A system is described and includes at least one track attached to an upper interior surface of a payload bay and extending along a bottom surface of a vehicle structure external to the payload bay, wherein the track comprises a horizontal flange; a rack moveably connected to the at least one track via at least one carrier assembly; and a payload actuator system for selectively extending the rack from the payload bay along the at least one track to a position from which payload carried by the rack may be safely deployed and retracting the rack into the payload bay along the at least one track.

A system is described and includes at least one track attached to an upper interior surface of a payload bay and extending along a bottom surface of a vehicle structure external to the payload bay, wherein the track comprises a horizontal flange; a rack moveably connected to the at least one track via at least one carrier assembly; and a payload actuator system for selectively extending the rack from the payload bay along the at least one track to a position from which payload carried by the rack may be safely deployed and retracting the rack into the payload bay along the at least one track.

A missile launching system for launching missiles from a mobile platform includes a rectangular primary carrier frame having a platform coupling structure for releasably fastening the first carrier frame to the mobile platform, and a launch tube. A locking device on the primary carrier frame includes a lock hook which projects from the primary carrier frame and has a receiving piece. A stop piece extends transverse to the receiving piece. A locking plate is inserted between the receiving piece and the stop piece. The launch tube has a fastening bracket with a fastening recess fitted onto the receiving piece and locked with the lock hook by inserting the locking plate between the stop piece and the receiving piece. Alternatively, two launch tube receiving devices are laterally attached to the primary carrier frame, each of which is designed as a closed frame defining a receiving opening.

Aeronautical conveying and release device comprising a frame, an actuator releasing a device, a first and second hook holding the device, first and second locking toggles having a locking and unlocking position, first and second cams in contact with the first or second toggle in a first direction, movement of the first or second cam in a second direction causing the toggle to leave the locking position and the unlocking of the hook, a third cam actuated from and returns to an idle position, a fourth cam driven by the third cam into unlocking, the third cam unlocking the first cam, a fifth cam coupled to the first cam, a safety member with lever with a first position which blocks the unlocked cams, the first cam and the second cam being blocked unlocked, blocking the locked toggles, a second position where the lever is blocked by the fourth and/or the fifth cam, and a third position where the lever frees the cams.

An UAV controller device is provided. In some embodiments, the device may include a control panel having one or more user control inputs, and a processing unit may be in communication with the control inputs. A display screen may also be in communication with the processing unit. Optionally, the display screen may be movable between an open and a closed position. A side wall may be coupled to a proximal wall and to a distal wall, the side wall, proximal wall, and distal wall forming a storage compartment. The storage compartment may have a storage cavity for removably receiving a UAV, and the UAV may be in wireless communication with the processing unit. A camera, for recording video, may be coupled to the UAV. Video recorded by the camera may be displayed on the display screen, and one or more of the control inputs may govern movement of the UAV.

A cargo transporting system for a tailsitter aircraft includes a cargo receptacle rotatably coupled to an underside of a wing and a cargo assembly selectively coupled to the cargo receptacle. By rotating the cargo receptacle, the cargo transporting system can transition between a deployed position and a retracted position. In the deployed position, the cargo receptacle is substantially perpendicular to the wing, and accommodates ground personnel charged with connecting or removing the cargo assembly from the cargo transporting system. In the retracted position, the cargo receptacle is substantially parallel to the wing, and positioned for flight operations.

A cargo transporting system for a tailsitter aircraft includes a cargo receptacle rotatably coupled to an underside of a wing and a cargo assembly selectively coupled to the cargo receptacle. By rotating the cargo receptacle, the cargo transporting system can transition between a deployed position and a retracted position. In the deployed position, the cargo receptacle is substantially perpendicular to the wing, and accommodates ground personnel charged with connecting or removing the cargo assembly from the cargo transporting system. In the retracted position, the cargo receptacle is substantially parallel to the wing, and positioned for flight operations.

The present disclosure provides an assembly including at least one adjustable coupling mechanism. In one aspect, the first coupling mechanism includes a first component having a central axis parallel to its outside surface. The first component further includes an inside surface defined by a bore formed in the first component along a central bore axis. The central bore axis is offset from the central axis. The first component can be coupled to the assembly, uncoupled, rotated about its central axis, and recoupled to change a distance between the first coupling mechanism and another part of the assembly. The first component further includes a plurality of holes formed circumferentially around the bore bottom and extending through the bore bottom and the bottom surface of the first component that can be used to removably couple the first component to the assembly.

The present disclosure provides a payload activation device. The payload activation device comprises a camera having a fixed focal length, arranged to capture an image of an object on a platform for carrying a payload having the payload activation device, wherein, when the payload is in a first position relative to the platform, the image of the object is in a first focused state and, when the payload is in a second position relative to the platform, the image of the object is in a second focused state. The payload activation device also comprises a processor configured to determine whether the image of the object is in the first focused state or the second focused state and to cause actuation of an activation mechanism within the payload when the image of object is in the second focused state to activate the payload. The present disclosure also provides a deployable payload having the payload activation device and an aircraft for carrying the deployable payload.

A munitions rack includes a munitions rack structure that houses multiple compact ejectors. The structure includes a pair of internal longitudinal ribs, inboard of a pair of external longitudinal ribs. A spine of the munitions rack structure links all the ribs, and the munitions rack structure may be formed out of a single piece of material. The ribs define a pair of side recesses on the port and starboard sides of the bomb, which each may be further subdivided into a forward pocket and an aft pocket. Removable ejectors are located in the pockets. The ejectors may receive pressurized gas from pressurized gas source(s) located outside of the ejectors. The ejectors may each have multiple forward pistons and multiple aft pistons. The ejectors may include pitch control valving to control the relative amounts of pressurized gas sent to the forward piston(s) and aft piston(s).