Abstract: An electrical connector includes: at least a first housing part and a second housing part, one of the first housing part and the second housing part engaging, at least partially and concentrically, in an other of the first housing part and the second housing part in an engagement region, the first housing part and the second housing part being rotatable relative to one another in the engagement region about an axis of rotation. The first housing part and the second housing part each have a magnetic structure extending, at least in part, circumferentially on an inside or an outside in the engagement region, the respective magnetic structures interacting.

Abstract: A wireless field device for use in an industrial process control or monitoring system includes a controller configured to control operation of the wireless field device. Wireless communication circuitry is configured to wirelessly communicate with a remote location. An internal power source powers the wireless field device. An image capture device is coupled to the controller and configured to capture an image of an environment of the wireless field device. The controller is adapted to receive image information from the image capture device and transmit compressed image information to the remote location.

Abstract: A wireless field device for use in an industrial process control or monitoring system includes a controller configured to control operation of the wireless field device. Wireless communication circuitry is configured to wirelessly communicate with a remote location. An internal power source powers the wireless field device. An image capture device is coupled to the controller and configured to capture an image of an environment of the wireless field device. The controller is adapted to receive image information from the image capture device and transmit compressed image information to the remote location.

Abstract: A pressure fuselage of an aircraft, which fuselage in longitudinal direction comprises several fuselage sections, wherein at least one rear dome-shaped pressure bulkhead is provided to form an aircraft-internal pressurized region, with a ring-shaped frame element profile being provided for radially outward attachment of said dome-shaped pressure bulkhead to at least one fuselage section, wherein the frame element profile on the side of the dome-shaped pressure bulkhead comprises a U-shaped profile section whose first end-side limb is attached towards the back on the dome-shaped pressure bulkhead by way of connecting means, and whose elongated radially outward extending second limb establishes a connection to the at least one fuselage section in such a manner that it is possible for the connecting means to be installed solely from the aircraft-internal pressurized region.

Abstract: A pressure fuselage of an aircraft, which fuselage in longitudinal direction comprises several fuselage sections, wherein at least one rear dome-shaped pressure bulkhead is provided to form an aircraft-internal pressurized region, with a ring-shaped frame element profile being provided for radially outward attachment of said dome-shaped pressure bulkhead to at least one fuselage section, wherein the frame element profile on the side of the dome-shaped pressure bulkhead comprises a U-shaped profile section whose first end-side limb is attached towards the back on the dome-shaped pressure bulkhead by way of connecting means, and whose elongated radially outward extending second limb establishes a connection to the at least one fuselage section in such a manner that it is possible for the connecting means to be installed solely from the aircraft-internal pressurized region.

Abstract: The present invention provides a radio navigation emulating GPS device. In one embodiment, the radio navigation emulating GPS device receives an identifier associated with a conventional radio navaid. The present radio navigation emulating GPS device then retrieves latitude and longitude information corresponding to the received conventional radio navaid from a database. A satellite based position information system generates position information for the aircraft on which the present radio navigation emulating GPS device is disposed. The present radio navigation emulating GPS device then generates navigation information for the aircraft using the retrieved latitude and longitude information and the satellite based position information for the aircraft. The present radio navigation emulating GPS device then presents the navigation information in a manner which emulates the presentation of navigation information generated by a conventional radio navigation device.

Abstract: The present invention provides a radio navigation emulating GPS device. In one embodiment, the radio navigation emulating GPS device receives an identifier associated with a conventional radio navaid. The present radio navigation emulating GPS device then retrieves latitude and longitude information corresponding to the received conventional radio navaid from a database. A satellite based position information system generates position information for the aircraft on which the present radio navigation emulating GPS device is disposed. The present radio navigation emulating GPS device then generates navigation information for the aircraft using the retrieved latitude and longitude information and the satellite based position information for the aircraft. The present radio navigation emulating GPS device then presents the navigation information in a manner which emulates the presentation of navigation information generated by a conventional radio navigation device.

Abstract: The present invention provides a radio navigation emulating GPS device. In one embodiment, the radio navigation emulating GPS device receives an identifier associated with a conventional radio navaid. The present radio navigation emulating GPS device then retrieves latitude and longitude information corresponding to the received conventional radio navaid from a database. A satellite based position information system generates position information for the aircraft on which the present radio navigation emulating GPS device is disposed. The present radio navigation emulating GPS device then generates navigation information for the aircraft using the retrieved latitude and longitude information and the satellite based position information for the aircraft. The present radio navigation emulating GPS device then presents the navigation information in a manner which emulates the presentation of navigation information generated by a conventional radio navigation device.

Abstract: The present invention provides a radio navigation emulating GPS device. In one embodiment, the radio navigation emulating GPS device receives an identifier associated with a conventional radio navaid. The present radio navigation emulating GPS device then retrieves latitude and longitude information corresponding to the received conventional radio navaid from a database. A satellite based position information system generates position information for the aircraft on which the present radio navigation emulating GPS device is disposed. The present radio navigation emulating GPS device then generates navigation information for the aircraft using the retrieved latitude and longitude information and the satellite based position information for the aircraft. The present radio navigation emulating GPS device then presents the navigation information in a manner which emulates the presentation of navigation information generated by a conventional radio navigation device.

Abstract: In a GPS navigation satellite receiver, a pseudorange step detection method integrates the pseudorange rates to predict expected changes in the pseudoranges from one measurement to the next. The pseudorange rate is directly measured as the carrier Doppler shift. The pseudorange and pseudorange rate from a last measurement from each satellite and a pseudorange rate from a new measurement are used to estimate the expected pseudorange. Such estimate accounts for vehicle velocity and accelerations. The expected pseudorange is compared to a newly measured pseudorange. An impermissible pseudorange step is declared when the difference exceeds a variable threshold. Tests can be done on measurements taken up to ten seconds apart, e.g., using a threshold of five hundred meters. The maximum position dilution of precision is typically set at a value of twelve. Satellites that manifest a pseudorange step are thereafter excluded from participating in subsequent position solution activity.

Abstract: The synthesizer uses phase lock loop techniques to generate either the carrier signal for an associated transmitter or the injection signal for an associated receiver. A programmable divider controls the specific channel to which the synthesizer tunes the transmitter or receiver whereas operation in the transmit or receive mode is dependent upon which of two oscillators is coupled in the synthesizer circuit. The oscillators are designed to run at two frequencies having a difference equal to the intermediate frequency of the receiver. This allows the one output from the synthesizer to be used in both the transmit and receive modes.