Abstract: In an example, a method is described. The method comprises placing a repair patch over a repair area of a structure, the repair patch comprising a repair-patch hole. The method also comprises sealing the repair patch and repair area with a vacuum bag having a seal ring around a periphery of the vacuum bag. The method also comprises evacuating, via an adhesive injection apparatus attached to the repair-patch hole and the seal ring of the vacuum bag, the repair area and an injection channel of the adhesive injection apparatus. The method also comprises forcing adhesive through the evacuated injection channel and into the evacuated repair area.

Abstract: An example method of joining a first structure and a second structure is described that includes placing an adhesive within a bond cavity for bonding a first structure to a second structure, securing a vacuum bag to the first structure and the second structure so as to surround a portion of the first structure and the second structure, evacuating the bond cavity via a vacuum port to deaerate the adhesive within the bond cavity, after deaerating the adhesive, moving the first structure and the second structure relative to one another such that deaerated adhesive is disposed between the first structure and the second structure, and curing, via one or more heaters, the deaerated adhesive disposed between the first structure and the second structure to bond the first structure to the second structure.

Abstract: An example method of joining a first structure and a second structure is described that includes forming a bond cavity between a first structure and a second structure, placing a semi-permeable breather material at one or more exits of the bond cavity, placing a vacuum bag around the bond cavity and the semi-permeable breather material, evacuating the bond cavity via a vacuum port and forcing adhesive into the bond cavity via an adhesive port while the bond cavity is evacuated, and curing the adhesive via one or more heaters to bond the first structure to the second structure.

Abstract: An aerial vehicle includes a wing body. The aerial vehicle includes a plurality of rotors coupled to the wing body. Each one of the rotors includes a plurality of rotor blades. The aerial vehicle includes a drive assembly configured to rotate the rotors. The aerial vehicle includes a controller configured to selectively control thrust produced by each one of the rotors. Selective control of the thrust produced by each one of the rotors induces a pitch motion of the aerial vehicle to transition the aerial vehicle between a horizontal flight state and a vertical flight state. In the horizontal flight state, the wing body is approximately horizontal and a collective thrust from the rotors is directed forward. In the vertical flight state, the wing body is approximately vertical and the collective thrust from the plurality rotors is directed upward.

Abstract: Systems and methods for tracking the location of a non-destructive inspection (NDI) scanner using scan data converted into images of a target object. Scan images are formed by aggregating successive scan strips acquired using one or two one-dimensional sensor arrays. An image processor constructs and then compares successive partially overlapping scan images that include common features corresponding to respective structural features of the target object. The image processor is further configured to compute a change in location of the NDI scanner relative to a previous location based on the respective positions of those common features in the partially overlapping scan images. This relative physical distance is then added to the previous (old) absolute location estimate to obtain the current (new) absolute location of the NDI scanner.

Abstract: A computing system includes a processor and a non-volatile memory storing executable instructions that, in response to execution by the processor, cause the processor to execute an inspection classifier including at least a first artificial intelligence model, the inspection classifier being configured to receive run-time event input data from a plurality of data sources associated with an aircraft, the data sources including structural health monitoring sensors instrumented on the aircraft; extract features of the run-time event input data; determine a predicted inspection classification based upon the extracted features, the predicted inspection classification being one of a plurality of candidate inspection classifications; and output the predicted inspection classification.

Abstract: Systems and methods for an Automated Guided Vehicle (AGV) capable of automatically balancing large and heavy objects for transport through a facility. One embodiment is an Automated Guided Vehicle (AGV) including a balancing plate configured to support a load, load sensors configured to detect a weight distribution of the load, and an actuator configured to shift the balancing plate laterally. The AGV also includes a weight balancing controller configured to determine a center of gravity of the load based on the weight distribution detected by the load sensors, to determine that the center of gravity of the load is vertically misaligned with a center of gravity of the AGV, and to direct the actuator to shift the balancing plate laterally to move the center of gravity of the load toward vertical alignment with the center of gravity of the AGV.

Abstract: Systems and methods are provided for composite part fabrication. One embodiment is a method for fabricating a composite part. The method includes selecting a tool with sides made of a core material in a desired size and shape, disposing a preform of a fiber reinforced material that surrounds the tool, resulting in a lamina assembly comprising the preform and the tool, heating the tool and the preform, co-bonding the tool to the fiber reinforced material within the lamina assembly, and hardening the preform and the tool into a hybrid composite part.

Abstract: Composite fabrication system and associated methods. In one embodiment, a composite fabrication system comprises a molding tool that includes a forming surface at least partially disposed within a constrained space, and a foamable material that expands inside of the constrained space to form an expanded material that presses a layup of one or more composite layers against the molding tool. The composite fabrication system further comprises a curing device configured to cure the layup to form a composite part, and a cutting wire embedded in the constrained space that is heated and configured to cut the expanded material into pieces that are removable from the constrained space.

Abstract: A system for curing a composite part, includes a mandrel configured to receive and support the uncured composite part; a plurality of expandable pellets disposed on the uncured composite part; and a mold configured to hold the mandrel, the uncured composite part, and the plurality of expandable pellets, wherein the plurality of expandable pellets are configured to expand and apply a positive pressure to the uncured composite part according to a change in condition or triggering event, and wherein each of the plurality of expandable pellets includes a blowing agent, a polymer matrix configured to hold the blowing agent, and a flexible skin configured to encapsulate the polymer matrix and the blowing agent, wherein the flexible skin is at least partially permeable with respect to the blowing agent or a gas released by the blowing agent.

Abstract: A fastener locating tool equipped with a sensor head having one or more probes and a method for operating such a tool for precisely locating a fastener that is hidden or buried under a thick coating applied on a surface of a structure. The fastener locating tool may be manually or automatically operated. The fastener locating tool includes a platform having a central opening, means for temporarily attaching the platform to a coated surface, and a sensor head that may be easily mechanically coupled to and then later decoupled from the platform. Optionally, the fastener locating tool also includes a multi-stage positioning system with X and Y stages which may be used to adjust the position of the sensor head. The sensor head includes at least one probe which generates electrical signals indicating the presence of a fastener beneath a coating when the probe is within a detection range.

Abstract: A deployable clasping system is configured to be deployed from a component and securely clasp and release an object. The deployable clasping system includes a cable that is deployable from the transit vehicle. A clasp assembly is coupled to the cable. The clasp assembly is configured to securely clasp the object. A propulsion sub-system is coupled to one or both of the cable and the clasp assembly. The propulsion sub-system is configured to maneuver the clasp assembly to the object.

Abstract: Devices for maintaining crawler alignment on complex-shaped blades and for enabling the blade crawler to traverse over trailing edge protrusions. Using ball and socket bearings or air pads in place of alignment wheels, the crawler will be able to track along complex-geometry rotor blades, propellers and other airfoils. Using an oversized-diameter roller, a semi-flexible roller, or a dual-roller arrangement, the crawler will be able to traverse over trailing edge protrusions.

Abstract: Automated apparatus for performing maintenance functions on airfoil-shaped bodies having short chord lengths, the apparatus being movable in a spanwise direction along the airfoil-shaped body. In accordance with various embodiments, the apparatus comprises a blade crawler capable of supporting any one of a plurality of end effectors for performing a set of maintenance functions on an airfoil-shaped body, such as a blade component. Included in these functions are multiple options for nondestructive inspection, drilling, grinding, fastening, appliqué application, scarfing, ply mapping, depainting, cleaning, and painting devices that are attached as the end effector for the blade crawler. As a whole, the blade crawler reduces maintenance time, labor hours and human errors when robotic maintenance functions are performed on blade components.

Abstract: Composite fabrication system and associated methods. In one embodiment, a composite fabrication system comprises a molding tool that includes a forming surface at least partially disposed within a constrained space, and a foamable material that expands inside of the constrained space to form an expanded material that presses a layup of one or more composite layers against the molding tool. The composite fabrication system further comprises a curing device configured to cure the layup to form a composite part, and a cutting wire embedded in the constrained space that is heated and configured to cut the expanded material into pieces that are removable from the constrained space.

Abstract: A method for testing a structure includes steps of: identifying a three-dimensional position of a surface of the structure relative to a reference frame; transmitting laser light from an output of a transmitter onto the surface of the structure to form ultrasonic waves in the structure and to detect a response to the ultrasonic waves; based on the three-dimensional position of the surface, moving the laser light over the structure along a scan path so that the output of the transmitter is located at a constant offset distance from the surface and that the laser light, transmitted from the output of the transmitter, is directed onto the surface at a constant angle of projection; and based on the response to the ultrasonic waves, determining whether an inconsistency is present in the structure.

Abstract: Disclosed herein is a non-destructive inspection (NDI) apparatus. The NDI comprises a main body and a modulated-frequency ultrasonic source, coupled to the main body. The modulated-frequency ultrasonic source comprises a low-frequency ultrasonic source, selectively operable to emit a low-frequency ultrasonic beam having a first frequency. The modulated-frequency ultrasonic source also comprises a high-frequency ultrasonic source, selectively operable to emit a high-frequency ultrasonic beam having a second frequency higher than the first frequency. The modulated-frequency ultrasonic source is configured to mix the low-frequency ultrasonic beam and the high-frequency ultrasonic beam at least at a surface of a structure to be inspected.

Abstract: Methods for performing repair operations using one or more unmanned aerial vehicles (UAVs). First, an unmanned aerial vehicle equipped with a camera is flown to a position in a vicinity of an area of interest on a surface of a structure. Image data representing one or more images of the structure in the area is acquired using the camera. Second, an unmanned aerial vehicle equipped with a non-destructive examination (NDE) sensor unit is flown until the NDE sensor unit is within measurement range of the structure in the area of interest. Then NDE sensor data representing structural characteristics of the structure in the area of interest is acquired. Third, an unmanned aerial vehicle equipped with a repair tool is moved to a location that places the repair tool in contact with the surface in the area of interest. Then the structure in the area is repaired using the repair tool.

Abstract: Various techniques are provided to utilize nanostructures for process monitoring and feedback control. In one example, a method includes forming a layer of material including nanostructures distributed therein. Each nanostructure includes a quantum dot and a shell encompassing the quantum dot. The shells and quantum dots are configured to emit a first and second wavelength, respectively, in response to an excitation signal. The method further includes applying the excitation signal to at least a portion of the layer of material. The method further includes detecting an emitted signal from the portion of the layer of material, where the emitted signal is provided by at least a subset of the nanostructures in response to the excitation signal. The method further includes determining whether a manufacturing characteristic has been satisfied based at least on a wavelength of the emitted signal. Related systems and products are also provided.

Abstract: A surface roughness analysis system and methods of analyzing surface roughness of a workpiece are presented. The surface roughness analysis system comprises a number of wave generators; a number of wave sensors; and an ultrasonic analysis system configured to receive material mechanical parameters for a workpiece, determine incident surface wave signal parameters for a source signal to be sent by the number of wave generators, and determine a cut-off wavelength using the material mechanical parameters, wherein the cut-off wavelength is a ratio of surface wavelength over incident wavelength.