Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example launch vehicle includes a first space vehicle including a first core structure and a first electric propulsion system, and a second space vehicle including a second core structure and a second electric propulsion system, the second core structure releasably attached to the first space vehicle in a stacked configuration.

Abstract: In an example, a hybrid cargo container system for use with ground transportation vehicles and air transportation vehicles is disclosed. The cargo container system includes a chamfered container body comprising a plurality of sidewalls defining a storage chamber, the plurality of sidewalls comprising a first sidewall, a second sidewall, and a chamfer sidewall attached to the first and second sidewalls. The cargo container system also includes a corner support assembly operably coupled to the chamfered container body. The corner support assembly is operable between a stowed position and a deployed position. Based on the corner support assembly being in the deployed position, the corner support assembly is configured to at least partially support another container stacked thereon for ground transportation, and based on the corner support assembly being in the stowed position, the cargo container system is configured to be stored in a fuselage of an aircraft for air transportation.

Abstract: A shrink mechanism for use with a landing gear of an aircraft. The landing gear includes an outer cylinder rotatably coupled to a frame of an aircraft about a trunnion axis of rotation and a shock strut assembly movably coupled to the outer cylinder so as to reciprocate along a longitudinal axis of the outer cylinder. The shrink mechanism incudes a first shrink link member pivotally coupled to the outer cylinder, a second shrink link member coupling the first shrink link member to the shock strut assembly, a crank member pivotally coupled to the outer cylinder, a drive member coupling the crank member to a walking beam of a landing gear retract mechanism, and a driven member coupling the crank member to the first shrink link member.

Abstract: A method for making a composite part using a reformable mandrel, including contouring a reformable mandrel; placing an uncured composite part on the reformable mandrel; curing the uncured composite part; and removing the reformable mandrel, wherein the reformable mandrel includes a core including a transitional state material having a transition temperature, and a sleeve at least partially surrounding the core and including a heat-resistant flexible material having an operational temperature.

Abstract: Methods and apparatus for performing repair operations using an unmanned aerial vehicle (UAV). The methods are enabled by equipping the UAV with tools for rapidly repairing a large structure or object (e.g., an aircraft or a wind turbine blade) that is not easily accessible to maintenance personnel. A plurality of tools are available for robotic selection and placement at the repair site. The tools are designed to perform respective repair operations in sequence in accordance with a specified repair plan, which plan may take into account the results of a previously performed UAV-enabled inspection.

Abstract: A barrier device is provided for an inlet cowl for an aircraft engine including an inner barrel circumferentially surrounding an opening in the inlet cowl formed along an axis of rotation of the aircraft engine, through which air passes to the aircraft engine, the inner barrel including a face sheet disposed on a radially inward side of the inner barrel relative to the axis. The barrier device includes a containment doubler of the inner barrel, disposed on a radially outward side of the inner barrel, and a blade fragment barrier including one or more strips disposed between the containment doubler and the face sheet, so as to extend circumferentially at least partially around the opening and to occupy a radial distance between the containment doubler and the face sheet.

Abstract: The present disclosure is directed to an exterior surface protective layer for protecting a composite structure from environmental conditions including: at least one curable film; such as at least two curable films, and an electrically conductive material, wherein the electrically conductive material comprises a wire-free electrically conductive material, and/or an electrically conductive polymer weave, wherein the at least one curable film includes at least one of polyurethane, polyimide, polyester or epoxy upon curing, and wherein a weight of the exterior surface protective layer ranges from about 0.02 pounds per square foot to about 0.1 pounds per square foot. An exterior surface protected composite structure and methods of forming an exterior surface protected composite structure are also provided.

Abstract: A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.

Abstract: A bifold door includes a first hinge and a second hinge configured to rotatably couple the bifold door to a doorframe. The bifold door includes a slider configured to slide within a track of the doorframe as the bifold door is opened and closed. At least one of the first hinge, the second hinge, and the slider includes a spherical bearing and a pin.

Abstract: Berthing systems for visiting spacecraft and associated methods. In one embodiment, a berthing system includes a tunnel having an interface surface that defines a hard capture mating plane for mating with a docking system of a target spacecraft. The berthing system further includes hooks disposed circumferentially on the interface surface, one or more pressure seals disposed on the interface surface, spring-loaded guide petals spaced around an inner peripheral surface of the tunnel that are configured to independently slide in the axial direction, and capture latches spaced around the inner peripheral surface that are configured to engage mechanical latch strikers on the docking system.

Abstract: Apparatus, systems, and methods for the inspection of holes in transparent materials, the apparatus including a processor, an illumination probe, and a detection probe. The illumination probe includes a laser light source and a reflective surface and is configured to be inserted into a first hole in the transparent material. The detection probe includes a second reflective surface and a photodetector and is configured to be inserted in a second hole in the transparent material. Laser light is directed onto the first reflective surface within the first hole and is reflected through a wall of the first hole, into the transparent material, and reflected by the second reflective surface to the photodetector. The photodetector transmits a measured light intensity value to the processor, which compares the light intensity value to a standard intensity value to determine whether or not a crazing condition exists in the second hole.

Abstract: Systems and methods are provided for a caul plate having a feature for removal. One embodiment is a caul plate for forming a composite part. The caul plate includes a body that includes a lower surface which faces the composite part, and an upper surface that is opposite to the lower surface. The caul plate also includes a groove in the upper surface to accept a tool to slide the caul plate laterally from the composite part.

Abstract: In an example, a method for accelerated conditioning of a composite core sandwich coupon is described. The method includes setting a first temperature and a first relative humidity level of the conditioning apparatus, wherein a combination of the first temperature and the first relative humidity level correspond to a desired relative humidity level of the plurality of cells of the core layer at room temperature. The method includes maintaining the first temperature and the first relative humidity for a first period, wherein during the first period a core humidity of the plurality of cells in the core layer approaches the first relative humidity level. The method includes determining that the core humidity has reached the first relative humidity level. The method includes, based on determining that the core humidity has reached the first relative humidity level, adjusting the first temperature to a second temperature.

Abstract: A robot end effector for dispensing an extrudable substance comprises a chassis, cartridge bays, attached to the chassis and each shaped to receive a corresponding one of two-part cartridges, and a manifold, comprising a manifold outlet, manifold inlets, and a valve inlet. When the two-part cartridges are received by the cartridge bays, the manifold inlets are in fluidic communication with corresponding ones of the two-part cartridges via static mixers, attached to cartridge outlets of the two-part cartridges. The robot end effector additionally comprises a head assembly, comprising pairs of fittings, configured to selectively supply compressed air from a pressure source to the two-part cartridges when the two-part cartridges are received by the cartridge bays, so that contents of the two-part cartridges are concurrently extruded through the cartridge outlets.

Abstract: Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.

Abstract: Apparatus, systems, and methods for providing a rearward view of an aircraft. The system, apparatus, and methods include one or more cameras disposed on an aft portion of a fuselage of the aircraft, a heads-up display is within a cockpit of the aircraft, and a heads-up control. The heads-up control receives image data from the one or more cameras and generates an image on the heads-up display based on the image data from the one or more cameras to provide a rearward view of an area behind the aircraft. The heads-up control may be configured to determine when an aerial object is within a predetermined range behind the aircraft and responsively generate the image on the heads-up display based on the image data from the one or more cameras to provide a rearward view of an area behind the aircraft in which the aerial object is located.

Abstract: A monument is presented. The monument comprises a floor panel; a left face panel perpendicular to the floor panel; a right face panel perpendicular to the floor panel; and an attachment system connecting the floor panel, the left face panel, and the right face panel. The attachment system comprises a right corner bracket fitting connecting the right face panel to the floor panel; a left corner bracket fitting connecting the left face panel to the floor panel; and a filler panel connected to and extending between the right corner bracket fitting and the left corner bracket fitting.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Abstract: Berthing systems for visiting spacecraft and associated methods. In one embodiment, a non-sealing berthing system includes a tunnel having an interface surface that mates with a docking system of a target spacecraft. The berthing system further includes sliding hooks disposed circumferentially on the interface surface of the tunnel, preload members disposed circumferentially at the interface surface of the tunnel and configured to extend and retract from the interface surface in an axial direction, guide petals spaced around an inner peripheral surface of the tunnel, and soft capture petals spaced around the inner peripheral surface of the tunnel. The soft capture petals include capture latches configured to engage mechanical latch strikers on the docking system of the target spacecraft.

Abstract: Provided are methods of forming stiffened stringer panels with integrated plank structures. A skin member having an inner surface is provided. A plank is positioned onto the inner surface of the skin member. The plank extends from a first side to a second side, and each laminate ply of the set of layered laminate plies is sized to form a geometric profile for each of the first side and the second side. Each laminate ply of the set of layered laminate plies is arranged to extend from the first side to the second side. A stringer is placed onto a support tool. The support tool, and the stringer thereon, is positioned upon an uppermost laminate ply of the set of layered laminate plies. The skin member, the plank, and the stringer are joined.