Abstract: The present disclosure relates, in one aspect of the disclosure, to an inflatable water sport safety garment for providing buoyancy to a wearer comprising a harness structure, at least one handle, and at least one inflatable flotation device. The harness structure may include at least two shoulder portions, at least one torso portion encircling the torso of the wearer and attached to the shoulder portions, and at least one central portion connected to the shoulder portions.

Abstract: This disclosure relates to modular locking connectors that enable discrete and fully separate components to be easily, quickly, and interchangeably connected together to result in a fully functional buoyancy compensator device. These separate components may include shoulders, waistbands, back panels, bladders or other buoyancy chambers, pockets including those for ballasting weights, and accessories such as knives, lights, signaling devices and the like.

Abstract: This disclosure relates to a modular cord connector that enables two cords to connect together and release. An embodiment of this cord connector disclosure is designed for use on cords integral to a gas release on buoyancy compensator devices. The preferred embodiment of this cord connector, shown for use on a buoyancy compensator device, includes modular male and female portions which include a T-shaped post on the male portion and a pathway with detents configured to retain the male portion when engaged with the female portion.

Abstract: The Dual Spacecraft Deployment System (DSDS) is a concept developed for deploying Dual Satellites into independent orbits from a single launch vehicle. The Deployment Concept, Deployment System and Spacecraft Design with Representative Instruments are presented herein. The design employs an innovative half-hex design for the spacecraft buses which allows the spacecraft to be accommodated in a parallel mounted configuration on the launch vehicle. The Spacecraft are arranged on the launch vehicle with a central deployment structure with a deployment mechanism which allows independent lateral deployment of two spacecraft. The Spacecraft Design can have a large volume, e.g., sized to accommodate Spacecraft Sub-systems and Instrument Systems. This concept allows the launch vehicle to accommodate two large Spacecraft deployed to different orbits with a single launch doubling the efficiency of the launch vehicle.

Abstract: The Dual Spacecraft Deployment System (DSDS) is a concept developed for deploying Dual Satellites into independent orbits from a single launch vehicle. The Deployment Concept, Deployment System and Spacecraft Design with Representative Instruments are presented herein. The design employs an innovative half-hex design for the spacecraft buses which allows the spacecraft to be accommodated in a parallel mounted configuration on the launch vehicle. The Spacecraft are arranged on the launch vehicle with a central deployment structure with a deployment mechanism which allows independent lateral deployment of two spacecraft. The Spacecraft Design can have a large volume, e.g., sized to accommodate Spacecraft Sub-systems and Instrument Systems. This concept allows the launch vehicle to accommodate two large Spacecraft deployed to different orbits with a single launch doubling the efficiency of the launch vehicle.