A vertical landing vehicle including an airframe forming a hull and having at least one wing coupled to the airframe, at least one proximity sensor coupled to the airframe, and a flight control system including a control processor and an operator interface, wherein the at least one proximity sensor is coupled to the control processor, wherein the control processor, based on signals from the at least one proximity sensor, is configured to generate, for presentation through the operator interface, situational awareness indications corresponding to portions of the hull sensed by the at least one proximity sensor and obstacles sensed by the at least one proximity sensor, and wherein the situational awareness indications comprise a terrain map overlay including positional relationships between the hull and the obstacles.

A method of operating a rotorcraft includes receiving multiple first height data signals from multiple first height sensors on the rotorcraft, wherein the first height sensors measure height using a first technique, receiving multiple second height data signals from multiple second height sensors on the rotorcraft, wherein the second height sensors measure height using a second technique that is different than the first technique, determining a first height signal from the multiple first height data signals based on a selection scheme, determining a second height signal from the multiple second height data signals, selecting the first height signal or the second height signal to determine a selected height signal, and generating a flight control signal and controlling operation of the rotorcraft according to the flight control signal, the flight control signal based on the selected height signal.

A system and method for controlling a flying toy is shown and described herein. The flying toy may transmit a signal and receive a return signal after the signal reflects off of a surface. The return signal may be compared to the transmitted signal to determine information indicative of an error between the transmitted signal and the return signal. A control signal may be sent to a motor to control the speed of the motor based on the information indicative of the error. The motor may operate a propeller to control the distance between the flying toy and the surface.

A method and a device for determining and displaying a flyaway distance for a rotorcraft in the event of an engine of the rotorcraft failing, and while taking account of the height of waves being overflown by the rotorcraft. The method includes a first determination for determining a flyaway distance of the rotorcraft in the event of a failure of an engine and under current flying conditions, a second determination for determining a maximum altitude of the waves being overflown by the rotorcraft and displaying the flyaway distance and the maximum altitude on a display instrument of the rotorcraft indicating the relative height of the rotorcraft or else its altitude. A safety margin is preferably added to the maximum altitude of the waves, or else to the flyaway distance of the rotorcraft.

A radar, flying device including such a radar, processing method in a radar embedded in a flying device and associated computer program are disclosed. In one aspect, the radar includes a transceiver antenna including a plurality of radiating elements configured to transmit and receive an electromagnetic wave. The radar includes an antenna gain control unit, by activating/inhibiting radiating elements, in transmission and/or reception configured to keep the reception level of an electromagnetic wave below a determined threshold below the saturation zone of the antenna, as well as by activating/inhibiting radiating elements in reception, configured to compensate the amplitude variation of the ground/sea clutter, over the duration of the reception.

In some examples, a system is configured to be mounted on a vehicle, the system including one or more phased-array radar devices configured to transmit first radar signals, receive first returned radar signals, transmit second radar signals, and receive second returned radar signals. In some examples, the system also includes processing circuitry configured to detect an object based on the first returned radar signals and determine an estimated altitude of the vehicle above a ground surface based on the second returned radar signals.

A system and method for providing wireless data communication between a wireless communication system in an aircraft and a stationary communication server outside the aircraft are disclosed. The wireless communication system includes a router network connected to a plurality of antennas, wherein the router network is configured to transmit and receive wireless data communication to and from a stationary communication server outside said aircraft through at least one ground base station via said antennas. The router network includes a plurality of connectivity nodes being physically separated and distributed within the aircraft, the connectivity nodes being connected to each other via a bus, and each connectivity node including a control unit, at least one modem, and preferably a plurality of modems, and a connection to at least one of the antennas. Further, each antenna is connected only to one of the connectivity nodes.

A distance sensor and a measured object are positioned at a known distance from each other. A measured distance between the distance sensor and the measured object is obtained from the distance sensor, where the distance sensor uses a plurality of signals at a plurality of angles to generate the measured distance. The known distance and the measured distance are compared in order to test the distance sensor and produce a test result.

A system for intelligent non-disruptive airspace integration of unmanned aircraft systems (UAS) is disclosed. The system includes an onboard positioning system and altimeter that determine a current position and altitude of the UAS. Under normal conditions, the UAS remains in inert mode: a transceiver listens for and decodes transmissions from nearby aircraft and ground-based traffic and control facilities. If certain conditions are met (e.g., proximate aircraft, altitude ceilings, controlled or restricted airspaces) the system may declare an alert mode. When in alert mode, the transceiver broadcasts position and identifier information of the UAS to alert neighboring aircraft to its presence. Intelligent transmission strategies regulate the power level or rate of alert-mode transmissions to reduce spectrum congestion due to high UAS density. Alert-mode transmissions continue until the underlying conditions change and inert mode is resumed.

In one aspect, a system for monitoring field profiles may include a vision-based sensor configured to capture vision data indicative of a profile of a field, with the profile being at least of a crop canopy profile of the field or a soil surface profile of the field. The system may also include a secondary sensor configured to capture secondary data indicative of the profile of the field. Furthermore, a controller of the disclosed system may be configured to receive the vision data from the vision-based sensor and the secondary data from the secondary sensor. Moreover, the controller may be configured to determine a quality parameter associated with the vision data. Additionally, when the quality parameter falls below a minimum threshold, the controller may be configured to determine at least a portion of the profile of the field based on the secondary data.