A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft.

An interior aircraft light includes a mounting structure for mounting the interior aircraft light to an aircraft seat; a UV radiation source; and an optical system, configured to direct UV radiation from the UV radiation source towards a floor portion underneath the aircraft seat.

An unmanned aerial vehicle for providing ameliorative action. The unmanned aerial vehicle includes a processor-based monitoring device to monitor a plurality of individuals to determine crowd data associated with the plurality of individuals, a crowd estimator configured to receive the crowd data to estimate a crowd pressure estimation value indicative of a likelihood of a crowd event, the crowd pressure estimation value being based on the crowd data, and an ameliorative action generator to automatically perform a function when the crowd pressure estimation value exceeds a predetermined threshold value, wherein the function includes activating one or more feedback outputs configured to provide an ameliorative action

This invention, the Motor-wing Gimbal Aircraft (MGA) is an aerial vehicle and waterborne craft. It launches and lands vertically from the ground and water. In flight, it transitions from vertical, hovering and forward flight to horizontal flight. The MGA embodies multiple configurations and arrangements of motor-wings, propulsion systems and hybrid engine combinations. The MGA uses a fly-by-light system for flight maneuvering and controlling the motorized multi-axis gimbal cockpit. The MGA uses cellular communications together with the Global Positioning System (GPS) for navigation, collision avoidance and restricted airspace avoidance. The MGA uses visible lights to signal its elevation and flight maneuvers. The MGA is constructed of modular apparatuses and assemblies that are interchangeable and work in concert to power and maneuver the vehicle. This invention includes: the method of construction, the method of control, the method of visual light signaling, the method of electronic mapping of airspace (EMA) and the method of navigation. This invention includes flight operation applications and military applications.

This invention, the Motor-wing Gimbal Aircraft (MGA) is an aerial vehicle and waterborne craft. It launches and lands vertically from the ground and water. In flight, it transitions from vertical, hovering and forward flight to horizontal flight. The MGA embodies multiple configurations and arrangements of motor-wings, propulsion systems and hybrid engine combinations. The MGA uses a fly-by-light system for flight maneuvering and controlling the motorized multi-axis gimbal cockpit. The MGA uses cellular communications together with the Global Positioning System (GPS) for navigation, collision avoidance and restricted airspace avoidance. The MGA uses visible lights to signal its elevation and flight maneuvers. The MGA is constructed of modular apparatuses and assemblies that are interchangeable and work in concert to power and maneuver the vehicle. This invention includes: the method of construction, the method of control, the method of visual light signaling, the method of electronic mapping of airspace (EMA) and the method of navigation. This invention includes flight operation applications and military applications.

A display device for a vehicle includes a housing, a display screen, and at least one functional unit, including an operating element, each being a switch unit or a communication unit, adapted to be releasably coupled to the housing and includes an insertion portion and an operating element support portion supporting the respective operating element, and a first contact arrangement provided on the insertion portion and electrically coupled to the operating element. The housing includes at least one functional unit coupling arrangement, each adapted to be selectively and releasably coupled to at least one of the at least one functional unit and including a cavity inside the housing for receiving the insertion portion of the at least one functional unit, a second contact arrangement in the cavity, a retaining means, and an opening in an exterior wall of the housing communicating the cavity with the exterior of the housing.

A display device for a vehicle includes a housing, a display screen, and at least one functional unit, including an operating element, each being a switch unit or a communication unit, adapted to be releasably coupled to the housing and includes an insertion portion and an operating element support portion supporting the respective operating element, and a first contact arrangement provided on the insertion portion and electrically coupled to the operating element. The housing includes at least one functional unit coupling arrangement, each adapted to be selectively and releasably coupled to at least one of the at least one functional unit and including a cavity inside the housing for receiving the insertion portion of the at least one functional unit, a second contact arrangement in the cavity, a retaining means, and an opening in an exterior wall of the housing communicating the cavity with the exterior of the housing.

A system for locking a foldable wing tip on a wing end of an aircraft includes at least one engagement device, at least one locking device comprising a support, a latch element rotatably held in the support and a lock element movably held on the support, a latch drive device coupled with the latch element of the at least one locking device for selectively rotating the latch element at least to an open position, a closed position and a test position, a lock drive device coupled with the lock element of the at least one locking device for selectively varying a distance of the lock element to the latch element between a neutral position and a locking position, wherein the support includes a receiving space extending into an insertion opening designed for receiving the engagement device. The latch element includes a circumferential surface section that selectively covers the insertion opening in an open position and uncovers the insertion opening in a closed position of the latch element. The latch element includes at least one locking recess arranged on a circumferential path of motion for engaging with the lock element in the closed position of the latch element and the locking position of the lock element. The rotatable latch element further includes at least one protrusion on the circumferential path of motion, which acts as a stop for the lock element. The system further includes a signaling device indicating a correct function when the lock element rests on the at least one protrusion.

A system for locking a foldable wing tip on a wing end of an aircraft includes at least one engagement device, at least one locking device comprising a support, a latch element rotatably held in the support and a lock element movably held on the support, a latch drive device coupled with the latch element of the at least one locking device for selectively rotating the latch element at least to an open position, a closed position and a test position, a lock drive device coupled with the lock element of the at least one locking device for selectively varying a distance of the lock element to the latch element between a neutral position and a locking position, wherein the support includes a receiving space extending into an insertion opening designed for receiving the engagement device. The latch element includes a circumferential surface section that selectively covers the insertion opening in an open position and uncovers the insertion opening in a closed position of the latch element. The latch element includes at least one locking recess arranged on a circumferential path of motion for engaging with the lock element in the closed position of the latch element and the locking position of the lock element. The rotatable latch element further includes at least one protrusion on the circumferential path of motion, which acts as a stop for the lock element. The system further includes a signaling device indicating a correct function when the lock element rests on the at least one protrusion.

Systems, devices, and methods for stopping the rotation of propellers used in unmanned aerial vehicles (UAV) such as drones are disclosed. The propellers are stopped in response to detecting when beams of light adjacent the propellers are blocked.