Abstract: A free-floating spherical gimbal (“gimbal”) that includes a moving portion substantially spherical in shape and partially enclosed within a larger spherical and stationary cavity. The moving portion of the spherical gimbal is maintained in a location without direct mechanical contact with the stationary cavity.

Abstract: Cell-based space systems with nested-ring structures that interlock and can change configuration to support a mission are provided. The cells may self-assemble into a larger structure to carry out a mission. Multiple rotatable rings may be included in a cell, with a payload/control section in the center. The rings may provide power and/or data to trams that move about the rails. Trams may interlock with other cells, carry sensors or other devices, etc. Cells may be stowed in a cell stack that is deployable. Such cell-based systems may have various applications in space, on Earth, other celestial bodies, and underwater.

Abstract: Wire holders removably retaining at least one wire for assembling a wire harness and methods for assembling a wire harness are provided. In one example, the wire holder includes a base section having a base bottom for positioning on a wire harness layout sheet. The wire harness layout sheet includes a wire routing pattern for forming the wire harness. A clip section extends generally upwardly from the base section and at least partially surrounds a clip channel having a channel diameter. The base section has a base height defined from the base bottom to a lowest point of the clip channel. A ratio of the channel diameter to the base height is from about 6:1 to about 9:1.

Abstract: Flight control systems, flight control methods, and aircraft are provided. An aircraft including a system and a method for receiving, via a fuel switch, a first control signal indicative of an off position on a fuel switch, determining a throttle resolver angle of a throttle controller in response to the first control signal, comparing the throttle resolver angle to a threshold throttle angle, and generating a pilot warning in response to the first control signal and the throttle resolver angle exceeding the threshold throttle angle.

Abstract: Sealers and methods for making a sealer are provided. In one example, the sealer includes an exterior wall extending in a longitudinal direction and at least partially surrounding a first channel. A first plurality of interior walls are spaced apart from each other and are disposed in the first channel transverse to the longitudinal direction to subdivide the first channel into a first plurality of cells.

Abstract: An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.

Abstract: Apparatuses and methods for facilitating fastening of a fastener are provided. In one example, the apparatus includes a body portion that extends distally from a body proximal portion to a body distal portion. A head portion extends distally from the body distal portion. A first prong that extends distally from a first prong proximal section that has a first thickness to a first prong distal section that has a second thickness that is less than the first thickness. A second prong that extends distally from a second prong proximal section that has a third thickness to a second prong distal section that has a fourth thickness that is less than the third thickness. The second prong is spaced apart from the first prong to define a gap therebetween that is configured to receive the fastener.

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: A cupholder assembly adapted to be mounted to a support structure and a table including a cupholder assembly are provided. In one example, the cupholder assembly includes a housing that extends in a distal direction from a proximal housing portion to a distal housing portion. The housing is configured to pivotally couple to the support structure to move between a mounted position and a rotated position that is rotated relative to the mounted position. A cupholder subassembly is slidingly coupled to the housing to move between a stowed position substantially within the housing and a deployed position extending from the housing in the distal direction.

Abstract: The disclosed embodiments relate to methods and systems for avoiding a collision between an aircraft on the ground and an obstacle using a three-dimensional visual indication of the area or plane of winglets on the wingtips of the aircraft. The method includes receiving a video image from a camera positioned in one of the winglets, the video image representing a field of view through which the winglet of the aircraft will pass along a present heading of the aircraft. Next a processor determines a three-dimensional area or plane within the field of view through which the winglet of the aircraft will pass. An overlay is displayed within the field of view to assist the pilot in avoiding collisions with obstacles.

Abstract: Apparatuses for supporting an object adjacent to an aircraft are provided. In one example, an apparatus for supporting an object adjacent to an aircraft includes a rotational tray assembly that includes a support subassembly. A platform subassembly is pivotally coupled to the support subassembly and is configured to support the object. A drive screw subassembly is operatively coupled to the platform subassembly and the support subassembly to move the platform subassembly relative to the support subassembly. The rotational tray assembly is configured to couple to a lift to position the rotational tray assembly adjacent to the aircraft.

Abstract: Adapters for use with a driving device for turning a knob, and methods for making and using such an adapter are provided. In one example, an adapter includes a shaft that extends distally from a proximal end portion to a distal end portion and that defines a longitudinal axis. The proximal end portion is configured to operatively couple to the driving device for rotating the shaft about the longitudinal axis. An adapter body is coupled to the distal end portion of the shaft. At least one engaging member is disposed radially outward from the longitudinal axis and is configured for removably engaging the knob. A collar surrounds at least a portion of the at least one engaging member.

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 system includes a curing assembly for low temperature curing and residual stress relief of material substrates. The curing assembly includes a first exposure chamber configured to expose the material substrate to UV radiation, and a second exposure chamber configured to expose the material substrate to Gamma radiation. In some embodiments, a mixing apparatus may mix nano-filler particles into the material substrate prior to exposure to Gamma radiation. The cure assembly may also include a control system for determining exposure dosages and exposure times based at least in part, on the material properties of the material substrate.

Abstract: The virtual camera system supplies terrain views to occupants of an aircraft, by employing a virtual reality image generator, disposed on the aircraft, that generates a terrain display image corresponding to a perspective based on supplied position data. At least one aircraft position sensor disposed on the aircraft supplies actual aircraft position as a position data to the virtual reality image generator. A display device disposed on the aircraft and coupled to the virtual reality image generator to reproduce the terrain display image for viewing by passengers within the aircraft. The image generator includes processor programmed to generate the terrain display image using actual aircraft latitude and longitude relative to the Earth and further using a synthetic altitude that differs from the actual aircraft altitude. The synthetic altitude is used above actual aircraft altitudes of a predetermined threshold; otherwise the actual aircraft altitude is used.

Abstract: Many in the space weather community consider our understanding of the buoyancy of the thermosphere and its effects on the orbits of satellites in Low Earth Orbit (LEO) to be insufficient during short time frames. Disclosed herein is an approach for making on-demand thermosphere buoyancy measurements using a deployable low mass retroreflector with CubeSat-like dimensions. A CubeSat storing many retroreflectors can dispense one or more of these passive satellites according to a predetermined schedule or on-command, in response to an observed space weather phenomenon like a coronal mass ejection. With measurements of the orbit decay from these passive satellites, a better understanding of the relationship between space weather and orbital decay can be established with relatively low cost.

Abstract: The modular networking system supplies data and aircraft power to an inflight entertainment, communication or cabin management device within the aircraft. At least one universal module package for placement within the passenger cabin carries an Ethernet switch which has a processor programmed to support deterministic networking, such as according to AVB/TNS protocols. Devices within the cabin are attachable to ports on the Ethernet switch. A power converter circuit and power injector circuit within the module package supply power to devices attached ports on the Ethernet switch. A microcontroller-controlled circuit switch selectively admits or inhibits supply of power attached devices in response to the received control data from the avionics system.

Abstract: A vane assembly for distribution of a stratified fluid in an aircraft is taught herein. The vane assembly includes a housing including a housing inlet and a housing outlet. The housing inlet is configured to receive the stratified fluid with the stratified fluid including a first portion and a second portion. The housing outlet is configured to exhaust the stratified fluid. The housing defines an interior housing volume between the housing inlet and the housing outlet. The vane assembly further includes a vane disposed within the interior housing volume and bisecting the interior housing volume. The vane includes a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The trailing edge is angularly offset from the leading edge.

Abstract: Flight control information systems, flight guidance display, and aircraft are provided. A navigational information system includes an input configured to receive a flight plan wherein the flight plan includes a first waypoint, a second waypoint, a third waypoint, and future waypoints, a user interface operative to generate a control signal in response to a user input, a display configured to display a graphical user interface, a processor operative to receive the flight plan from the input, to generate the graphical user interface to include to the first waypoint and the second waypoint and to couple the graphical user interface to the display, the processor being further operative to generate the graphical user interface in to include the first waypoint and the third waypoint in response to the control signal and to couple the graphical user interface to the display.

Abstract: Methods for monitoring engine health of an aircraft having a first engine and a second engine are provided. In one example, the method includes obtaining a first turbine gas temperature of the first engine and a second engine turbine gas temperature of the second engine from a first flight. The first turbine gas temperature and the second turbine gas temperature are related to each other to define a first value. The first value is compared to a data set for monitoring the engine health.