Abstract: An aircraft, including a fixed nacelle disposed on a wing of the aircraft, the fixed nacelle including a nacelle opening; a proprotor pylon disposed on the wing and rotatable relative to the fixed nacelle between a substantially horizontal position and a non-horizontal position, wherein rotation of the proprotor pylon to a non-horizontal position exposes the nacelle opening; and a movable cover disposed on at least one of the wing and fixed nacelle, said movable cover including a plurality of cover members that are movable between a closed position where at least a portion of the cover members collectively form a protective cover in front of the nacelle opening when the proprotor pylon is positioned in the non-horizontal position and a stowed position where at least a portion of the plurality of cover members are stowed. In other aspects, there is provide a method of covering a nacelle opening.

Abstract: An exemplary cushion for a fuel system is constructed of a lattice structure formed of a material that is substantially nonabsorbent of fuel and has a network of nodes and beams defining cells, an exterior surface of the lattice structure is configured to be oriented toward a fuel cell and an interior surface of the lattice structure is configured to fit to a mounting surface.

Abstract: A scarecrow includes a scarecrow body corresponding generally in shape to a body of a live animal; and an assembled and balanced hollow head of molded plastic construction corresponding in shape to a head of the live animal. The assembled and balanced head includes a front face portion and a rear head portion fixed together to form the head. The front face portion has a first thickness and the rear head portion has a second thickness, the front face portion and the rear head portion being unequal in weight, with the rear head portion having selected areas on an interior surface thereof that are thicker than the first thickness and define an offset weight so that the assembled head is substantially balanced as assembled. An unstable mount is disposed between the body and the head onto which the head is rotatably mounted for 360-degree movement of the head to the body without interfering with free movement of the head, the head being balanced on the unstable mount.

Abstract: An assembly having an aircraft door and auxiliary equipment. The aircraft door and the auxiliary equipment are connected by a flexible deformable bellows having creases. The door comprises a passing through hole and a support joinable to the first end of the bellows. The auxiliary equipment comprises a support joinable to the second end of the bellows and a projecting part. The projecting part is configured to have elevation movement and/or azimuth movement, and the projecting part crosses the interior of the bellows and the hole of the door and protrudes out of the door. At both ends of the bellows a clamp joins and tightens each end of the bellows with the corresponding support. There is a fixed joint between the first end of the bellows and the door and a movable joint between the second end of the bellows and the auxiliary equipment.

Abstract: A cushion length adjusting system for use in an ejection seat of an aircraft may include a seat pan and first cushion length adjuster coupled to the seat pan. The cushion length adjuster may be hingedly or slidingly coupled to the seat pan. The cushion length adjuster may be configured to adjust a leg support length for greater ergonomics for a pilot of an aircraft.

Abstract: A satellite is provided, configured for stacking with another similarly designed satellite and to facilitate separation thereof. The satellite comprises a housing for carrying functional components, having a plurality of pairing arrangements and a separation arrangement. Each of the pairing arrangements comprises a post extending perpendicularly to a horizontal plane of the housing, and first and second guide members. First guide members of the satellite are configured to couple with second guide members of the other satellite when stacked therewith. The separation arrangement comprises a thrust element configured to impart an ejection force to facilitate the separation, and a release assembly configured to selectively facilitate allowing the ejection force to propel one of the satellites, thereby initiating the separation. The first guide member of the satellite cooperates with the second guide member of the other satellite to deflect it from the horizontal plane during separation.

Abstract: A galley message center defines a tablet recess were a tablet is docked, substantially flush with the surrounding bulkhead so that a utensil storage drawer may be closely disposed to the message center and slide out in front of the tablet without the tablet needing to be removed. The docking element of the message center may be hinged to allow the tablet to be folded down with the screen against a recessed surface to protect the screen and prevent undesired or accidental interaction. The utensil storage drawer includes a plurality of features for securely holding utensils when not in use and place all of the stored utensils within reach of the flight staff, in proximity to a galley working surface.

Abstract: A flying insect deterrence system and device is provided. The flying insect deterrence device may include a rotary element, a vertical column, a cordage, a cordage element, and a motor. The flying insect deterrence system may include a base and an insect deterrence device. The insect deterrence device may include a vertical column, a rotary element, a motor, a cordage, and a cordage element. The rotary device is located on top of the vertical column and is powered by the motor that spins a cordage attached to the rotary device to deter flying insects from flying or landing in the area.

Abstract: A self-wicking plant growth receptacle is provided. The device includes a housing having a base opposite and upper side and a plurality of sidewalls extending therebetween. An upper opening is disposed through the upper side providing access to an interior volume dimensioned to removably receive a grow bag therein. A wick port is disposed through the base in fluid communication with the interior volume. A reservoir housing is securable to the base to define an assembled configuration. The reservoir housing includes a lower side and a perimeter sidewall defining a reservoir volume. A lip is disposed about a perimeter of the upper side, wherein the lip includes a plurality of apertures therethrough. A channel extends through the housing between an inlet on the upper side and an outlet on the base, wherein the channel is in fluid communication with the reservoir volume. A filter is removably secured within the channel.

Abstract: A process of joining a wing to an aircraft fuselage comprising the steps of: mapping the wing root of the wing, mapping the center-wing-box (CWB) of the aircraft fuselage, determining the position to provide the hole pattern on the CWB, providing the holes on the CWB, and attaching the wing root to the CWB. Primary and secondary templates with corresponding hole patterns may be used in combination with targets and laser trackers to implement the process. The hole pattern of the wing root can therefore be duplicated on the CWB at a position such that when the wings are joined to the fuselage, the aircraft will have optimum flight performance and dynamic symmetry. A predictive fit is thus provided, based on virtual representation and analysis, and advantageously permits the hole pattern to be provided without requiring the CWB and wing root to be brought together.

Abstract: Disclosed is a door assembly for enclosing a compartment, for instance a cabin attendant seat (CAS) compartment. The assembly generally includes spaced guides for guiding opening and closing movement of a bi-fold door including coupled upper and lower door sections. The door sections are coupled through an interface that allows vertical displacement of the lower door section relative to the upper door section when the door assembly is in the closed condition to engage or disengage latches from respective catches. In some embodiments, the assembly further includes cam latches and a biasing mechanism for driving bi-fold door movement toward the open condition, among other features.

Abstract: An aircraft seat may include an integrated control panel at least partially embedded within an armrest of the aircraft seat. The integrated aircraft seat control panel may include at least one signal path for communicatively coupling the user interface device to at least one component of the aircraft seat. The user interface device may generate signals for at least one control function of the at least one component following an input being received. The integrated aircraft seat control panel may include a textile covering coupled to the armrest and positioned above the user interface device, the textile covering including a plurality of icons configured to indicate the location of the at least one control function on a respective portion of the user interface device. At least one icon is configured to illuminate following a receipt by at least one of a power signal or a light source output.

Abstract: Systems, methods, and apparatus for controlling aircraft roll operations are disclosed. An example system includes a wing actuator coupled to an aileron of an aircraft, an alternate power unit (APU), a control wheel position sensor to measure a control wheel position of a control wheel of the aircraft, a flight control computer (FCC) coupled to the APU and the control wheel position sensor, the FCC to invoke the APU to provide power to the wing actuator, and transmit a control signal to the wing actuator, the control signal to invoke the wing actuator to control the aileron based on the control wheel position, and a differential linkage coupled to the wing actuator and the aileron, the differential linkage to convert first movement of the wing actuator into second movement to control the aileron, the first movement of the wing actuator based on the control wheel position.

Abstract: A reinforced, foldable component for an aircraft is provided, configured to stabilize a high frequency aeroelastic fluttering movement. The reinforced component may include a frame structure defining at least one air chamber, and a plurality of sealed compartments. A shear thickening fluid is disposed in at least one of the sealed compartments, exhibiting a decreasing viscosity responsive to an impact force. The frame structure may define one of an inflatable wing structure, a fairing structure, an aileron structure, and a stabilizer structure, and the like. The foldable component may include an exterior layer with an exterior surface exposed to an external environment and an interior layer adjacent the at least one air chamber, wherein the plurality of sealed compartments are disposed between the exterior layer and the interior layer. The exterior layer or the interior layer may include an impact-resistant fabric layer including a shear thickening material.

Abstract: A method of fabricating a panel for a helicopter airframe configurable in a plurality of helicopter configurations comprises the following steps. Operational characteristics of the helicopter airframe are defined. A skin panel is provided, where the skin panel is configured according to the operational characteristics of the helicopter airframe. A brace region is defined relative to the skin panel based on the operational characteristics of the helicopter airframe and the plurality of helicopter configurations. A brace assembly is operatively connected to the skin panel within the brace region to form a blank panel assembly. Accessories are arranged relative to the blank panel assembly according on one of the helicopter configurations to obtain a configured panel assembly.

Abstract: An electronic monitor can monitor experimental animals in a cage. The cage has one or more walls that enclose a living space for the experimental animals. The electronic monitor is coupled to the cage. The electronic monitor may include a housing adapted to be mechanically coupled to the cage in a predefined position relative to the cage. A substantially sterile barrier is provided between the living space and the external environment in this coupled state. The walls of the cage may include a signal-interface section. An electromagnetic detector may be coupled to the housing to have a line-of-sight through the signal-interface section and into the living space of the cage. The electromagnetic detector is adapted to detect electromagnetic radiation that is transmitted through the signal-interface section. A controller processes a signal received from the electromagnetic detector to determine a status of the experimental animals or the living space.

Abstract: A method of operating a fuel tanker aircraft for in-flight fuelling comprises: transmitting a deploy command signal from a communication unit of the tanker aircraft to a communication unit of a fuel receiver aircraft, to cause a line and drogue to deploy from the receiver aircraft; controlling at least one of the tanker aircraft and the drogue to engage the drogue with a first end of a fuel hose of the tanker aircraft, a second end of the fuel hose being connected to the tanker aircraft; and transmitting a return command signal from the communication unit of the tanker aircraft to the communication unit of the receiver aircraft, to cause the line and drogue to return to the receiver aircraft with the first end of the fuel hose.

Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is translatable relative to the nacelle along the fore-aft direction.

Abstract: Some example systems and methods for retrofitting bulk product dispersal mechanism of aircrafts (e.g., aerial crop dusters, air tankers, airplanes and helicopters) involve replacing one link of the dispersal mechanism's linkage assembly with a powered linear actuator. The linkage assembly connects a manually operated lever in the cockpit to a movable gate at an outlet of a bulk container of the aircraft. The bulk container carries a bulk product, such as dry fertilizer or fire extinguishing liquid. In some examples, the pilot can operate the lever to control the release and aerial dispersion of the bulk material. With the powered linear actuator, however, the lever can be latched at a stationary position, while the powered linear actuator extends or retracts to respectively open or close the gate. In an emergency, a brake on the linear actuator allows the pilot to seamlessly switch from a power mode to a manual mode.

Abstract: A method of controlling at least a first pitch of a first propeller and a second pitch of a second propeller of a hybrid helicopter, the hybrid helicopter having a thrust control and a yaw control that are configured to generate orders for modifying respectively a mean pitch component and a differential pitch component of the first pitch and of the second pitch, the hybrid helicopter having a collective pitch control for modifying a collective pitch component of main blades of the lift rotor. The method includes a step of: keeping with the control system the first pitch and the second pitch within a control domain that varies as a function of information relating to the collective pitch component.