Abstract: A fastener assembly includes a bolt having a shaft and a head. The shaft has proximal and distal shaft ends and a shaft body, with the head at the proximal shaft end. At least a bondable portion of the shaft body is at least partially made of a bondable material. At least one collar has proximal and distal collar ends longitudinally separated by a collar body which includes a longitudinally oriented collar aperture extending through a thickness thereof between proximal and distal collar surfaces. The collar aperture defines an inner collar wall having a bondable portion which is at least partially made of a bondable material. At least the bondable portion of the shaft body is located inside the collar aperture. The bondable material of both of the inner collar wall and the shaft body is activated to bond the shaft and the collar into an integral fastener assembly structure.

Abstract: One example includes a system that is comprised of a transparent protective panel, a transparent electrically conductive thin film, a transparent pane, and an adhesive. The transparent electrically conductive thin film is fixed to the transparent protective panel, the transparent protective panel and the transparent electrically conductive film together forming a composite transparent panel. The adhesive adhesively couples the composite transparent panel to the transparent pane, the adhesive failing adhesively at an interface between the adhesive and the transparent pane.

Abstract: An aircraft structural component, for example, a wing spar that has an I-beam shape having upper and lower spar caps coupled by a web therebetween and that provides structural support for an aircraft wing. The wing spar may be fabricated as a graphite composite that is thermally cured to have a certain stiffness. In one embodiment, the wing spar is fabricated so that the upper spar cap has a higher CTE than the web, which creates tension forces in the spar cap when the spar is thermally cured and then cooled. Therefore, when the wing spar is mounted to the wing and the aircraft is in flight, compression forces on the wing skin act to relieve the tension forces in the spar cap, which reduces the compression buckling load on the wing.

Abstract: An aircraft structural component, for example, a wing spar that has an I-beam shape having upper and lower spar caps coupled by a web therebetween and that provides structural support for an aircraft wing. The wing spar may be fabricated as a graphite composite that is thermally cured to have a certain stiffness. In one embodiment, the wing spar is fabricated so that the upper spar cap has a higher CTE than the web, which creates tension forces in the spar cap when the spar is thermally cured and then cooled. Therefore, when the wing spar is mounted to the wing and the aircraft is in flight, compression forces on the wing skin act to relieve the tension forces in the spar cap, which reduces the compression buckling load on the wing.

Abstract: A latching mechanism is provided for engaging an aircraft surface panel to a support member. The aircraft panel is provided with a post extending from the lower surface, which extends through a panel support member into a post engagement mechanism. The post engagement mechanism defines a rotatable sleeve, which rotates for locking and unlocking engagement between the post and the post engagement mechanism. Locking engagement continues when power to the post engagement actuator is terminated. The post engagement mechanism may utilize various types of actuators, including mechanical, hydraulic, and pneumatic. The aircraft panel and the panel support member are translatable into and out of abutting engagement independent of the need for any contact with the aircraft panel upper surface.

Abstract: A ball-lock type fastening device for connecting a work piece to a structure is disclosed. The fastening device includes a number of features designed to improve the reliability, repeatability and strength of the locking mechanism compared to traditional ball-lock fasteners. The features include the shape of the locking balls, the shape of the retention housing which engages the locking balls, and mechanisms for controlling deployment and retraction of the locking balls.

Abstract: A dynamic conformal aerodynamic seal that bridges the gap between an aircraft control surface and an aircraft wing, stabilizer or tail. The seal has a first edge and a second edge, where the first edge of the seal is rigidly coupled to the aircraft wing, stabilizer or tail and the second edge of the seal is slidably coupled to the control surface by magnetic coupling so that when the control surface pivots relative to the aircraft wing, stabilizer or tail, the second edge of the seal slides along the control surface.

Abstract: A fastener assembly includes a bolt having a shaft and a head. The shaft has proximal and distal shaft ends and a shaft body, with the head at the proximal shaft end. At least a bondable portion of the shaft body is at least partially made of a bondable material. At least one collar has proximal and distal collar ends longitudinally separated by a collar body which includes a longitudinally oriented collar aperture extending through a thickness thereof between proximal and distal collar surfaces. The collar aperture defines an inner collar wall having a bondable portion which is at least partially made of a bondable material. At least the bondable portion of the shaft body is located inside the collar aperture. The bondable material of both of the inner collar wall and the shaft body is activated to bond the shaft and the collar into an integral fastener assembly structure.

Abstract: A fastener assembly includes a bolt having a shaft and a head. The shaft has proximal and distal shaft ends and a shaft body, with the head at the proximal shaft end. At least a bondable portion of the shaft body is at least partially made of a bondable material. At least one collar has proximal and distal collar ends longitudinally separated by a collar body which includes a longitudinally oriented collar aperture extending through a thickness thereof between proximal and distal collar surfaces. The collar aperture defines an inner collar wall having a bondable portion which is at least partially made of a bondable material. At least the bondable portion of the shaft body is located inside the collar aperture. The bondable material of both of the inner collar wall and the shaft body is activated to bond the shaft and the collar into an integral fastener assembly structure.

Abstract: A ball-lock type fastening device for connecting a work piece to a structure is disclosed. The fastening device includes a number of features designed to improve the reliability, repeatability and strength of the locking mechanism compared to traditional ball-lock fasteners. The features include the shape of the locking balls, the shape of the retention housing which engages the locking balls, and mechanisms for controlling deployment and retraction of the locking balls.

Abstract: A permanent faster is disclosed that utilizes an amorphous metal alloy for a retaining collar that is thermoplastically formed on install. The fastener includes a headed pin with locking grooves disposed thereon and a collar having a cylindrical inner wall. Head geometry may be any suitable shape; countersunk, counter bore, flat, etc., and may also be non-rotationally symmetric. The pin is disposed into aligned holes through the work pieces to be secured, and the collar is disposed about the pin over the locking grooves. The collar is heated into a thermoplastic region, something only allowed because of the amorphous metal material properties. The cylindrical wall of the collar is then radically compressed into the locking grooves to affix the collar on the pin. The amorphous metal properties allow use of a smaller fastener, and the thermoplastic region is reached at a temperature which does not damage composite work pieces.

Abstract: A bi-directional coupler that selectively couples and de-couples a driving element to a driven element. The coupler includes an outer shaft having an outer shaft slot and an inner shaft having an inner shaft slot, where the inner and outer shafts are configured to rotate independently of each other. The coupler also includes a ball bearing provided within the inner shaft slot and having a size so that when the ball bearing is located at a center portion of the inner shaft slot it does not interfere with rotation of the outer shaft, where the ball bearing is held in that location by a magnet located in the inner shaft. Rotation of the inner shaft above a predetermined rotational speed causes the ball bearing to engage the outer shaft slot so as to cause the inner shaft to be locked to the outer shaft and rotate therewith.

Abstract: A method for providing air traffic controlled flight of drones flying in to and out of an air traffic controlled space around an airport. The method includes causing the drones to congregate at a congregation area in the air traffic controlled space, causing the drones to fly from the congregation area as a group out of the air traffic controlled space under air traffic control, causing the drones to disperse from the group once the drones are out of the air traffic controlled space, causing the drones to fly to a package delivery location after they are dispersed to deliver the package, causing return drones to fly to a re-congregation area outside of the air traffic controlled space after they have delivered their packages, and causing the return drones to enter the air traffic controlled space as a group under air traffic control.

Abstract: A method for providing air traffic controlled flight of a large number of commercial drones each carrying one or more packages in to and out of an air traffic controlled space around an airport. The method includes providing an outbound corridor from a carrier facility through and out of the air traffic controlled space, where the outbound corridor does not allow any other air traffic to fly therein, and allowing the drones to fly through the outbound corridor to leave the air traffic controlled space without requiring air traffic control. The method also includes providing an inbound corridor through the air traffic controlled space to the carrier facility that does not allow any other air traffic to fly therein, and allowing drones to return to the carrier facility through the air traffic controlled space by flying through the inbound corridor without requiring air traffic control.

Abstract: A magnetic fastener assembly for securing an access panel to an aircraft structure. A panel magnetic foundation member is rigidly secured to a surface of the panel facing the aircraft structure and a land magnetic foundation member is rigidly secured to a surface of the aircraft structure facing the panel. A planar magnet is positioned between the panel magnetic foundation member and the land magnetic foundation member and being magnetically coupled thereto so as to secure the panel to the aircraft structure. A separation device, such as a pneumatic bladder, is positioned between the panel and the land structure and adjacent to the magnet, and is rigidly secured to the aircraft structure. The separation device is actuated to apply pressure to the panel and break the magnetic attraction between one or both of the panel magnetic foundation member and the magnet or the land magnetic foundation member and the magnet.

Abstract: A dynamic conformal aerodynamic seal that bridges the gap between an aircraft control surface and an aircraft wing, stabilizer or tail. The seal has a first edge and a second edge, where the first edge of the seal is rigidly coupled to the aircraft wing, stabilizer or tail and the second edge of the seal is slidably coupled to the control surface by magnetic coupling so that when the control surface pivots relative to the aircraft wing, stabilizer or tail, the second edge of the seal slides along the control surface.

Abstract: A fluid-actuated fastening device comprises a housing including a housing body defining a fluid cavity and a fluid port. The fluid port places the fluid cavity in selective communication with an outside fluid source. A telescoping mast assembly includes a mast sleeve. A spindle has longitudinally spaced inner and outer spindle ends separated by a longitudinally oriented spindle body. The spindle body is at least partially located within the mast sleeve for telescoping longitudinal movement with respect thereto to transform the mast assembly between compressed and expanded mast states. At least one disc spring is located substantially within the fluid cavity. Introduction of pressurized fluid into the fluid cavity via the fluid port causes at least one of travel of the disc spring between flexed and relaxed spring states and translational movement of the mast between the compressed and expanded mast states.

Abstract: A Z-pin including a first bi-metal structure having a first metal strip and a second metal strip bonded together, where the first and second metal strips have different coefficients of thermal expansion, and a second bi-metal structure having a third metal strip and fourth metal strip bonded together, where the third metal strip and the fourth metal strip have different coefficients of thermal expansion. The first and third metal strips are selectively secured together at at least one discrete location so that heating of the Z-pin causes the first and second bi-metal structures to deform relative to each other. The Z-pin is inserted into a composite laminate structure while it is in its uncured state, where curing of the composite structure causes the first and second bi-metal structures to deform relative to each other to lock the laminate layers together.

Abstract: A magnetic latching system is provided for removably latching a panel to an aircraft surface portion. The latching system includes a removable axis panel engageable to a latching land. The panel and land define opposing magnetically attractive surface portions, with a body of magnetic material disposed there between. An inflatable seal is also disposed intermediate the panel and the land. Upon inflation, the inflatable seal is operative to urge the panel away from the land far enough to reconnect magnetic engagement between the panel and the land, sufficient to permit disengagement of the panel from the land.

Abstract: A ball-lock type fastening device for connecting a work piece to a structure is disclosed. The fastening device includes a number of features designed to improve the reliability, repeatability and strength of the locking mechanism compared to traditional ball-lock fasteners. The features include the shape of the locking balls, the shape of the retention housing which engages the locking balls, and mechanisms for controlling deployment and retraction of the locking balls.