Abstract: A fuselage section of an aircraft has an inner surface with a non-circular contour. A pressure bulkhead for use in the fuselage section has a non-circular outer edge that is aligned with the non-circular contour of the inner surface of the fuselage section. The pressure bulkhead has a spherically-shaped inner section having radially arranged stiffening units and a non-spherically outer section having additional radially arranged stiffening units; the stiffening units corresponding to each section do no extend into the other section. The pressure bulkhead is attached to the fuselage section. A method of manufacturing a fuselage section having such a pressure bulkhead is also provided.

Abstract: An aircraft landing gear assembly has a main strut and a bogie beam pivotally coupled to the main strut via a coupling assembly. The coupling assembly is arranged to define a bogie beam pivot axis relative to the main strut which is spaced from the landing gear assembly, and perpendicular to the direction of travel. The coupling assembly has a pair of arms, each having an upper pivotal coupling to the main strut and a respective lower pivotal coupling to the bogie beam. Each arm has a respective connection axis which intersects respective axes of its upper pivotal coupling and lower pivotal coupling. The upper pivotal couplings and lower pivotal couplings are arranged such that their connection axes intersect at a virtual pivot axis which defines the bogie beam pivot axis.

Abstract: A spacecraft includes at least a first thruster support mechanism (TSM) and a second TSM, each TSM including a pointing arrangement, an elongated structural member and thruster for performing orbit raising north-south stationkeeping, east-west stationkeeping, and momentum management. A first pointing arrangement is articulable only by way of first and second revolute joints, the first revolute joint being rotatable about a first axis fixed with respect to the spacecraft. The second pointing arrangement is articulable only by way of third and fourth revolute joints, the third revolute joint being rotatable about a third axis fixed with respect to the spacecraft. The first axis and the third axis are asymmetrically arranged with respect to a spacecraft coordinate system origin such that the first and third axis are at acute angles to a spacecraft pitch axis and the acute angle of the first axis is less than that of the third axis.

Abstract: A spacecraft includes: a body a surface of revolution connected with the body, and a heat engine positioned at the center of the surface of revolution. The surface of revolution has a substantially open hollow torus shape with a transverse cross-section of a circle and two diametrically opposite portions each having a curvature extending from the circle. A first portion of the diametrically opposite portions has an opening and forms a solar concentrator for concentrating solar radiation in the direction of the heat engine. The first portion forms a primary solar radiation reflector. A second portion of the diametrically opposite portions is coaxial with the first portion and forms a secondary solar radiation reflector. The opening is configured so that the solar radiation passes in the direction of the center of the surface of revolution after reflection at the primary and secondary reflectors.

Abstract: A system comprising an unmanned aerial vehicle launch tube comprising a sabot disposed in an interior of the launch tube, the sabot having a first clasp tab and an expandable skirt. The sabot is hollow, and the expandable skirt has a circumferential skirt protrusion and is configured to provide a pressure seal with the inner circumferential wall of the launch tube. The system further comprises a clasp detachably coupled to the first clasp tab and contacting the inner circumferential wall of the launch tube.

Abstract: Using a programmable aerial drone assembly configured to actuate a gearbox that repositions one or more solar panels, automated drones may be deployed to adjust the position of the solar panels throughout the day according to a programmable schedule. In exemplary embodiments, a plurality of docking stations may be deployed throughout a solar farm, such that one or more solar panels are mechanically coupled to the docking station, wherein the docking station includes a landing platform and a gearbox mechanically configured to adjust the position of the solar panels. One or more gearbox arms protrude from the top of the docking station landing platform, and corresponding arms on the aerial drone assembly engage the gearbox arms to actuate the gearbox. The aerial drone assembly also includes landing posts that register with the docking station.

Abstract: A rudder control apparatus includes a pair of pedal assemblies, coupled to a support frame for control of a rudder control device. Each one of the pedal assemblies includes an idler link, a coupler link, and a drive link. The idler link is coupled to the support frame and is pivotable relative to the support frame. The coupler link is coupled to the idler link and is pivotable relative to the idler link. The drive link is coupled to the coupler link and to the support frame and is pivotable relative to the coupler link and relative to the support frame. A pedal is coupled to the coupler link. A four-bar linkage is formed by the support frame, the idler link, the coupler link, and the drive link and confines movement of the pedal to a linear travel path in a forward direction and a rearward direction.

Abstract: An unmanned lighter-than-air aircraft includes an outer membrane, a flexible bladder within the outer membrane and containing a lighter-than-air gas, a region disposed between the outer membrane and flexible bladder, a volume detection device configured to measure the volume of the flexible bladder, a pressure adjustment device to adjust the pressure within the region, and pressure control circuitry to control the region pressure adjustment device based on measurements from the volume detection device. The aircraft is maintained at a desired altitude, and the volume of the flexible bladder is measured. The pressure within the region is then adjusted by the pressure control circuitry to maintain the volume of the flexible bladder at a desired volume less than its maximum volume, equalizing its pressure with that of the region to reduce lighter-than-air gas leakage from the flexible bladder.

Abstract: A torque and pitch managed four rotor aircraft includes intersecting blades connected by synchronizing gears. The power for the rotors is provided by individual motors, one for each rotor, the motors preferably electric. Each rotor-motor assembly includes a torque management system including a set of torque sensors mounted on the drive shaft of the rotor-motor, the torque management system configured to balance the load torque presented by the rotors against the torque supplied by the motors. An additional overriding feedback system regulates rotational speed of the rotors. Direction of the aircraft is effected by adjusting the pitch of the individual rotors, and power is supplied through a battery and/or a motor-generator system located in the aircraft.

Abstract: An insulative ring protects a burst disc of an aircraft from the shock of lightning strikes. The burst disc device includes: a burst disc which is installed inside a main wing to prevent over-pressurization of the main wing; a pressure release passage partially constituted by a support tube and is blocked with the burst disc and leads to the outside of the main wing; an insulative ring which is disposed along the inner peripheral edge at a terminal end of the pressure release passage and exposed to the outside of the main wing, and an insulation layer which is disposed between a flange of the support tube and an inner surface of a panel of the main wing.

Abstract: An aircraft window includes: a window body including window panels, and an electromagnetic shield layer laminated on the window panels; a window frame that is made of a conductive material, and that surrounds the window body; a rubber-based gasket provided with conductivity, the gasket being at least partially held between the window body and the window frame; and a conductive layer that is located between the window body and the gasket, and that brings the electromagnetic shield layer and the gasket into conduction with each other. The window frame includes a holding section that holds the window body. At least a part of the conductive layer extends to a portion of the window body facing an extending part of the holding section. Moreover, the conductive layer extends about an entire perimeter of the window body, and extends only partially along an interface between the window body and interposition member.

Abstract: A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region, the overhanging edge being without any joggle. The composite ramp has a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder, having a relief radius, on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Abstract: There is provided a conductive radius filler system and method. The system has a composite assembly with one or more composite structures having one or more radius filler regions. The system further has one or more conductive radius fillers filling the one or more radius filler regions. Each of the conductive radius fillers has a conductive element of electrically conductive material. The system further has one or more conductive radius filler connections connecting the conductive radius fillers to one of, a fastener system, a fuel tank system, and a current generating system, to form one or more current handling systems of the system. The one or more current handling systems provide one of, edge glow mitigation of edge glow as a secondary effect of lightning strikes, electrostatic discharge mitigation of electrostatic discharge caused by refueling electrification and fuel slosh, and current return handling to provide a minimized dedicated conductive system.

Abstract: A multi-tank system and aircraft for dispersing firefighting materials includes a fuselage, a pair of wings, a first storage tank, a second storage tank, a first opening, a second opening, a first closure, a second closure, and an actuator. The first opening is disposed forward of a center of gravity of the aircraft and the second opening is disposed rearward of the center of gravity of the aircraft to maintain stability of the aircraft. The first opening is coupled to the first storage tank and the second opening is coupled to the second storage tank; a fuselage keel beam is positioned around the perimeters of the first and second openings. The actuator is configured to open the first closure and the second closure, in order to disperse firefighting materials such as water, fire retardant, or a mixture thereof.

Abstract: A flight attendant seat arrangement comprises a monument which is suitable for installation in an aircraft cabin, a first receiving recess being constructed in a wall of said monument. A flight attendant seat has a backrest element and also a seat element. The backrest element and seat element are at least partially received within the first receiving recess constructed in the wall of the monument. The wall of the monument is of a double-walled design comprising a support wall which forms the rear wall of the first receiving recess and extends from said first receiving recess as far as an end of the monument on a floor side, and an outer wall which is oriented substantially parallel to the support wall, and wherein the backrest element and the seat element of the flight attendant seat are fastened to the support wall.

Abstract: An ice-protection system has first and second zones of a leading edge of an aerodynamic or streamlined aerodynamic component, each zone having a de-icing apparatus and an ice-detection sensor positioned behind an elongated convex window as to be aero-conformal with the leading edge. The ice-detection sensor is in the form of a module and has a sensor head having a front face and abutments at ends of the window. The ice-detection sensors may have a central light emitter and a plurality of sensor elements peripheral to the light emitter. The ice-protection system also has a control system responsive to the ice-detection sensors to control the respective de-icing apparatus, and may activate automatically a sequence of operation.

Abstract: A return air bridge for use in an aircraft assembly includes an inboard portion configured to couple to a sidewall assembly at a bottom edge of the sidewall assembly and an outboard portion configured to couple to a structural member. The return air bridge also includes at least one support coupling the inboard portion to the outboard portion such that a return air flow path is defined between the inboard portion and the outboard portion. The outboard portion comprises a plate configured to direct an air flow along the return air flow path upwardly with respect to the bottom edge of the sidewall assembly.

Abstract: An actuator device includes a first and second actuators. The actuator device comprises a control system that is configured to switch the first actuator to a standby state and switch the second actuator to an active state in response to a first condition set wherein a hydraulic value in a first hydraulic system is equal to or less than a predetermined first threshold value and a second hydraulic value in a second hydraulic system is equal to or more than the predetermined second threshold value; and in response to a second condition set wherein the first hydraulic value is equal to or less than the predetermined first threshold value, the second hydraulic value is less than the predetermined second threshold value, and a difference between a current position and target position of a cylinder of the first actuator is equal to or more than a predetermined third threshold value.

Abstract: An aircraft is described and includes a fuselage, a wing coupled to the fuselage, and a rotor system including a proprotor system and an engine. An interconnect driveshaft gear is configured to communicate mechanical energy between a gearbox and an interconnect driveshaft. An accessory gear is coplanar with and in mechanical communication with the driveshaft gear. A proprotor gear is coplanar with and in mechanical communication with the interconnect driveshaft gear and the accessory gear and communicates mechanical energy to the proprotor system. An engine gear coplanar and in mechanical communication with the interconnect driveshaft ear, the accessory gear, and the proprotor gear transmits mechanical energy to the proprotor system via the proprotor gear.

Abstract: An emergency beacon is configured to replace of one or more navigation lamps installed on an aircraft, which has a fuselage with an outer face, on which is fixed a second interface, on which such a navigation lamp is typically disposed; the emergency beacon includes a base, which has a first interface configured to cooperate with the second interface of the aircraft to fix the base onto the outer face of the fuselage; a casing with a control unit, a radio transmitter for transmitting a distress signal, and a detector to detect abnormal aircraft behavior; and a fixing structure to take up a fixation position, ensuring the casing is fixed to the base, or a separation position, in which it does not ensure the casing is fixed to the base; the transition from fixation position to separation position is controlled by the control unit when an abnormal behavior is detected.