Abstract: There is provided an energy absorbing landing gear system for attachment to a vertical landing apparatus. The energy absorbing landing gear system includes a linear damper assembly, and a load limiter assembly coupled to the linear damper assembly, the load limiter assembly having at least one deformable element to enhance an energy absorption capability. When the energy absorbing landing gear system is attached to the vertical landing apparatus, during a landing phase, the linear damper assembly contacts a landing surface, and a piston assembly of the linear damper assembly moves a first compression distance toward the load limiter assembly, and when the linear damper assembly reaches a maximum compression, the linear damper assembly moves a second compression distance into the load limiter assembly, and the at least one deformable element deforms.

Abstract: A wide-body aircraft is disclosed with a fuselage section that includes a set of side-by-side fuselage lobes having a fuselage skin. A first woven composite preform positioned at a first intersection of the set of side-by-side fuselage lobes located at a first cusp of the side-by-side fuselage lobes. A second woven composite preform positioned at a second intersection of the set of side-by-side fuselage lobes located at a second cusp of the side-by-side fuselage lobes. Each of the first and second woven composite preforms are configured to receive a structural component, such that each of the first and second woven composite preforms accommodates vertical load imparted through the structural component.

Abstract: A system for registering multiple point clouds captured by an aircraft is disclosed. The system includes a speckle generator, at least one three-dimensional (3D) scanner, and a processor coupled thereto. In operation, the speckle generator projects a laser speckle pattern onto a surface (e.g., a featureless surface). The at least one 3D scanner scans the featureless surface to generate a plurality of point clouds of the featureless surface and to image at least a portion of the laser speckle pattern. The processor, which is communicatively coupled with the at least one 3D scanner, registers the plurality of point clouds to generate a complete 3D model of the featureless surface based at least in part on the laser speckle pattern.

Abstract: Rotor assemblies for aircraft are described where one or more blades of the rotor assembly includes a blade alignment device that passively orients a blade in response to an airflow around the blade alignment device when the rotor assembly is free-wheeling. One embodiment comprises a method of operating a rotor assembly for aircraft. The method comprises operating the rotor assembly in a free-wheeling state, where the rotor assembly includes a rotary hub that rotates about an axis and a plurality of blades extending radially from the rotary hub. At least one of the plurality of blades includes a blade alignment device. The method further comprises aligning the at least one of the plurality of blades in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state.

Abstract: Retractable propulsor assemblies for aircraft are described that generate lift during vertical take-off, hover, and vertical landing. The retractable propulsor assemblies are deployed from a compartment in a fuselage of the aircraft to transition the aircraft into vertical flight, and are stowed in the compartment during cruise flight to reduce aerodynamic drag on the aircraft. One embodiment comprises a method of operating a VTOL aircraft. The method comprises deploying the retractable propulsor assembly from the compartment of the fuselage to provide the lift for vertical flight. The method further comprises transitioning the VTOL aircraft from the vertical flight to cruise flight, and stowing the retractable propulsor assembly in the compartment during the cruise flight to reduce the aerodynamic drag on the VTOL aircraft.

Abstract: The present disclosure relates to a reconfigurable battery system and method of operating the same. The reconfigurable battery system comprising a plurality of switchable battery modules, a battery supervisory circuit, and a battery pack controller, where the plurality of switchable battery modules electrically arranged in series to define a battery string defining an output voltage. The battery pack controller operably coupled to the battery supervisory circuit to selectively switch, for each of the plurality of switchable battery modules, the battery switch between the first position and the second position such that the output voltage is substantially equal to a predetermined target output voltage.

Abstract: Propulsors (e.g., an electric motor mechanically coupled to a rotor) are described that passively cool the electric motors via an airflow path through the electric motor and out of the rotors. One embodiment comprises a method of cooling an electric motor. The method comprises operating the electric motor of a propulsor for an aircraft to rotate a rotor of the propulsor, where the rotor has one or more air outlets, and where the electric motor has a housing that includes one or more air inlets in fluid communication with the one or more air inlets. The method further comprises generating, by rotating the rotor using the electric motor, an airflow through the electric motor from the one or more air inlets to the one or more air outlets to cool the electric motor.

Abstract: Rotor assemblies for aircraft are described that include a plurality of blades that are disposed vertically on a common axis along different horizontal planes. When the rotor assemblies are free-wheeling, the blades form a vertically stacked configuration, and when the rotor assembly is driven in rotation to generate lift, the blades bloom out from the vertically stacked configuration. At least one of the blades in the rotor assembly has a blade geometry that is different with respect to other blades such that when the blades are vertically stacked and free-wheeling, the collective shape of the blades is aerodynamic in shape, based on the different blade geometry, that reduces aerodynamic drag on the rotor assembly.

Abstract: An aircraft design optimization system and associated aircraft design optimization architecture. The aircraft design optimization system may comprise an input circuit to provide input data and an optimizer circuit to receive the input data and to communicate with a plurality of modules to create output data. At least one abstraction layer can be provided between the optimizer circuit and each of the plurality of modules. The optimizer circuit is configured to output the output data to a post-processing circuit. Each of the plurality of modules implements a different function.

Abstract: An automated inspection system for monitoring a manufacturing process includes a core platform to operatively connect a plurality of systems or subsystems via one or more interfaces. A sensor system operatively coupled with the core platform to monitor one or more characteristics of a manufactured article. An actuation system operatively coupled with the core platform to implement the manufacturing process based on instruction from the core platform. The core platform is configured to receive a first measurement of the one or more characteristics of a composite article from the sensor system after application of a plurality of layers of one or more raw materials; receive data regarding a second measurement of the one or more characteristics from the sensor system after curing the composite article; and generate an alert in response to a determination that a defect exists in the composite article based on the first or second measurement.

Abstract: A method includes receiving a first image. The method also includes detecting a plurality of edges in the first image. The method also includes connecting the edges. The method also includes identifying a contour in the first image based at least partially upon the connected edges. The method also includes determining a convex hull of the contour. The method also includes generating a second image comprising the convex hull.

Abstract: A method includes identifying a first image that is captured at a first time. The method also includes segmenting the first image into a plurality of first image portions. The method also includes identifying a second image that is captured at a second time. The method also includes segmenting the second image into a plurality of second image portions. The method also includes comparing one of the plurality of first image portions and a corresponding one of the plurality of second image portions. The method also includes determining a difference between the first image and the second image based at least partially upon the comparison. The method also includes transforming the first image into a transformed first image based at least partially upon the difference.

Abstract: A method includes receiving a first image that is captured at a first time. The method also includes detecting a location of a first object in the first image. The method also includes determining a region of interest based at least partially upon the location of the first object in the first image. The method also includes receiving a second image that is captured at a second time. The method also includes identifying the region of interest in the second image. The method also includes detecting a location of a second object in a portion of the second image that is outside of the region of interest.

Abstract: A method includes identifying a first image. The method also includes determining a distribution based at least partially upon an intensity of each pixel in the first image. The method also includes determining that the distribution is bimodal. The method also includes dividing the first image to produce a second image in response to determining that the distribution is bimodal. The second image includes a plurality of first pixels and a plurality of second pixels. The method also includes determining that a horizon is defined between the plurality of first pixels and the plurality of second pixels.

Abstract: A method, apparatus, system for tracking an object, the method. A region of interest in an image pair is determined based on a bounding box determined for the object in the image pair. A mask based on the region of interest is applied to the image pair. The mask masks out portions of the image pair outside of the region of interest to form masked images. Intensity averaging is performed on the masked images to detect a set of pixels having a greatest intensity in the masked images. The set of pixels in the masked images is a set of common pixels in the masked images in which the set of common pixels is assumed to have a same location in both of the masked images. A three-dimensional position of the object is determined using the set of common pixels.

Abstract: Presented are passive-release, snap-fit coupling devices for attaching cargo to cargo suspension systems, methods for making/using such devices, and aircraft equipped with underbody suspension systems using passive-release, snap-fit coupling devices for securing payloads. An object mounting device is presented for securing an object, such as a cargo container, to a tether hook of a suspension system, such as an aircraft's payload suspension system. The object mounting device includes a base plate that affixes to the object, and a hook latch mounted onto the base plate. The hook latch includes a guide surface adjacent a catch cavity. The catch cavity releasably receives therein the tether hook. The guide surface is oriented at an oblique angle with respect to the base plate in order to slidably engage the tether hook, upon release from the catch cavity and under the force of gravity, to thereby eject the tether hook from the hook latch.

Abstract: A boundary layer control (BLC) system for embedment in a flight surface having a top surface, a bottom surface, a leading edge, and a trailing edge. The BLC system may comprises an actuator having a crossflow fan and an electric motor to drive the crossflow fan about an axis of rotation. The actuator may be embedded within the flight surface and adjacent the leading edge. In operation, the actuator is configured to output local airflow via an outlet channel through an outlet aperture adjacent the top surface to energize a boundary layer of air adjacent the top surface of the flight surface.

Abstract: Presented are corner attachment assemblies for cargo suspension systems, methods for making/using such assemblies, and aircraft equipped with underbody suspension systems using corner attachment assemblies for securing payload containers. Mounting assemblies are presented for securing objects to tether cables of suspension systems. A representative cargo mounting assembly includes a pair of shoulder clamps, each of which includes a flap that projects from a cup. Each shoulder clamp flap mechanically attaches, e.g., via a flap through-hole with a structurally reinforcing grommet, to a respective segment of a tether cable of a cargo suspension system. In addition, each shoulder clamp cup includes multiple noncoplanar, mutually adjoining contact surfaces. For instance, the cup may have a tetrahedral geometry with three mutually orthogonal, triangular-shaped contact surfaces. Each contact surface attaches, e.g., via a high-strength adhesive, to a respective surface of a corner of a cargo container.

Abstract: Presented are weight distribution systems for aircraft center of gravity (CG) management, methods for making/operating such systems, and aircraft equipped with CG management systems. A method is presented for managing the CG of an aircraft. The aircraft includes first and second landing gears and an airframe that removably attaches thereto one or more payloads and/or hardware modules. The method includes supporting the aircraft on a support leg that operatively attaches to the airframe and, while supported on the support leg, determining if the aircraft pivots onto the first or second landing gear. If the aircraft pivots onto either landing gear, the method responsively identifies a new airframe position for the payload/hardware module that will shift the aircraft's CG to within a calibrated “acceptable” CG range; doing so should balance the aircraft on the support leg. The payload/hardware module is then relocated to the new airframe position.