Abstract: An example robotic device includes: a circumferential carriage configured to drive the robotic device along a rail configured to be mounted to a curved surface, the circumferential carriage comprising: (i) a frame base, (ii) a frame mounted to the frame base, (iii) one or more wheels coupled to the frame base and configured to engage with the rail, (iv) a worm gear arrangement, and (v) a main drive gear coupled to the worm gear arrangement and configured to engage with a rack disposed on the rail; and a transversal carriage comprising: (i) a cross slide slidably mounted to the frame, (ii) a transversal rack coupled to the cross slide, (iii) a cross slide motor mounted to the circumferential carriage, and (iv) a cross slide drive gear coupled to the cross slide motor and having gear teeth engaging with respective teeth of the transversal rack.

Abstract: There is provided a portable wand system having a wand applicator, a wand controller subsystem, a selector assembly, an indicator element, and a power assembly. The wand controller subsystem includes a computer program, and a memory unit storing paths learned and recorded during a learn mode, by an operator manually moving the wand applicator. The paths include desired paths in stay-in zones to be surface treated, and include stay-out zone paths in, or near, stay-out zones to be avoided. The portable wand system is used in an operation mode to measure the operator manually moving the wand applicator in operation paths, based on the desired paths. For a selected stay-in zone, the portable wand system compares the operation path to the desired path, and indicates when the operation path deviates from the desired path, and when the wand applicator is in proximity to, and oriented towards, the stay-out zones.

Abstract: An example robotic device includes: a circumferential carriage configured to drive the robotic device along a rail configured to be mounted to a curved surface, the circumferential carriage comprising: (i) a frame base, (ii) a frame mounted to the frame base, (iii) one or more wheels coupled to the frame base and configured to engage with the rail, (iv) a worm gear arrangement, and (v) a main drive gear coupled to the worm gear arrangement and configured to engage with a rack disposed on the rail; and a transversal carriage comprising: (i) a cross slide slidably mounted to the frame, (ii) a transversal rack coupled to the cross slide, (iii) a cross slide motor mounted to the circumferential carriage, and (iv) a cross slide drive gear coupled to the cross slide motor and having gear teeth engaging with respective teeth of the transversal rack.

Abstract: An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. A micro-lattice support structure is coupled to the inner surface and defines airflow gaps allowing suctioning of air from the outer surface through the perforated panel skin and into a plenum of the aerodynamic body. Rows of main beams of the micro-lattice support structure are aligned along land lines oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Abstract: A structural assembly including a first member having an external side and an internal side, the first member defining a first member through-bore, a second member having an external side and an internal side, the second member defining a second member through-bore aligned with the first member through-bore, and a mechanical fastening system including a bushing at least partially received in the first member through-bore, the bushing defining a bushing through-bore and including a flange, wherein the flange is positioned in a gap between the internal side of the first member and the external side of the second member, a nut plate connected to the internal side of the second member, the nut plate defining a clearance bore aligned with the second member through-bore and the bushing through-bore, the nut plate including a nut, and a bolt extending through the bushing through-bore and into threaded engagement with the nut.

Abstract: An aircraft includes a plurality of seats and an input device coupled to each of the plurality of seats. The aircraft also includes a remotely controlled nozzle positioned proximate each seat of the plurality of seats. Each nozzle includes an actuator assembly including at least one actuator and an actuator shaft. The at least one actuator is configured to move the actuator shaft between an open position and a closed position to control an airflow through the nozzle in response to a signal received from a respective input device of the input devices, wherein the signal represents a position of the actuator shaft.

Abstract: Systems, methods, and devices are configured to implement hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Abstract: A structural assembly including a first member having an external side and an internal side, the first member defining a first member through-bore, a second member having an external side and an internal side, the second member defining a second member through-bore aligned with the first member through-bore, and a mechanical fastening system including a bushing at least partially received in the first member through-bore, the bushing defining a bushing through-bore and including a flange, wherein the flange is positioned in a gap between the internal side of the first member and the external side of the second member, a nut plate connected to the internal side of the second member, the nut plate defining a clearance bore aligned with the second member through-bore and the bushing through-bore, the nut plate including a nut, and a bolt extending through the bushing through-bore and into threaded engagement with the nut.

Abstract: A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.

Abstract: An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. A micro-lattice support structure is coupled to the inner surface and defines airflow gaps allowing suctioning of air from the outer surface through the perforated panel skin and into a plenum of the aerodynamic body. Rows of main beams of the micro-lattice support structure are aligned along land lines oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Abstract: Systems, methods, and devices are disclosed for implementing hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Abstract: A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.

Abstract: An aircraft includes a plurality of seats and an input device coupled to each of the plurality of seats. The aircraft also includes a remotely controlled nozzle positioned proximate each seat of the plurality of seats. Each nozzle includes an actuator assembly including at least one actuator and an actuator shaft. The at least one actuator is configured to move the actuator shaft between an open position and a closed position to control an airflow through the nozzle in response to a signal received from a respective input device of the input devices, wherein the signal represents a position of the actuator shaft.

Abstract: A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.

Abstract: A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.