Abstract: An electronic device and method are provided. The electronic device includes a display, a processor electrically connected with the display, and a memory electrically connected with the processor. The memory stores instructions that when executed cause the processor to display a plurality of objects for executing at least one application, wherein each of the plurality of objects has a second form corresponding to a first form of the display and has at least a part thereof overlapping with another object. The instructions, when executed, cause the processor to display an execution screen of an application corresponding to an object which is selected from among the plurality of objects in response to an input.

Abstract: A display device and a method are provided. The display device includes a network interface connected to a network; an internal storage configured to store at least one content; a display; and a processor configured to control the display to display, in a first area of a user interface (UI) screen, a category list, including a video category and a photo category, to enable selection of one category from the list, and control the display to display, in a second area of the UI screen, at least one thumbnail image corresponding to at least one content stored in at least one external device connected through the network interface and at least one thumbnail image corresponding to the at least one content stored in the internal storage.

Abstract: Methods and apparatus to increase strength and toughness of aircraft structural components are disclosed. An example apparatus includes a composite structure of an aircraft, a stringer coupled to the composite structure of the aircraft, where the stringer and the composite structure form a stringer radius gap. A gap filler is disposed in the stringer radius gap, which includes chopped fibers randomly distributed throughout an entire volume of the gap filler.

Abstract: An autonomous flight vehicle capable of both rotary wing flight and fixed wing flight may include a pair of rotary wing flight thrusters used during rotary wing flight and a smaller pair of hybrid flight thrusters used during both rotary wing flight and fixed wing flight. The larger rotary wing flight thrusters are skewed at an angle to reduce an apparent torque and improve the controllability of the autonomous flight vehicle, while using smaller, and so more efficient, thrusters during fixed wing flight.

Abstract: An apparatus and method are provided for a shape adaptive airfoil configured to be coupled with a tip of an airplane wing. In one embodiment, the shape adaptive airfoil is a blended winglet comprised of a base section coupled with the airplane wing, a blade section projecting in a vertical direction above the base section, and a radius section interconnecting the base and blade sections. Adaptive control structures may be incorporated into leading and trailing edges of the base section and the blade section. The adaptive control structures of the base section may facilitate changing a camber profile of the shape adaptive airfoil. The adaptive control structures of the blade section may enable changes to a toe angle of the blade section.

Abstract: The present disclosure provides a method of for interacting with a button. The method includes determining whether a state of the button is being switched among a normal state, a hover state, and a press state, presenting a first predetermined pattern around the button in response to determining that a state of the button is being switched from the normal state to the hover state; and presenting a second predetermined pattern around the button in response to determining that the state of the button is being switched from the hover state to the press state. The first and second predetermined patterns are displayed to a user switching the button. Through the present disclosure, a clear and accurate interaction indication and the whole interaction process can be presented to the user during button interaction, improving the user experience during interaction.

Abstract: Stringer stiffened composite panels having improved pull-off strength are disclosed. An example stringer includes a first surface, a second surface, an edge, and a chamfer. The second surface is located opposite the first surface and is to be coupled to a composite structure of an aircraft. The edge extends from the second surface toward the first surface. The chamfer extends from the first surface to the edge at an angle between twelve and eighteen degrees relative to the first surface.

Abstract: Disclosed is a spacecraft including a casing having a face, a radiator borne by the face, and a thermal insulation device borne by the radiator. The thermal insulation device includes: —a first screen device able to cover a first zone of the radiator, the first screen device including a thermally insulating and flexible sheet, and at least two springs capable of producing a constant reaction force, the springs being preformed in such a way as to wind up on themselves at rest and being fixed to the insulating sheet, the springs each having an end fixed to the radiator and a free end; and—a traction device able to pull on the free end of the springs to make the sheet cover the first zone and to release the free end in order to expose the first zone to space.

Abstract: An aircraft include a landing gear is disclosed. The landing gear comprises a main strut and an inboard stay assembly connected to the aircraft fuselage such that landing gear loads can be transferred from the inboard stay assembly into the fuselage. The landing gear also comprises a sidestay connected to the wing such that landing gear loads can be transferred from the sidestay into the wing and a link assembly connected to the aircraft such that landing gear loads can be transferred via the link assembly into the aircraft. The landing gear is arranged such that, in use, when the landing gear is extended, substantially all the landing gear loads are transferred from the landing gear to the aircraft via one or more of the inboard stay assembly, the sidestay and the link assembly.

Abstract: A rotary propulsion system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The rotary propulsion system includes an engine that is coupled to a freewheeling unit. A gear system has a torque path coupling assembly between a first gear assembly that is coupled to the freewheeling unit and a second gear assembly that is coupled to a proprotor assembly. The torque path coupling assembly has an engaged position wherein the output of the first gear assembly is coupled to the input of the second gear assembly thereby providing a torque path between the engine and the proprotor assembly. The torque path coupling assembly also has a disengaged position wherein the output of the first gear assembly is independent of the input of the second gear assembly thereby interrupting the torque path between the engine and the proprotor assembly.

Abstract: A system for creating and operating virtual worlds has an Internet-connected server, and software executing on the Internet-connected server from a non-transitory physical medium. The software provides tools enabling creation of a new virtual world, including terrain and objects in the new virtual world, and a physics simulation engine providing simulation for movement of objects in the new virtual world created. The physics simulation engine has a default physics simulation mode wherein simulation approximates real-world physics, and at least one alternative simulation mode wherein simulation applies physics substantially different than real-world physics. Simulation may be switched between the default mode and the alternative mode.

Abstract: The present invention is a double wing aircraft with two fixed wings embodied as either a flying wing configuration or a double wing configuration having a fuselage with smaller external dimensions, larger airlifting area, thinner airfoils, and lighter airframe relative to prior art that altogether is resulting with lower drag, fuel consumption, harmful emissions, and noise, as well as higher speed and flight safety, longer range, and shorter runway when compared to prior art.

Abstract: A deployment system for solar panels has the panels spring loaded to deploy, but held folded against a satellite framework, held folded by trigger bars engaging slots or notches in hinge bodies holding the solar panels. A remotely-operable linear actuator moves the trigger bars to disengage the trigger bars to release the panels to deploy.

Abstract: Techniques for articulating a sunshield to shade portions of a spacecraft are disclosed. In one aspect, a spacecraft includes a body and an articulable sunshield. The spacecraft is configured to operate in an orbital plane, such that the spacecraft has a yaw axis within the orbital plane and directed from a spacecraft coordinate system origin toward nadir, a pitch axis orthogonal to the orbital plane and passing through the spacecraft coordinate system origin, and a roll axis orthogonal to the pitch axis and the yaw axis and passing through the spacecraft coordinate system origin. The sunshield is configured to rotate about an axis substantially parallel to the pitch axis such that a selected location of an exterior portion of the body is shaded from the Sun by a surface of the sunshield irrespective of seasonal and diurnal variations in orientation of the spacecraft with respect to the Sun.

Abstract: Systems and methods according to one or more embodiments are provided for reducing noise levels in a passenger cabin of an aircraft. In one example, an aircraft includes a wing coupled to a fuselage. The wing is configured to heat air to provide a first stream of air from a central portion of a wing segment of the wing extending between the fuselage and a first engine of an aircraft. The first stream of air is at a higher temperature than an adjacent stream of air from the wing.

Abstract: An apparatus for connecting a windscreen and a canopy to an aircraft is provided that includes a first frame for securing to the windscreen and a second frame for securing to the canopy. At least one movable joint connects the first frame to the second frame. The at least one movable joint deforms in response to an object striking at least one of the windscreen and the canopy to allow for relative movement between the first and second frames.

Abstract: An aircraft aerodynamic surface (1) including a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) including a front spar (31) and a trailing edge (32) and a second control surface (4) having a front spar (41), a trailing edge (42), and a pivot device (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) including two lateral ribs (9, 9?), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which includes two lateral ribs (20, 20?), three internal ribs (17, 18, 19), two internal spars (24, 24?) and one internal spar (23).

Abstract: A pin array release and capture chamber system includes a chamber assembly having two parallel plates of pin arrays from which a plurality of pins extends and retract vertically opposite each other so as to release and capture a space vehicle. The pin arrays are separated from each other by a space having two vertical and two horizontal sides, and the space is sized so as to receive the space vehicle. Each pin arrays may be housed in a pin array chamber enclosure. The chamber assembly may be attached to a moving object, such as a host space vessel.

Abstract: A plurality of groups each including a plurality of terminal devices are formed, and each of a plurality of base station devices assigns a channel to each group to enable communication from one of the terminal devices included in the group to which the channel is assigned to another terminal device included in the group, and a receiving unit receives information on the number of terminal devices included in the groups registered in each base station device. A display unit displays information indicating the number of terminal devices for each base station device based on the received information.

Abstract: Techniques disclosed herein describe rendering a 3D menu object in a scene, e.g., from other 3D objects in the scene. A menu component receives a selection of a point-of-origin in a 3D geometric scene having 3D objects. The menu component retrieves predefined menu items and renders, from the selected point-of-origin, the 3D menu object. The 3D menu object presents a selectable list of the predefined menu items.