Abstract: A deployable/retractable expandable bag system for enclosure and release of space objects, constructed from materials exhibiting abrasion resistance and ballistic protection. Pressurized expandable textile trusses support textile membrane materials exhibiting radial contracting or collapsing contracting directional qualities. Stabilizing wires define bag length and minimize rotational forces of the captured object. Upon entry of the space object into the bag system, pressurized gas in trusses is released. The expandable trusses and membranes retract over and onto the space object. The expandable bag may be re-pressurized, and the bag re-opened, for removal and redirection of the space object; upon re-stowing, the system is ready for another capture mission.

Abstract: Irreversible first cycle capacity loss in lithium secondary cells having a cell electrode based on a powdered material and a binder may be significantly decreased or eliminated by using an aliphatic or cycloaliphatic polyimide binder. Compared to conventional polyimide binders prepared by reacting an aromatic dianhydride and a diamine, the disclosed polyimide binders have decreased aromatic carbonyl content, may be less likely to undergo electrochemical reduction, and may be less likely to consume electrons that might otherwise help lithiate the electrode.

Abstract: The invention discloses a deployable, inflatable conformable fuel tank assembly constructed to be installed at a certain location on an aircraft and to be retained at that certain location throughout the entire flight operation of the aircraft. The fuel tank assembly is constructed to be movable between a first, deployed aerodynamic configuration in which the assembly can hold a supply of liquid fuel, and a second, stowed aerodynamic configuration in which the exterior surface of the assembly conforms to a surface of the aircraft underlying the assembly.

Abstract: The invention discloses a method for fabricating a deployable, inflatable aerodynamic control structure for aerospace vehicles which has a desired noncircular or noncylindrical cross-section. In a preferred embodiment, the control structure is configured as an inflatable airfoil and includes a flexible skin and a plurality of internally disposed airfoil-shaped bulkheads or integral rib members that are arranged, spaced apart, in cross-wise fashion along the axial length of the airfoil shaped control structure. The flexible skin is fabricated as a lay up, in ordered sequence, of plural layers of elastomeric rubber material and plural ply layers of resin-impregnated yarns or fabric. The result is a fiber-reinforced pressure membrane that is flexible and compactly foldable.

Abstract: The invention discloses a deployable, inflatable aerodynamic control structure for aerospace vehicles which has a desired noncircular or noncylindrical cross-section and fabrication methods therefor. In a preferred embodiment, the control structure is configured as an inflatable airfoil and includes a flexible skin and a plurality of internally disposed airfoil-shaped bulkheads or integral rib members that are arranged, spaced apart, in cross-wise fashion along the axial length of the airfoil shaped control structure. The flexible skin is fabricated as a lay up, in ordered sequence, of plural layers of elastomeric rubber material and plural ply layers of resin-impregnated yarns or fabric. The result is a fiber-reinforced pressure membrane that is flexible and compactly foldable.