Abstract: A system includes a computing device that generates at least one process script for the modification to a material substrate and at least one pattern script that corresponds to the process script. The computing device also merges the process script with the pattern script and generates a plurality of command signals that are based on the merged process and pattern scripts. An energy source generates a plurality of light beams based on the generated command signal(s). At least one modulating component modulates the generated light beams based on generated command signal(s). A waveform apparatus generates at least one waveform signal to customize the generated light beams based on the generated command signal(s). A motion control apparatus controls at least one parameter of the light beams based on the generated command signal(s).

Abstract: An apparatus for detecting leaks in batteries may include an applicator, and an indicator comprising a chemical configured to detect a trace amount of leakage in the battery.

Abstract: Cable retainer apparatuses for retaining a cable, and aircraft and methods including such apparatuses are provided. In one example, a cable retainer for retaining a cable proximate a surface of an aircraft includes a cable retainer. The cable retainer is configured to retain the cable. A fairing is disposed about the cable retainer and is configured to couple to the aircraft to support the cable retainer adjacent to the surface of the aircraft.

Abstract: Disclosed herein are spectral imaging systems having an internally folded prism, which can have four different refracting surfaces. A first angle defines the spatial relationship between the first and second refracting surfaces. The first angle can have a range between 45-95 degrees. In some embodiments, the first angle can be 70 degrees. The spatial relationship of the third and fourth refracting surfaces can be defined by a second angle, which can be the same as the first angle. Finally, the spatial relationship of the second and third refracting surfaces can be defined by a third angle, which can have a range between 90-145 degrees. The prism index of refraction, the first, second, and third angles are selected such that TIR is achieved at two of the refracting surfaces. Additionally, these prism parameters are selected such that a 180 degrees fold of the optical path is achieved entirely within the prism.

Abstract: An avionics system for an aircraft includes a threat data structure and a processor. The threat data structure stores an alert threshold and a margin threshold. The processor is programmed to: predict an aircraft state at a plurality of positions along a potential future trajectory; calculate a margin value at each of the plurality of positions as a difference between the predicted future condition and the threat value at each respective one of the plurality of positions; calculate a margin rate of change at each of the plurality of positions based on a change in the margin value along the potential future trajectory; estimate a time to go value based on a minimum calculated margin value and a maximum calculated margin rate of change among the plurality of positions; and command an indicator to alert the pilot in response to the time to go value reaching the alert threshold.

Abstract: A projected recovery trajectory for an aircraft autopilot system is precomputed by providing a stored set of predefined recovery mode segments, including: a mode 1 segment that models the aircraft coasting; a mode 2 segment that models the aircraft executing a nose high recovery; a mode 3 segment that models the aircraft executing a nose low recovery; a mode 4 segment that models the aircraft executing a throttle only recovery; and a mode 5 segment that models the aircraft executing a terrain avoidance recovery. A processor generates at least one projected recovery trajectory based on a current state of the aircraft, where the processor selectively concatenates selected ones of the predefined recovery mode segments into a sequence and uses that sequence to generate the projected trajectory.

Abstract: The processor supplies flight commands to the flight control system by selectively blending pilot input with control signals from the autopilot. The processor generates a projected recovery trajectory through successive iterations, each beginning at the current aircraft location and using a recovery constraint selectable by the processor to influences a degree of flight aggressiveness. A detection system that identifies and invokes a state of threat existence if a threat exists along the projected recovery trajectory. The processor during threat existence in a first iteration commands an initial soft recovery, with permitted blended pilot input. If the threat exists on subsequent iteration, the processor commands a more aggressive recovery while attenuating blended pilot input.

Abstract: Avionics systems, aircraft, and methods are provided. An avionics system for a subject aircraft includes an intruder aircraft detection device and a processor. The processor is programmed to: identify an intruder aircraft using the intruder aircraft detection device; predict a future path of the intruder aircraft; estimate strength, size, and location characteristics of a wake vortex created by the intruder aircraft at future points in time along the future path; calculate a potential trajectory with potential positions of the subject aircraft at each of the future points in time; compare the potential positions with the strength, size, and location characteristics of the wake vortex at each of the future points in time to identify a wake conflict; and maneuver the subject aircraft based on the wake conflict.

Abstract: The aircraft threat envelope protection system employs a threat envelope data structure in a computer-readable medium that stores at least one trigger condition for each of a plurality of different types of threats associated with the aircraft, and modeled using a common schema. A processor computes plural different projected trajectories representing different possible aircraft paths through spacetime. The processor associates at least some of the plurality of the threats to specific trigger points in spacetime along each of the projected trajectories. The processor will deprecate ones of the projected trajectories when they are deemed not viable to recover from a threat. The processor initiates an aircraft protective response when all projected trajectories but one have been deprecated and the aircraft is within a predetermined proximity to the closest trigger point in spacetime along the non-deprecated trajectory.

Abstract: Under one aspect, a method is provided for processing a received signal, the received signal including a desired signal and an interference signal that spectrally overlaps the desired signal. The method can include obtaining an amplitude of the received signal. The method also can include obtaining an average amplitude of the received signal based on at least one prior amplitude of the received signal. The method also can include subtracting the amplitude from the average amplitude to obtain an amplitude residual. The method also can include, based upon an absolute value of the amplitude residual being less than or equal to a first threshold, inputting the received signal into an interference suppression algorithm so as to generate a first output including the desired signal with reduced contribution from the interference signal.

Abstract: A deposition assembly generally comprises a first deposition apparatus that is configured to receive a substrate, such as a glass mandrel. The first deposition apparatus is further configured to deposit a plurality of first monolayer molecules onto at least a surface of the substrate to generate a first coating structure on the substrate. A second deposition apparatus is coupled to the first deposition apparatus, and wherein the second deposition apparatus is configured to deposit a plurality of second monolayer molecules onto at least the surface of the substrate such that the second monolayer molecules are diffused through the first coating structure and at least one aperture is filled by at least one of the second monolayer molecules to generate at least one mold release layer on at least the surface of the substrate.

Abstract: Drilling aid apparatuses and methods for drilling a structure are provided. In one example, a drilling aid apparatus includes a bushing holder portion. The bushing holder portion has a first surface for facing a first structure portion, a second surface on a side opposite the first surface, and an opening formed through the bushing holder portion extending from the first surface to the second surface. The opening is configured to receive a bushing that is sized for guiding a drill bit for drilling into the first structure portion. A first coupling member is coupled to the bushing holder portion and is configured to couple to a second structure portion for supporting the bushing holder portion in a fixed position relative to the first structure portion.

Abstract: An apparatus for wheel maintenance includes a base configured to rotate about a vertical rotational axis and a frame mounted to the base that has a pair of opposing longitudinal members and a pair of opposing transverse members. First and second rollers are spaced apart from one another and coupled to the pair of opposing transverse members. Both the first and second rollers rotate about a longitudinal rotational axis orthogonal to the vertical rotational axis. In this way, when a wheel is positioned on the first and second rollers, the wheel may be rotated about the vertical rotational axis and a wheel rotational axis during a maintenance procedure.

Abstract: A device, a system and a method for dispensing adhesive elements are provided. The device comprising a first holder, a second holder, and an alignment element. The first holder is configured to rotatably hold a film having adhesive elements and a protective layer attached on adhesive areas of the adhesive elements. The second holder is configured to receive the protective layer as the protective layer is peeled off the adhesive areas of the adhesive elements while the adhesive elements are moved towards an alignment element. The alignment element is arranged in a direction of movement of the adhesive elements and configured to receive and align the adhesive elements at a predetermined position on the alignment element.

Abstract: A system and a method for drone detection and collision avoidance, particularly for use in an aircraft, is provided. The system includes, but is not limited to a sensor, a processor, and an avoidance unit comprising a control unit. The sensor is configured to detect a drone signal in a predetermined space and to transmit the drone signal to the processor. The processor is configured to determine the presence of a drone in the predetermined space based on the drone signal. The processor is configured to transmit a command to the avoidance unit when the processor determines the presence of a drone. The control unit is configured to receive the command and to generate a warning signal in response to receiving the command.

Abstract: A computer-implemented method for generating a 3-dimensional (3D) model to characterize and visualize debris. The computer-implemented method includes defining a bounding surface for one or more debris fields generated by an on-orbit breakup event. The bounding surface is defined by using an upper limit fragment spreading speed predicted by a breakup model and applying the upper limit fragment spreading speed in different directions to generate points on the bounding surface. The computer-implemented method also includes connecting one or more points on the bounding surface to maintain a single bounded 3D mesh. The computer-implemented method further includes applying color and/or transparency to the 3D model.

Abstract: Methods for characterizing shape changes of an aircraft due to flight loads are provided. In one example, a method for characterizing shape changes of an interior portion of an aircraft from flight loads includes positioning one or more 3D scanners within the interior portion of the aircraft. A reference scan of the interior portion is created with the one or more 3D scanners while the aircraft is substantially stationary and/or on the ground. A deformed scan of the interior portion is created with the one or more 3D scanners while the aircraft is in flight subject to substantial flight loads. The reference scan and the deformed scan are postprocessed and analyzed to characterize the shape changes of the interior portion of the aircraft from the substantial flight loads.

Abstract: A process for sharing spectrum based on signal based shared access (SSA) includes measuring by a primary wireless system, the quality of a signal of interest (SOI) over a shared spectrum band. The process includes transmitting a signal quality indicator related to an associated action message from the primary wireless system to a second wireless system. The process also includes receiving spectrum usage information by the primary wireless system from the second wireless system. The process further includes determining by the primary wireless system whether the second wireless system complies with spectrum sharing band conditions between the primary wireless system and the second wireless system.

Abstract: Aircraft instrumentation systems, aircraft, and controllers are provided for transcribing radio communications. An aircraft instrumentation system and an aircraft include a radio device, a display device, and a controller. The controller is communicatively coupled with the radio device and the display device. The controller is configured to monitor the radio device and recognize a voice communication received over the radio device. The controller is further configured to generate an electronic transcript of the voice communication and control the display device to display a transcript of the voice communication.