An unmanned aerial vehicle (UAV) airbag may protect protection for a UAV or other objects when making contact with one another. The UAV airbag may at least partially surround the UAV while allowing the UAV to remain at least partially operable. In some embodiments, the UAV airbag may be inflated just prior to making contact with another object. After inflation, the UAV airbag may be at least partially sealed to reduce or inhibit deflation of the UAV airbag, but possibly not to completely prevent airflow from the UAV airbag upon contact with another object. The UAV airbag may exhaust some air upon impact, thereby reducing a deceleration of a UAV contained inside of the UAV airbag.

An unmanned aerial vehicle (UAV) airbag may protect protection for a UAV or other objects when making contact with one another. The UAV airbag may at least partially surround the UAV while allowing the UAV to remain at least partially operable. In some embodiments, the UAV airbag may be inflated just prior to making contact with another object. After inflation, the UAV airbag may be at least partially sealed to reduce or inhibit deflation of the UAV airbag, but possibly not to completely prevent airflow from the UAV airbag upon contact with another object. The UAV airbag may exhaust some air upon impact, thereby reducing a deceleration of a UAV contained inside of the UAV airbag.

An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.

An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.

An unmanned aerial vehicle includes a fuselage, a power device connected to the fuselage, and a control device disposed at the fuselage and electrically connected with the power device. The control device is configured to control the power device to switch an operating mode of the power device to cause the unmanned aerial vehicle to fly in air or navigate on a water surface.

An unmanned aerial vehicle includes a fuselage, a power device connected to the fuselage, and a control device disposed at the fuselage and electrically connected with the power device. The control device is configured to control the power device to switch an operating mode of the power device to cause the unmanned aerial vehicle to fly in air or navigate on a water surface.

The present invention relates to a control method for inflating at least one float of a buoyancy system. During a mode (MOD1) of automatic inflation in flight, calculation means determine whether a predetermined ditching condition is true during a step (STP1) of predicting a forthcoming impact. During a step (STP2) of characterizing said impact, at least one predicted component of a ditching speed is determined. During an automatic inflation step (STP3), each float is automatically inflated in flight when at least said ditching condition is true and when each determined predicted component is less than a corresponding speed threshold.

The present invention relates to a control method for inflating at least one float of a buoyancy system. During a mode (MOD1) of automatic inflation in flight, calculation means determine whether a predetermined ditching condition is true during a step (STP1) of predicting a forthcoming impact. During a step (STP2) of characterizing said impact, at least one predicted component of a ditching speed is determined. During an automatic inflation step (STP3), each float is automatically inflated in flight when at least said ditching condition is true and when each determined predicted component is less than a corresponding speed threshold.

A de-linking assembly includes an actuator defining a chamber and an inlet, a piston slideably disposed within the chamber, link coupled to the actuator, and a ram disposed between the piston and the link. The link defines a stress concentration features and a load point on a side of the link on a side of the stress concentration feature opposite the actuator. The ram is seated to the piston and against the load point such that air introduced into the chamber through the inlet applies force to the piston and ram sufficient to sever the link by inducing stress in the stress concentration feature.

A de-linking assembly includes an actuator defining a chamber and an inlet, a piston slideably disposed within the chamber, link coupled to the actuator, and a ram disposed between the piston and the link. The link defines a stress concentration features and a load point on a side of the link on a side of the stress concentration feature opposite the actuator. The ram is seated to the piston and against the load point such that air introduced into the chamber through the inlet applies force to the piston and ram sufficient to sever the link by inducing stress in the stress concentration feature.