An aft pivot assembly can include a mount device securable to an aft portion of a payload of an aircraft for facilitating release of the payload. The aft pivot assembly can include a shaft operable with the mount device and a release component, the shaft being rotatable about multiple shaft axes relative to the mount device so as to either minimize or eliminate carriage loads about the aft portion, while reacting jettison loads during a jettison event or phase. The rotation of the shaft about its shaft axes can further be limited via a limit device. As the payload transitions from a carriage phase to a jettison phase, the shaft moves in multiple degrees of freedom and in multiple axes relative to the mount device.

A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft.

A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft.

A diffuser for distributing insects such as mosquitoes from an aircraft, comprises a distribution tube connected to an insect source at a first end and open to the outside at a second end in a direction away from that of travel of the aircraft, for distribution of the insects; and a profile surrounding the second end, the profile being shaped to define a steadily changing airspeed. The pipe may be aligned with airflow at the point of exit of the pipe and protection may be provided around or just upstream of the exit to provide a point of minimal air velocity at the exit, the exit being the point of release of the insects.

A diffuser for distributing insects such as mosquitoes from an aircraft, comprises a distribution tube connected to an insect source at a first end and open to the outside at a second end in a direction away from that of travel of the aircraft, for distribution of the insects; and a profile surrounding the second end, the profile being shaped to define a steadily changing airspeed. The pipe may be aligned with airflow at the point of exit of the pipe and protection may be provided around or just upstream of the exit to provide a point of minimal air velocity at the exit, the exit being the point of release of the insects.

A hovering aerial vehicle is provided, comprising an airborne unit and an auxiliary unit. The airborne unit is configured to carry the auxiliary unit during flight and comprises a flight system configured to facilitate providing aerodynamic lift to facilitate hovering of the vehicle. The auxiliary unit comprises an electrical power source in electrical communication with the flight system to provide electrical power for its operation. The hovering aerial vehicle further comprises a decoupling system configured to facilitate selectively switching the vehicle between a detached configuration thereof wherein the airborne and auxiliary units are remote from each other, and an attached configuration thereof wherein the airborne and auxiliary units are secured to one another, and to maintain the electrical communication when the vehicle is in its detached configuration.

A hovering aerial vehicle is provided, comprising an airborne unit and an auxiliary unit. The airborne unit is configured to carry the auxiliary unit during flight and comprises a flight system configured to facilitate providing aerodynamic lift to facilitate hovering of the vehicle. The auxiliary unit comprises an electrical power source in electrical communication with the flight system to provide electrical power for its operation. The hovering aerial vehicle further comprises a decoupling system configured to facilitate selectively switching the vehicle between a detached configuration thereof wherein the airborne and auxiliary units are remote from each other, and an attached configuration thereof wherein the airborne and auxiliary units are secured to one another, and to maintain the electrical communication when the vehicle is in its detached configuration.

An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, a line having one end coupled to the chassis and an opposite free end, wherein the free end is positioned below the chassis, and a severing mechanism operable to sever the line under control of the control system.

A device includes hauling means for the movement of a payload while suspended from one or more lines. The or each line is suspended or suspendable from one end, the hauling means being provided at or in the region of the other end of the line/s and at which end the payload is situated in use.

A device includes hauling means for the movement of a payload while suspended from one or more lines. The or each line is suspended or suspendable from one end, the hauling means being provided at or in the region of the other end of the line/s and at which end the payload is situated in use.