A communication system for a vehicle comprises a mechanism for sensing a motion status of a vehicle, a control device, plurality of data acquisition sensors, and one or more alerting device activation circuits. The communication system is customizable with the plurality of data acquisition sensors and one or more alerting device activation circuits based upon the needs of the vehicle.

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. The processer includes a radar altimeter inertial vertical loop (RIVL) filter that determines relative vertical acceleration based on a difference between vehicle vertical acceleration and ground/object vertical acceleration; determines relative vertical velocity based on a difference between vehicle vertical velocity and ground/object vertical velocity; performs consistency checks on the relative vertical acceleration and relative vertical velocity; and outputs estimated vehicle vertical position and vertical velocity statistics for compensation of the navigation filter outputs.

An air data probe (10) and associated method of method of measuring air data is disclosed. The air data probe includes a plurality of air pressure sensors, and a body (14) that encloses a hollow interior cavity (16), where the body (14) has a generally symmetrical airfoil profile. The body (14) includes a plurality of projections (20a-d) extending beyond the generally symmetrical airfoil profile, each of the plurality of projections (20a-d) including an pressure port (22a-d) at a distal end (24a-d) that is in communication with the hollow interior cavity. Each of the pressure ports (22a-d) receives a corresponding air pressure sensor (12a-d) that is configured to collect static and dynamic air pressure data.

The present invention relates to a method for calibrating an altitude sensing stereo vision device (122) of an unmanned aerial vehicle (100), wherein the method includes: arranging the unmanned aerial vehicle to take off from ground (G) and ascend; deriving at least one first altitude value (10a-15a) from the stereo vision device and obtaining at least one corresponding second altitude value (10b-15b) from another device (123) of the unmanned aerial vehicle during the ascent (1) of the unmanned aerial vehicle; recording the derived at least one first altitude value and the obtained at least one corresponding second altitude value as calibration data; deriving an additional first altitude value from the stereo vision device while the unmanned aerial vehicle flies a route; and adjusting the derived additional first altitude value based on the recorded calibration data.

A low range altimeter (LRA) may include a transmitter, a receiver, at least one antenna, an active leakage cancellation circuit, and a microcontroller unit (MCU). The transmitter may be configured to transmit a first signal (or transmitted signal) via the at least one antenna. The receiver may be configured to receive a second signal (or received signal) via the at least one antenna. The active leakage cancellation circuit may be configured to receive a portion of the transmitted signal from the transmitter, and may be configured to inject the portion of the transmitted signal into the receiver after an adjustment of the portion of the transmitted signal to reduce leakage observed in the received signal. The MCU may be coupled to the transmitter and the receiver, and may be configured to adjust the portion of the portion of the transmitted signal.

A method and a system for establishing a route of an unmanned aerial vehicle are provided. The method includes identifying an object from surface scanning data and shaping a space, which facilitates autonomous flight, as a layer, collecting surface image data for a flight path from the shaped layer, and analyzing a change in image resolution according to a distance from the object through the collected surface image data and extracting an altitude value on a flight route.

A flight imaging system and a method suitable where an unmanned flying object equipped with a visible camera and millimeter-wave radar is used, and a structure imaged by the visible camera and millimeter-wave radar mounted on the unmanned flying object are provided. A drone constituting the flight imaging system is equipped with a visible camera and a millimeter-wave radar. A processor of the drone performs control of the visible camera to capture a visible image of a surface layer of the structure, and control the millimeter-wave radar to transmit a millimeter wave toward the structure and receive a reflected wave of the millimeter wave from the structure, in a case of imaging the structure. During flight of the drone, the altitude of the drone is measured by an altitude meter mounted on the drone, altitude information indicating the measured altitude is acquired, and is used, in flying the drone.

A method for calculating a sensitivity of a displacement of Synthetic Aperture Radar (SAR) along line-of-sight direction to a slope gradient and a slope aspect is provided, comprising: obtaining SAR data and Digital Elevation Model (DEM) data covering slope bodies, and extracting a local incident angle of an image by utilizing a satellite side-looking imaging principle; carrying out geometric distortion on the slope bodies under ascending and descending orbits by utilizing the local incident angle, to obtain specific locations of geometric distortion areas under ascending and descending orbit; calculating sensitivities of detections to changes of the slope gradient and the slope aspect under ascending and descending orbits according to the extracted parameter information of the SAR satellite in ascending and descending orbits and satellite heights, and dividing a sensitivity distribution by combining the sensitivity and the specific locations of the geometric distortion.

A method for measuring a height on a plane, implemented by an electronic device, includes displaying an altitude obtained in a first detection manner, and displaying an altitude obtained in a second detection manner when a first switching condition is met. In this way, the electronic device displays an altitude detected based on a barometric pressure sensor. When a barometric pressure value of an environment in which the electronic device is located is inconsistent with an atmospheric pressure value, the data of the barometric pressure sensor is invalid. The electronic device displays an altitude obtained in another detection manner. In this way, the electronic device can display an accurate altitude in a case in which a user takes a plane.

To provide a fuel cell system configured to increase fuel cell performance even at high altitude. A fuel cell system for air vehicles, wherein the fuel cell system comprises: a fuel cell, an oxidant gas system for supplying oxidant gas to the fuel cell, an altitude sensor, and a controller; wherein the oxidant gas system comprises an air compressor and a bypass flow path bypassing the fuel cell; wherein the bypass flow path comprises a bypass valve; and wherein, when the controller detects an altitude increase measured by the altitude sensor, the controller increases a rotational speed of the air compressor, and the controller increases an opening degree of the bypass valve.