Abstract: Systems and methods for performing self calibration of a radar altimeter. An example system includes a first component that generates a simulated return signal based on one or more range values. A transmitter generates a transmission radar signal and a receiver processes the simulated return signal based on the transmission radar signal. A second component determines one or more calibration factors based on the processed simulated return signal and ideal return signal characteristics. The transmission radar signal is a fixed frequency signal and the first component includes a programmable frequency divider that creates at least on sideband of a known signal. A third component determines if the radar system is in at least one of a calibration mode or normal mode of operation. If the radar system is determined to be in a normal mode of operation, a fourth component applies the determined calibration factors to actual radar return signals.

Abstract: Systems and methods for testing a signal generated by a Direct Digital Synthesizer (DDS) in a radar altimeter. In an embodiment of the method, a voltage signal derived by comparing a fixed reference frequency to a ramped frequency signal generated by the DDS based on a clock-based reference signal is generated. The generated voltage signal is integrated over a predefined range of clock signals. The integration is sampled at a previously defined clock tick. The sample is compared to a desired value and an indication that the radar altimeter is malfunctioning is provided if the comparison exceeds a predefined threshold value. The radar altimeter system is deactivated if an indication that the radar altimeter is malfunctioning has been provided.

Abstract: The present invention provides systems and methods for pre-filter in a VHF receiver using Micro-Electro-Mechanical Systems (MEMS) filters. The system includes an antenna, and first and second Micro-Electro-Mechanical Systems (MEMS) filters. The first MEMS filter filters a signal received by the antenna based on a first pre-defined bandwidth, and the second MEMS filter filters the signal filtered by the first MEMS filter based on a second bandwidth. The system also includes an analog to digital converter that converts the signal filtered by the second MEMS filter into a digital signal, a down converter that down converts the digital signal produced by the A to D converter, and a digital signal processor that processes the down converted digital signal produced by the down converter. The first and second MEMS filters or the down converter are adjustable based on a received tuning signal.

Abstract: A radar altimeter system with a closed-loop modulation for generating more accurate radar altimeter values. The present invention combines flight safety critical sensors into a common platform to permit autonomous or semi-autonomous landing, enroute navigation and complex precision approaches in all weather conditions. An Inertial Navigation System (INS) circuit board, a radar altimeter circuit board and a Global Navigation Satellite System (GNSS) circuit board are housed in a single chassis. VHF (Very High Frequency) Omni-directional Radio (VOR), Marker Beacon (MB), and VDB (VHF Data Broadcast) receiver circuit boards may also be implemented on circuit boards in the chassis.

Abstract: The present invention provides a radar altimeter system with a closed loop modulation for generating more accurate radar altimeter values. The system includes an antenna, a circulator, a receiver, and a transmitter. The circulator receives or sends a radar signal from/to the antenna. The receiver receives the received radar signal via the circulator. The transmitter generates a radar signal and includes a phase-locked loop circuit for generating the radar signal based on a pre-defined phase signal. The transmitter includes a direct digital synthesizer that generates the phase signal based on a pre-defined clock signal and a control signal. The system includes a digital signal processor and a tail strike warning processor that determine position of a tail of the aircraft relative to ground and present an alert if a warning condition exists based on the determined position of the tail of the aircraft and a predefined threshold.