Abstract: In one embodiment, a method is provided. The method comprises: selecting, with a communications management system configured to be installed on a vehicle, at least one primary channel on a multichannel transceiver; transmitting and/or receiving data over the at least one primary channel; searching, with the multichannel transceiver for other viable communications links; and selecting a new at least one primary channel.

Abstract: In one embodiment, a method is provided. The method comprises: selecting, with a communications management system configured to be installed on a vehicle, at least one primary channel on a multichannel transceiver; transmitting and/or receiving data over the at least one primary channel; searching, with the multichannel transceiver for other viable communications links; and selecting a new at least one primary channel.

Abstract: A method and system for estimating velocity of an aircraft is provided. The method comprises transmitting a beam toward a surface from the aircraft using a Doppler beam sharpened radar altimeter, receiving a plurality of reflected signals that correspond to portions of the transmitted beam that are reflected by the surface, and forming a plurality of Doppler beams by filtering the received signals. A complex-valued array of range bin is computed with respect to frequency of the Doppler beams from at least one antenna aperture of the radar altimeter, and a range for each of the Doppler beams is estimated. A velocity vector magnitude for the aircraft is estimated by a curve fit of the range with respect to the frequency of the Doppler beams.

Abstract: A method and system for estimating velocity of an aircraft is provided. The method comprises transmitting a beam toward a surface from the aircraft using a Doppler beam sharpened radar altimeter, receiving a plurality of reflected signals that correspond to portions of the transmitted beam that are reflected by the surface, and forming a plurality of Doppler beams by filtering the received signals. A complex-valued array of range bin is computed with respect to frequency of the Doppler beams from at least one antenna aperture of the radar altimeter, and a range for each of the Doppler beams is estimated. A velocity vector magnitude for the aircraft is estimated by a curve fit of the range with respect to the frequency of the Doppler beams.

Abstract: An integrated transceiver system for an avionics radio comprises a first transceiver comprising a first duplexer coupled with a first antenna, a first transmitter that sends an RF signal to the first duplexer, a first receiver that receives an RF signal from the first antenna through the first duplexer, and a first processor in communication with the first transmitter. The first transceiver is reconfigurable for ATG communications or DME navigation. A second transceiver comprises a second duplexer coupled with a second antenna, a second transmitter that sends an RF signal to the second duplexer, a second receiver that receives an RF signal from the second antenna through the second duplexer, and a second processor in communication with the second receiver. The second transceiver is reconfigurable for ATG communications, DME navigation, transponder signal communications, or satellite communications. The first and second transceivers are integrated into a line-replaceable unit of the radio.

Abstract: A differential calorimetric gas sensor (10) which includes a sensing element (12) having a catalytic layer (14) disposed on a multi-layered substrate (26). Catalytic layer (14) includes an active catalyst region (14a) which oxidizes total combustibles within an exhaust gas stream and a reference catalyst region (14b) which oxidizes selective combustibles within the exhaust gas stream. An electrochemical oxygen source (18) is disposed on an opposite side of multi-layer substrate (26) from sensing element (12). An oxygen sensor cell (170) may be incorporated into electrochemical oxygen source (18). The multi-layered substrate (26) includes a plurality of overlaying insulating layers in which an intermediate layer (60) and a bottom layer (64) support primary heaters (58, 62), and in which another intermediate layer (52) supports compensation heaters (50a, 50b).

Abstract: A calorimetric hydrocarbon gas sensor (10) includes an electrochemical oxygen pump (18), a sensing element (12), and a multi-layered substrate (26) separating the sensing element (12) from the electrochemical oxygen pump (18). The multi-layered substrate (26) includes a plurality of overlying insulating layers, in which at least one intermediate layer (60) supports a first primary heater (58), and in which another intermediate layer (52) supports a temperature compensation heaters (50a, 50b). The primary heater (58) functions to maintain the calorimetric hydrocarbon gas sensor (10) at a constant, elevated temperature, while the active compensation heater (50a) functions to maintain substantially equal temperatures as determined by the thermometers (46a, 46b) located on an intermediate layer (48) overlying the compensation heaters (50a, 50b).