A releasable sling device includes first, second, and third attachment devices. The first attachment device is configured to an elevating device. The second attachment device is configured to be attached to an object. The third attachment device configured to be attached to a structure. A connection element is connected between the first attachment device and the second attachment device. A securing device has a first end that is connected to the second attachment device and a second end that is connected via a releasable connection device to the third attachment device. A releaser element is connected between the first attachment device and the releasable connection device. The releasable connection device is configured to release the third attachment device from the securing device when the releaser element is pulled away from the releasable connection device with a predetermined force threshold.

A storage locker for drone delivery provides for weathertight doors that open automatically on sensing the approach of a drone and close to cover the package once deposited by the drone. The storage locker may be operated in conjunction with an elevator to allow elevated placement, removing drones from the vicinity of interfering structures, people, and pets.

An aircraft store ejector systems and subsystems thereof. Embodiments can include a two-reservoir re-pressurization system wherein a remote reservoir is used to maintain desired pressure in a local ejector reservoir. The system can include a release valve having a vent valve and valve piston. The release valve can control release of pressurized gas to a pitch control valve. The pitch control valve can be configured to distribute the pressurized gas between two or more ejector piston assemblies. One or more of the ejector piston assemblies can include multiple concentric piston stages and piston chambers, the piston chambers configured to contain a volume of gas. The ejector piston assemblies can be configured to compress the volume of gas within the piston chambers as the piston stages are extended out from the aircraft. Such compression can provide a return force to the piston stages.

The present invention has an object of providing an unmanned aircraft system, control device and control method which can more easily anchor a package to a linear member. An unmanned aircraft system (1) of an embodiment of the present invention includes: an unmanned aircraft (2) including a hoisting mechanism capable of feeding out and hoisting a linear member (31); a flight control unit (61) which causes the unmanned aircraft (2) to take off in a state in which a package (T) anchored to the linear member (31) is arranged on a ground surface; and a hoisting control unit (62) which causes the linear member (31) to be hoisted by the hoisting mechanism (3), after the unmanned aircraft (2) has taken off, in a case of a hoisting condition indicating a state enabling hoisting of the linear member (31) being satisfied.

Various embodiments of the present invention comprise systems for providing a lifesaving apparatus to a distressed individual. Such systems may comprise an unmanned aerial vehicle (UAV) configured to selectably support a lifesaving apparatus. The UAV may comprise a release mechanism configured to release the lifesaving apparatus when proximate a distressed person. The system may additionally comprise a control device configured to wirelessly communicate with the UAV such that a user can pilot the UAV from a distance and deliver the lifesaving apparatus to a distressed person. Methods of using the same may comprise piloting the UAV proximate a distressed person, providing a signal to the UAV to release the lifesaving apparatus by operating the release mechanism, and then pulling the lifesaving apparatus and the distressed person to safety via a control line secured to the lifesaving apparatus.

Various embodiments of the present invention comprise systems for providing a lifesaving apparatus to a distressed individual. Such systems may comprise an unmanned aerial vehicle (UAV) configured to selectably support a lifesaving apparatus. The UAV may comprise a release mechanism configured to release the lifesaving apparatus when proximate a distressed person. The system may additionally comprise a control device configured to wirelessly communicate with the UAV such that a user can pilot the UAV from a distance and deliver the lifesaving apparatus to a distressed person. Methods of using the same may comprise piloting the UAV proximate a distressed person, providing a signal to the UAV to release the lifesaving apparatus by operating the release mechanism, and then pulling the lifesaving apparatus and the distressed person to safety via a control line secured to the lifesaving apparatus.

A hitch mount assembly for an unmanned aerial vehicle is shown and described. The hitch mount assembly may include a mount body operatively engagable with an aerial vehicle such as an unmanned aerial vehicle (UAV), where the mount body has an attachment feature to be selectively secured to the UAV and allow for selective attachment to a plurality of UAVs. A stabilizing unit attached to the mount body. The stabilizing unit may include a gimbal mounted gyro stabilization unit. A connection plate attached to the stabilizing unit. The connection plate may be attachable to various implement assemblies.

Systems and methods are provided for decoupling movable control surfaces. Such systems may detect that a movable control surface is in a non-responsive state, such as a hard-over, and decouple the movable control surface from the main, fixed, control surface. The control surfaces may be coupled to an aircraft. A controller of the aircraft may detect the nonresponsive movable control surface, provide instructions to decouple the movable control surface, and compensate for the decoupling of the movable control surface in instructions provided to flight systems of the aircraft.

Systems and methods are provided for decoupling movable control surfaces. Such systems may detect that a movable control surface is in a non-responsive state, such as a hard-over, and decouple the movable control surface from the main, fixed, control surface. The control surfaces may be coupled to an aircraft. A controller of the aircraft may detect the nonresponsive movable control surface, provide instructions to decouple the movable control surface, and compensate for the decoupling of the movable control surface in instructions provided to flight systems of the aircraft.

An aircraft store ejector systems and subsystems thereof. Embodiments can include a two-reservoir re-pressurization system wherein a remote reservoir is used to maintain desired pressure in a local ejector reservoir. The system can include a release valve having a vent valve and valve piston. The release valve can control release of pressurized gas to a pitch control valve. The pitch control valve can be configured to distribute the pressurized gas between two or more ejector piston assemblies. One or more of the ejector piston assemblies can include multiple concentric piston stages and piston chambers, the piston chambers configured to contain a volume of gas. The ejector piston assemblies can be configured to compress the volume of gas within the piston chambers as the piston stages are extended out from the aircraft. Such compression can provide a return force to the piston stages.