A stabilizing system for a cable has a cable deployed and suspended from a helicopter, a cargo support attached at a deployed end of the cable, an end effector attached to the cable, the end effector comprising thrusters directed in a plurality of directions orthogonal to a vertical axis of the cable, first control circuitry in the helicopter, and second control circuitry in the end effector. Thrust of individual thrusters is controlled through the first and second control circuitry maintaining the axis of the cable vertical, damping swinging of the cable.

The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect/disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.

The present invention is an Electric servo system which controls and automates gate openings based on GPS speed and position data that results in precise and reliable modern variable and constant rate application. The Electric servo system also allows for Mechanical gate linkages to remain intact, resulting in few changes to the aircraft and redundancy of emergency components. A Mechanical input connect/disconnect is used to effortlessly transfer between the automated Electric servo system and the Mechanical gate system.

A payload mechanism for a vehicle is provided. The payload mechanism comprises: a door (2) operable to be in a closed configuration or an open configuration within a recess of the vehicle, the recess having an aperture (10); a first bearing unit comprising a first bearing (3a) and a second bearing (4a), the first bearing unit being coupled to one end of the door such that the door can rotate about the axis of rotation (y) of the first bearing and wherein the first bearing unit can rotate about the axis of rotation (x) of the second bearing, wherein the axis of rotation of the first bearing is offset from the axis of rotation of the second bearing; and a drive unit arranged to selectively drive either: the first bearing and the second bearing simultaneously at opposite and equal angular rates of motion to rotate the door in a first direction about the axis of rotation of the first bearing and to rotate the first bearing unit in a second direction about the axis of rotation of the second bearing to move the door closer to or away from the aperture, or the first bearing but not the second bearing to rotate the door about the axis of rotation of the first bearing. Methods of operating said payload mechanism are also provided, along with a vehicle having the payload mechanism.

A payload mechanism for a vehicle is provided. The payload mechanism comprises: a door (2) operable to be in a closed configuration or an open configuration within a recess of the vehicle, the recess having an aperture (10); a first bearing unit comprising a first bearing (3a) and a second bearing (4a), the first bearing unit being coupled to one end of the door such that the door can rotate about the axis of rotation (y) of the first bearing and wherein the first bearing unit can rotate about the axis of rotation (x) of the second bearing, wherein the axis of rotation of the first bearing is offset from the axis of rotation of the second bearing; and a drive unit arranged to selectively drive either: the first bearing and the second bearing simultaneously at opposite and equal angular rates of motion to rotate the door in a first direction about the axis of rotation of the first bearing and to rotate the first bearing unit in a second direction about the axis of rotation of the second bearing to move the door closer to or away from the aperture, or the first bearing but not the second bearing to rotate the door about the axis of rotation of the first bearing. Methods of operating said payload mechanism are also provided, along with a vehicle having the payload mechanism.

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.

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.

An aircraft pylon is provided, configured for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom. The pylon comprises an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing, and a carrying arrangement configured for carrying the payload and being pivotally articulated to the attachment mechanism. The pylon is configured to selectively pivot the carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward the fuselage.

An aircraft pylon is provided, configured for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom. The pylon comprises an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing, and a carrying arrangement configured for carrying the payload and being pivotally articulated to the attachment mechanism. The pylon is configured to selectively pivot the carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward the fuselage.

An aircraft comprises a weapons bay, the weapons bay comprising a cavity having an opening through which stores may be deployed, and a door assembly for exposing/closing the opening of the cavity. A first store is held in the cavity via a launcher and a first structure is disposed inside the cavity, for controlling the aero-acoustic environment. The first structure for controlling the aero-acoustic environment is removeably mounted in the weapons bay, such that if the first store is exchanged for a second, different, store, the structure for controlling the aero-acoustic environment may be unmounted from the weapons bay and removed, to be exchanged for a second, different, structure for controlling the aero-acoustic environment.