Abstract: A watercraft arresting system and method including an entanglement subsystem including at least two arms in a V-configuration. A deployment subsystem deploys the entanglement subsystem so the arms are spread apart in the water in the path of the watercraft to arrest it.

Abstract: A launch vehicle is deployed from an aircraft using gravity extraction of the launch vehicle with the aid of a small parachute which assists the extraction and damps the yaw and pitch of the launch vehicle. The launch vehicle is supported on two rows of tires which are rotatably mounted to the aircraft. Gravity and the drag force of the parachute causes the launch vehicle to roll on the tires along the load deck and out of the aircraft. Because the extraction forces are dominated by gravity, the launch vehicle acquires a rotation in the pitch axis as the launch vehicle leaves the aircraft. After the launch vehicle clears the aircraft, the launch vehicle rotates in the pitch plane, and is damped in the pitch plane by the parachute to a pitch attitude which is 70-80° and the vehicle engine is ignited, detaching the drag parachute.

Abstract: System for launching a missile from a launch region within the atmosphere of a planet, the missile being located within a flying vehicle before launching the missile, the system including a missile support coupled with the missile, and a foldable control-surface mechanism coupled with the missile support, the foldable control-surface mechanism being in a folded position before ejecting the missile support and the missile from the flying vehicle, the foldable control-surface mechanism moving from a folded position to an operational position after ejecting the missile support and the missile from the flying vehicle, wherein the foldable control-surface mechanism maneuvers the missile and the missile support to a predetermined orientation suitable for launching the missile, wherein the missile support is decoupled from the missile when the missile and the missile support are at the predetermined orientation, and wherein the missile is launched after reaching the predetermined orientation.

Abstract: A parachute steering system allows load drops to be guided until being landed on a defined target. The steering system includes an upper platform and a lower platform, joined in articulated fashion. The upper platform incorporates a device for fastening the parachute thereto, while the lower platform has a device for anchoring the load. The two platforms are connected to each other through the use of an actuator system which allows the parallelism or inclination between them to be altered, also displacing the center of gravity of the parachute-load combination, and therefore allowing the direction of the displacement of the load to be altered, as well as the speed of the same.

Abstract: The capture of payloads carried by a descending parafoil is facilitated by the use of a trailing line from the parafoil that is snagged by a hook on a recovery line from a helicopter. The trailing line can be more easily snagged by the use of a drogue at its end to facilitate the extension of the trailing line. The trailing line can take the form of a loop extending from the parafoil canopy. The trailing line can actuate a slider to collapse the parafoil's suspension lines and canopy for easier handling by the capturing helicopter. Cutters can be installed on the lines holding the load to cut those lines when the recovery line pulls to hoist the load, thus separating the parafoil from the load as the load is lifted by the helicopter.

Abstract: Cargo drop system and process (1) with a cargo (2), a cargo parachute (6) and an auxiliary parachute (7), which, by means of at least one ripcord (12; 12a, 12b), connects the auxiliary parachute (7) to the cargo glide chute (6), whereby a stabilization harness (14; 14a, 14b) is connected to the ripcord (12; 12a, 12b) on one side and to the cargo (2) on the other side, in order to attain a stable position of the cargo (2) relative to the ripcord (12; 12a, 12b), which is pulled by aerodynamic forces after the drop. A first trigger device (20) is provided for the release of the stabilization harness (14; 14a, 14b), and a second trigger device (40) is provided for the release of the cargo parachute (6) from the cargo (2), so that the cargo (2) hangs from a hanging device (60) on the cargo parachute (6).

Abstract: The invention relates to the aerospace engineering and can be used for jettisoning boost rockets from an aircraft. The inventive device comprises a landing container (3) with an open end (4) provided with a high-pressure source (5). The freight to be jettisoned (2) is arranged in two sections inside the container (3) on mounting elements (10), one of which is embodied in the form of a calibrated support (9). The values of maximum efforts and acceptable lateral movements (13) of the supports (9) are chosen in such a way that a minimum positive allowance (12) between the container (3) and the freight (2) is provided. The supports (9) are provided with dampers. The aim of the invention is to reduce a transverse load affecting the freight to be jettisoned landing.

Abstract: The present invention relates to self contained, modular integrated deployment and retrieval system for use with an aircraft such as a helicopter. The deployment and retrieval system comprises a support frame, a winch connected to the support frame, a tow cable wound around the winch, which tow cable is connected to the external load, and a support structure connected to the support frame. The support structure is axially movable relative to the support frame for moving the external load so as to control the center of gravity of the aircraft and so as to deploy and retrieve the external load.

Abstract: A cruise missile, such as the Tomahawk cruise missile, is adapted to deploy decoys in an area as the missile progresses along its preprogrammed course. Each decoy is shaped to be compatible with and ejected from the Tomahawk and has a preprogrammed control unit operating a transmitter connected to an extendible antenna. False beacon signals and/or false message signals are transmitted from each of the decoys to deceive and confuse defensive forces, such as enemy searchers looking for a downed airman.

Abstract: The door (10) of an aircraft incorporates a housing (14) able to receive a slide, in a folded up state. The housing (14) is delimited between a cover (16) facing outwards from the door (10) and intermediate bulkhead (18). The cover (16) is jettisonable outside the aircraft or able to swivel by its lower edge on a threshold of the door, by the use of setting de-setting means. In one embodiment, the housing occupies the greater part of the door surface.

Abstract: A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Abstract: A device and method of use for opening a container during descent so that objects within the container may be dispersed over a controlled ground area. The device includes a housing with a parachute canopy contained within. A sling is attached to the canopy within the housing and extends external to the housing. A cap is selectively engageable with the housing to close the housing. A spring within the housing exerts outward force on the cap. An actuation device is mounted to the cap to selectively disengage the cap from the housing. When the cap is disengaged from the housing the cap is ejected by the force of the spring. A lanyard connecting the cap to the canopy draws the canopy out of the housing for deployment. Deployment of the canopy transfers tension force through the slings to the container. The tension force imposed on the container by the slings opens the container, releasing objects held therein. The objects are released at a predetermined height.

Abstract: A system and method for evaluating flexible structures such as textiles under load generally. A specific embodiment is shown for parachutes. A plurality of first sensors and second sensors are attached to the parachute on its canopy and suspension lines. Preferred first sensors are fiber Bragg gratings (FBG) type sensors, and preferred second sensors are modal power distribution (MPD) type sensors. A fiber optic network interconnects the pluralities of first and second sensors to provide sensor outputs which are converted to electronic signals, modulated and transmitted to a receiving station for receiving and processing the transmitted modulated electronic signals. The preferred fiber optic network includes a plurality of light emitting diodes positioned at one end of each fibers and a photodiode array positioned to receive light from each of the fibers.

Abstract: In order to accurately parachute cargo, a towplate assembly is mounted in the rear bay of a cargo aircraft, the drogue chute is attached to a towlink in the towplate assembly. The main parachutes are also attached to the towlink and the cargo. The drogue chute pulls the main parachutes from the aircraft which causes them to deploy and then pull the cargo from the aircraft. The removal of the towlink from the towplate is controlled by a positive lock device. A forward cam follower, in the locked mode, rests against the forward cam of the towlink. An electrically controlled actuator acting through a forward interlock pushing on an aft interlock being attached to the forward cam follower is biased against a stop by a spring. Undesired movement of the towlink will only force the aft interlock in the direction of further bias. Upon command, the actuator retracts and pulls the forward interlock to release the aft interlock from the stop position. When this occurs the towlink is free to leave the towplate assembly.