A system may include a display and a processor. The processor may be configured to: obtain aircraft data associated with an aircraft; obtain or generate storm top data, the storm top data including information associated with storm top altitudes and storm top locations; generate aircraft relative storm top data; generate an aircraft relative storm top image based at least on the aircraft relative storm top data, wherein the aircraft relative storm top image depicts a view of weather in front of the aircraft, wherein the aircraft relative storm top image conveys information associated with a difference between at least some of the storm top altitudes and an altitude of the aircraft; and output the aircraft relative storm top image as graphical data.

A method and a device for measuring altitude of an aircraft relative to a point on the ground, said aircraft carrying a radar system comprising a directional antenna to transmit a radio frequency signal along a aiming axis, including. controlling the transmission of a radiofrequency signal along the axis, calculating received powers as a function of radial distance on a sum channel and an elevation deviation channel, calculating tilt angular deviation values, determining an estimator of the radial distance of the aircraft relative to the point on the ground intercepted by the aiming axis as a function of at least one zero crossing of the angular deviation measurement in a selected area of the angular deviation measurement curve, calculating an aircraft altitude relative to said point on the ground as a function of the estimator of the radial distance and the elevation angle of the aiming axis.

In some examples, a system includes a memory configured to store a buffer storing volumetric weather data. The system also includes processing circuitry configured to retrieve weather radar data from the buffer by retrieving a first reflectivity value associated with a first cell of the buffer, where the first cell represents a first volume of space. The processing circuitry is further configured to determine an altitude of a first location based on a parameter and an altitude extent of the first volume of space. The altitude of the first location is lower than an altitude of a centroid of the first volume of space. The processing circuitry is also configured to associate the first reflectivity value with the first location.

A weather radar system initiates a horizontal scan at a first tilt angle, then adjusts the tilt angle down during an intermediate phase of the horizontal scan, and finally adjust the tilt angle back to the first tilt angle for an end phase of the horizontal scan. The intermediate phase may comprise a fifteen-to-twenty-degree arc centered about a centerline of the weather radar antenna. The radar system may perform test horizontal scans at intervals within a predefined range, each having a different fixed tilt angle to identify tilt angles having desirable signal-to-noise ratio and signal-to-clutter ratio at different phases of the scan. Alternatively, the system may execute a vertical scan and at one or more horizontal positions to identify desirable tilt angles at various phases.

An aircraft-based synthetic vision system (SVS) is disclosed. In embodiments, the SVS includes avionics processors in communication with onboard lightning detection sensors, which provide the SVS with real-time lightning data (e.g., bearing to, and distance from, the aircraft) about proximate lightning strikes. Based on the real-time lightning data, the avionics processors generate flight deck effects (FDE) corresponding to identified areas of lightning activity (e.g., a sufficient quantity of strikes, exceeding a strike threshold, within a particular airspace during a time window), each FDE having a particular bearing to and distance from the aircraft. The FDE data is processed by a display system aboard the aircraft (e.g., a cockpit-based primary flight display (PFD) or head-worn/heads-up display (HWD/HUD)) which incorporates the generated FDEs into the SVS status display provided to the flight crew or pilot at the appropriate bearing and distance relative to the aircraft.

A weather depiction system for an aircraft is disclosed. A radar is configured to scan a surrounding environment of the aircraft and provide weather data. An aircraft computing device is configured to: detect weather patterns using the weather data, receive a flight trajectory of the aircraft from a flight management system (FMS), compare the flight trajectory to an altitude of each of the weather patterns, identify the weather pattern as relevant or non-relevant based on the comparison, and present symbols corresponding to the relevant weather patterns on the weather display and exclude symbols corresponding to the non-relevant weather patterns on the weather display.

In some examples, a system includes a weather radar device configured to transmit radar signals, receive first reflected radar signals at a first time, and receive second reflected radar signals at a second time. In some examples, the system also includes processing circuitry configured to determine a first magnitude of reflectivity based on the first reflected radar signals and determine a second magnitude of reflectivity based on the second reflected radar signals. In some examples, the processing circuitry is also configured to determine a temporal variance in reflectivity magnitudes based on determining a difference in reflectivity between the first magnitude and the second magnitude. In some examples, the processing circuitry is further configured to determine a presence of ice crystals based on the first magnitude of reflectivity, the second magnitude of reflectivity, and the temporal variance in reflectivity magnitudes.

A method, apparatus, and system for managing sensor system for an aircraft. A presence of erroneous sensor data generated by a set of external sensors on an exterior of the aircraft is detected. A set of deployable sensors is deployed in response to the erroneous sensor data being received from the set of external sensors on the exterior of the aircraft when an undesired environmental condition adverse to the set of external sensors on the exterior of the aircraft is absent. Sensor data is received from the set of deployable sensors.

A system and method for ice crystal detection and qualification are disclosed. The system for ice crystal detection may include an aircraft weather radar and processing circuitry. The aircraft weather radar may perform scans at one or more elevations at successive times. The processing circuitry may calculate power and reflectivity values based on the scans. The processing circuitry may further compare the power and reflectivity values to threshold values to determine the presence of ice water content. The processing circuitry may display different colors on a display for areas in which the power and reflectivity values are lower than the threshold values.

The present disclosure discloses a system for echo intensity calibration based on continuous wave weather radar data. The system includes a communication module used for establishing a network protocol or local protocol-based communication link between a radar receiver and a radar terminal computer; a main control module which is in communication connection with the communication module to receive radar data of the radar receiver or a control signal of the radar terminal computer and execute an echo intensity calibration strategy; and a storage module which temporarily stores continuous wave weather radar data, and aircraft echo power values that are identified by the main control module within a period of time.