A monitoring system for a gearbox having at least one rotational component having a design lifetime and at least one design parameter is disclosed. The monitoring system may include a first sensor configured to generate a first signal indicative of a speed associated with the at least one rotational component, a second sensor configured to generate a second signal indicative of a torque associated with the rotational component, and a controller electronically connected to the first and second sensors. The controller may be configured to determine a remaining lifetime of the at least one rotational component based on the design lifetime, the at least one design parameter, and the first and second signals over a period of operating time, and generate a maintenance signal based on the remaining lifetime.

An apparatus for preventing a jackrabbit accident using a vehicle black box includes a jackrabbit accident prevention unit that is provided in the vehicle black box, synchronizes an accelerator position signal with a vertical synchronization signal for recording of an image to generate first jackrabbit analysis information to be transmitted to an accident record unit, combines the accelerator position signal with a throttle position signal to be transmitted to the accident record unit as second jackrabbit analysis information and to determine jackrabbit based on the second jackrabbit analysis information, and prevents the jackrabbit accident by automatically shutting off driving power to a fuel pump in the jackrabbit state, and the accident recording unit that provides horizontal and vertical synchronization signals for storing of an image to the jackrabbit accident prevention unit, maps the first jackrabbit analysis information with a recorded image, and stores the mapping result in a memory card.

A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. The method also includes observing at least one failure detection parameter obtained from one of the intermediate parameters of the baro-inertial loop; and determining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.

An autonomous floor cleaning robot includes a transport drive and control system arranged for autonomous movement of the robot over a floor for performing cleaning operations. The robot chassis carries a first cleaning zone comprising cleaning elements arranged to suction loose particulates up from the cleaning surface and a second cleaning zone comprising cleaning elements arraigned to apply a cleaning fluid onto the surface and to thereafter collect the cleaning fluid up from the surface after it has been used to clean the surface. The robot chassis carries a supply of cleaning fluid and a waste container for storing waste materials collected up from the cleaning surface.

A driving device 5 includes: a fault detection device 11 that determines a fault in an actuator 6; a serial interface 7 that communicates with an MCU 2; a memory device 10 that stores a program received from the MCU 2 and a fault determination result by the fault detection device 11; a CPU 9 that causes the fault detection device 11 to execute the fault determination according to a fault determination request from the MCU 2; a timer device 16 that measures a limit time over which fault determination is performed and a determination period of fault determination; and a counter device 17 that counts the number of repeats of fault determination and the number of fault occurrences in the actuator 6.

A driving device 5 includes: a fault detection device 11 that determines a fault in an actuator 6; a serial interface 7 that communicates with an MCU 2; a memory device 10 that stores a program received from the MCU 2 and a fault determination result by the fault detection device 11; a CPU 9 that causes the fault detection device 11 to execute the fault determination according to a fault determination request from the MCU 2; a timer device 16 that measures a limit time over which fault determination is performed and a determination period of fault determination; and a counter device 17 that counts the number of repeats of fault determination and the number of fault occurrences in the actuator 6.

A method and a system of determining a position of a mobile machine are disclosed. According to certain embodiments, the system may include a first sensor configured to generate a first signal indicative of a parameter of the mobile machine. The system may also include a second sensor configured to generate a second signal indicative of a pose of the mobile machine. The system may further include a controller in communication with the first and second sensors. The controller may be configured to generate one or more estimated poses of the mobile machine based on the first signal. The controller may further be configured to update each estimated pose with a fraction of a correction. The correction may be determined, based on the second signal, in a measurement update stage of a Kalman filter.

A method for determining a state of a component in a high lift system of an aircraft comprises the steps of extending at least one high lift surface, which is coupled with two drive struts, wherein at least one of the two drive struts is a load sensing drive strut, to a first extended position, acquiring a first load sensed by a load sensing drive strut associated with the at least one high lift surface at a first flight state having a first speed, comparing the first load with a known nominal load for the first extended position and the first flight state under consideration of a predetermined threshold, and producing an alarm signal in case the acquired load differs from the nominal load including the predetermined threshold.

An engine failure diagnosis system simply performs failure diagnosis of engine components, which are driven while an engine is operating, even at the time when the engine is stopped, and identifies a component that has failed and a location where a failure has occurred. The engine failure diagnosis system includes an ECM arranged to control an engine provided in an outboard motor of a watercraft. The ECM includes an actuation command section arranged to actuate engine components, which are driven while the engine is running, in a given manner, and a failure diagnosis section arranged to diagnose the presence of a failure in the engine components. The engine components of the engine are provided with actuated condition detecting sections arranged to detect a predetermined actuated condition. When the actuation command section outputs an actuation command while the engine is stopped, the engine components are actuated in a given manner.

A system for managing a mining machine is included in a mining machine that travels in a mine. The system includes: a positional information detecting unit configured to acquire positional information indicating a position of the mining machine; and a traveling path calculating unit configured to obtain, from each of a plurality of the mining machines, positional information about an actual traveling path on which each of the mining machines actually has traveled, and generate a reference traveling path in the mine with the obtained positional information.