Abstract: An inflatable unit load device that is used to deploy cargo from an aircraft is described herein. In some instances, the inflatable unit load device may include a bladder having one or more inflatable interior bladder cells and a top surface, the top surface of the bladder forming a rigid support surface when the bladder is inflated on which cargo can be loaded, an outer material that positions the one or more inflatable interior bladder cells of the bladder, and a cargo retaining system that retains the cargo on the top surface.

Abstract: A method for controlling a position of a flap of an aircraft includes: receiving, by an actuator, a signal indicative of a desired flap position; when the desired flap position is a retracted flap position: moving the carriage along a track to a first carriage position thereby pivoting the flap to the retracted flap position where the flap is at a neutral flap angle; when the desired flap position is an intermediate flap position: moving the carriage along the track to a second carriage position thereby pivoting the flap to the intermediate flap position where the flap is at a negative flap angle; when the desired flap position is an extended flap position: moving the carriage along the track to a third carriage position thereby pivoting the flap to the extended flap position where the flap is at a positive flap angle. An aircraft flap deployment system is also disclosed.

Abstract: Various aspects of the disclosure generally relate a fish trap for use in waters among marine predators which use echolocation. In one aspect the fish trap has acoustic masking properties. In one aspect the fish trap may be a lightweight, collapsible column for use by small commercial vessels and recreational fishing. In one aspect the fish trap may have an overlapping net, forming a double seam for added strength. In one aspect the fish trap may have reinforcing wire along bridle attachment points to hold heavier loads of fish.

Abstract: A landing gear door system for a landing gear compartment includes a door pivotable about a pivot pin configured for disposition in a longitudinal direction on an airframe, and a mechanism configured to rotate the door about the pivot pin between a closed position, in which an outer surface of the door panel is configured to provide aerodynamic continuity with an outer aircraft skin of the airframe, and an open position, in which the door is rotated into the landing gear compartment and an opening is exposed. The door has a door panel rigidly connected with an arm such that the door panel and arm generally form a V-shape as viewed in the longitudinal direction.

Abstract: To provide a parachute device capable of quickly and reliably opening a parachute even when an airflow effect during flying or falling of a flight device cannot be immediately obtained. A parachute device (4) includes a parachute (400), a parachute accommodation section (40) configured to accommodate the parachute, at least one flying body (43) connected to the parachute, and an ejection section (41) configured to hold the flying body and to eject the flying body held, and the flying body includes a flying body main body section (44) engaged with the ejection section, and a gas generating device (45) disposed in an internal space (440) defined by the ejection section and the flying body main body section, and configured to generate gas.

Abstract: An apparatus an unmanned aerial vehicle recovery system is provided. The apparatus includes a base to mount to an unmanned aerial vehicle. The apparatus further includes a housing to engage the base. In addition, the apparatus includes a parachute disposed within the housing. Also, the apparatus includes a deployment mechanism to deploy the parachute. The deployment mechanism is to eject the housing away from the base upon a triggering event.

Abstract: The present invention relates to a device for directly controlling a blade which comprises a stator (1), at least one blade carrier (7) composed of at least one curved magnet (6), the blade carrier (7) being secured to at least one blade (3) and pivotally coupled to the rotor (8) for varying the alpha angle of said blades with the excitation of the stator (1). The stator (1) is a partially spherical stator, the stator core (1) being the intersection of the blade axis (22) and the rotor axis (20), said stator being radially close to the magnets (3) to control the rotation of the blades (3) around the blade axis (22). A magnetic ring (5) holds the blades (3) in a neutral position, the system can be compared to a cyclically controlled mechanical oscillator, the frequency, phase and amplitude of the oscillation being controlled by said stator. Device providing a compact, lightweight and robust solution for controlling the direction of an aircraft.

Abstract: A control system for an aircraft includes a hydraulic pump, first hydraulic line, second hydraulic line, a first actuator coupled with a first control surface, a second actuator coupled with a second control surface, and a third actuator coupled with a third control surface. The first control surface and the second control surface are at a distance to each other and symmetrically relative to a symmetry axis. The third control surface is substantially on the symmetry axis, and the first hydraulic line and the second hydraulic line are connected to the hydraulic pump. The first actuator is connected to the first hydraulic line, and the second actuator is connected to the second hydraulic line. The third actuator is connected to the first hydraulic line downstream of the first actuator at a junction point, and the first hydraulic line at least partially includes a larger diameter than the second hydraulic line.

Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.

Abstract: A cockpit for an airplane having, in a plan view, an aft direction, a central longitudinal axis parallel to the aft direction and a rear axis perpendicular to the central longitudinal axis. The cockpit as seen in the plan view comprises: a first seat having a first seating surface with a first seat rear edge passing through an intersection between the longitudinal and rear axes, the first seat being disposed within the cockpit and configured so as to allow a pilot sitting on the first seating surface to perform pre-determined primary pilot functions; and a second seat having a second seating surface with a second seat rear edge.

Abstract: A container for dropping from an aerial vehicle in flight comprises an upper wall, a lower wall, a plurality of side walls, and a plurality of air brakes comprising flat panels. A plurality of side air brakes, wherein each side air brake is connected to a corresponding side wall at or near an upper edge thereof, is freely pivotable around a side air brake pivot axis at or near the upper edge of the corresponding side wall from a passive position, in which the side air brake extends substantially parallel to the corresponding side wall, to a deployed position, in which the side air brake extends substantially transversely relative to the corresponding side wall, by air flowing between the side air brake and the corresponding side wall.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon for controlling deployment of aircraft escape and ejection seat subsystems. The instructions, in response to execution by a first sequencer, cause the first sequencer to perform operations which may comprise receiving a power input, determining a seat location and a seat identity of a first ejection seat in which the first sequencer is installed, determining an ejection mode, sending a first deploy command to an escape path clearance subsystem, determining a deployment sequence for a seat rocket catapult subsystem and a plurality of ejection seat subsystems of the first ejection seat based on the seat location, the seat identity, and the ejection mode, sending a second deploy command to the seat rocket catapult subsystem, and sending a series of third deploy commands to the plurality of ejection seat subsystems.

Abstract: A vehicle fishing rod holder with a rod holder body that is couplable to the bed of a truck in a locked configuration utilizing one or more mounting brackets. The rod holder body defines a holding channel for a fishing rod and a discontinuous slot for receiving a rod reel post of the fishing rod. A locking bar is coupled to the rod holder body and is operably configured to selectively lock the rod and reel into place by being positioned over the rod reel post. The rod holder body is also vertically adjustable using a clamping member and rotationally adjustable or pivoted using one or more arms.

Abstract: A latch assembly may comprise a keeper and a lever. The keeper may include a keeper channel defined at least partially by a first channel surface and a second channel surface. The lever may be configured to rotate relative to the keeper and between an engaged state and a released state. The lever may comprise a shaft and a lever protrusion extending from the shaft. The lever protrusion may be defined at least partially by a proximal surface and a distal surface. The keeper channel may be configured to receive the lever protrusion. In the engaged state, the proximal surface of the lever may contact the second channel surface of the keeper and the first channel surface of the keeper may be spaced apart from the lever protrusion.

Abstract: An actuation system for a control surface for an aircraft includes a first, second, third and fourth actuator, a first and second bell crank, and at least one push pull rod system. Each of the first and second bell cranks comprises a first and a second crank arm, the first and second crank arms intersect with and are joined to each other at an intersection, the first and second crank arms extend from the intersection at an angle to each other, the first bell crank is pivotally connected to the sub-structure by a first pivot extending through the first bell crank's intersection, and the second bell crank is pivotally connected to the sub-structure by a second pivot extending through the second bell crank's intersection.

Abstract: An autopilot device for attaching to and exerting forces upon a control wheel of an aircraft includes an actuator fixed with a base, the actuator adapted to move a weight between a left-most position, a center position, and a right-most position. When the weight is in the center position, the base has a center-of-gravity vertically aligned with the rotational axis of the control wheel. When the weight is left or right of the center position, the weight causes a left or right rotational moment on the control wheel, respectively. A controller is connected with the actuator and a power source and is adapted to detect flight parameters including an aircraft orientation, an aircraft heading, and a desired flight path. The controller applies power from the power source to the actuator to move the actuator and weight, thereby causing the aircraft to intercept and track the desired flight path.

Abstract: An example aircraft disclosed herein includes a wing, a spoiler rotatably coupled to the wing, the spoiler movable between a cruise position and an upward position and between the cruise position and a droop position, and a spoiler actuation system coupled to a hydraulic system of the aircraft, the spoiler actuation system including a first piston and a second piston, a rack coupled between the first piston and the second piston, the rack movable between a first position and a second position, a pinion coupled to the rack, the pinion to rotate between a third position and a fourth position when the rack moves between the first position and the second position, a first crank arm coupled to the pinion, the first crank arm to rotate with the pinion between the third position and the fourth position, and a second crank arm coupled to the first crank arm and to the spoiler, the second crank arm to move the spoiler between the cruise position and the upward position when the first crank arm rotates between the thir

Abstract: An up-lock apparatus for landing gear of an aircraft includes a hook member configured to receive an up-lock roller pin of the landing gear when the landing gear is retracted. An up-lock actuator is coupled to the hook member and is configured to maintain the hook member in a locked state responsive to a first movement of the up-lock roller pin against the hook member to thereby prevent deployment of the landing gear. The up-lock actuator is further configured to allow the hook member to move to a released state responsive to a second movement of the up-lock roller pin against the hook member to facilitate deployment of the landing gear.

Abstract: A wild game call includes a bugle tube and a damper. The bugle tube includes a first end with a first aperture, a second end with a second aperture, and a wall extending from the first end to the second end. The wall defines an interior volume, and the first aperture and the second aperture provide access to the interior volume such that a flow path is defined through the bugle tube from the first end, through the second end, and out the second end. The bugle tube includes a metal and is configured to generate sound waves by vibrating responsive to air flowing along the flow path. The damper surrounds the outer surface of the wall of the bugle tube between the first end and the second end and may reduce unwanted ringing while improving the sound of the bugle call.

Abstract: An electronic release system for an aircraft ejection system may comprise: a controller; a plurality of release devices in operable communication with the controller; a plurality of pins, each pin in the plurality of pins operably coupled to a release device in the plurality of release devices, the controller configured to: receive an indication that an ejection event from an aircraft has been initiated, command activation of the plurality of release devices, and in response to commanding the activation, releasing the plurality of pins from an ejection seat.