A flight path setting apparatus includes a display unit, a selector, a range calculator, and a display controller. The display unit displays a flight path of an aircraft. The flight path includes a plurality of points. The selector selects a first point on the basis of an operation performed by a user. The first point is any one of the points displayed by the display unit. The range calculator calculates a non-settable range on the basis of a flight performance and a surrounding environment of the aircraft. The non-settable range is a region that is around the first point and in which a second point is not settable. The second point is subsequent to the first point on the flight path. The display controller causes the display unit to display the non-settable range that relates to the first point and is calculated by the range calculator.

Flexible printed circuit boards and related methods are disclosed herein. An example printed circuit board includes a controller interface coupled to a surface of the printed circuit board between a first end of the printed circuit board and a second end of the printed circuit board. The example printed circuit board includes a connector coupled to the surface proximate to the first end. The example printed circuit board includes a notch formed between the controller interface and the connector. The notch is to form a narrowed portion of the printed circuit board to enable the printed circuit board to bend at the narrowed portion.

An example method for predictive take-off rejection (TOR) of an aircraft includes receiving, at a computing device on the aircraft and at a time before the aircraft takes off for a current flight, outputs from a plurality of sensors positioned on the aircraft, comparing the outputs received from the plurality of sensors for the current flight to reference flight data, based on comparing the outputs received from the plurality of sensors for the current flight to the reference flight data the computing device making a determination of whether to initiate a TOR procedure before the aircraft reaches a takeoff speed on a runway, and based on determining to initiate the TOR procedure, the computing device sending a signal to a control device on the aircraft to initiate the TOR procedure.

Safety systems for unmanned vehicles are disclosed. An example vehicle includes a housing and a propulsion system supported by the housing. The propulsion system to generate lift. An anti-crash module is coupled to the housing. The anti-crash module has a compressible foam that is to deploy to protect the propulsion system from an impact.

An aerial payload vehicle descent arrest system, method operating and device, including an aerial payload vehicle configured to descend along a predetermined flightpath toward a target destination, a descent state detection system configured to receive sensor output information from a plurality of sensors, to compute a sensed distance to the target destination based on sensor output information from at least two sensors of the plurality of sensors, and to generate a descent arrest device trigger signal based on a sensed altitude, and a descent arrest device configured to receive the descent arrest device trigger signal from the descent state detection system and to decelerate the aerial payload vehicle before a payload from the aerial payload vehicle is delivered to the target destination.

An aerial payload vehicle descent arrest system, method operating and device, including an aerial payload vehicle configured to descend along a predetermined flightpath toward a target destination, a descent state detection system configured to receive sensor output information from a plurality of sensors, to compute a sensed distance to the target destination based on sensor output information from at least two sensors of the plurality of sensors, and to generate a descent arrest device trigger signal based on a sensed altitude, and a descent arrest device configured to receive the descent arrest device trigger signal from the descent state detection system and to decelerate the aerial payload vehicle before a payload from the aerial payload vehicle is delivered to the target destination.

In one aspect, a magnetic drone is disclosed. The magnetic drone includes a drone, a cage surrounding the drone, and one or more magnets disposed on the cage surrounding the drone. The drone includes a camera, a battery, one or more electric motors, and one or more propellers. In other aspects, a method to operate a magnetic drone and a non-transitory computer readable medium storing instructions for performing operation that flies a magnetic drone are also disclosed.

The invention relates to an aircraft (1), more particularly a drone, and to a corresponding method for cleaning especially substantially flat surfaces that are preferably delimited by a frame (5), especially of windows or doors. The aircraft comprises at least one drive device (2), more particularly four drive devices (2), a controller, and a cleaning device (3), and at least one sensor (4) is provided on the aircraft (1) and the at least one sensor (4) is designed to control the aircraft on the surface.

The invention relates to an aircraft (1), more particularly a drone, and to a corresponding method for cleaning especially substantially flat surfaces that are preferably delimited by a frame (5), especially of windows or doors. The aircraft comprises at least one drive device (2), more particularly four drive devices (2), a controller, and a cleaning device (3), and at least one sensor (4) is provided on the aircraft (1) and the at least one sensor (4) is designed to control the aircraft on the surface.

There is provided a safety apparatus that not only has excellent safety performance but also has improved ease of accommodation of an ejected object in a container, and is capable of securing diversity of attachment positions to an aerial vehicle as compared with a related art, and an aerial vehicle including the safety apparatus. The safety apparatus includes a pilot chute ejector 62 and a main parachute storage. The pilot chute ejector 62 includes an actuator 1, a push-up member 15 pushed up in one direction by the actuator 1, a pilot chute 16 pushed up while being supported by the push-up member 15, a bottomed cylindrical container 18 that accommodates the actuator 1, the push-up member 15, and the pilot chute 16, and a lid 21 having a fan-shaped cross section that closes an opening end of the container 18. The actuator 1 is fixed at a position shifted from a geometric center of the fan-shaped cross section on a bottom surface of the container 18 via a base 2.