Abstract: A feed bin with a lateral discharging auger chute is used for the deliver of a bulk particulate feed, the bin including a hopper in which feed is held defining a lower taper floor forming a lower opening which directs the contents by a horizontal auger positioned within the lower opening into a horizontal chute where the particulate feed is dispensed. The feed bin with an auger is a component part of an overall system for the deliver and exchange of bulk feed through storage and exchange bins for the convenience and used by ranchers and bulk feed distributors.

Abstract: A parasitic drag induced boundary layer reduction system and methods for reducing the boundary layer on aircraft, vehicles, and structure. The system may include a suction generator configured to utilize parasitic drag in reducing boundary layer effect and enhancing laminate flow. The suction generator may include at least one of a suction port on a rearward facing surface of an aircraft, a suction vane on each wing of the aircraft, a wingtip vane on each wing of the aircraft, and a slotted tail section on a tail of the aircraft. The system may also include an induction structure configured to introduce airflow to suction created by the suction generator as the aircraft is in flight.

Abstract: An aircraft structure 101 comprising a skin panel 111, having an outer surface forming an external face of the structure, and an inner surface internal to the structure, the aircraft structure 101 also comprising a plurality of stringers 150 extending along a length of the inner surface of the skin panel, and an inner panel 112 spaced apart from the inner surface of the skin panel 111, so as to form an internal cavity adjacent to the skin panel, and wherein the stringers 150 are located within the cavity.

Abstract: A window assembly particularly for use in a commercial airplane is provided. Many windows are provided on most commercial passenger airplanes. Solar radiation causes the passage of infrared heat radiation through each window assembly into the passenger cabin during daylight hours. The disclosure involves the window assemblies of airplanes and the use of a protective coating that is bonded to the outermost surface of an outermost window pane, with the outermost window pane bonded to an inner window pane of the airplane window assembly. The protective coating has a metallic element component that has the capability of reflecting an effective amount of infrared heat radiation from solar radiation away from passing through the window assembly and into the cabin of the airplane.

Abstract: A method for growing grapevines in a root inhibiting vessel permanently planted in previously existing solid waste landfill mounds is disclosed. The vessel or container is a porous polymeric bag or fabric sleeve liner closely received in the container. A fabric disc is positioned in the bottom of an excavated hole in the cover layer of a landfill. The fabric liner is needle-punched to create a rough surface capable of trapping the roots of the growing grapevine and direct the roots into the side of the container such that the apical dominance of the root is stopped to restrict growth and promote root branching on the inside of the container to create a fibrous root system within the container.

Abstract: A system and method are provided for controlling the power setting of an aircraft engine when the current height-above-terrain (HAT) value Hc is less then a predetermined minimum H(min). The system includes a ground proximity unit (GPU) for measuring Hc, one or more sensors coupled to the engine for detecting an out-of-range operating condition of the engine, an engine control unit (ECU) coupled to the GPU and the one or more sensors and the engine, for controlling operation of the engine in response to Hc, H(min) and the engine operating values. When the one or more sensors detects an out-of-range operating condition normally curable by reducing the engine power setting, the ECU is prevented from automatically reducing the power setting of the engine if Hc<H(min). No pilot action is required.

Abstract: Methods and apparatus to control a gap between movable aircraft wing components are disclosed. An example apparatus includes a body having a trailing edge and a leading edge. The leading edge is to be coupled to an aircraft wing. The trailing edge is to engage a flap of the aircraft wing. The body includes a structure located between the trailing edge and the leading edge. The structure is to engage the flap to maintain a distance between the body and the flap.

Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

Abstract: Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.

Abstract: An aircraft monument comprising a first compartment and a cabin attendant seat having a backrest and a seat element. The seat element is movable relative to the backrest between a folded position, wherein a seat surface of the seat element extends substantially parallel to a backrest surface of the backrest, and an unfolded position, wherein the seat surface of the seat element extends substantially perpendicular to the backrest surface of the backrest. The cabin attendant seat is movable relative to the aircraft monument between a stowed position, wherein the cabin attendant seat, with the seat element being in its folded position, is received in the first compartment of the aircraft monument, and an operating position, wherein the cabin attendant seat is disposed outside of the first compartment of the aircraft monument in a position which allows the seat element to be moved into its unfolded position.

Abstract: An aircraft landing gear including an axle and a wheel (5) that includes a rim (6) mounted to turn on the axle about a first rotation axis (X1), the landing gear further comprising an actuator (12) for driving the wheel (5) in rotation. The rim (6) includes obstacles (33) that project from a lateral face (F) of the rim and the driving actuator includes a lead screw (32) mounted to turn about a second rotation axis (X2) perpendicular to the first rotation axis (X1) and adapted to cooperate with the obstacles of the rim to drive the wheel in rotation.

Abstract: A spring assembly elongate along a longitudinal direction includes a first spring that includes a first spring member and a first elongate member that extends from the first spring member along the longitudinal direction. The spring assembly includes a second spring including a second spring member and a second elongate member that extends from the second spring member along the longitudinal direction. The second elongate member extends through the first spring member, and the first elongate member extends through the second spring member such that the first and second spring members are spaced apart with respect to each other along the longitudinal direction.

Abstract: Systems, devices, and methods for impacting, by a small unmanned aerial vehicle (SUAV), a net having at least three sides; and converting the kinetic energy of the SUAV into at least one of: elastic potential energy of one or more tensioned elastic cords connected to at least one corner of the net, gravitational potential energy of a frame member connected to at least one corner of the net, rotational kinetic energy of the frame member connected to at least one corner of the net, and elastic potential energy of the frame member connected to at least one corner of the net.

Abstract: An aerial balloon system comprising a payload platform suspended from an inflated balloon by means of a balloon cable, and an anchoring cable attaching the platform to an anchor point beneath it. The balloon cable and anchoring cable are attached to the payload platform by means of a connecting element pivotally attached to the platform. The platform may include a servo controlled pitch stabilizing system using the input from a pitch sensor mounted on the platform to control an angular actuator to change the angle which the platform makes with the pivoted connection element. Additionally, the platform may include a servo controlled orientation stabilizing system using the input from an orientation sensor mounted thereon to control the departure of the orientation of the platform from a predetermined orientation. This may be readily accomplished using a variable pitch rotor, the pitch being controlled by the orientation sensor signal.

Abstract: The present disclosure relates to an animal ball. The animal ball includes a hollow sphere having a first half and a second half mate-able with said first half. The first half includes a first wall and a first rim and the second half also a second wall and a second rim. In addition, the animal ball includes a mating fastener including a first fastening portion and a second fastening portion. The first fastening portion is connected to the first wall and the second fastening portion is connected to the second wall and the first fastening portion is spaced from the first and second walls.

Abstract: Techniques for performing orbit raising, north-south stationkeeping, east-west stationkeeping, and momentum management with thrusters disposed on a spacecraft are disclosed. The spacecraft includes at least one thruster support mechanism (TSM), including a pointing arrangement and an elongated structural member, the structural member having a long dimension defining a first axis a proximal portion of the structural member is attached to the pointing arrangement each of the thrusters is fixedly coupled with a distal portion of the structural member. The pointing arrangement includes a first, second, and third revolute joint, the first revolute joint being rotatable about the first axis; the third revolute joint being rotatable about a third axis, the third axis being fixed with respect to the spacecraft; and the second revolute joint being rotatable about a second axis, the second axis being orthogonal to each of the first axis and the third axis.

Abstract: An air purification system includes a photocatalyst on a support disposed to contact airflow through an airflow channel passing across or through the support; an ultraviolet light emitting diode (UV-LED) disposed to emit ultraviolet light onto the photocatalyst, the UV-LED operated at a less than one hundred percent duty cycle, the duty cycle determined at least in part as a function of a desired minimum volatile organic compound conversion rate of air flowing through the airflow channel and a desired maximum by-product concentration of air flowing through an outlet of the airflow channel.

Abstract: A stowage bin cover assembly coupleable to a stowage bin is provided. The stowage bin cover assembly includes a stowage bin cover coupleable to the stowage bin, the stowage bin cover including a first groove; and an anti-slip strip coupleably received in the first groove. The anti-slip strip can be positioned and oriented to project above an uppermost outer surface of the first groove such that the anti-slip strip will frictionally engage a payload received in the stowage bin, the frictional engagement resisting movement of the payload. Related methods are also provided.

Abstract: Aspects of the present disclosure generally relate to an SMA actuator that includes a cooling device disposed within a torque tube. In one aspect, the cooling device includes a sliding sleeve, an expandable sleeve, and plurality of cooling fins coupled to the expandable sleeve. Axial movement of the sliding sleeve relative to the expandable sleeve facilitates radial expansion of the expandable sleeve and urges the cooling fins into contact with the torque tube. The cooling fins function as heat sinks when in contact with the torque tube to facilitate the removal of heat from the torque tube to increase the cooling rate of the torque tube. During heating of the torque tube, the cooling fins may be spaced apart from the torque tube to reduce the thermal mass that is heated, thus increasing the heating rate of the torque tube.

Abstract: An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it.