Abstract: A method detects an impendent situation of an operating aircraft. The method comprises receiving data corresponding to a plurality of parameters related to an operation of the aircraft. It is determined if any of the plurality of parameters is at or beyond at least a first respective threshold by comparing the plurality of parameters with the first respective thresholds. If at least one of the parameters is an outlier parameter at or beyond its first respective threshold, another or others of the plurality of parameters associated to the at least one outlier parameter is identified, the at least one other parameter being selected based on a predetermined combination of parameters representative of an adverse condition. The associated parameters are compared with a stored data combination threshold specific to the associated parameters. A signal indicative of an impending situation is output if the associated parameters are on or beyond the data combination threshold.

Abstract: There is provided a low profile antenna comprising a line source, a corporate feed network, and a plurality of radiating elements. The radiating elements are arranged in a linear array so as to be discrete in a first direction and each continuous in a second direction substantially perpendicular to the first direction. The corporate feed network is integrated with the linear array of radiating elements to provide for a compact design.

Abstract: There is provided a waveguide combiner/splitter comprising an input waveguide, a first and a second waveguide matching section, and at least a first and a second output waveguide. The lengths and the widths of the matching sections may be adjusted for tuning to frequency bands of interest. The combiner/splitter may be incorporated into a corporate feed structure for use in an antenna system.

Abstract: There is provided a reflective line source for an antenna system. The reflective line source comprises at least one region adapted to receive an electromagnetic field and to expand the field in at least one dimension. The reflective line source further comprises a reflective phase compensator that is coupled to the region. The reflective phase compensator is adapted to correct a phase error resulting from propagation of the field through the region as well as to fold a direction of propagation of the field. For this purpose, the reflective phase compensator comprises at least two reflective phase compensating surfaces oriented at ninety degrees relative to one another.

Abstract: There is described a Passive Intermodulation (PIM) shield for use with an aircraft for reducing PIM sources, the PIM shield comprising: a conductive material adapted to be placed between an antenna and a fuselage of the aircraft for preventing undesired Radio Frequency (RF) signals resulting from a combination of RF signals transmitted from and to the antenna and generated by non-linear junctions or material between the antenna and the fuselage of the aircraft, the conductive material having a thickness based on an RF skin-depth related to an operating frequency of the antenna. There is described a method for determining an operating frequency of an antenna, determining an RF skin-depth related to the operating frequency of the antenna, and providing the PIM shield.

Abstract: A method for confirming mobile base station integrity in a relative GNSS aircraft landing system, the method comprising: determining a relative position of a first GNSS antenna fixed to the mobile base station with respect to a second GNSS antenna also fixed to the mobile base station by processing signals from a GNSS satellite constellation; calculating a distance between the first GNSS antenna and the second GNSS antenna using the measured relative position; comparing a calculated distance to a known fixed distance; and confirming mobile base station integrity if the calculated distance is within a predetermined threshold of the known fixed distance.

Abstract: An LED source for a liquid crystal display includes a heat sink having a top surface and a first side surface and a plurality of LEDs arranged in a row. Each LED includes a base and a first lead and is disposed such that the base of each LED contacts the top surface of the heat sink. A first circuit board is disposed such that the first circuit board contacts the first side surface of the heat sink.

Abstract: A cockpit display system has a display, such as a multi-function display (MFD) for displaying a graphical representation of an input device when a sensor senses that an aviator's finger is proximate to the input device. The display graphically depicts in real-time the position of the aviator's finger relative to the buttons of the input device. The aviator's finger can be depicted by an icon, shading or highlighting. When the aviator lightly touches a button, the graphical representation of that button can for example be highlighted, shaded or colored. Furthermore, when the button is firmly depressed, the graphical representation of that button can change color or shading. The aviator can thus operate any awkwardly located input device by simply reaching toward the input device and then guiding his finger to the correct button by looking at the graphical representation of the input device.

Abstract: A light source includes at least one optical fiber having a length and first and second ends and at least one electromagnetic wave source disposed along at least a portion of the length of the fiber for transmitting electromagnetic waves through a side surface of the fiber. A reflective surface is disposed at the first end of the fiber for directing light generated within the fiber toward the second end. A heads-up display can make effective use of the light source.

Abstract: A temperature compensation technique is disclosed which allows to obtain a compensated clock signal. The temperature compensation technique comprises the use of a thermal model of the oscillator with a temperature sensor in order to accurately compute the oscillator frequency, irrespective of time-variations and rates.

Abstract: A temperature compensation technique is disclosed which allows to obtain a compensated clock signal. The temperature compensation technique comprises the use of a thermal model of the oscillator with a temperature sensor in order to accurately compute the oscillator frequency, irrespective of time-variations and rates.