Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Abstract: A UAV includes a body. The body defines a payload opening 14. The payload opening is circular, but any shape may be used. A payload of the UAV is arranged in the payload opening. The payload may be a camera, sensors, a package, etc. A payload shroud may be installed which prohibits or reduced ingress of foreign material via payload opening. A payload shroud may include a diverter. The diverter may act as a barrier wall preventing the water or debris from entering the body of the UAV. The diverter should fit flush with the payload opening in the body of the UAV.

Abstract: An airfoil may include a leading edge and a shape control mechanism. The leading edge may include a flexible leading edge skin having a first end, a second end, and an arc length defined therebetween. The shape control mechanism may be attached to the flexible leading edge skin at a plurality of support locations and may transition the flexible leading edge skin from a first shape having a first curvature profile to a second shape having a second curvature profile different than the first curvature profile without a change in the arc length.

Abstract: A propeller assembly has a main hub and a propeller hub circumferentially movable relative to the main hub about a main axis of the assembly. Circumferentially spaced propeller blades on the propeller hub are i) circumferentially movable together with the propeller hub relative to the main hub between a first position and a second position against a biasing force, and ii) pivotal about respective radial axes. A pitch linkage mechanism is operatively connected between each propeller blade and the main hub such that each propeller blade is pivotal about the respective radial axis from a first pitch orientation to a second pitch orientation together with movement of the propeller hub relative to the main hub from the first position to the second position responsive to air resistance in the second direction exceeding the biasing force.

Abstract: A system and method for regulating and actuating bleed over a structure exposed in a fluid motion are disclosed. The bleed inlet and outlet are formed on the surface of the structure establishing fluidic communication across surfaces. The disclosed system and method contemplates active control and regulation of the bleed to modify crossflow properties such as, aerodynamic forces, hydrodynamic forces, vorticity, and moments.

Abstract: A high lift control system for an aircraft having at least one high lift surface includes a selector having a predetermined number of discrete positions, at least one of the predetermined positions corresponding to different positions of the at least one high lift surface.

Abstract: The herein invention is presenting a lift generating method based on a semi-open fluid jet flowing in a closed circuit around a lifting airfoil. A VTOL aircraft with maximized pay load room and car-like shape is the preferred embodiment of the invention. The herein aircraft uses no wings, exposed propellers, hot gas jets or other high injury risk means for propulsion and life, and it can be driven by ordinary skilled people. Furthermore the aircraft has a small footprint and can land, take off and even cruise on water in one of the preferred embodiments.

Abstract: An aircraft having a moveable ejector member for assisting in alleviating a boundary layer flowing along an aircraft surface is disclosed. The moveable ejector member is capable of being placed at a variety of positions between a fully open position and a nested position to entrain the boundary layer with another fluid flow. The ejector member can take the form of an ejector shroud used with a nacelle. In some forms, a gas turbine engine is used to provide an ejector flow to entrain the boundary layer through the flow path.

Abstract: An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition.

Abstract: A method and apparatus for forming a composite winglet for an aircraft is presented. The composite winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the composite winglet. The root region is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft.

Abstract: A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet may have a length of approximately 50-80 percent of a length of the upper winglet.

Abstract: The fast fixing system comprises a link part (24) integral with the accessory (22), and a support face (26) formed on the drone body (12). The link part is mobile in rotation (28) with respect to the frame between a free position allowing the placing or the removal of the accessory, and a locked position in which the link part is immobilized in rotation and in translation on the frame, so as to form with the latter an integral unit. Means are provided, which define the locked position by a rotation stop of the link part with respect to the frame, means for axial translation blocking of the link part with respect to the frame when the link part is in the locked position, and means for elastic fastening of the link part to the frame once the locked position reached.

Abstract: An aircraft landing gear self-orients so to align itself within a plane parallel to the plane defined by the aircraft's roll and yaw axis. A nose gear of a tricycle landing gear configuration includes the ability to not only caster 360 degrees but also self-orient itself to be aligned parallel with the plane defined by the aircraft's roll and yaw axis once removed from any interaction with the ground. A simple and efficient mechanical design provides the landing gear with a substantially constant centering torque that neither impedes nor impairs ground movement yet returns the nose gear to a proper alignment for retraction and stowage.

Abstract: A drive unit (16) for an aircraft running gear (2) having at least a first wheel (4) and a second wheel (6) on a common wheel axis (A) is characterized in that the drive unit (16) is drivingly coupleable to the first and second wheels (4, 6) such that a direction of longitudinal extension (C) of the drive unit (16) is in a plane orthogonal to the common wheel axis (A).

Abstract: A system for providing control to a parking brake for an aircraft (10) having a power source includes a panel (28) accessible from an exterior of the aircraft (10) and a parking brake switch (32) disposed on the panel (28) providing control over the engagement and disengagement of the parking brake on the aircraft (10), a method operating such a system for providing control to a parking brake is also disclosed.

Abstract: Methods and means for reducing wear in electric or electro-hydraulic braking systems utilizing an adjustable (adaptive) filter, wherein the adaptive filter provides for rapid response during anti-skid operation and a smooth and filtered response during non-anti-skid operation.

Abstract: Improved force generator (FG) devices and methods are provided herein. A FG device (10) includes a housing (16, 18), a shaft (S) centrally disposed within the housing, and multiple imbalance rotors (30, 32, 34, 36, 38) disposed within the housing and provided along the shaft. At least two pairs (PA, PB) of imbalance rotors are provided in a nested configuration with respect to each other along the shaft. The at least two pairs (PA, PB) of imbalance rotors are supported in the nested configuration by large and small bearings (BA, BB). Any two imbalance rotors are paired to rotate together in a same direction according to a desired vibration canceling force. A method of controlling vibration within a structure is provided. The method includes detecting vibration, receiving a force command at a FG device, and pairing any two imbalance masses together and rotating a pair of imbalance masses via the rotors together in a same direction to cancel the detected vibration.

Abstract: A hybrid axial/cross-flow fan aerial vehicle includes both axial and cross-flow fan propulsion for efficient hover and forward flight performance. The axial fans provide primarily vertical thrust, while the cross-flow fan provides horizontal, as well as vertical, thrust. The vehicle takes off vertically, is capable of hover, and can fly forward by vectoring the thrust of the cross-flow fan system. This approach provides large internal cargo capacity and high forward flight speeds.

Abstract: An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions.

Abstract: An ornithopter includes a main wing mounted on a fuselage, and a control system configured to control a flapping motion of the main wing. The main wing includes an inner spar, an outer spar, and a wrist portion disposed between the inner spar and the outer spar and which varies a bending angle, which is a relative angle between the inner spar and the outer spar, within a predetermined angle range. The control system includes an actuator which performs a raising motion and a lowering motion of the inner spar by moving the inner spar in an upward direction and in a downward direction, an angle sensor which measures the bending angle, and a control unit which controls the actuator to move the inner spar in response to the measured bending angle.

Abstract: One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map.

Abstract: A low aspect ratio flying wing provides aerodynamic stability throughout the flight envelope with improved aerodynamic efficiency. Insufficient stability and reduced aerodynamic efficiency typical of low aspect ratio flying wings is improved through wing design and proper application and placement of horizontal stabilizers and boundary layer control. Lateral asymmetric boundary layer manipulation is employed to alter flying wing orientation in flight. Lateral extension and retraction of the main structure wing optimizes efficiency. This novel flying wing is not found in literature or “prior art” and provides improvement in aerodynamic stability and efficiency over previous designs. Given the large amount of research, literature, patents and activity in the field since the 1930's and the absence of a practical design indicates the non-obvious nature of these disclosures. In addition, those skilled in the art teach away from present disclosures failing to realize the better than predicted advantages.

Abstract: Disclosed is an an unmanned aerial vehicle. The unmanned aerial vehicle includes a payload arranged in a container, said container being equipped with a parachute; means for attaching the payload to the unmanned aerial vehicle and means for ejecting the payload from the unmanned aerial vehicle. The means for ejecting the payload from the unmanned aerial vehicle is communicatively coupled with the payload and configured to be actioned upon an emergency situation.

Abstract: A helicopter-hoist system is described. The system may include: hoist equipment, illumination systems, range-measuring equipment, camera(s), communication systems, display devices, processing/control systems including image-processing systems, and power-management systems. The system may also include a smart-hook for measuring a load on the hook. Based on the measured load on the cable, the lighting may be illuminated in different manners. In another aspect, the system may communicate with display devices, which render images of a mission to helicopter crew members or other observers.

Abstract: A vehicle seat includes a backrest, a recess made in the backrest, a holder base fitted to a rear wall of the recess, an upper holder clip which is movably and resiliently mounted in a clip rail extending vertically from top to bottom in the holder base, and a fold-out tray which can be folded out from the recess by two folding hinges which are fitted to the inner side walls of the recess inside the recess.

Abstract: A monument configured to be positioned in the interior of an aircraft that includes first, second, third and fourth sides and first and second lavatories spaced apart from one another by at least a portion of a galley storage section that is open to the first side. The first and second sides are opposite to one another and the third and fourth sides are opposite to one another. The first lavatory defines a first lavatory interior and includes a first toilet therein and the second lavatory defines a second lavatory interior and includes a second toilet therein.

Abstract: Lavatories on-board a vehicle, and in particular to a lavatory unit for use by persons with reduced mobility on-board a vehicle are described. The lavatory unit includes a lavatory housing structure enclosing a lavatory interior space, a door opening in the lavatory housing structure, a toilet assembly inside the lavatory interior space, and a transition seating support for a user. The transition seating support provides a first transfer position and a second transfer position. In the first transfer position, in an open door state the transition seating support is directly accessible for a person sitting in a wheelchair that is located at least partly outside the lavatory unit such that the person can transfer to the transition seating support and vice versa, and in the second transfer position, a person sitting on the transition seating support can transfer to the toilet assembly and vice versa.

Abstract: Occupant support for enhanced comfort safety and utility.

Abstract: A passenger seat for a means of transportation is provided, which comprises a seat frame with a top side, which top side is configured for supporting a seat pan with a seat cushion for providing a seating area for a passenger, and a bottom side opposing the top side. The passenger seat further comprises a stowage cavity arranged between the top side and the bottom side of the seat frame. The seat frame further comprises a first beam and a second beam, both beams being arranged parallel to each other and parallel to a transversal axis of the passenger seat. The top side of the seat frame provides an access to the stowage cavity such that a stowage compartment, which is configured to accommodate an item of luggage, is insertable into the stowage cavity through the access.

Abstract: A gas turbine engine comprises at least two compressor rotors, including a first lower pressure compressor rotor and a second higher pressure compressor rotor. At least two corresponding air taps include a low tap for tapping low pressure compressor air from a location downstream of a first stage of the lower pressure compressor rotor, and upstream of a first stage of the higher pressure compressor rotor, and a high tap to tap air downstream of the first stage of the higher pressure compressor rotor. an air handling system selectively communicates both the low tap and the high tap to an air use destination. Air is selectively supplied from the low tap to the air handling system at a high power operation and from the high tap to the air handling system at a low power operation.

Abstract: An ice-protection system suitable for use in an aircraft comprises first de-icing apparatus operable to de-ice a first zone; a first ice-detection sensor positioned in the first zone and arranged to detect ice accreted on the first zone; and a control system responsive to the first ice-detection sensor and arranged to control the operation of the first de-icing apparatus.

Abstract: A tool to aid with pulling a closing loop cord through grommets in closing flaps on a parachute container. The cord is looped in a “U” shaped arrangement with two pulling “legs” of equal length being wrapped around a handle to provide a better grip. Only one leg of the cord can be permanently attached to the handle as the other leg must be removable for fishing through the grommets. The handle must have a diameter to permit passage through the eye of the grommet with the two legs of the cord trailing behind. With existing handles, the removable end of the cord slides off the end of the handle when passing through the grommet. An “O” ring placed on one or both ends of a radial groove in the handle holds the cord captive when passing the handle through the grommets to prevent the cord from sliding off.

Abstract: A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. An electric motor in electrical connection with said solar radiation receiver to receive the electrical energy and drives a propeller to propel the solar relay aircraft. A number of ground-based reflector arrays include a plurality of reflecting mirrors for receiving solar radiation from the sun and direct the solar radiation from the sun towards the solar relay aircraft.

Abstract: Exemplary embodiments are provided to reduce the high transient mount load in an aircraft engine mounting system under extreme loading condition. The exemplary embodiments reduce the impact of the snubbing phenomenon without adding to the weight or space claim of the engine mounting system.

Abstract: Autonomous propulsion apparatus and methods are disclosed. An example autonomous propulsion unit includes a flight controller capable of executing flight control instructions stored in a memory of the autonomous propulsion unit; and a propulsor to generate propulsion in accordance with the instructions for a payload carrier to which the autonomous propulsion unit is coupled, wherein the flight controller is to provide flight control for the propulsor in an absence of flight control instructions from the payload carrier.

Abstract: One embodiment of the present disclosure is a unique machine. Another embodiment is a unique system for supplying electrical power to a machine, such as a vehicle, having an electrical load during operation. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems.

Abstract: The invention provides an aircraft fuel system comprising a fuel storage facility for storing fuel and ullage, a separate ullage storage facility for storing ullage, and a transfer arrangement for transferring ullage between the fuel storage facility and the ullage storage facility, wherein the transfer arrangement is capable of controlling the transfer of ullage based on a pressure input to the transfer arrangement. The invention also provides an aircraft with such a fuel system and a method of operating an aircraft.

Abstract: The present invention intends to extend the operating life of an air separation module (ASM) in a nitrogen enriched air (NEA) supply system by controlling the temperature of bleed air as a supply source of the NEA. The NEA supply system produces NEA that is enriched with nitrogen upon supply of source gas during a flight through an ascent phase, a cruising phase, and a descent phase, and supplies the NEA to a fuel tank, the system including: an air separation module that separates oxygen and nitrogen in the source gas; and a temperature regulation mechanism that regulates a temperature of the source gas supplied to the air separation module. In at least a part of a flight period through the ascent phase and the cruising phase, the temperature regulation mechanism regulates the temperature of the source gas to below a temperature of the source gas in the descent phase.

Abstract: To provide a system which supplies nitrogen enriched air (NEA) produced by using bleed air as a supply source of the NEA to a fuel tank, and which can further improve the fuel consumption. The present invention employs an NEA supply system 10 that controls a supply in a flow control valve (FCV) 11 so as to obtain a supply flow rate Fs as a value obtained by adding a small margin flow rate Fm to a required amount Fn of nitrogen enriched air required to be supplied to a first fuel tank 15, in at least a part of a descent phase of an aircraft 100. Accordingly, explosion of the first fuel tank 15 can be prevented, and the fuel consumption of an engine 1 can be improved in the descent phase.

Abstract: The invention concerns a structure (3) for providing emergency electric power to an aircraft (1) comprising a pressurized cabin (10), at least one main engine and an auxiliary power unit (APU), the structure being designed to provide electric power to the aircraft in the event of failure of the main engine and the emergency auxiliary unit, the structure comprising a circuit (30) for recovering air from the cabin (10), and an electricity-generating system (32, 24, 34) which generates electricity by depressurizing the air recovered from the cabin (10).

Abstract: A system and method for state estimation of a surface of a platform at sea, includes receiving sensor signals indicative of LIDAR data for the platform; applying a Bayesian filter to the LIDAR data for a plurality of hypotheses; determining vertical planes representing azimuth and elevation angles for the LIDAR data; applying a robust linear estimation algorithm to the vertical planes; and determining candidate points in response to the applying of the robust linear estimation algorithm.

Abstract: A visual search assistance system and related operating method are disclosed. An exemplary embodiment of the method dynamically determines a desired line-of-sight vector from an occupant of a vehicle to a visual target, and dynamically determines, with an onboard tracking system of the vehicle, an actual line-of-sight vector for the occupant of the vehicle. The actual line-of-sight vector is temporally associated with the desired line-of-sight vector. The method compares the actual line-of-sight vector against the desired line-of-sight vector to obtain a difference measurement, and generates a notification when the obtained difference measurement exceeds a threshold value. The notification provides guidance to redirect a gaze direction of the occupant toward the visual target.

Abstract: A technique is directed to launching an unmanned aerial vehicle (UAV). The technique involves attaching a UAV launcher to a hand-held weapon, and installing a UAV onto the UAV launcher while the UAV launcher is attached to the hand-held weapon. The technique further involves activating the hand-held weapon to launch the UAV into flight from the UAV launcher. Since a user already may be carrying the hand-held weapon for firing ammunition, the user simply needs to further carry the UAV launcher and the UAV which, in some situations, can be packaged into an easy-to-carry container such as a backpack, a carrying case, and so on.

Abstract: An apparatus and method of charging and housing of an unmanned vertical take-off and landing (VTOL) aircraft is disclosed. The apparatus includes an accommodator to accommodate an aircraft, a landing platform on which the aircraft lands, a housing portion to monitor state data by housing or charging the aircraft, and a sensor to assist in landing of the aircraft by allowing the aircraft to communicate with the apparatus. The apparatus enhances operational efficiency by reducing a travel time of the aircraft.

Abstract: An aircraft boarding apparatus has a passenger bridge that has a confinement structure coupled to the second passenger bridge. The confinement structure exerts a ground-anchoring effect on the second passenger bridge to offset the ultralight configuration of the passenger bridge.

Abstract: Currently the world's largest airplane is Airbus A380, can carry 525 people in a normal three-class configuration. It can travel nonstop 15,700 kilometers (8,500 nmi; 9,800 mi), at a speed of Mach 0.85 (about 900 Km/h or 560 mph; 490 kn at cursing altitude). To carry twice as many passengers and fly the same distance with the similar performance or better can achieved by joining the two same types of airplanes in the rear to front, (FIG. 1), or rear to rear (FIG. 2), can have the equivalent or better effect, and have similar or better performance than keep on building larger, fatter, airplanes such as A380. For example, Airbus, A350 can carry 350 passengers in a three-class setting, if the two A350s are jointed, it can carry, 700 passengers instead of only 350. This will work on other makers with the two same types of large airplanes.

Abstract: A method and apparatus for performing an assembly operation. A tool may be macro-positioned within an interior of a fuselage assembly. The tool may be micro-positioned relative to a particular location on a panel of the fuselage assembly. An assembly operation may be performed at the particular location on the panel using the tool.

Abstract: A method for coupling a number of utilities between a first system and a second system is provided. A first interface that couples the number of utilities between the first system and the second system is created between the first system and a utilities unit. The first interface is activated. A second interface between the second system and the utilities unit is deactivated, while the first interface remains activated.

Abstract: An attachment for an end effector. The attachment may include a clamp and a foot adhesively bonded to an edge of the clamp and having a set of interlocking features that form a mechanical interlock with the clamp.

Abstract: A method and apparatus for accessing an interior of a fuselage assembly. A tower having a number of platform levels may be driven into a selected tower position within an assembly area. The interior of the fuselage assembly may be accessed using the number of platform levels.