Abstract: A device includes one or more processors configured to generate simulation data by providing first sets of first values of first input parameters to a simulation of a physical system. The processors are configured to develop at least one surrogate model based on the simulation data, and to select second input parameters from the first input parameters based on the at least one surrogate model. A count of the second input parameters is less than a count of the first input parameters. The processors are configured to generate second simulation data by providing second sets of second values of the second input parameters to the simulation. The processors are configured to develop at least a second surrogate model based on the second simulation data.

Abstract: A dual agent reinforcement learning autonomous system (DARLAS) for the autonomous operation of aircraft and/or provide pilot assistance. DARLAS includes an artificial neural network, safe agent, and cost agent. The safe agent is configured to calculate safe reward Q values associated with landing the aircraft at a predetermined destination or calculated emergency destination. The cost agent is configured to calculate cost reward Q values associated with maximum fuel efficiency and aircraft performance. The safe and cost reward Q values are based on state-action vectors associated with an aircraft, which may include state data and action data. The system may include a user output device that provides an indication of an action to a user. The action corresponds to an agent action having the highest safe reward Q value and the highest cost require Q value. DARLAS prioritizes the highest safe reward Q value in the event of conflict.

Abstract: A machine and process for control of rotation of a vehicle about an axis of the vehicle is shown. A flight control system includes control laws that control the rotation of the vehicle around the axis of the vehicle. An estimate is derived for an inertia about the axis. The estimated inertia is derived from sensed quantities of material in a component of the vehicle. An inertia gain schedule and filter are added to enhance, using the estimated inertia, the accuracy of the control laws that control the rotation of the vehicle around the axis of the vehicle.

Abstract: Fiber-reinforced thermoplastic composite structural members (FRTCSM), aircraft including the same, and related methods are disclosed herein. The FRTCSMs include a first thermoplastic sub-structure that includes a first web, a first flange that extends away from the first web, and a first transition region between the first flange and the first web. The FRTCSMs also include a second thermoplastic sub-structure that includes a second web, a second flange that extends away from the second web, and a second transition region between the second flange and the second web. The first web is welded to the second web. The aircraft include at least one FRTCSM. The methods include positioning the first thermoplastic sub-structure and the second thermoplastic sub-structure such that the first web faces the second web, compressing the first web and the second web together, and welding the first web and the second web to one another.

Abstract: Compositions and coatings for thin films designed to protect surfaces and windows from environmental abrasion (e.g., sand, dust, and rubbing) that are transparent in visual and infrared wavelengths are disclosed. The compositions comprise thiol-containing copolymers comprising: (1) 10-(3-butyl-2-hexyl-6-(9-mercaptononyl)cyclohexyl) decane-1-thiol; and (2) a multifunctional terminally unsaturated hydrocarbon monomer; wherein (1) and (2) are combined to form a UV curable crosslinked thermoset polymer network and no particulate fillers are added to the composition. The films exhibit a specular transmission of greater than 70% in the visual spectrum at about 400-700 nm, and IR wavelengths at about 4-5 ?m, and about 7.5-12 ?m when applied to a surface of a substrate in a coating thickness of about 1-500 ?m. A method for making the films involving an UV initiated thiol-ene curing mechanism is also provided.

Abstract: A system and a method include a heating layer including perforations extending from a first surface to a second surface opposite from the first surface. The perforations provide acoustic paths. The heating layer is configured to provide electrically resistive heating to a component. An acoustic layer can be coupled to the heating layer. The perforations extend to the acoustic layer.

Abstract: An over-pressure vent (OPV) system is provided for a fuel tank of an aircraft. The OPV system includes an OPV valve configured to be coupled in fluid communication with a supply line of a nitrogen enriched air distribution system (NEADS) such that the OPV valve is configured to vent pressure from the supply line. The OPV valve is configured to be coupled in fluid communication with the supply line upstream from an outlet of the supply line from which the NEADS delivers nitrogen enriched gas to the fuel tank. The OPV valve is configured to sense a pressure within the supply line upstream from the outlet of the supply line.

Abstract: Systems, apparatuses and methods can provide for technology to perform a discrete cosine transform (DCT) on a first digital signal to obtain a frequency domain signal, wherein the frequency domain signal contains energy in a plurality of frequency bins, apply convolutional neural network (CNN) operations on the frequency domain signal, and output a probability for each of the plurality of frequency bins in accordance with the CNN operations, wherein each probability indicates whether the energy in a corresponding frequency bin contains a transmitted signal.

Abstract: An additive manufacturing system includes a first robotic arm and a print head with a nozzle. The first robotic arm is configured to hold a build part during a build process. The print head is configured to deposit source material layer by layer during the build process to construct the build part. The first robotic arm is configured to reorient the build part relative to the print head during the build process to modify an angle of a surface layer of the build part relative to the print head.

Abstract: A system for forming a component includes one or more heaters configured to generate heat to form the component, wherein the component, upon formation, includes the one or more heaters. A method for forming a component includes generating, by one or more heaters, heat to form the component; and forming the component, at least in part, by said generating, wherein the component, upon formation, includes the one or more heaters.

Abstract: An aerospace panel includes a first skin, a second skin spaced apart from the first skin, and a first truss structure connecting the first skin to the second skin. The first truss structure includes a plurality of truss members. Each truss member is integral with the first skin and the second skin, such that the first skin, the second skin, and the first truss structure collectively form a single monolithic joint-free structure. At least one of the skins also includes at least one lattice region that includes a lattice grid and an array of openings.

Abstract: A system includes a control unit configured to receive one or more force signals from one or more force sensors coupled to one or both of a tool or an end effector. The one or more force signals are indicative of one or more forces exerted in relation to the tool or the end effector as the tool operates on one or more components to form an expanded hole. The control unit is further configured to compare the one or more forces in relation to force data associated with a reference expanded hole that is aligned with an alignment hole of the one or more components. The control unit is further configured to determine that the expanded hole caused a deformation when the one or more forces differ from the force data.

Abstract: Aspects of the present disclosure provide fluoropolymers and methods for forming and using such fluoropolymers. Fluoropolymers include polyfluorobenzoxazines and polyfluoroimides. Methods for forming polyphthalonitriles are also provided. The present disclosure is further directed to compositions containing one or more fluoropolymers and one or more metal oxides.

Abstract: A method of forming a composite part from a mufti-ply prepreg composite charge comprises reducing pressure inside a bladder, located in a chamber that is at atmospheric pressure, below the atmospheric pressure. The method also comprises placing the multi-ply prepreg composite charge, having a first shape, in the chamber and reducing pressure inside the chamber below the atmospheric pressure. The method additionally comprises, while maintaining pressure inside the chamber below the atmospheric pressure, expanding the bladder within the chamber by increasing pressure inside the bladder to the atmospheric pressure, so that the multi-ply prepreg composite charge is compressed between the bladder and a forming tool, which is located inside the chamber, and the multi-ply prepreg composite charge is configured by the forming tool to a second shape, different from the first shape. The method also comprises curing the multi-ply prepreg composite charge, having the second shape.

Abstract: A method of manufacturing a composite structure includes accessing design data for the composite structure that is manufactured according to a process including forming a layup of plies of fibers using a machine tool. The method includes applying the design data to an ANN classifier to classify a localized inconsistency of a type of inconsistency on the composite structure, the localized inconsistency spatially referenced to a location on the composite structure. The method includes performing a root cause analysis to identify one or more of process parameters as a potential cause of the type of inconsistency, and modifying one or more of the geometric model, the layup design, or values of the one or more of the process parameters to address the potential cause.

Abstract: A panel assembly (such as for an internal cabin of an aircraft) includes at least one liquid flow path formed on at least one surface through surface treatment. The at least one liquid flow path is formed in relation to at least one bank on the at least one surface. The at least one liquid flow path is configured to divert liquid to a desired location.

Abstract: A vertical intercostal for an aircraft vehicle having a vehicle cabin and an over-monument fairing arranged in a non-flex zone area of the vehicle cabin. The intercostal includes a frame member that includes an upper frame attachment region, a lower frame attachment region, and an intermediate frame attachment region to provide lateral structural support for the over-monument fairing to the airframe of the aircraft.

Abstract: An inter-substrate bond structure includes an adhesion layer that attached to a first substrate, and an outer gas-permeable layer coupled to the adhesion layer. The outer gas-permeable layer expands and fractures in response to absorbing a gas. The inter-substrate bond structure includes an outer bond layer coupled to the outer gas-permeable layer. The outer bond layer forms an initial thermocompression bond with a mating layer on a second substrate. The initial thermocompression bond bonds the first substrate to the second substrate with the inter-substrate bond structure. The fracture in the inter-substrate bond structure debonds the first substrate from the second substrate while leaving a first portion of the inter-substrate bond structure attached to the first substrate.

Abstract: A thrust reverser in an engine includes a first reverser portion configured to direct a gas in a first direction to create reverse thrust. The thrust reverser also includes a second reverser portion configured to direct the gas in a second direction that is different than the first direction. The second reverser portion is upstream or downstream from the first reverser portion.

Abstract: A system includes one or more control units configured to determine one or more fuel consumption models for an aircraft. A method includes determining, by one or more control units, one or more fuel consumption models for an aircraft. A non-transitory computer-readable storage medium comprising executable instructions that, in response to execution, cause one or more control units comprising a processor, to perform operations including determining one or more fuel consumption models for an aircraft.