Abstract: Separable partition assemblies provide privacy between adjoining aircraft cabin sections, e.g., between a main passenger cabin section and a section having an emergency exit and a belted toilet seat such as may be provided in executive aircraft. The separable partition assembly includes a bulkhead structure defining a bulkhead passageway opening to allow passenger egress from one vehicle cabin section to an adjoining vehicle cabin section that is provided with at least one panel sized and configured to close the bulkhead passageway. A nonpermanent mounting system mounts the panel to an inboard edge of the bulkhead structure to allow the at least one panel to be separably uncoupled from the bulkhead structure in response to exertion of a force of predetermined magnitude thereagainst to thereby allow unimpeded passenger egress between the adjoining vehicle cabin sections.

Abstract: An aircraft includes the aircraft component. The aircraft component includes an outer skin portion, a plurality of major stiffeners, and a plurality of minor stiffeners. The outer skin portion has an interior side and an exterior side configured to define an exterior boundary of the aircraft. The major stiffeners are integral with the outer skin portion and extend out from the interior side. The major stiffeners are configured to resist global deflection of the aircraft component in response to a bird strike on the aircraft component. The minor stiffeners are disposed between the major stiffeners, are integral with the outer skin portion, and extend out from the interior side. The minor stiffeners are configured to resist perforation of the aircraft component in response to the bird strike on the aircraft component.

Abstract: Embodiments of the disclosure include a redundant control system for a vehicle. The redundant control system includes first and second actuator pistons mechanically coupled to one another and disposed in respective first and second fluid chambers. The first and second actuator pistons are movable by first and second primary stages. One of the primary stages includes a bypass valve with a pilot valve actuatable in response to movement of the first actuator piston.

Abstract: A waste compaction system includes a trolley for collecting waste and a docking station that is integratable into a cabin monument of a vehicle. The trolley includes a housing with chambers for waste, an opening for introducing waste, a vacuum compaction mechanism assigned to a chamber, and a suction port accessible from outside the housing and couplable to the compaction mechanism. The compaction mechanism includes a compaction sheath extending from a bottom of the housing to a frame arranged opposite the bottom, and is fillable through the opening, and a rigid plate is arranged on or in at least one lateral surface of the compaction sheath and moves together with the compaction sheath during the evacuation thereof. The docking station and the trolley mate with each other. The docking station includes another suction port that is couplable to a suction line in the vehicle and the first suction port.

Abstract: An aircraft includes a partition wall for supporting monuments such as lavatories and galleys. The partition wall may support a large majority of the weight of the monuments such that the flooring of the aircraft is relieved of the force from various monuments. Additionally, the partition wall may be used to support the fuselage of the aircraft.

Abstract: A seat array that includes a first and a second seat arranged with their backrests opposite one another, seats being able to move from a sitting position to a lying position, a portion of a dividing wall being arranged laterally with respect to the seats, the portion of dividing wall being provided in such a way as to leave an entry/exit passage, and thus access, to the seats, the entry/exit passage leading to a lane for reaching the first or the second seat, the dividing walls, on their respective end constituting the entry/exit passage provide, externally, a respective footrest, which is positioned in front of a respective third and fourth seats, which are arranged in an opposite direction with respect to the respective seat arranged on the opposite side of the same dividing wall.

Abstract: The disclosure relates to an unmanned aerial vehicle, wherein the fuel cell provides a structural component of the vehicle.

Abstract: Aircraft configuration by applying the following method steps for improving the conventional box wing aircraft concept: dividing both the backward swept front and the forward swept rear wings into root and tip sections, wherein the tip sections (34) of the front wings are more backward swept than the root sections (37), and the tip sections (35) of the rear wings are more forward swept than the root sections (38). Preferred embodiments comprise moving the front wing to the nose and the rear wing towards the rear end of a long fuselage; adding a middle wing and thereby decreasing the wingspan by one third; dividing the middle wing into a backward swept root section (28) and two tip sections (29,30), one forward and another backward swept. The four wingtips on each side are interconnected by a wingtip fence (26), obtaining seven closed frame structures, as well as seven aerodynamic channels for the stream flow.

Abstract: A launch includes a frame including a platform defining a slot designed to slideably receive a rudder of a fixed-wing unmanned aerial vehicle. The launch includes two drive wheels rotatably supported by the frame and defining a space between each other. The space is open to the slot and designed to receive the rudder. The launch includes at least one variable speed drive wheel motor supported by the frame and operatively engaged with the drive wheels.

Abstract: Described herein is an auxiliary support system for a flap coupled to a wing of an aircraft. The auxiliary support system comprises a base fixable relative to the wing. The auxiliary support system also comprises a first track engagement assembly fixed to the base. The auxiliary support system further comprises a second track engagement assembly fixed to the base. The auxiliary support system additionally comprises a track arm attachable to the flap and comprising a first rail, movably engaged with the first track engagement assembly, and a second rail, movably engaged with the second track engagement assembly. The first rail is spaced apart from and non-parallel to the second rail.

Abstract: Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap, an actuator, a first hydraulic module, and a second hydraulic module. The flap is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The actuator is to move the flap relative to the fixed trailing edge. The first hydraulic module is located at the actuator. The second hydraulic module is located remotely from the first hydraulic module and includes a local power unit. The actuator is hydraulically drivable via first pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the actuator via the second hydraulic module and further via the first hydraulic module. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied from the local power unit to the actuator via the second hydraulic module and further via the first hydraulic module.

Abstract: A passenger seat arrangement is provided for a single-aisle vehicle, such as a narrow-body aircraft. In some examples, the passenger seat includes a passenger seat having a seat plane. The passenger seat is positioned such that the seat plane is at a non-square and non-zero acute angle relative to a plane of the aisle. The passenger seat is a non-lie flat seat movable between an upright position and a neutral position. A seat back of the passenger seat is at a non-zero angle relative to a seat base of the passenger seat in both the upright position and the neutral position.

Abstract: A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.

Abstract: Systems and methods include providing an aircraft with a fuselage and a wing assembly rotatable relative to the fuselage about a stow axis between a flight position and a stowed position. The aircraft includes an engine reduction gearbox (“ERGB”) having a retractable driveshaft assembly with an actuation shaft and a first friction plate. Actuation of the retractable driveshaft assembly by the actuation shaft causes the first friction plate to selectively engage and disengage a second friction plate associated with a mid-wing gearbox (“MWGB”) via axially translatable motion of the retractable driveshaft assembly along its rotation axis. When the friction plates are engaged, rotation of the retractable driveshaft assembly imparts rotation to at least one rotor assembly. When the friction plates are disengaged, the wing assembly is capable of selectively rotation with respect to the fuselage about the stow axis between the flight position and the stowed position.

Abstract: A drone comprises at least one propeller for generating lift and an article containment area for containing an article to be carried by the drone. The floor of the article containment area comprises a dynamic support surface for supporting the article and allowing the article to move into, out of and through the article containment area. The dynamic support surface may be a conveyor belt forming the floor of the article containment area.

Abstract: A main rotor blade assembly for a rotary wing aircraft is provided including a main rotor blade root region, a main rotor blade inboard region arranged outboard of said main rotor blade root region, a main rotor blade main region arranged outboard of said main rotor blade inboard region, and a main rotor blade tip region arranged outboard of said main rotor blade main region. At least one of chord, twist, sweep, airfoil shape, and thickness/chord of the main rotor blade assembly has been optimized to achieve balanced high speed forward flight and hover relative to both efficiency and high thrust capability.

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

Abstract: A pressure bulkhead system comprises a pressure bulkhead adapted to be connected to a fuselage of a vehicle to separate a pressurized cabin space of the vehicle from an unpressurized cabin space of the vehicle, and a peripheral pressure frame to sealingly connect the pressure bulkhead to the vehicle fuselage. The peripheral pressure frame comprises an attachment section sealingly attached to an outer rim portion of a first surface of the pressure bulkhead. The first surface, when the pressure bulkhead system is installed in the vehicle, faces the unpressurized cabin space of the vehicle. A flange section is adapted to be sealingly attached to an inner surface of the vehicle fuselage and extends in a direction facing away from the first surface of the pressure bulkhead. A flexible section interconnects the attachment section and the flange section and is flexible to accommodate cabin pressure acting on the pressure bulkhead.

Abstract: A satellite system may have a constellation of communications satellites that provides services to users with electronic devices such as portable electronic devices and home/office equipment. A network operations center may use gateways to communicate with the satellite constellation. The satellite constellation may include sets of satellites with different orbits such as circular orbits with different inclinations, sets of satellites with elliptic orbits, sets of satellites with circular orbits of different altitudes including low earth orbits, medium earth orbits, and/or geosynchronous orbits, sets of satellites with sun synchronous orbits, and/or sets of satellites with other orbits. The orbits of the satellites in the constellation may be selected to provide coverage to desired user population concentrations at different locations on the Earth, while reducing the amount of capacity that goes unused (e.g., is idle) at one or more times of day.

Abstract: A satellite system may have a constellation of communications satellites in orbits such as highly inclined eccentric geosynchronous orbits and low earth orbits. To place satellites in inclined eccentric geosynchronous orbits, a series of launch vehicles may be launched. Each launch vehicle may be used to place a set of satellites, such as a set of three satellites, into a common orbital plane with distinct longitude of ascending node values. To place satellites in low earth orbits, a series of launch vehicles may be launched, each of which releases satellites in sequence from a stack of satellites into a common orbital plane. After desired separations have been produced between the released satellites, circularization procedures may be performed using the propulsion systems of the satellites to place the satellites into final orbit.