Abstract: A control apparatus 300 for controlling a steering system 301 of an aircraft landing gear, the aircraft landing gear being configurable in a stowed configuration and a deployed configuration. The steering system 301 includes a wheel arrangement 202 including one or more wheels. The control apparatus 300 is arranged to perform a control process which includes: receiving one or more signals from one or more sensors 302a, 302b indicating a position of the wheel arrangement 202 when the landing gear is in the stowed configuration; determining whether a predetermined condition is satisfied in relation to the position of the wheel arrangement 202; and, in response to determining that the predetermined condition is satisfied, performing an adjustment process to control the steering system 301 to adjust the position of the wheel arrangement 202.

Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.

Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

Abstract: A hub system comprises at least one yoke, at least one shear bearing, and at least one mast adapter. The at least one mast adapter is configured to support the at least one yoke and the at least one shear bearing, and the at least one yoke has a flapping hinge that is non-coincident with a flapping hinge of the at least one shear bearing. Another hub system comprises a stacked yoke and a mast adapter. The mast adapter is configured to transfer rotation from a rotor mast to the hub system to rotate the hub system about a central axis of rotation. The mast adapter is further configured to support the stacked yoke such that each yoke in the stacked yoke is configured to accommodate at least some amount of rotation about an axis that is perpendicular to or about perpendicular to the central axis of rotation.

Abstract: The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.

Abstract: A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.

Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.

Abstract: A kite launch device that includes a kite, a mast, a guide device coupled to the mast, and a winch. The kite includes a canopy, a base structure for at least one device, a plurality of support lines coupled to the canopy and the base structure, a guide line coupled to the canopy, and a tether coupled to the base structure. The guide device is configured to grab the guide line. The winch is coupled to the tether of the kite. The winch is configured to extend and retract the tether. The kite includes a guide element coupled to the base structure and the guide line. The guide device is configured to encircle the guide element in order to grab the guide line.

Abstract: A system for maintaining a machine. The system includes an aerial vehicle configured to fly to a lubrication location proximate the machine. A supply of friction minimizing material is carried by the aerial vehicle. A controller is configured to deliver at least part of the supply of friction minimizing material to the machine when the aerial vehicle is at the lubrication location.

Abstract: An embodiment of the present disclosure provides an unmanned aerial vehicle, An unmanned aerial vehicle, with a double-layered structure formed by stacking a cover and a main component layer, wherein, the main component layer includes a base body and at least one functional component, the base body has a top facing to the cover layer and a bottom opposite to the top, the cover is in direct contact with the top of the base body, and the at least one functional component is mounted on the base body.

Abstract: A flight control method includes: determining a positional relationship between an aircraft and a control device; determining a polar coordinate system with the control device as an origin according to the positional relationship; receiving a flight direction control instruction sent by the control device, the flight direction control instruction being generated on the basis of the polar coordinate system; and driving, according to coordinate information about the aircraft in the polar coordinate system, the aircraft to fly in accordance with the flight direction control instruction.

Abstract: A method includes controlling an unmanned aerial vehicle to fly over a forestry worksite and capture imagery information with an image capture component. The imagery information is used to generate a set of ground disturbance metrics, each having a value indicative of a measure of ground disturbance at a different geographic location in the forestry worksite. Alternatively, the imagery information is used to generate a set of slope metrics or a firefighting metric. According to the ground disturbance, slope, and firefighting metrics, the method is used to generate an action signal, such as an action signal that controls movement of a mobile machine operating at the forestry worksite, among others.

Abstract: This document generally describes a safe-passage guidance strategy developed in a relative velocity framework to enable a generic aerial robot execute a precision three-dimensional maneuver through a narrow orifice in a wall. The relative sizes of the robot and the orifice can be such that the orifice is only slightly larger than the robot. The orifice can be approximated as an elliptical shape, and analytical nonlinear guidance laws incorporating state-based switching can be derived. Guidance laws can be used to maneuver the robot through both fixed and moving orifices as well as in scenarios when the orifice is closing with time.

Abstract: A dispensing device for connection to a drone is provided. The dispensing device has an outer housing and an inner housing interior of the outer housing. The inner housing has an inner cavity having an entrance opening and an opposing exhaust opening. The area between the outer housing and the inner housing defines an outer cavity adapted to hold a material. The dispensing device also has a fluid access opening to provide fluid access between outer cavity and the inner cavity to allow material in the outer cavity to be transferred to the inner cavity and mixed with air to create an air and material mixture. An air accelerator is provided adjacent the inner cavity to accelerate the air and material mixture out of the dispensing device.

Abstract: A mounting arm assembly movable between stowed and deployed configurations, includes a pivot arm pivotally engaging an armrest of a seat; a tilt arm engaging the pivot arm; and a mount engaging the tilt arm for supporting a personal electronic device.

Abstract: An aircraft ceiling liner element comprises a load-bearing carrier platform, configured to form a part of an aircraft ceiling liner, and a mounting mounted on the carrier platform, connectable to a primary structure of the aircraft. An electrical connection mounted on the carrier platform is connectable to an electrical supply network of the aircraft. Furthermore, the aircraft ceiling liner element comprises a mechanical interface mounted on the carrier platform, configured to attach various interchangeable modular units detachably and in a load-transferring manner to the carrier platform, and an electrical interface mounted on the carrier platform, which interface is configured to create an electrical connection between the modular unit and the carrier platform.

Abstract: An arrangement for selectively arresting a serving trolley in a cabin includes a walling extending perpendicularly to a cabin floor. The walling has a height at least equal to the height of a serving trolley. The arrangement has an upper arresting unit positioned at an upper fastening section of the walling and a lower arresting unit positioned at a lower fastening section of the walling. The upper arresting unit has a first engagement element and a second engagement element, wherein at least one of the engagement elements is movable relative to the other engagement element. The upper arresting unit releasably engages two distanced recesses at an upper end of the serving trolley by way of the engagement elements. The lower arresting unit includes at least one third engagement element and is designed for engaging a bottom side component of the serving trolley by way of the third engagement element.

Abstract: A multiple seat set for use in a transport vehicle such as an aircraft is disclosed. The seat set increases seating room and comfort for passengers without increasing the footprint of the seat set. The seat set includes a staggered seating arrangement where seating surfaces of adjacent seats are disposed in alternating heights (e.g., vertical heights) while the seating surfaces and seat backs of such adjacent seats are disposed in alternating forward and back positions. The staggering of the seat surfaces and seat backs results in misalignment of shoulders and hips of passengers in adjacent seats.

Abstract: A multiple seat set for use in a transport vehicle such as an aircraft is disclosed. The seat set increases seating room and comfort for passengers without increasing the footprint of the seat set. The seat set includes a staggered seating arrangement where seating surfaces of adjacent seats are disposed in alternating heights (e.g., vertical heights) while the seating surfaces and seat backs of such adjacent seats are disposed in alternating forward and back positions. The staggering of the seat surfaces and seat backs results in misalignment of shoulders and hips of passengers in adjacent seats.

Abstract: A seating arrangement comprising at least one seat; a console adjacent the at least one seat; a deployable table assembly; and locking device. The table assembly is movable in a longitudinal direction from a stowed position into a deployed position in which it is located on an upper surface of the console. The locking device is operable to releasably engage the table assembly in the deployed position to prevent movement of the table assembly in a lateral direction.

Abstract: In an illustrative embodiment of an aircraft cabin passenger seating arrangement, first and second adjacent passenger seats are positioned at different angles with reference to a longitudinal axis of an aircraft, and longitudinally offset from each other such that the first seat is positioned forward of the second seat by an amount less than a length of the second passenger seat when in the lie-flat position. The first and second adjacent passenger seats may be longitudinally offset from a third passenger seat separated from the second passenger seat by an aisle, the third passenger seat disposed proximate a fourth passenger seat, such that a row of passenger seats includes two staggered groups of passenger seating. The first passenger seat may be vertically offset from the second passenger seat.

Abstract: There is provided an aeronautic vehicle including a first engine capable of providing propulsion and pressurising air and an environmental control system. The environmental control system includes an electrically powered compressor capable of pressurising air and a first pressurised air powered environmental control system pack. The environmental control system is configurable to provide pressurised air from the first engine to the first environmental control system pack, and the environmental control system is configurable to a ground configuration in which pressurised air is provided from the electrically powered compressor to the first environmental control system pack. There is also provided an environmental control system for an aeronautic vehicle and a method of operating an environmental control system of an aeronautic vehicle.

Abstract: An aircraft air conditioning system includes an ambient air line which is configured have ambient air flow therethrough and is connected to a mixer of the aircraft air conditioning system to supply ambient air to the mixer, and a refrigerating machine which includes a refrigerant circuit configured to have a refrigerant flow therethrough, the refrigerant circuit being thermally coupled to the ambient air line to transfer heat, from the ambient air flowing through the ambient air line, to the refrigerant circulating in the refrigerant circuit, before the ambient air is supplied into the mixer. A control device is configured to control the ambient air flow through the ambient air line such that the ambient air is selectively conducted through different sections of the ambient air line or different bypass lines running parallel to the sections of the ambient air line.

Abstract: A system and method onboard an aircraft includes a ram air temperature sensor, a bleed air temperature sensor, a valve, and a controller. The ram air temperature sensor is positioned to sense a ram air temperature of a ram air flow. The bleed air temperature sensor is positioned to sense a bleed air temperature of a bleed air flow, wherein the bleed air flow is cooled by a heat exchanger using the ram air flow. The valve is configured to control the bleed air flow upstream of the heat exchanger. The controller is configured to determine a bleed air threshold based on the ram air temperature, and control the valve to reduce the bleed air flow in response to the bleed air temperature reaching the bleed air threshold.

Abstract: An ice-protection system for an aerodynamic structure for an aircraft comprising: an outer skin defined by a leading edge point and a trailing edge point that are interconnected by an upper skin and a lower skin, an internal chamber defined within the outer skin configured to be in fluid communication with the atmosphere external to the outer skin via an inlet and an outlet, and at least one air heater provided within the chamber in proximity to the inlet, wherein during use, a pressure differential exists between the inlet and the outlet that causes external air to flow through the chamber from the inlet to the outlet, and wherein the heater is configured to heat the air passing through the inlet such that the temperature of the air in the chamber is sufficiently increased so as to prevent ice accretion on the outer skin.

Abstract: A selection is made between single stage and multistage parachute deployment for a vehicle based at least in part on vehicle state information. In the event multistage parachute deployment is selected, a drogue parachute is deployed during a first deployment stage and afterwards, a main parachute is deployed during a second deployment stage. In the event single stage parachute deployment is selected, at least the main parachute is deployed in a single stage where in the event the drogue parachute is deployed during the single stage, the drogue and main parachute are deployed simultaneously.

Abstract: An airbag assembly for leg flail protection and associated systems and methods are described herein. An airbag system configured in accordance with an embodiment of the present technology can include, for example, a housing having a cavity and an opening in communication with the cavity, an airbag stowed within the cavity, and an inflator operably coupled to the airbag. The airbag can be configured to deploy through the opening of the housing during a crash or other significant dynamic event. The airbag can deploy outwardly from the side-facing seat to reduce occupant leg rotation during the crash or other significant dynamic event. The airbag can be pushed out of the housing before it is fully inflated. The airbag can be stowed and include folded first and second opposing side portions such that when the airbag is deployed, the portion nearest the occupant unfurls toward the occupant prior to the other portion farthest from the occupant unfurling in a direction away from the occupant.

Abstract: The vehicle receives batteries comprising cells arranged into at least one pack configured to be held in a vehicle structure, the pack being alternatively chosen from among at least one pack(P) and at least one pack(E) which are mechanically interchangeable and electrically substitutable. The pack(P) cells exhibit a maximum power density substantially higher than the pack(E) cells exhibit, and comprise cells exhibiting an energy density per unit mass substantially less than the pack(E) cells exhibit. The maximum electrical power of the pack(P) corresponds to the maximum electrical power needed to accomplish a first vehicle mission and the energy storage capacity of the pack(P) is at least sufficient to accomplish the first mission. The electrical energy storage capacity of the pack(E) corresponds to the electrical energy storage capacity needed to accomplish a second vehicle mission and the maximum electrical power is at least sufficient to accomplish the second mission.

Abstract: Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady state load condition, selecting at least one power source configuration to supplement power provided by the at least one prime mover during a transient load condition associated with the operation of the aircraft, and selecting, by the computing device, a parameter of the at least one power source configuration to provide a total power in an amount that is greater than a threshold during the transient condition.

Abstract: Auxiliary power unit inlet apparatus and methods are disclosed. An example apparatus includes an aircraft including a fuselage, the fuselage including an air inlet including a first sub-inlet and a second sub-inlet separated from the first sub-inlet; and a door coupled along the air inlet to enable air to separably flow into the first sub-inlet and the second sub-inlet, the door to deter the air from flowing between the first sub-inlet and the second sub-inlet.

Abstract: A manufacturing method is provided. During this method, a panel is provided that includes non-conductive material and a plurality of conductive elements at least partially embedded within the non-conductive material. The conductive elements include a first conductive element. An electric current is applied to the first conductive element such that the first conductive element produces a signature. A location of the first conductive element in the panel is determined based on the signature. An aperture is formed in the panel based on the determined location of the first conductive element.

Abstract: Systems, methods, and devices for aircraft power distribution include a bipolar high voltage direct current source component; an electrical loading component capable of drawing electrical power from the bipolar high voltage direct current source component; a set of switching components configured to selectively couple power from the bipolar high voltage DC source component to the electrical loading and a ground fault interruption component coupled to the set of switching components. The ground fault interruption component is configured to detect a ground fault based on a sensed difference between a current flowing out of the set of switching components and back from the electrical loading component.

Abstract: A fuel tank inerting system is disclosed. In addition to a fuel tank, the system includes a catalytic reactor with an inlet, an outlet, a reactive flow path between the inlet and the outlet, and a catalyst on the reactive flow path. The catalytic reactor is arranged to receive fuel from the fuel tank and air from an air source, and to react the fuel and air along the reactive flow path to generate an inert gas. The system also includes an inert gas flow path from the catalytic reactor to the fuel tank. The system also includes (a) an air distributor in the catalytic reactor arranged to distribute air along the reactive flow path, or (b) non-uniform catalyst loading or non-uniform catalyst composition along the reactive flow path, or both (a) and (b).

Abstract: A method is provided for two-dimensional graphic representation on an aircraft display screen of an image or of a symbol or of a symbology (PE) whose three-dimensional coordinates in a terrestrial reference frame are known. The graphic representation of the object or of the symbol is stretched in a vertical axis by a constant factor (?) lying between 1.0 and 1.2, the stretching having, for its neutral plane, the local horizontal geographic plane containing the aircraft. Furthermore, when the symbology is a pitch scale consisting of graduations, two successive graduations being separated by a constant angular value, the graphic representations of two successive graduations of the pitch scale are separated by a constant distance on the display screen.

Abstract: Methods and systems are provided for generating an alert for an aircraft potentially exceeding speed limits in airspace with speed limitations. The method comprises retrieving a flight plan for the aircraft and identifying airspace with speed limitations along the flight plan. A speed profile is generated based on the in-flight aircraft's current position, speed and trajectory. Any predicted speed violations are identified by comparing the speed profile with the airspace with speed limitations along the flight plan. A predictive time window is calculated that allows for the in-flight aircraft to decelerate sufficiently to comply with the speed limits of the airspace with speed limitations. The predictive time window includes a zone for the aircraft to reduce its airspeed and a reaction buffer zone to allow the aircrew sufficient time to comply with instructions to decelerate the aircraft. Finally, an alert is generated for the crew of the in-flight aircraft upon entering the predictive time window.

Abstract: The invention relates to a method for controlling the restitution of alert(s) and/or of system(s) reconfiguration procedure(s), including the surveillance of device(s) of a vehicle and the determination of alert(s) and/or of associated reconfiguration procedure(s) to be restituted for the crew, the vehicle operating according to a mission carried out by using at least one operational capacity, and further including, for a current mission: obtaining a list of operational capacities required by said current mission; from said required operational capacities and at least one piece of information from an accessible database, controlling the restitution of alert(s) and/or of system(s) reconfiguration procedure(s) by: modifying the associated level of alert(s) and/or of procedure(s), and sequencing the restitution of alert(s) and/or of procedure(s) based on said level, and/or filtering said alert(s) and/or reconfiguration procedure(s) before restitution.

Abstract: A method of and a system for presenting an operating status of an aircraft engine. The method comprises accessing a first indication indicative of a position of an aircraft engine start switch and accessing a second indication indicative of an aircraft engine start operating mode, the second indication having been generated based on an analysis of a parameter associated with an operating condition of the aircraft engine. The method, upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is a healthy start causes the display of a visual indication indicative of the healthy start. The method upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is an abnormal start causes the display of a visual indication indicative of the abnormal start.

Abstract: A drone includes a light emitter that emits light and circuitry which, in operation, obtains flight state information regarding a flight state of the drone, determines, on the basis of the flight state information, a direction in which the light emitter is to emit light, and controls the light emitter such that the light emitter emits light in the determined direction.

Abstract: An exterior aircraft light unit according to exemplary embodiments of the invention comprises: a housing including a mounting portion, which is configured for mounting the aircraft light unit to an aircraft; at least one light source; and a heat sink; wherein the heat sink comprises: a first heat sink portion comprising a plurality of cooling ribs being thermally connected with the at least one light source for transferring heat from the at least one light source to the plurality of cooling ribs; and at least one second heat sink portion comprising two heat sink plates and a clamping pin and being configured such that the second heat sink portion is selectively attachable, particularly clampable, to a respective cooling rib of the first heat sink portion.

Abstract: An apparatus including a platform, casters attached to the platform, and a carriage supported by the platform is described. The carriage includes a left arm, a right arm, and an actuation mechanism. The left arm can pivot about a left lateral axis, and the right arm can pivot about a right lateral axis. The actuation mechanism allows a distance between a proximal end of the left arm and a proximal end of the right arm to be modified. Increasing the distance causes a distal end of the left arm and a distal end of the right arm to swing towards each other. Decreasing the distance causes the distal end of the left arm and the distal end of the right are to swing away from each other. The apparatus provides a convenient means by which to move a helicopter equipped with skids while the helicopter is on the ground.

Abstract: In one aspect, there is disclosed a taxi vehicle comprising a chassis having a coupler to connect to a coupling location of a craft and a set of wheels with at least one electric motor coupled to the set of wheels. The taxi vehicle can include a fuel cell coupled to the at least one electric motor and a battery coupled to the fuel cell. The battery can be configured to supply peak power demand to the at least one electric motor to start moving the craft. The battery can receive charging from the fuel cell when not supplying peak power demand while the fuel cell supplies power to the at least one electric motor to continue moving the craft.

Abstract: A system for providing pre-conditioned air to an aircraft on the ground includes a ground air conditioning unit configured to produce air-conditioned air, a control module for controlling operation of the air conditioning unit, and an air hose having a first end in communication with a pre-conditioned air outlet of the air conditioning unit and a second end having a connector for connection to an aircraft on the ground. A pressure sensing device provides pressure information to the control module and is arranged so as to allow pressure monitoring of the flow of pre-conditioned air in the vicinity of the second end of the air hose.

Abstract: A method of making a rotor blade assembly includes receiving a sheath assembly and a blade body at a blade assembly tool. The sheath assembly is spread by applying force to an interior surface of the sheath assembly. The blade body is inserted within the interior of the sheath assembly, registered with the sheath assembly, and the force removed from the interior surface of the sheath assembly such that the sheath assembly collapses on the blade body.

Abstract: Devices for maintaining crawler alignment on complex-shaped blades and for enabling the blade crawler to traverse over trailing edge protrusions. Using ball and socket bearings or air pads in place of alignment wheels, the crawler will be able to track along complex-geometry rotor blades, propellers and other airfoils. Using an oversized-diameter roller, a semi-flexible roller, or a dual-roller arrangement, the crawler will be able to traverse over trailing edge protrusions.

Abstract: A method for preserving and recovering the main engine of the first stage of a multistage launch vehicle involves utilizing a portion of a first stage propellant tank together with a parachute and a deployed buoyancy device to float the engine in a body of water until the engine can be recovered. Controlled explosions remove portions of the propellant tank to permit it to stabilize the position of the engine relative to the water following splash down.

Abstract: An example spacecraft includes a first arm having a first end pivotably coupled to the spacecraft and a second end. The example spacecraft includes a first thruster rotatably coupled to the second end of the first arm. The first arm extends from the first pivot point along a first edge of an anti-nadir face of the spacecraft when the first arm is in a stowed position. The first arm is configured to pivot between the stowed position, a first extended position in which the first arm extends outward from the spacecraft relative to the first edge, and a second extended position in which the first arm extends along a third edge of the anti-nadir face and the first thruster is disposed outward of a second edge of the anti-nadir face opposite the first edge.

Abstract: The invention relates to an ejection unit for at least one satellite, in particular a picosatellite, comprising a frame that defines an inner space for receiving the satellite; and a retention device for holding the satellite in the inner space, the retention device being configured such that the satellite is releasable from the retention device.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Abstract: A tamping punch station for filling capsules in a capsule filling machine is described. The machine includes a rotatably drivable dosing disk with bore holes and a filling device for filling the bore holes. Tamping punches and ejection punches are held on a punch support, and vertical movement of the punch support causes the tamping punches to press filling material into the bore holes and the ejection punches to eject pellets created by the tamping punches in the bore holes. A first drive rotates the dosing disk along punches and a second drive moves the punch support. The second drive includes at least two spindle drives acting on the punch support with respectively one spindle nut and respectively one vertical drive spindle guided in the spindle nut and at least two drive motors, which drive respectively one of the spindle drives for vertical movement of the punch support.

Abstract: Methods for manufacturing a plastic container and for filling it with a fill product are described. The methods include introducing a perform into a blow mold, pressuring the preform with a blowing medium, evacuating the interior space of the container to an underpressure, and introducing a fill product in the interior space at an overpressure.