Abstract: An unmanned aerial vehicle (UAV) jettison apparatus. The UAV jettison apparatus may comprise a payload bay, fairing, ejector plate, and releasable latch. The payload bay may be mounted beneath an aircraft and may have an inner space and a top plate attached therewith. The fairing may substantially cover the inner space of the payload bay and may have an opening positioned directly below the top plate. The ejector plate, which may be spring-loaded, may substantially cover the opening and may be used to mount the UAV. The releasable latch, which may be disposed between the top plate and the ejector plate, may releasably lock and hold the UAV in a stowed position and, upon release, may allow the ejector plate to move into a launch position, such that the UAV is released and jettisoned from a larger aircraft.

Abstract: A connector may couple to a non-cylindrical composite tubing having at least two lateral sides disposed in parallel and an open end. The connector may comprise first and second bonding plates adhered to an inner surface of the two lateral sides via an epoxy adhesive uniformly distributed. The first and second bonding plates may each have a distal lateral face defining a plurality of first threaded holes accessible at the open end of the composite tubing. The connector may also comprise an end plate having a plurality of first and second slotted holes disposed substantially in parallel and each aligned with an associating one of the first threaded holes. The connector may also comprise end plate fasteners loosely inserted through the first and second slotted holes and engaged with the first threaded holes. The end plate may also comprise one or more attachment points.

Abstract: An unmanned aerial vehicle (UAV) jettison apparatus. The UAV jettison apparatus may comprise a payload bay, fairing, ejector plate, and releasable latch. The payload bay may be mounted beneath an aircraft and may have an inner space and a top plate attached therewith. The fairing may substantially cover the inner space of the payload bay and may have an opening positioned directly below the top plate. The ejector plate, which may be spring-loaded, may substantially cover the opening and may be used to mount the UAV. The releasable latch, which may be disposed between the top plate and the ejector plate, may releasably lock and hold the UAV in a stowed position and, upon release, may allow the ejector plate to move into a launch position, such that the UAV is released and jettisoned from a larger aircraft.

Abstract: A UAV recovery system. The UAV recovery system may comprise: a mast having a mast pulley with a swivel, a base, upper and lower booms extending somewhat horizontally from the mast, a cable and pulley arrangement, a shock absorber, and a mast cable coupled between the mast pulley and the shock absorber. The cable and pulley arrangement may comprise: upper boom pulleys coupled near an associated end of the upper boom, lower boom pulleys coupled near an associated end of the lower boom, and a cable forming a loop around the upper and lower boom pulleys. The cable and pulley arrangement may also comprise a net for capturing the UAV. The shock absorber may urge the mast to rotate into a neutral position, but permit the mast to rotate not more than a controlled-tensioned position.

Abstract: A launcher for an unmanned aircraft may comprise: a launch rail, a carriage, pair of pulley drivers, and a cable and pulley system. The pulley drivers may produce opposing pulley drive forces, which may be converted into a single launching force via the cable and pulley system for launching the carriage. The cable and pulley system may comprise: launch rail pulleys, pulley block pulleys, cam pulleys, drive cables, and one or more winches. Embodiments of the launcher may apply a constant force to the aircraft uniformly over the launch distance, such that the unmanned aircraft may be propelled within a relatively short distance by applying energy to the aircraft in the smallest period of time and without exceeding the aircraft's acceleration limits.

Abstract: A launcher for an unmanned aircraft may comprise: a launch rail, a carriage, pair of pulley drivers, and a cable and pulley system. The pulley drivers may produce opposing pulley drive forces, which may be converted into a single launching force via the cable and pulley system for launching the carriage. The cable and pulley system may comprise: launch rail pulleys, pulley block pulleys, cam pulleys, drive cables, and one or more winches. Embodiments of the launcher may apply a constant force to the aircraft uniformly over the launch distance, such that the unmanned aircraft may be propelled within a relatively short distance by applying energy to the aircraft in the smallest period of time and without exceeding the aircraft's acceleration limits.

Abstract: A connector for non-cylindrical composite tubing and methods for making the same. The method may involve assembling a connector for a non-cylindrical composite tubing by loosely fastening a pair of bonding plates to an end plate; arranging the bonding plates in an inward configuration; applying an epoxy adhesive onto the outer faces of the bonding plates, inserting the bonding plates into the open end of the composite tubing, inserting the bonding plate fasteners through the through-holes of the composite tubing and tightly fastening the bonding plate fasteners into the bonding plates until the bonding plates engage against the inner surface of the composite tubing until the epoxy adhesive is uniformly distributed. The method may also include steps of removing the bonding plate screw fasteners and adding shims between each bonding plate and the inner surface of the composite tubing in order to maintain a predetermined thickness of the epoxy adhesive.