Abstract: A method of calculating Federal Aviation Administration (FAA) published or FAA Air Traffic Control assigned aeronautical holding patterns, comprising the steps of: defining navigational way points using their latitude and longitude coordinates; displaying the latitude and longitude that define the point for an inbound turn; defining four posts of a holding pattern; and showing the actual holding space dimensions along with the non-protected airspace. The method may be performed by a stand-alone electronic device or an electronic device having other functions. The latitude and longitude that define the point for an inbound turn can be displayed as a bearing, and/or as a distance along a radial. The inbound turning point can be calculated using a global positioning or flight management system. A turn may be commanded using an automatic flight control system or flight director.

Abstract: A wire harness includes a standard connection circuit part which connects a standard electronic device and an ECU, and an optional connection circuit part which connects optional electronic devices and the ECU. The optional connection circuit part includes a communication connector which is provided to be connectable to the optional electronic devices, and an optional circuit which connects the ECU to the communication connector. The communication connector performs multiplex communication which multiplexes communication of the optional electronic devices and the ECU.

Abstract: The present invention relates to an electric vehicle and a method for controlling same, which involve monitoring the state of PRA which switches power supply so as to stably supply power or cut off the supply of power during the operation of the electric vehicle, and controlling of a plurality of switches for supplying power from a battery or cutting off the result of the switching, thus enabling the accurate control of switching and preventing an erroneous operation.

Abstract: A wire harness includes a standard connection circuit part which connects a standard electronic device and an ECU, and an optional connection circuit part which connects optional electronic devices and the ECU. The optional connection circuit part includes a communication connector which is provided to be connectable to the optional electronic devices, and an optional circuit which connects the ECU to the communication connector. The communication connector performs multiplex communication which multiplexes communication of the optional electronic devices and the ECU.

Abstract: The invention relates to a control method for a steering system with electric power assistance, comprising a steering wheel, an electric power assist motor, an electric control unit, which includes a memory for storing digital data, a motor driver unit which based on a target engine torque that is delivered to the motor driver unit, determines and sends out electrical signals for controlling the electric power assist motor, at least one sensor device for determining a control variable introduced into the steering wheel, for example a manual torque, wherein in the control unit with the help of the control variable a preset value is determined for a engine torque of the power assist motor, characterized in that in the memory an upper threshold value for the target engine torque is stored and for a case A, in which the preset value exceeds the upper threshold value, the control unit sends out the upper threshold value as the target engine torque to the motor driver unit and in a case B, in which the preset value

Abstract: A controller determines whether or not the storage amount of a battery is below a threshold, and reduces an assist output of a sub-pump by controlling an assist control mechanism based on an assist correction coefficient, increases the discharge amount of a main pump by controlling an engine controller based on an engine rotation speed correction coefficient and increasing the rotation speed of an engine, and increases an output of the main pump by increasing the rotation speed of the engine by as much as a reduction in the assist output of the sub-pump.

Abstract: A system for measuring fatigue of a component of an aircraft subject to mechanical stresses includes: a plurality of stress sensors mounted on the component, each sensor being configured to detect a predetermined mechanical stress threshold and to deliver a data signal representative of exceeding of the threshold; and a mechanism for recording the data and the sensors configured to detect different stress thresholds so as to make it possible to calculate, on the basis of the data recorded by the system, an estimation of fatigue of the component due to the mechanical stresses. It is thus possible to optimize overhaul of the components.

Abstract: A protective device for an electronic unit on a space exploration vehicle. A Laplace transform calculation unit generates a Laplace transform of an electronic unit state. A system parameter identification unit identifies system parameters based on the Laplace transform of electronic unit states. A Fourier transform calculation unit generates a ratio of the ground contacting mechanism state to a highest dominant frequency of the measured electronic unit state. A critical travel speed calculation unit generates a critical travel speed based on the identified system parameters. A calculation unit for threshold of travel speed generates a threshold of a travel speed based on the critical travel speed. An autonomous motion controller generates a control signal that drives the space exploration vehicle based on the threshold of the travel speed.

Abstract: The respective motors of the drone (10) can be controlled to rotate at different speeds in order to pilot the drone both in attitude and speed. A remote control appliance produces a command to turn along a curvilinear path, this command comprising a left or right turning direction parameter and a parameter that defines the radius of curvature of the turn. The drone receives said command and acquires instantaneous measurements of linear velocity components, of angles of inclination, and of angular speeds of the drone. On the basis of the received command and the acquired measurements, setpoint values are generated for a control loop for controlling motors of the drone, these setpoint values controlling horizontal linear speed and inclination of the drone relative to a frame of reference associated with the ground so as to cause the drone to follow curvilinear path (C) at predetermined tangential speed (u).