A system delivering fire retardant materials in fighting a surface fire is provided, having an aircraft carrying the fire-retardant material, a hose deployable from the aircraft, the delivery hose connected to the reservoir and having a controllable nozzle at a deployed end with a remotely operable valve, an end effector connected by a multi-axis gimbal at the deployed end of the delivery hose the end effector having fixed wings with ailerons and elevators, and a rudder, the ailerons, elevators and rudder moved by electrical actuators, and control apparatus and circuitry in the aircraft and the end effector enabling an operator in manipulating the ailerons, elevators and the rudder. An operative in the aircraft controls the end effector via the control apparatus to fly at a lower altitude and in a different path than the aircraft, and opens the remotely operable valve to deliver the fire-retardant material from the delivery hose.

A system delivering fire retardant materials in fighting a surface fire is provided, having an aircraft carrying the fire-retardant material, a hose deployable from the aircraft, the delivery hose connected to the reservoir and having a controllable nozzle at a deployed end with a remotely operable valve, an end effector connected by a multi-axis gimbal at the deployed end of the delivery hose the end effector having fixed wings with ailerons and elevators, and a rudder, the ailerons, elevators and rudder moved by electrical actuators, and control apparatus and circuitry in the aircraft and the end effector enabling an operator in manipulating the ailerons, elevators and the rudder. An operative in the aircraft controls the end effector via the control apparatus to fly at a lower altitude and in a different path than the aircraft, and opens the remotely operable valve to deliver the fire-retardant material from the delivery hose.

A refueling system has a first vehicle having a fuel tank connected to a deployable fuel hose with a nozzle on the deployable end, a second vehicle carrying a supply of fuel, having a refueling panel with a refueling port adapted to connect to the nozzle on the deployed end of the fuel hose, an end effector joined to the fuel hose proximate the nozzle, the end effector having a plurality of thrusters providing thrust in a plurality of directions; and control circuitry in the first vehicle and in the end effector enabling an operative to vary direction and thrust of the thrusters. The operative controls the thrusters through the control circuitry to direct the nozzle toward and to connect the nozzle to the refueling port on the refueling panel of the second vehicle.

A refueling system has a first vehicle having a fuel tank connected to a deployable fuel hose with a nozzle on the deployable end, a second vehicle carrying a supply of fuel, having a refueling panel with a refueling port adapted to connect to the nozzle on the deployed end of the fuel hose, an end effector joined to the fuel hose proximate the nozzle, the end effector having a plurality of thrusters providing thrust in a plurality of directions; and control circuitry in the first vehicle and in the end effector enabling an operative to vary direction and thrust of the thrusters. The operative controls the thrusters through the control circuitry to direct the nozzle toward and to connect the nozzle to the refueling port on the refueling panel of the second vehicle.

When the tension across the cord's 24 length reaches a predetermined threshold, an activation mechanism within the payload 16 and coupled to one of the cord's 24 ends is actuated in order to activate the payload 16. Activating the payload 16 may include deactivating a SAFU, activating a motor 32 disposed within the housing, or causing flight controls to extend from a housed position. Here, “within the payload 16” may mean part of the activation mechanism is disposed on the outer surface or housing of the payload 16.

When the tension across the cord's 24 length reaches a predetermined threshold, an activation mechanism within the payload 16 and coupled to one of the cord's 24 ends is actuated in order to activate the payload 16. Activating the payload 16 may include deactivating a SAFU, activating a motor 32 disposed within the housing, or causing flight controls to extend from a housed position. Here, “within the payload 16” may mean part of the activation mechanism is disposed on the outer surface or housing of the payload 16.

A convertiplane is described that comprises: a fuselage, having a first longitudinal axis and, in turn, comprising a nose and a tail portion; a pair of wings arranged on respective opposite sides of the fuselage, carrying respective rotors and generating a lift value; and a pair of engines operatively connected to respective rotors; each rotor comprising a mast rotatable about a second axis between a helicopter configuration and an aeroplane configuration; each rotor is interposed between the fuselage and the relative rotor along the direction of extension of the relative wing.

An aft pivot assembly includes a height adjustment mechanism integrated into a device for mounting a payload, to enable release of the payload. The aft pivot assembly releasably secures an aft portion of the payload, such a pod, store, ordinance, or fuel tank. The aft pivot assembly includes 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 restrain and release mechanism for an externally airborne load, includes at least one stiff support for suspending the load and an elastically deformable adaptive member designed to maintain the load at pressure contact against the support. The adaptive member is a three-dimensional monolithic metallic body obtained using an additive manufacturing method and having a flexural orthotropic behaviour.

A restrain and release mechanism for an externally airborne load, includes at least one stiff support for suspending the load and an elastically deformable adaptive member designed to maintain the load at pressure contact against the support. The adaptive member is a three-dimensional monolithic metallic body obtained using an additive manufacturing method and having a flexural orthotropic behaviour.