Methods and apparatus to deploy unmanned aerial vehicles (UAVs) by kites are disclosed. An example apparatus to deploy a UAV includes a tether line to support the UAV, a tensioner operatively coupled to the tether line, and a kite operatively coupled to the tether line to support the tether line for deployment of the UAV.

Methods and apparatus to deploy unmanned aerial vehicles (UAVs) by kites are disclosed. An example apparatus to deploy a UAV includes a tether line to support the UAV, a tensioner operatively coupled to the tether line, and a kite operatively coupled to the tether line to support the tether line for deployment of the UAV.

Examples include an apparatus for restraining an aircraft during engine acceleration, the apparatus including: a collet shaft that is configured to attach to the aircraft, a rod that is configured to attach to a runway, and a release mechanism that is configured to restrain the collet shaft to the release mechanism and configured to release the collet shaft in response to the release mechanism receiving an electric current.

A device for catching and launching a guided UAV, the device comprises a supporting post, a horizontal shaft mounted on the post, and a lever is mounted on the horizontal shaft and can make a full revolution around a horizontal axis within a vertical plane, the lever is equipped with an engagement/disengagement device a means for interaction with the UAV catching device and an optical member, preferably arranged on the lever, for determining a location of the lever interaction means by an optical guidance system of the UAV. The lever comprises two coaxial portions, one is the engagement/disengagement device, and the second is a bar, wherein one end of the bar is coupled to the horizontal shaft, while another end thereof is connected to the engagement/disengagement device. The bar and the engagement/disengagement device are connected by a hinge that enables their fixation in a coaxial state and allows offset the axis of the engagement/disengagement device relative to the axis of the bar within a rotation plane of the lever. The horizontal shaft is equipped with a means for accumulating and/or dissipating the kinetic energy of the UAV, the lever is fixed on the shaft and can provide an elastic offset of the interaction means of the engagement/disengagement device within a plane perpendicular to the rotation plane of the lever, the interaction means configured to provide mutual locking/unlocking with the UAV catching device.

A device for catching and launching a guided UAV, the device comprises a supporting post, a horizontal shaft mounted on the post, and a lever is mounted on the horizontal shaft and can make a full revolution around a horizontal axis within a vertical plane, the lever is equipped with an engagement/disengagement device a means for interaction with the UAV catching device and an optical member, preferably arranged on the lever, for determining a location of the lever interaction means by an optical guidance system of the UAV. The lever comprises two coaxial portions, one is the engagement/disengagement device, and the second is a bar, wherein one end of the bar is coupled to the horizontal shaft, while another end thereof is connected to the engagement/disengagement device. The bar and the engagement/disengagement device are connected by a hinge that enables their fixation in a coaxial state and allows offset the axis of the engagement/disengagement device relative to the axis of the bar within a rotation plane of the lever. The horizontal shaft is equipped with a means for accumulating and/or dissipating the kinetic energy of the UAV, the lever is fixed on the shaft and can provide an elastic offset of the interaction means of the engagement/disengagement device within a plane perpendicular to the rotation plane of the lever, the interaction means configured to provide mutual locking/unlocking with the UAV catching device.

The disclosed invention comprises a spring-based launch device, and method of using the device within a system for launching an unmanned aerial vehicle (UAV) using constant torque springs to pull a carriage to accelerate a UAV to the necessary launch speed. A torque frame holds multiple constant torque springs attached to an adjustable power system, enabling a selectable number of springs to connect to a spool. The adjustable power system enables the launch speed of the UAV to vary based on its launch requirements. The spool is used to move a carriage at constant acceleration. The carriage holds the UAV and is pulled along rails until it hits a stop spring system, which stops the carriage, causing the aircraft to be launched off the carriage. Re-tensioning of the system occurs through a retraction mechanism which pulls the carriage back to a spring box, where it is positioned in tensioned configuration.

The disclosed invention comprises a spring-based launch device, and method of using the device within a system for launching an unmanned aerial vehicle (UAV) using constant torque springs to pull a carriage to accelerate a UAV to the necessary launch speed. A torque frame holds multiple constant torque springs attached to an adjustable power system, enabling a selectable number of springs to connect to a spool. The adjustable power system enables the launch speed of the UAV to vary based on its launch requirements. The spool is used to move a carriage at constant acceleration. The carriage holds the UAV and is pulled along rails until it hits a stop spring system, which stops the carriage, causing the aircraft to be launched off the carriage. Re-tensioning of the system occurs through a retraction mechanism which pulls the carriage back to a spring box, where it is positioned in tensioned configuration.

Adapter assemblies for aircraft and launchers for deploying aircraft are described herein. An example adapter assembly for an unmanned aerial vehicle (UAV) includes a first adapter to be removeably coupled to a first side of a fuselage of the UAV. The first adapter includes first and second posts to interface with a carriage of a launcher. The adapter assembly also includes second adapter to be removeably coupled to a second side of the fuselage of the UAV. The second adapter includes third and fourth posts to interface with the carriage of the launcher.

Adapter assemblies for aircraft and launchers for deploying aircraft are described herein. An example adapter assembly for an unmanned aerial vehicle (UAV) includes a first adapter to be removeably coupled to a first side of a fuselage of the UAV. The first adapter includes first and second posts to interface with a carriage of a launcher. The adapter assembly also includes second adapter to be removeably coupled to a second side of the fuselage of the UAV. The second adapter includes third and fourth posts to interface with the carriage of the launcher.

The invention relates to an emergency support robot for polar UAVs, belonging to the technical field of emergency support robots for polar UAVs. The technical problem to be solved is to improve the structure of the existing emergency support robots for polar UAVs. The technical scheme adopted is as follows: the robot is of a car body structure; a support table is arranged on the upper side of the chassis of the car body; a traveling mechanism is arranged on both sides of the chassis of the car body; the two sides of the support table are hinged with a pair of casings through hinged buckles and push rods; the casings are also provided with a wind power plant; the support table is provided with a launching guide rail.