Abstract: An apparatus, a vehicle and a method for securing intermodal cargo containers is provided. Couplers include pins and bottom supports to engage apertures and bottom surfaces of corner fittings for intermodal cargo containers. The couplers may also include sidewall supports to engage forward facing side surfaces of the corner fittings. The pins, bottom supports, and sidewall supports hold an intermodal cargo container in place through a relatively large range of acceleration forces without damaging the corner fittings of the intermodal cargo containers. The couplers are selectively movable from a retracted position to an extended position to engage the corner fittings of the intermodal cargo containers.

Abstract: An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: An apparatus, a vehicle and a method for securing intermodal cargo containers is provided. Couplers include pins and bottom supports to engage apertures and bottom surfaces of corner fittings for intermodal cargo containers. The couplers may also include sidewall supports to engage forward facing side surfaces of the corner fittings. The pins, bottom supports, and sidewall supports hold an intermodal cargo container in place through a relatively large range of acceleration forces without damaging the corner fittings of the intermodal cargo containers. The couplers are selectively movable from a retracted position to an extended position to engage the corner fittings of the intermodal cargo containers.

Abstract: An apparatus, a vehicle and a method for securing intermodal cargo containers is provided. Couplers include pins and bottom supports to engage apertures and bottom surfaces of corner fittings for intermodal cargo containers. The couplers may also include sidewall supports to engage forward facing side surfaces of the corner fittings. The pins, bottom supports, and sidewall supports hold an intermodal cargo container in place through a relatively large range of acceleration forces without damaging the corner fittings of the intermodal cargo containers. The couplers are selectively movable from a retracted position to an extended position to engage the corner fittings of the intermodal cargo containers.

Abstract: An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: An aircraft emergency landing stability system includes an aircraft a fuselage and landing gear, and a landing stability apparatus coupled to the fuselage, wherein the landing stability structure mitigates a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: An apparatus, a vehicle and a method for securing intermodal cargo containers is provided. Couplers include pins and bottom supports to engage apertures and bottom surfaces of corner fittings for intermodal cargo containers. The couplers may also include sidewall supports to engage forward facing side surfaces of the corner fittings. The pins, bottom supports, and sidewall supports hold an intermodal cargo container in place through a relatively large range of acceleration forces without damaging the corner fittings of the intermodal cargo containers. The couplers are selectively movable from a retracted position to an extended position to engage the corner fittings of the intermodal cargo containers.

Abstract: An aircraft emergency landing stability system includes an aircraft a fuselage and landing gear, and a landing stability apparatus coupled to the fuselage, wherein the landing stability structure mitigates a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

Abstract: A brace (200) for geometrically interlocking stringer pairs A of first stringers (106), coupled to a first panel (102), and stringer pairs B of second stringers (108), coupled to a second panel (104), of a structure (100). The brace (200) comprises a chassis (202) comprising first interlocks (204) and second interlocks (206) opposite the first interlocks (204). The first interlocks (204) geometrically engage with one of the stringer pairs A of the first stringers (106) and the second interlocks (206) geometrically engage with one of the stringer pairs B of the second stringers (108) to constrain the brace (200) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).

Abstract: A brace (200) for geometrically interlocking stringer pairs A of first stringers (106), coupled to a first panel (102), and stringer pairs B of second stringers (108), coupled to a second panel (104), of a structure (100). The brace (200) comprises a chassis (202) comprising first interlocks (204) and second interlocks (206) opposite the first interlocks (204). The first interlocks (204) geometrically engage with one of the stringer pairs A of the first stringers (106) and the second interlocks (206) geometrically engage with one of the stringer pairs B of the second stringers (108) to constrain the brace (200) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).

Abstract: A structure (100) comprises a first panel (102); first stringers (106), coupled to the first panel (102) and comprising stringer pairs A; a second panel (104) opposite the first panel (102); and second stringers (108), coupled to the second panel (104) and opposite the first stringers (106). The second stringers (108) comprise stringer pairs B. The structure (100) also comprises braces (200). Each of the braces (200) is geometrically interlocked with one of the stringer pairs A of the first stringers (106) and one of the stringer pairs B of the second stringers (108) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).

Abstract: A structure (100) comprises a first panel (102); first stringers (106), coupled to the first panel (102) and comprising stringer pairs A; a second panel (104) opposite the first panel (102); and second stringers (108), coupled to the second panel (104) and opposite the first stringers (106). The second stringers (108) comprise stringer pairs B. The structure (100) also comprises braces (200). Each of the braces (200) is geometrically interlocked with one of the stringer pairs A of the first stringers (106) and one of the stringer pairs B of the second stringers (108) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).

Abstract: In one implementation, a hydropower module for use in a flowing body of water is described. The module includes an axle and a plurality of paddle fans rotatably coupled to the axle and having a paddle fan rotation. Each paddle fan of the plurality of paddle fans includes a plurality of blades configured to be driven by the body of water. The plurality of paddle fans are oriented in an arc wherein the blades of adjacent paddle fans are closer together at a top of the paddle fan rotation than at a bottom of the paddle fan rotation.

Abstract: A rapid response self-closing pressure equalization vent employs a frame supported in a compartment divider and a movable vent portion having a periphery sealingly engaging the frame in a closed position. Multiple resilient extension elements are attached to the frame and engage the movable vent portion for even displacement around a periphery of the movable vent portion relative to the frame to an open position responsive to a pressure differential on the movable vent portion. The resilient extension elements retract upon equalization of the pressure differential to reseat the movable vent portion in the frame.

Abstract: A rapid response self-closing pressure equalization vent employs a frame supported in a compartment divider and a movable vent portion having a periphery sealingly engaging the frame in a closed position. Multiple resilient extension elements are attached to the frame and engage the movable vent portion for even displacement around a periphery of the movable vent portion relative to the frame to an open position responsive to a pressure differential on the movable vent portion. The resilient extension elements retract upon equalization of the pressure differential to reseat the movable vent portion in the frame.

Abstract: A material handling apparatus comprises a chassis, an anchoring mechanism retained in the chassis and a material handling mechanism secured to the chassis. The anchoring mechanism provides multi-directional anchoring of the chassis onto a penetrable surface upon which the apparatus rests. The anchoring mechanism comprises a pair of counter-rotating shafts whose lower ends comprise left and right-hand helical augers, respectfully. The upper ends of the shafts are drivingly connected to a means of rotation. The material handling mechanism pulls, pushes or lifts the material being handled. The anchoring mechanism is so retained in the chassis to react the operating forces of the material handling apparatus. Use of this multi-directional anchoring mechanism obviates the requirement for massive, traction based devices, which presently perform large material handling tasks.