Abstract: A method and system providing farm decision support relating to individual animals in a herd in a farm environment includes a brush station having a reader configured to remotely register, via identification devices, an identity of each animal visiting the brush station responsive to a detection unit detecting a repositioning of the brush from a neutral position resulting from an animal pushing against the brush. The reader unit has a detection range within which identity data can be read out from the identification device of each animal. In response to a detected repositioning of the brush, the reader unit registers the identity data from a first detected identification device within the detection range, and forwards the identity data to a processing unit via an output interface. The processing unit stores registered data representing animal visits to the brush station as decision support data.

Abstract: A fish-sorting system for sorting fish in a dragged fishing net (1), wherein the fish are actively sorted by means of a detection device (2, 3) which detects at least one size of a fish to be sorted; a processing unit which compares the size detected by the detection means (2, 3) with the desired size; and a sorting device (4) which retains fish in the fishing net (1) of a size greater than the desired size and which releases fish of a size smaller than the desired size from the fishing net (1) on the basis of the comparison between the detected size and the desired size carried out by the processing unit.

Abstract: Method of device for installation of avionics cabinets, electrical master boxes and IFE bays includes relocating at least some of the systems cabinets toward the front of the aircraft by making use of the space available in the area around the landing gear compartment. To do so, systems cabinets are used which incorporate a structural function. The use of such system cabinet designs thus allows a reduction in the aerodynamic drag and mass of the aircraft, thereby positively impacting fuel consumption and performance of the aircraft.

Abstract: An aircraft fuselage includes at least one space arranged in the aircraft fuselage and at least one wall. The wall resists burnthrough for a period of at least four minutes from outside the aircraft fuselage towards the space, wherein the region of the aircraft fuselage underneath the space does not include burnthrough-resistant insulation. The space may be a cargo compartment of the aircraft or a passenger cabin, while the wall may be designed as a cargo compartment floor, passenger cabin floor or wing/fuselage fairing (belly fairing). The design of the aircraft fuselage results in burnthrough resistance that meets the requirements of FAR §25.856 (b) without any additional burnthrough-resistant insulation in the aircraft fuselage.

Abstract: An aircraft with a fuselage that comprises a framework structure having at least one hollow frame that is integrally formed in one piece and comprises fiber reinforced polymers, the at least one hollow frame defining an integrated ventilation air duct that is adapted for guiding ventilation air into the aircraft.

Abstract: An airfoil configured for low speed performance in an unmanned aerial vehicle includes an upper surface having an upper surface portion with a top local surface angle magnitude of less than 5 degrees at a subsection of a chord and a lower surface having a lower surface portion with a bottom local surface angle magnitude of less than 5 degrees at the subsection of the chord. The chord is defined by a line starting at a leading edge of the airfoil and extending to a trailing edge of the airfoil.

Abstract: A fleet of small spacecraft (“cells”) in low Earth orbit combine to form an integrated Earth observing system providing many observations previously requiring distinct sensing systems. Each cell performs a few relatively primitive functions, including emission, reception, sampling, and recording of radio and microwave signals. Each cell observes over a spherical field of view, samples the received signals independently at many small antenna elements, and stores the data from each element. Data from all cells are sent to a common location where they can be combined in diverse ways to realize a wide range of observing functions. These functions may include ionosphere and gravity field mapping; atmospheric radio occultation; ocean, ice, and land altimetry; ocean scatterometry; synthetic aperture radar (SAR) imaging; radar sensing of soil moisture, land cover, and geological surface properties; and interferometric SAR sensing of surface change.

Abstract: A spacecraft system may include a storage portion (e.g., a first portion and a second portion) and a solar array apparatus that may be configurable in at least a stowed configuration and a deployed configuration. The solar array apparatus may include at least one solar array to collect incident radiation when the solar array apparatus is in the deployed configuration. In one or more embodiments, the at least one solar array may extend away from the storage portion. In one or more embodiments, the at least one solar array may extend between the first portion and the second portion. The solar array apparatus may also include an extendable boom operable to extend the at least one solar array apparatus from the stowed configuration to the deployed configuration.

Abstract: An aircraft seating group has first and second laterally-adjacent passenger seats; a center console positioned between the first and second passenger seats; a center console disposed between the first and second laterally-adjacent passenger seats and having a shelf for supporting a handheld electronic device at approximately an eye level of a passenger in the first passenger seat. The center console may further include a retention system to maintain the electronic device in the shelf in a position allowing the passenger to comfortably view the screen of the electronic device.

Abstract: An electrical energy generator system for an aircraft, the system including a streamlined fairing containing at least one turbine housed in the front portion of the fairing, and an electrical energy generator connected to said turbine. The front portion of the fairing is fitted with air admission means that are movable between an open position in which the turbine is exposed to the stream of air outside the fairing and a closed position in which the turbine is masked inside the fairing. The system may serve to reduce the aerodynamic drag caused by turbulence present at a wing tip for a conventional wing having sharp edges during stages of takeoff, climbing, and cruising; and during stages of descent it makes it possible to recover the kinetic and potential energy that has been accumulated by the aircraft during its stages of climbing and cruising.

Abstract: An aircraft seating group including first and second laterally-adjacent seats, a center console positioned between the seats, a rear privacy shell positioned behind the seats and forming part of the center console, a vertical partition extending forward from the rear privacy shell to divide the center console, and a deployable shelf positioned to one side of the vertical partition, the shelf configured to hold a tablet for viewing by a passenger facing the shelf.

Abstract: A satellite system includes a so-called carrier satellite and a so-called piggyback satellite, each one having an Earth face. The piggyback satellite is attached to the carrier satellite by fastening elements that can be released on command. The piggyback satellite includes propulsion elements suitable for maintaining same in orbit, and the carrier satellite includes propulsion elements for performing a change of orbit of the satellite system including the carrier satellite and the piggyback satellite. The piggyback satellite is attached to the Earth face of the carrier satellite in such a way that the Earth face of the piggyback satellite is essentially perpendicular to the Earth face of the carrier satellite.

Abstract: An aerial platform receives power in the form of light, for example laser light, transmitted via an optical fiber from a remote optical power source. The platform comprises a receiver which converts at least a portion of the light to a different form of power, for example electric power. The platform also comprises a propulsion element which consumes the different form of power to generate propulsive thrust. Supplying power to the aerial platform from a remote source enables the platform to remain aloft longer than a battery or fuel tank carried by the platform would allow. Transmitting the power in the form of light is preferable in many cases to transmitting electric power, because electrical conductors are generally heavier than optical fibers, and are hazardous in the presence of lightning or a high-voltage power line.

Abstract: A dental care product for a pet, such as a dog, includes at least one chew strand having a fragrance and at least one flossing strand. The flossing strand is formed from rawhide and has a thickness less than a thickness of the chew strand. The chew strand and the flossing strand are interwoven with each other along a length of the dental care product to define an interwoven portion of the dental care product. The flossing strand is wrapped around and binds free ends of the chew strand in a wrapped portion of the dental care product. The free ends extend outwardly from the wrapped portion of the dental care product on a side of the wrapped portion opposite the interwoven portion of the dental care product. Advantageously, the dental care product permits the strands to abrade with the pet's teeth in various ways to deliver cleaning benefits.

Abstract: A system and method is provided for controlling electric power in a plug-in vehicle, such as a pure electric vehicle or hybrid electric vehicle. The electric power is controlled from an external power source to one or more predetermined components in the plug-in vehicle. The power source is external to the vehicle and has a maximum power level. Electric power at a charging level from the external power source is received. Based on the charging level and the maximum power level, an available power level is determined. Based on the available power level, the electric power is controlled from the external power source to the predetermined components in the plug-in vehicle.

Abstract: A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

Abstract: A pet training apparatus and waste receptacle that allows a pet to simulate urinating outdoors in an indoors environment. A base frame supports a grated cover on which a permeable sheet is positioned. As a pet urinates, the urine is passes through the permeable sheet and through a plurality of openings in the grated cover. The urine is then collected in a receptacle positioned below the base frame. The permeable sheet includes a plurality of synthetic fibers in order to give the appearance of natural grass. An enclosure can be attached to the base frame, such that the together the enclosure and base frame form a pet crate in which the pet can urinate. A bed can also be placed on the permeable sheet in order to differentiate a sanitary area for the pet to rest. A splash guard prevents urine from leaving the confines of the grated cover.

Abstract: A rocket launch system includes a tubular rocket launcher carriage with electromotive cableway traction drives conveyed beneath a two axis pivot anchored to the earth, elevated into a co-axial transfer tube leading to three primary tether cables whose weight is offset by balloons. The carriage is conveyed to a docking station supported into the stratosphere by a pair of secondary cables suspended under an attachment frame for tensioning balloons. The carriage is engaged by a carriage end gripper guided by two sets of secondary cables and two sets of tertiary cables and lifted by a lower hoist guided by the secondary cables to a lift ring assembly. This lower hoist is supported by an upper hoist suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring guided by two secondary cables, is elevated further, rotated in azimuth and elevation, and rocket ejection occurs from a launch tube during freefall of the carriage, with engine ignition occurring at a safe distance.

Abstract: An interior component carrier system for use in assembly of aircraft interior components in an aircraft includes a retaining system with at least one retaining element. A first connection device for connecting the retaining element to a first aircraft interior component and a second connection device are provided on the retaining element. On the retaining element a structural retainer is provided for fastening the retaining element to an aircraft structure. The interior component carrier system includes a hinge connectable to a second and a third aircraft interior component such that the third aircraft interior component is pivotable about a longitudinal axis of the hinge relative to the second aircraft interior component. The second connection device mounted on the retaining element is configured to be connected to the hinge and/or to a region of the second or third aircraft interior component, that is adjacent to the hinge.

Abstract: An aircraft including a wing, the end of the wing having a wing tip device, wherein the wing tip device includes a moveable region that is rotatable, about an axis of rotation extending out of the plane of the wing tip device, between: (i) a high-altitude cruise configuration in which the moveable region extends downwardly below the wing; and (ii) a ground-operating configuration in which the moveable region extends rearwardly behind the wing such that the ground clearance of the wing tip device is increased.