Abstract: A system to provide navigation solutions for vehicle landing guidance comprises onboard aiding sensors, an IMU, a radar altimeter, a map database, and a navigation system including a navigation filter that outputs estimated kinematic state statistics for the vehicle. An onboard processor inputs horizontal and vertical position statistics from the navigation filter into the map database, and computes an estimated ground/object height, ground/object velocity, ground/object acceleration, and error statistics thereof, based on terrain and object map data.

Abstract: Disclosed is a vehicle-mounted ranging system having a communication transceiver configured to wirelessly communicate with at least one external communication transceiver and a plurality of ultra-wideband (UWB) transceivers configured to transmit and receive ranging pulses to and from at least one external UWB transceiver associated with the at least one external communication transceiver. A controller is interfaced between the communication transceiver and the plurality of UWB transceivers. The controller is configured to communicate with the associated at least one external communication transceiver to schedule transmission of ranging pulses between the plurality of UWB transceivers and the at least one external UWB transceiver and to calculate ranges between each of the plurality of UWB transceivers and the at least one external UWB transceiver based upon time-of-arrival of ranging pulses transmitted between the plurality of UWB ranging transceivers and the at least one external UWB transceiver.

Abstract: An electronic device, method and system for global navigation satellite system (GNSS) are herein disclosed. The electronic device includes an antenna configured to receive a satellite vehicle (SV) signal, and a processor configured to determine a carrier-to-noise density ratio (CNO) of the SV signal, compare the determined CNO of the SV signal with a threshold, and identify whether the SV signal is a true SV signal or a false SV signal when the determined CNO is less than the threshold.

Abstract: A system for maneuvering an aircraft for operations in connection with a sea-going vessel, the vessel having a designated area for landings and sling-load operations. Each of the aircraft has a navigation unit (INU) comprising a GPS receiver and an inertial navigation unit. The INU's are updated by data from the GPS receivers and the data from the shipboard unit's GPS receiver and INU are transmitted to the aircraft. The aircraft performs RTK calculations to determine a vector to the shipboard GPS antennas and modifies the vector with data from the INU's.

Abstract: Systems and methods for monitoring broadband radio frequency interference are provided. In certain embodiments, a method comprises calculating a smoothed carrier to noise value for a received signal on a processing unit, wherein the received signal is associated with a receiver and at least one satellite; calculating an average jammer power to noise power value for the receiver; calculating an instantaneous carrier to noise value for the received signal based on the average jammer power to noise power value and the smoothed carrier to noise value; comparing the instantaneous carrier to noise value to an exclusion threshold, and determining whether to exclude the received signal from calculations of global positioning data based on the comparison of the instantaneous carrier to noise value to the exclusion threshold; and when the received signal is excluded, monitoring the received signal for readmittance to the calculation of global positioning data.

Abstract: Disclosed herein are a system for automatically landing an aircraft using image signals and a method of controlling the system. The system includes an altimeter installed on the aircraft; a landing mark placed at a landing location on a landing runway; a camera installed on the aircraft, oriented toward the front of the aircraft, and configured to detect the shape of the landing mark in image information form; and a FCC configured to calculate the angle between the aircraft and the ground, the ground range and the slant range between the aircraft and the landing location using the altitude information measured by the altimeter, the image information of the landing mark captured by the camera, angle information composed of the pitch, roll and yaw angles of the aircraft, and the angle of entry into the landing runway, and configured to control the automatic landing of the aircraft.

Abstract: The inventive flight control assisting device comprises first means (4) for determining the actual aircraft flight conditions, second means (5) for determining, with the aid of said actual flight conditions and a predetermined pattern, a minimum approaching distance corresponding to a minimum distance between projections on the horizontal plane of the aircraft actual position and a touch-down point when said aircraft moves downwards and decelerates according to an optimised approach in such a way that stabilised approaching conditions are attained, and display means (7) for displaying at least said minimum approaching distance on a navigation screen (9) in the form of a first circular arc focused on a position relative to the aircraft which displays the touch-down position.

Abstract: A reconfigurable wireless modem adapter is provided. The reconfigurable wireless modem adapter includes a control board and a radio frequency switch. The control board has at least two interfaces for a respective at least two modems and is configured to communicatively couple to at least one onboard system in a vehicle. The control board activates a selected modem interfaced to one of the at least two interfaces. The radio frequency switch is communicatively coupled to the control board via the selected one of the at least one modem. The radio frequency switch communicatively couples an antenna to the selected modem. When the control board is communicatively coupled to the at least one onboard system and activates the selected modem, and when the radio frequency switch is communicatively coupled to the antenna, the antenna is communicatively coupled to the at least one onboard system via the selected modem.

Abstract: A reconfigurable wireless modem adapter is provided. The reconfigurable wireless modem adapter includes a control board and a radio frequency switch. The control board includes at least two user-data interfaces for respective at least two modems, the modems including at least one diversity/multiple-input-multiple-output (MIMO) modem. The control board is configured to communicatively couple to at least one onboard system in a vehicle and to activate one of the at least one diversity/MIMO modem interfaced to one of the at least two user-data interfaces. The radio frequency switch is communicatively coupled to the control board via a modem-select interface and the selected one of the at least one diversity/MIMO modem. The radio frequency switch communicatively couples one of at least one diversity/MIMO antenna on the vehicle to the selected one of the at least one diversity/MIMO modem based on a control signal.

Abstract: In a method for aiding aircraft landing using a GPS and an MLS within the context of a computed axial approach, the method uses coordinates of an azimuth antenna and/or of an elevation antenna as a reference point for the computation of a position of the aircraft in a reference frame centered on the landing runway. This position of the aircraft is thereafter used to determine an angle of azimuth between a longitudinal axis of the landing runway and the aircraft.

Abstract: Disclosed herein are a system for automatically landing an aircraft using image signals and a method of controlling the system. The system includes an altimeter installed on the aircraft; a landing mark placed at a landing location on a landing runway; a camera installed on the aircraft, oriented toward the front of the aircraft, and configured to detect the shape of the landing mark in image information form; and a FCC configured to calculate the angle between the aircraft and the ground, the ground range and the slant range between the aircraft and the landing location using the altitude information measured by the altimeter, the image information of the landing mark captured by the camera, angle information composed of the pitch, roll and yaw angles of the aircraft, and the angle of entry into the landing runway, and configured to control the automatic landing of the aircraft.

Abstract: The integrity of operation of a GPS precision aircraft approach and landing system may be compromised by error producing effects of reflected multipath signals. An integrity monitor antenna system as disclosed may utilize both attenuation and shadowing of reflected multipath GPS signals to achieve extreme multipath mitigation of the order of 50 dB suppression. An antenna with a right-hand circular polarization pattern having a sharp cut off at the horizon may provide 30 dB suppression of reflected multipath signals. A signal absorbent ground plane bed of defined dimensions may provide 20 dB attenuation of incident multipath signals. A signal/processor may be employed to derive position error data for integrity monitoring, based upon differentials between a known fixed location and a current GPS-indicated location. Communication of identification of a subset of particular GPS satellites for common usage may also reduce potential error levels.