Abstract: An electronic device may be provided with control circuitry and doublets of first and second antennas that are used to determine the position and orientation of the device relative to external wireless equipment. The control circuitry may determine the relative position and orientation of the external equipment by measuring the angle of arrival of radio-frequency signals from the external equipment. Each doublet may include first and second cavity-backed slot antennas. The first and second antennas may each include a first slot element that is directly fed and a second slot element that is parasitically fed by the first slot element. The first slot element may radiate in an ultra-wideband communications band at 8.0 GHz and the second slot element may radiate in an ultra-wideband communications band at 6.5 GHz. The doublet may be aligned with a dielectric window in a conductive sidewall for the device.

Abstract: An electronic device may be provided with control circuitry and doublets of first and second antennas that are used to determine the position and orientation of the device relative to external wireless equipment. The control circuitry may determine the relative position and orientation of the external equipment by measuring the angle of arrival of radio-frequency signals from the external equipment. Each doublet may include first and second cavity-backed slot antennas. The first and second antennas may each include a first slot element that is directly fed and a second slot element that is parasitically fed by the first slot element. The first slot element may radiate in an ultra-wideband communications band at 8.0 GHz and the second slot element may radiate in an ultra-wideband communications band at 6.5 GHz. The doublet may be aligned with a dielectric window in a conductive sidewall for the device.

Abstract: An electronic device may have peripheral conductive structures and a conductive layer that define edges of a slot element for a slot antenna. The slot element may be configured to cover wireless communications in a 1575 MHz satellite navigation band and 2.4 GHz and 5 GHz wireless local area network bands. A tuning circuit may be coupled across the slot approximately half way across the length of the slot. The antenna tuning circuit may include an inductor coupled in series with a notch filter (in scenarios where the slot is long enough to cover the 1575 MHz satellite navigation band in its fundamental mode) or may include a capacitor coupled in series with a notch or low pass filter. The fundamental mode and one or more harmonic modes of the slot element may cover the satellite navigation and wireless local area network bands.

Abstract: A system and a method for planning and flying a cost-optimal cruise vertical profile in combination with a required time-of-arrival (RTA) constraint. The method may be implemented as a single function in a flight management system (FMS). The FMS plans the aircraft trajectory with cruise vertical and speed profiles that are optimized to minimize flight cost (e.g., fuel burn) while meeting the time constraint. When appropriate under the circumstances, this integrated function is also able to degrade the cruise vertical profile in order to open the window of achievable RTAs and increase the RTA success rate. The method also monitors progress of the flight along the planned trajectory as actual flight conditions may differ from the forecasted flight conditions, and readapts the cruise speed profile when the estimated arrival time is deviating from the RTA constraint by more than a specified threshold.

Abstract: Electronic devices and methods for optimizing the vertical profile to be flown by an aircraft during the cruise phase of a flight. Based on continuously updated information about the aircraft's weight and the atmospheric wind and temperature, the method provides an optimal sequence of climbs and/or descents along the flight path during the cruise phase. Following the step climb/descent profile proposed by the method results in the most cost-optimal flight (if a cost index was selected) or in the most fuel-efficient flight (if the long-range cruise mode was selected). The method may be implemented in the flight management computer or any other electronic data processing device that can access the required information to perform the calculations.

Abstract: An electronic device may be provided an antenna, a display, and a housing. The display may include a conductive display structure and a cover layer. The housing may include peripheral conductive structures and a conductive rear wall. The peripheral structures may include a ledge separated from the conductive display structure by a gap. The peripheral structures and the rear wall may define opposing edges of a slot element for the antenna. Conductive bridging structures may be coupled between the conductive display structure and the ledge across the gap. The bridging structures may at least partially overlap locations along the length of the slot element where antenna currents around the slot element exhibit a maximum magnitude. The bridging structures may align the phase of current induced on the ledge with the phase of the current induced on the conductive display structure to maximize antenna efficiency through the cover layer.

Abstract: Methods and systems for controlling the flight of aircraft are disclosed. An example system includes a flight management computer to receive a first time of arrival at a first target waypoint of an aircraft and a second time of arrival at a second target waypoint, determine a first set of cruise speed and descent speed pairs corresponding to the first time, the first set satisfying the first time, determine a second set of cruise speed and descent speed pairs corresponding to the second time, the second set satisfying the second time, select a cruise speed and descent speed pair from the first set or the second set, determine an aircraft trajectory that satisfies the selected cruise speed and descent speed pair, and cause at least one of: 1) the aircraft to travel along the aircraft trajectory or 2) the aircraft trajectory to be displayed.

Abstract: A method and electronic device for providing an optimal quantity of aircraft fuel. The method comprises collecting recorded flight data from past flights of an aircraft; determining aircraft specific performance correction parameters per flight phase, using the recorded flight data; collecting a flight plan of the aircraft; determining the total fuel required for the given flight plan, using the aircraft specific performance correction parameters; determining a single synthetic drag factor (?DFMS) and a single synthetic fuel factor (?FFFMS) that, when used by the aircraft FMS, yield the said total fuel required for the given flight plan; receiving an estimated total fuel required determined by the aircraft FMS based on the flight plan, the single synthetic drag factor (?DFMS) and the single synthetic fuel factor (?FFFMS). The method allows reducing the fuel weight and total flight cost, and is particularly advantageous for FMS which only admit one single drag factor and one single fuel factor.

Abstract: An electronic device may include first, second, and third antennas and conductive housing structures. The first, second, and third antennas may each include slots having open ends defined by gaps in the conductive housing structures. The second antenna may be interposed between the first and third antennas. The first and second antennas may convey signals at the same frequencies. The third antenna may convey signals at a lower frequency than the first and second antennas. A switch may be coupled across the third slot and may have a first state at which the switch forms a closed end of the third slot and a second state at which the third slot has two opposing open ends. Control circuitry may selectively activate one of two feeds for the third antenna and may adjust the switch so that the third antenna exhibits satisfactory antenna efficiency regardless of environmental conditions for the device.

Abstract: An electronic device may have peripheral conductive structures and a conductive layer that define edges of a slot element for a slot antenna. The slot element may be configured to cover wireless communications in a 1575 MHz satellite navigation band and 2.4 GHz and 5 GHz wireless local area network bands. A tuning circuit may be coupled across the slot approximately half way across the length of the slot. The antenna tuning circuit may include an inductor coupled in series with a notch filter (in scenarios where the slot is long enough to cover the 1575 MHz satellite navigation band in its fundamental mode) or may include a capacitor coupled in series with a notch or low pass filter. The fundamental mode and one or more harmonic modes of the slot element may cover the satellite navigation and wireless local area network bands.

Abstract: An electronic device may include a peripheral conductive housing sidewall with an integral ledge extending towards the device interior. A display cover layer may be supported by the integral ledge. A slot antenna may be formed from a slot in the integral ledge. The integral ledge may be mounted to a surface of a substrate and coupled to a conductive rear housing wall by a conductive layer extending over an additional surface of the substrate. The sidewall may include a vertical portion extending from the ledge to the rear wall. The slot antenna may be fed via near-field coupling using a conductive patch that is located within the slot at the surface of the substrate. The conductive layer, rear housing wall, and vertical portion may form a cavity for the slot antenna. The conductive layer may isolate the slot from interference with a battery, display circuitry, or other components.

Abstract: An electronic device may be provided with a conductive wall. A gap in the wall may divide the wall into first and second segments. A ground may be separated from the wall by first, second, and third slots that form radiating elements for first, second, and third non-near-field communications antennas. First and second conductive structures may be coupled between the wall and the ground. A near-field communications antenna may include a first feed terminal coupled to the first segment and a second feed terminal coupled to the second segment. The antenna may convey signals over a conductive loop path that includes portions of the first and second segments, the antenna ground, and the first and second conductive structures. A differential or single-ended signal transmission line may be coupled to the terminals. Phase shifters may configure the signals to be out of phase at the feed terminals.

Abstract: An electronic device may have conductive housing structures and first, second, third, and fourth slot antennas having respective first, second, third, and fourth slot elements in the conductive housing structures. The third slot element may be interposed between the first and second slot elements and the second slot element may be interposed between the third and fourth slot elements. Switching circuitry may be coupled between a transceiver and the slot elements. Control circuitry may control the switching circuitry to activate a selected pair of the slot antennas based on an orientation of the device or other data. The active pair of antennas may convey radio-frequency signals at the same frequencies using a multiple-input and multiple-output (MIMO) communications scheme. In this way, the device may perform wireless communications at relatively high data throughputs regardless of how the device is being held by a user.

Abstract: A method and electronic device for providing an optimal quantity of aircraft fuel. The method comprises collecting recorded flight data from past flights of an aircraft; determining aircraft specific performance correction parameters per flight phase, using the recorded flight data; collecting a flight plan of the aircraft; determining the total fuel required for the given flight plan, using the aircraft specific performance correction parameters; determining a single synthetic drag factor (?DFMS) and a single synthetic fuel factor (?FFFMS) that, when used by the aircraft FMS, yield the said total fuel required for the given flight plan; receiving an estimated total fuel required determined by the aircraft FMS based on the flight plan, the single synthetic drag factor (?DFMS) and the single synthetic fuel factor (?FFFMS). The method allows reducing the fuel weight and total flight cost, and is particularly advantageous for FMS which only admit one single drag factor and one single fuel factor.

Abstract: Example systems and methods for controlling a flight of an aircraft subjected to a required time of arrival constraint at a target waypoint and to an additional flight criterion are disclosed herein. An example method includes calculating combinations of cruise speed and descent speed for estimated times of arrival (ETAs) at the target waypoint and determining a subset of the combinations that introduce substantially a same amount of time change in the ETA when changing the corresponding cruise speed to a cruise speed limit as when changing the corresponding descent speed to a descent speed limit. The example method also includes selecting a combination of the subset of the combinations having an ETA substantially equal to the RTA and modifying at least one of a cruise speed or a descent speed of the aircraft based on the selected combination.

Abstract: Methods and systems for controlling the flight of aircraft are disclosed. An example system includes a flight management computer to receive a first time of arrival at a first target waypoint of an aircraft and a second time of arrival at a second target waypoint, determine a first set of cruise speed and descent speed pairs corresponding to the first time, the first set satisfying the first time, determine a second set of cruise speed and descent speed pairs corresponding to the second time, the second set satisfying the second time, select a cruise speed and descent speed pair from the first set or the second set, determine an aircraft trajectory that satisfies the selected cruise speed and descent speed pair, and cause at least one of: 1) the aircraft to travel along the aircraft trajectory or 2) the aircraft trajectory to be displayed.

Abstract: Methods and systems for controlling the flight of aircraft are disclosed. An example method includes in response to a first time of arrival at a first waypoint, determining first cruise speeds and corresponding first descent speeds for the first waypoint at the first time of arrival; in response to a second time of arrival at a second waypoint, determining second cruise speeds and corresponding second descent speeds for the second waypoint at the second time of arrival, at least one of the first waypoint or the second waypoint being in a descent phase of a flight; identifying a third cruise speed and a third descent speed based on the first cruise and descent speeds and the second cruise and descent speeds, the first cruise and descent speeds including the third cruise speed and the third descent speed, the second cruise and descent speeds including the third cruise speed and the third descent speed; and identifying a trajectory of an aircraft that satisfies the third cruise speed and the third descent speed.

Abstract: The present invention relates to methods of controlling the flight path of an aircraft to follow as closely as possible a predetermined four-dimensional flight path, such as when flying continuous descent approaches. A method of controlling an aircraft to follow a predetermined four-dimensional flight path is provided that comprises monitoring the actual along-track position and the actual vertical position of the aircraft relative to the corresponding desired positions on the predetermined flight path. The aircraft's elevators are used to correct deviations of the along-track position and the aircraft's throttle is used to correct deviations of the vertical position.

Abstract: Example systems and methods for controlling a flight of an aircraft subjected to a required time of arrival constraint at a target waypoint and to an additional flight criterion are disclosed herein. An example method includes calculating combinations of cruise speed and descent speed for estimated times of arrival (ETAs) at the target waypoint and determining a subset of the combinations that introduce substantially a same amount of time change in the ETA when changing the corresponding cruise speed to a cruise speed limit as when changing the corresponding descent speed to a descent speed limit. The example method also includes selecting a combination of the subset of the combinations having an ETA substantially equal to the RTA and modifying at least one of a cruise speed or a descent speed of the aircraft based on the selected combination.

Abstract: Methods and systems for controlling the flight of aircraft are disclosed. An example method includes in response to a first time of arrival at a first waypoint, determining first cruise speeds and corresponding first descent speeds for the first waypoint at the first time of arrival; in response to a second time of arrival at a second waypoint, determining second cruise speeds and corresponding second descent speeds for the second waypoint at the second time of arrival, at least one of the first waypoint or the second waypoint being in a descent phase of a flight; identifying a third cruise speed and a third descent speed based on the first cruise and descent speeds and the second cruise and descent speeds, the first cruise and descent speeds including the third cruise speed and the third descent speed, the second cruise and descent speeds including the third cruise speed and the third descent speed; and identifying a trajectory of an aircraft that satisfies the third cruise speed and the third descent speed.