Abstract: An antenna array for use in an aviation application setting comprises an external covering and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. A deposit of phosphor material is also disposed beneath this covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering can be fixed to an exterior surface of an aircraft. The four radio frequency antennas are electrically discrete from one another though also being configured as an integral mechanical structure. The phosphor material, in turn, can serve to facilitate detection of a parameter of interest, such as temperature or airspeed.

Abstract: Specific determinations are made in a moving vehicle (901) and with respect to a person in the vehicle who has an ordinary expected gaze directionality while in the moving vehicle. These determinations can comprise automatically determining a position (101) of the moving vehicle with respect to terrain past which the moving vehicle is traveling, and automatically determining an orientation attitude (102) of the moving vehicle with respect to the terrain, and then automatically using (103) this position and orientation attitude to determine (in the absence of executable program instructions) a synthetic view to provide to the person in the vehicle. By one approach this synthetic view comprises a view of the terrain that comports with the ordinary expected gaze directionality of the person in the vehicle.

Abstract: An antenna array for use in an aviation application setting comprises an external covering and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. A deposit of phosphor material is also disposed beneath this covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering can be fixed to an exterior surface of an aircraft. The four radio frequency antennas are electrically discrete from one another though also being configured as an integral mechanical structure. The phosphor material, in turn, can serve to facilitate detection of a parameter of interest, such as temperature or airspeed.

Abstract: A vehicle such as an aircraft (400) is provided (101) with a source of power having a power output such as a source of light (401). This power output can then be combined with an identifier (103, 416) that is substantially unique to the aircraft. An optical conduit (405) can then be used (104) to couple this source of light to a light-to-electricity conversion apparatus (406). So configured, the optical conduit delivers light from this source of light to the light-to-electricity conversion apparatus such that the light source then serves as a source of electricity in the vehicle and as a source of a substantially unique identifier as corresponds to the vehicle is available for such use as may be appropriate.

Abstract: A vehicle (400) such as an aircraft is provided (101) with a source of light (401). An optical conduit is then used to couple (104) this source of light to a light-to-electricity conversion apparatus (408). which then converts (105) such light into electricity. A rechargeable power supply (407), such as a battery, uses (106) at least part of the electrical power output of the light-to-electricity conversion apparatus to be charged.

Abstract: A vehicle (400) such as an aircraft is provided (101) with a source of light (401) that provides both a power wavelength component (404) as well as a safety-pilot wavelength component (102, 415). An optical conduit (405) is then used (104) to couple this source of light to a light-to-electricity conversion apparatus. So configured, the optical conduit delivers light from this source of light to the light-to-electricity conversion apparatus such that the light source then serves as a source of electricity in the vehicle while the safety-pilot wavelength component serves, at least in part, as a visual warning and/or beneficial reaction-inducement to onlookers.

Abstract: These teachings present triple data transport redundancy in the form of three data bus interfaces that are each designed and manufactured independently from one another and compatible with a common data handling protocol. This protocol can be one that includes no error correction. These interfaces can each couple to a corresponding first, second, and third data bus that may comprise optical data busses. Information gauges can be realized through use a memory that stores a plurality of images comprising views of an information gauge (or gauges) of interest showing a variety of different readings. Upon receiving information regarding a monitored parameter of interest (via, for example, the aforementioned data busses and data bus interfaces), this information can be used to address the stored information gauge view that corresponds to the present parameter value. That particular view can be recalled and displayed to thereby provide the corresponding information to a viewer.

Abstract: These teachings present triple data transport redundancy in the form of three data bus interfaces that are each designed and manufactured independently from one another and compatible with a common data handling protocol. This protocol can be one that includes no error correction. These interfaces can each couple to a corresponding first, second, and third data bus that may comprise optical data busses. Information gauges can be realized through use a memory that stores a plurality of images comprising views of an information gauge (or gauges) of interest showing a variety of different readings. Upon receiving information regarding a monitored parameter of interest (via, for example, the aforementioned data busses and data bus interfaces), this information can be used to address the stored information gauge view that corresponds to the present parameter value. That particular view can be recalled and displayed to thereby provide the corresponding information to a viewer.

Abstract: A vehicle (400) such as an aircraft is provided (101) with a source of light (401). An optical conduit is then used to couple (104) this source of light to a light-to-electricity conversion apparatus (408). So configured, the optical conduit delivers light from this source of light to the light-to-electricity conversion apparatus such that the light source then serves as a source of electricity in the vehicle.

Abstract: A vehicle such as an aircraft (400) is provided (101) with a source of power having a power output such as a source of light (401). This power output can then be combined with an identifier (103, 416) that is substantially unique to the aircraft. An optical conduit (405) can then be used (104) to couple this source of light to a light-to-electricity conversion apparatus (406). So configured, the optical conduit delivers light from this source of light to the light-to-electricity conversion apparatus such that the light source then serves as a source of electricity in the vehicle and as a source of a substantially unique identifier as corresponds to the vehicle is available for such use as may be appropriate.

Abstract: A vehicle (400) such as an aircraft is provided (101) with a source of light (401). An optical conduit is then used to couple (104) this source of light to a light-to-electricity conversion apparatus (408). which then converts (105) such light into electricity. A rechargeable power supply (407), such as a battery, uses (106) at least part of the electrical power output of the light-to-electricity conversion apparatus to be charged.

Abstract: A vehicle (400) such as an aircraft is provided (101) with a source of light (401) that provides both a power wavelength component (404) as well as a safety-pilot wavelength component (102, 415). An optical conduit (405) is then used (104) to couple this source of light to a light-to-electricity conversion apparatus. So configured, the optical conduit delivers light from this source of light to the light-to-electricity conversion apparatus such that the light source then serves as a source of electricity in the vehicle while the safety-pilot wavelength component serves, at least in part, as a visual warning and/or beneficial reaction-inducement to onlookers.

Abstract: These teachings present triple data transport redundancy in the form of three data bus interfaces that are each designed and manufactured independently from one another and compatible with a common data handling protocol. This protocol can be one that includes no error correction. These interfaces can each couple to a corresponding first, second, and third data bus that may comprise optical data busses. Information gauges can be realized through use a memory that stores a plurality of images comprising views of an information gauge (or gauges) of interest showing a variety of different readings. Upon receiving information regarding a monitored parameter of interest (via, for example, the aforementioned data busses and data bus interfaces), this information can be used to address the stored information gauge view that corresponds to the present parameter value. That particular view can be recalled and displayed to thereby provide the corresponding information to a viewer.

Abstract: These teachings present triple data transport redundancy in the form of three data bus interfaces that are each designed and manufactured independently from one another and compatible with a common data handling protocol. This protocol can be one that includes no error correction. These interfaces can each couple to a corresponding first, second, and third data bus that may comprise optical data busses. Information gauges can be realized through use a memory that stores a plurality of images comprising views of an information gauge (or gauges) of interest showing a variety of different readings. Upon receiving information regarding a monitored parameter of interest (via, for example, the aforementioned data busses and data bus interfaces), this information can be used to address the stored information gauge view that corresponds to the present parameter value. That particular view can be recalled and displayed to thereby provide the corresponding information to a viewer.

Abstract: A vehicle (400) such as an aircraft is provided (101) with a source of light (401). An optical conduit is then used to couple (104) this source of light to a light-to-electricity conversion apparatus (408). So configured, the optical conduit delivers light from this source of light to the light-to-electricity conversion apparatus such that the light source then serves as a source of electricity in the vehicle.

Abstract: These teachings present triple data transport redundancy in the form of three data bus interfaces that are each designed and manufactured independently from one another and compatible with a common data handling protocol. This protocol can be one that includes no error correction. These interfaces can each couple to a corresponding first, second, and third data bus that may comprise optical data busses. Information gauges can be realized through use a memory that stores a plurality of images comprising views of an information gauge (or gauges) of interest showing a variety of different readings. Upon receiving information regarding a monitored parameter of interest (via, for example, the aforementioned data busses and data bus interfaces), this information can be used to address the stored information gauge view that corresponds to the present parameter value. That particular view can be recalled and displayed to thereby provide the corresponding information to a viewer.

Abstract: An aviation radio frequency receiver front end (502) and a corresponding antenna (501) are coupled together. The antenna is configured and arranged to be disposed during use in a fixed position proximal to an exterior surface of the aircraft fuselage. By one approach the antenna and the aviation radio frequency receiver front end are disposed in close physical proximity to one another. This can comprise, for example, having these elements comprise a single integrated physical structure. This can also comprise, where desired, disposing a corresponding aviation radio frequency receiver back end in close proximity to such components.

Abstract: A group multiplexed output (208) operably couples to each unique intermediate frequency received signal output as corresponds to a plurality of aviation radio frequency receiver front ends (502). By one approach, this can comprise, in particular, multiplexing, in frequency, each of the discrete received signal outputs for each of the plurality of aviation radio frequency receiver front ends with one another. By one approach, each such aviation radio frequency receiver front end is configured and arranged to receive radio frequency signals for a corresponding different radio frequency platform (as may each correspond, for example, to a different aviation operational purpose).

Abstract: An antenna array (501) for use in an aviation application setting comprises an external covering (503) and at least four radio frequency antennas that are disposed underneath and that are protected by the external covering. This external covering is at least partially permeable to radio frequency signals and will provide at least a substantial barrier against external moisture and objects that might otherwise harm the antennas. This external covering is also configured and arranged to be disposed, at least in part, in a fixed position proximal to an exterior surface (206) of an aircraft. The four radio frequency antennas are electrically discrete from one another and are each configured and arranged to receive radio frequency signals for a corresponding different radio frequency platform. These four radio frequency antennas are also configured and arranged as an integral mechanical structure.