performance deviation from a plurality of recommended corrective actions using one or more logic algorithms. Handheld instruments and methods of analyzing and diagnosing combustion processes are also included.

One or more devices in a data analysis computing system may be configured to receive and analyze movement data and driving data, and determine driving trips and associated drivers based on the received data. Movement data may be collected by one or more mobile devices, such as smartphones, tablet computers, and on-board vehicle systems. Drivers associated with driving trips may be identified based on the movement data collected by the mobile devices, such as speed data, acceleration data, or distance data.

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 method for determining a ride height of a body of a motor vehicle and includes the steps of determining wheel heights at at least four different wheels of the motor vehicle, forming different selections of in each case three of the determined wheel heights, determining a ride height of the body for each selection, comparing the determined ride heights, and determining that at least one measurement value for a wheel height is implausible if the determined ride heights differ from one another by more than a predetermined amount.

A method for determining a ride height of a body of a motor vehicle and includes the steps of determining wheel heights at at least four different wheels of the motor vehicle, forming different selections of in each case three of the determined wheel heights, determining a ride height of the body for each selection, comparing the determined ride heights, and determining that at least one measurement value for a wheel height is implausible if the determined ride heights differ from one another by more than a predetermined amount.

The purpose of the present invention is to provide a determining device and a determining method to determine whether an inspected jet nozzle is defective by inspecting the jet nozzle for injecting a jet stream with long ground penetrating distance at a stage before installing in a construction site where a large diameter jet grouting method is used. To achieve this purpose, with this invention, in which a nozzle to be inspected is mounted onto an outlet port, a jet stream is ejected from a jet stream generating device, and measurement data measured by a pressure sensing unit when the jet stream impacts the pressure sensing unit is processed with a controlling device (for example, a computer), a nozzle to be inspected is determined to be a non-defective product if a first ratio is no less than a first prescribed value, a second ratio is no less than a second prescribed value, and a third ratio is no less than a third prescribed value.

Systems and methods for determining aircraft component phase position are provided. In one embodiment, a method can include receiving a set of data from a data acquisition system associated with a component. The method can include identifying a plurality of phase reference points based, at least in part, on the set of data. Each phase reference point can be indicative of a phase position of the component relative to the data acquisition system at a respective point in time. The method can include generating a model based, at least in part, on the plurality of phase reference points. The model can be indicative of the phase position of the component relative to the data acquisition system at a plurality of times. The method can include determining the phase position of the component at one or more points in time based, at least in part, on the model.

Systems and methods for determining aircraft component phase position are provided. In one embodiment, a method can include receiving a set of data from a data acquisition system associated with a component. The method can include identifying a plurality of phase reference points based, at least in part, on the set of data. Each phase reference point can be indicative of a phase position of the component relative to the data acquisition system at a respective point in time. The method can include generating a model based, at least in part, on the plurality of phase reference points. The model can be indicative of the phase position of the component relative to the data acquisition system at a plurality of times. The method can include determining the phase position of the component at one or more points in time based, at least in part, on the model.