Abstract: A method includes providing a radar sensor onboard a vehicle, and one or more active radar beacons around a landing site. Each beacon produces a pattern of one or more artificial echoes that is different from a pattern of echoes produced by others of the beacons. The method further includes guiding the vehicle toward the landing site by transmitting radar signals from the radar sensor to an area around the landing site; receiving return signals from the area around the landing site, including ground reflected signals and transmitted signals from each beacon; and determining whether artificial echoes are detected in the received return signals. When artificial echoes are detected, beacon parameters are loaded from an onboard active beacons database; patterns in the artificial echoes are identified and associated with corresponding beacons from the database; and a slant range to each of the beacons is estimated through the patterns.

Abstract: A system comprises a vehicle radar sensor including an antenna, transmitter, receiver, and processor. The processor hosts a scanning control module that sends a control signal to the transmitter, receiver, or both, to generate radar beams; and a signal processing module that receives a reflected signal from the receiver to generate radar data. The system also includes an onboard application module and ground surface database. The application module is operative to access information from the surface database, access position and attitude data, access position and attitude uncertainty data, access radar installation data, and access radar data from the signal processing module; identify ground surface areas to be avoided based on the information from the surface database, the position and attitude, the position and attitude uncertainty, and the radar installation data; and perform modified radar operations and/or processing when the ground surface areas to be avoided are within a radar FOV.

Abstract: A system comprises a vehicle radar sensor including an antenna, transmitter, receiver, and processor. The processor hosts a scanning control module that sends a control signal to the transmitter, receiver, or both, to generate radar beams; and a signal processing module that receives a reflected signal from the receiver to generate radar data. The system also includes an onboard application module and ground surface database. The application module is operative to access information from the surface database, access position and attitude data, access position and attitude uncertainty data, access radar installation data, and access radar data from the signal processing module; identify ground surface areas to be avoided based on the information from the surface database, the position and attitude, the position and attitude uncertainty, and the radar installation data; and perform modified radar operations and/or processing when the ground surface areas to be avoided are within a radar FOV.

Abstract: A method of supplementing a satellite based augmentation system approach during low visibility conditions is provided. The method includes acquiring satellite range measurements and additional measurements from at least one additional onboard independent sensor. Core sigma values are assigned for satellite range measurements and for each additional measurement from the at least one additional onboard independent sensor. A weighted position solution is determined using the acquired satellite range measurements, the acquired additional measurements and the assigned core sigma values. A discriminator is applied that utilizes vehicle positions derived from the acquired satellite range measurements and from the additional measurements to determine if a fault is present in the weighted position solution. An alert is generated if an output of the discriminator is outside a set tolerance value needed for low visibility operation.

Abstract: Systems and methods directed to evaluating and enabling enhanced glide slope angles are provided. The method includes, in a control module, identifying a designated glide slope angle (D_GSA) based on a designated approach procedure; receiving and processing sensor data and navigation data; and, generating an adaptive glide slope angle (A_GSA) and an associated final capture altitude (FCA) based thereon. The method includes determining whether (a) an altitude constraint applies at the FCA, and determining whether (b) a level segment exists at the FCA. When (a) and (b) are concurrent, the method enables modification of the designated approach procedure with the A_GSA; and, the method prevents modification of the designated approach procedure with the A_GSA when there is no concurrence of (a) and (b).

Abstract: A method of supplementing a satellite based augmentation system approach during low visibility conditions is provided. The method includes acquiring satellite range measurements and additional measurements from at least one additional onboard independent sensor. Core sigma values are assigned for satellite range measurements and for each additional measurement from the at least one additional onboard independent sensor. A weighted position solution is determined using the acquired satellite range measurements, the acquired additional measurements and the assigned core sigma values. A discriminator is applied that utilizes vehicle positions derived from the acquired satellite range measurements and from the additional measurements to determine if a fault is present in the weighted position solution. An alert is generated if an output of the discriminator is outside a set tolerance value needed for low visibility operation.

Abstract: Systems and methods directed to evaluating and enabling enhanced glide slope angles are provided. The method includes, in a control module, identifying a designated glide slope angle (D_GSA) based on a designated approach procedure; receiving and processing sensor data and navigation data; and, generating an adaptive glide slope angle (A_GSA) and an associated final capture altitude (FCA) based thereon. The method includes determining whether (a) an altitude constraint applies at the FCA, and determining whether (b) a level segment exists at the FCA. When (a) and (b) are concurrent, the method enables modification of the designated approach procedure with the A_GSA; and, the method prevents modification of the designated approach procedure with the A_GSA when there is no concurrence of (a) and (b).

Abstract: The preferred embodiments are directed to discloses a metal halide high-pressure discharge lamp comprising a burner which is enclosed by an outer bulb. In the outer bulb samarium is provided.

Abstract: Systems and methods directed to generating an adaptive glide slope angle and allowing a pilot to interact with the generated glide slope angle are provided. The systems and methods retrieve, from a navigation database (NDB), a designated approach procedure for the aircraft, and identify a designated glide slope angle (D_GSA) based thereon. The systems and methods receive sensed actual weather data and sensed aircraft status data and generate an adaptive glide slope angle A_GSA based thereon. The systems and methods allow modification of and modify, or prevent modification of, the designated approach procedure with the A_GSA based on the determination of whether or not the A_GSA is compatible with the designated approach procedure.

Abstract: The preferred embodiments are directed to discloses a metal halide high-pressure discharge lamp comprising a burner which is enclosed by an outer bulb. In the outer bulb samarium is provided.

Abstract: Systems and methods, and non-transitory computer readable mediums directed to generating an adaptive glide slope angle and allowing a pilot to interact with the generated glide slope angle are provided. The systems and methods, and non-transitory computer readable mediums retrieve, from a navigation database (NDB), a designated approach procedure for the aircraft, and identify a designated glide slope angle (D_GSA) based thereon. The systems and methods, and non-transitory computer readable mediums receive sensed actual weather data and sensed aircraft status data and generate an adaptive glide slope angle A_GSA based thereon. The systems and methods, and non-transitory computer readable mediums allow modification of and modify, or prevent modification of, the designated approach procedure with the A_GSA based on the determination of whether or not the A_GSA is compatible with the designated approach procedure.