Abstract: There is provided an outboard motor. In a posture in use of the outboard motor, an oil filter is inclined such that a mounting portion side is located lower than a tip end side and the mounting portion side is located at an inner side and a tip end side is located at an outer side in the width direction of the outboard motor, a cover mating position between an upper engine cover and a lower engine cover is set to a position lower than an upper part of the tip end, and is higher than a lower part of the mounting portion, and an electric actuator is mounted on a lower part of an engine block and is mounted on a position closer to a center of the engine relative to a position of an outermost end of the oil filter in a width direction of the engine.

Abstract: A structural assembly includes a support structure and an elongate structure intersecting the support structure. The elongate structure has a length and a mass. The mass of the elongate structure varies along the length of the elongate structure. A localized mass of the elongate structure decreases toward the support structure and increases away from the support structure.

Abstract: A decorative laminate is disclosed, including a first laminate layer containing an anti-microbial agent and a second laminate layer. A decorative layer is disposed selectively between the first laminate layer and the second laminate layer. The first and second laminate layers include a thermoplastic fluoropolymer material. The first laminate layer, the decorative layer, and the second laminate layer are laminated together to form the decorative laminate, which is configured for application to a structural component.

Abstract: A cargo loading platform for an aircraft, with a plate-like supporting structure, which is configured to support or to receive cargo, and a lifting device. The lifting device is arranged asymmetrically on the plate-like supporting structure and can be moved from a stowage position to a lifting position. In the stowage position, the lifting device is arranged here above a lower side of the plate-like supporting structure and, in the lifting position, is at least partially arranged below the lower side of the plate-like supporting structure. This permits asymmetrical raising of the plate-like supporting structure by the lifting device, as a result of which steps during the transportation of the cargo loading platform can be easily and rapidly overcome. Furthermore, a cargo loading apparatus and a cargo container each with such a cargo loading platform, and also an aircraft with such a cargo loading apparatus are described.

Abstract: A system and method for constructing a composite structure using a multi-piece tool. The pieces are assembled, including making a connection, such as a mortise-and-tenon connection, between pieces using an adhesive mixed with an induction heatable material, such as iron filings having a unit size of between 5 microns and 600 microns, and an amount of between 5% and 50% by volume. Plies of a material are applied around the connection between the pieces, and the plies are cured to create the composite structure, which results in the pieces being trapped within the composite structure by the connection. The adhesive is exposed to electromagnetic induction from an electromagnetic induction coil which generates heat in the induction heatable material and thereby loosens the connection. The tool can then be disassembled by individually pulling at least some of the pieces from within the composite structure.

Abstract: An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and an electrical storage device; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.

Abstract: The invention relates to an aircraft having a tailless fuselage. The fuselage has a body which includes a transverse trailing edge. The aircraft further includes a wing having two sides which protrude from opposite sides of the fuselage. The body typically has a fineness ratio of between 3 and 7. Each side of the wing has an inner section having a first dihedral angle and an outer section having a second dihedral angle, the second dihedral angle being less than the first dihedral angle. At least part of the outer section is typically swept back. The configuration of the aircraft provides it with improved flight efficiency.

Abstract: Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.

Abstract: Systems and methods for hydraulic droop control of an aircraft wing. One embodiment is a hydraulic droop panel system for an aircraft wing. The hydraulic droop panel system includes a first hydraulic actuator attached to a flap of the aircraft wing, and a second hydraulic actuator attached to a droop panel of the aircraft wing and fluidly coupled with the first hydraulic actuator. The second hydraulic actuator is configured to move the droop panel to a droop position corresponding with movement of the flap and the first hydraulic actuator.

Abstract: Variably porous panels and panel assemblies incorporating shape memory alloy components along with methods for actuating the shape memory alloys are disclosed to predictably alter the porosity of a substrate surface, with the shape memory alloy maintained in an orientation relative to the panel that is in-plane with a mold-line of the panel outer surface.

Abstract: The turboshaft engine for a rotorcraft includes a low pressure spool having a low pressure compressor and a low pressure turbine section, and a high pressure spool having a high pressure compressor and a high pressure turbine section. The spools are independently rotatable relative to one another. The low pressure compressor section includes a mixed flow rotor. A set of variable guide vanes (VGVs) are disposed upstream of each of the low pressure and high pressure compressors, the VGVs being configured to be independently operable relative to one another.

Abstract: Systems, devices, and methods for an aircraft having a fuselage; a wing extending from both sides of the fuselage; a first pair of motors disposed at a first end of the wing; and a second pair of motors disposed at a second end of the wing; where each motor is angled to provide a component of thrust by a propeller attached thereto that for a desired aircraft movement applies a resulting torque additive to the resulting torque created by rotating the propellers.

Abstract: A method of mounting a replacement tip section to an exposed end of a rotor blade includes removing an existing tip section from the rotor blade to create the exposed end of the rotor blade, installing the rotor blade having the exposed end onto a holding fixture, assembling the replacement tip section about the exposed end of the rotor blade, positioning a bonding fixture about the replacement tip section, and curing the replacement tip section to the exposed end of the rotor blade.

Abstract: Embodiments are directed to systems and methods for creating a tubular composite structure. In one embodiment, a device comprises multiple layers of cured composite fabric bonded together to form a tubular composite structure, wherein alternating groups of the multiple layers comprise on-axis fabric and off-axis fabric. The tubular composite structure may form a spar for an aerodynamic component. The composite fabric may comprise one or more of carbon, fiberglass, or other composite materials, or a combination of materials. One or more stacks of the fabric wrap completely around the tubular composite structure, and other stacks of fabric may not wrap completely around the tubular composite structure.

Abstract: A bushing assembly for receiving a fastener includes a first bushing portion and a second bushing portion arranged coaxially with the first bushing portion. The second bushing portion defines at least part of an opening for receiving the fastener. The second bushing portion is rotatable relative to the first bushing portion about an axis of rotation to adjust a position of the opening about a first axis and a second axis independently relative to the first bushing portion and the second bushing portion. The first axis is coplanar with and perpendicular to the second axis.

Abstract: An aircraft is provided including at least one pilot input and a flight control system n communication with the at least one pilot input. The flight control system is operable in a manual mode and a pointing mode. In the manual mode, a velocity, position, and attitude of the aircraft are controlled manually, and in the pointing mode, at least one of the velocity and position of the aircraft is controlled by the flight control system and at least one of the attitude and heading of the aircraft is controlled manually.

Abstract: A disaster response robot includes: a disaster scene map storing module configured to store the disaster scene map; an autonomous driving module configured to perform autonomous driving based on the disaster scene map; a manual driving route receiving module configured to receive a manual driving route from a control device for an area; a manual driving module configured to perform manual driving; an investigation information real-time collecting module configured to collect investigation information during the autonomous driving performed by the autonomous driving module and the manual driving performed by a manual driving module; and an investigation information transmitting module configured to transmit the investigation information collected in real time by the investigation information real-time collecting module to the control device.

Abstract: Embodiments relate to a client-facing application for interacting with a transport service that transports items via unmanned aerial vehicles (UAVs). An example graphic interface may allow a user to order items to specific delivery areas associated with their larger delivery location, and may dynamically provide status updates and other functionality during the process of fulfilling an aerial vehicle transport request.

Abstract: A fire suppression drone comprises a main body, a plurality of propellers provided on an outer circumference of the main body and driven by a driving motor, a pump provided in the main body and connected to a water feeding vehicle through a water feeding hose, at least one water jet nozzle provided on the outer circumference of the main body to jet water supplied by the pump, a camera provided on the outer circumference of the main body, and a controller connected with the driving motor, the pump, and the camera and connected with a remote controller to be wirelessly communicable with the remote controller, wherein the remote controller includes a monitor, the monitor capable of display, in real-time, an image captured by the camera.

Abstract: A tow cable system and method of use wherein, in the context of towed flight of a glider behind an aircraft, positive load or tension of the cable therebetween is achieved through one or more of cable design and material selection, cable pre-tensioning, in-flight cable tensioning, and/or load dampening device(s), and the related interplay of such various components or sub-systems of the overall tow cable system.

Abstract: Disclosed herein is an Unmanned Aerial Vehicle (“UAV”) capable of carrying modules of Sub Unmanned Aerial Vehicles (“Sub UAVs”). More particularly, a UAV may be capable of communicating via satellite and remote control technology, ejecting said Sub UAVs, flying in sequence in a coordinated manner with the Sub UAVs, and capable of engaging in multiple missions in high, medium, low altitude, and surface. Further, the Sub UAVs can be enabled to return back to the UAV after the mission is completed and be firmly secured to the flatbed of the UAV.

Abstract: A method includes receiving, at a controller, a signal from each load cell of a plurality of load cells coupled to an aircraft cargo roller panel of an aircraft. Each signal is indicative of a load experienced by the load cell when cargo is on the aircraft cargo roller panel. The method also includes determining, based on the signals, a weight of the cargo, a center of gravity of the cargo, or both.

Abstract: The invention relates to a monument assembly designed for being fitted into an aircraft which is optimized with respect to crew attendant seats (11, 12, 21, 22), by replacing direct vision monitoring of passenger seats (10) with a cabin monitoring system including a capturing device (101, 102, 103). Benefits are at least one amongst improved comfort for the passengers, increased number of passenger seats, and reduced weight contribution due to the crew attendant seats, while maintaining fulfilment of the safety requirements.

Abstract: Disclosed is a monument for an aircraft cabin (11). On said monument, a screen (4) is provided for displaying the images captured by a video surveillance device (5).

Abstract: The present disclosure relates to seating apparatus. In particular, the present application relates to an aircraft seat (1). The aircraft seat (1) includes a seat chassis (4) and a seat assembly (5). The seat assembly (5) has a seat pan (6) and a seat back (7). The seat pan (6) is mounted to the seat chassis (4) by a first pivoting connection (30) defining a seat pan pivot axis (Y1) about which the seat pan (6) pivots. The location of the seat pan pivot axis (Y1) is fixed relative to the seat chassis (4). At least one seat pan link (53-1) is provided for controlling pivoting of the seat pan (6) about said seat pan pivot axis (Y1). The at least one seat pan link (53-1) is coupled to the seat pan (6) in front of the seat pan pivot axis (Y1). The present disclosure also relates to an aircraft (2) including one or more of the aircraft seat (1).

Abstract: A ram air fan and fan bypass shutoff check valve assembly includes a ram air fan configured to draw an airflow through a fan inlet, and a ram fan bypass duct positioned downstream of the ram air fan. The ram fan bypass duct includes a valve assembly configured to selectably direct the airflow through the ram air fan when the valve assembly is in an open position, and direct the airflow through a bypass duct thereby bypassing the ram air fan when the valve assembly is in a closed position.

Abstract: In an embodiment, a system to deploy a plurality of parachutes includes a plurality of parachute canopies each packed in a canister, a plurality of rockets adapted to extract an associated canopy from the canister, and a controller. The controller is configured to determine that an aircraft is at least one of: in a hover mode of operation and a forward flight mode of operation. In response to the determination that the aircraft is in the hover mode of operation, the controller applies a hover deployment sequence including by instructing the plurality of parachutes to deploy substantially simultaneously. In response to the determination that the aircraft is in the forward mode of operation and above a threshold airspeed, the controller applies a forward deployment sequence including by instructing the plurality of parachutes to deploy in a predefined sequence.

Abstract: A method for deploying an inflatable slide includes increasing pressure within the inflatable slide, increasing a load in a force releasing member and a dampener, both of which are attached to the inflatable slide, in response to the increasing pressure within the evacuation slide, the load being increased at a slower rate than would occur if the dampener were not present, separating the force releasing member, and inflating the inflatable slide.

Abstract: This disclosure generally relates to the use of solid fuel rockets with drone aircraft. Solid fuel tanks can be mounted to a Drone, for example, the underside of the drone. They may be built similar to guided missiles and once they complete their task they may detach from the drone and, in embodiments, equipped with all components found on guided missiles, i.e., guidance Section, control section, wings and fins, they may return to point of origin. In other embodiments, they may be deployed as missiles or remain attached to the drone.

Abstract: An aircraft power system according to an exemplary embodiment of this disclosure includes, among other possible things, a battery, a motor/generator coupled to the battery, an inertial drum rotatable about an axis of rotation and coupled to the motor/generator, wherein the motor/generator drives rotation of the inertial drum in a first operating mode and is driven by the inertial drum in a second operating mode; and a housing defining a chamber for the inertial drum, the chamber filled with low-viscosity medium to reduce friction on the inertial drum.

Abstract: A propulsor includes an electric motor, a fan unit, and a thrust system positioned downstream of and coupled to the fan unit.

Abstract: An alternating current type electric propulsion system is described that includes an AC generator and a plurality of propulsors electrically coupled to the AC generator. A first propulsor from the plurality of propulsors includes a first motor that drives a first fan of the first propulsor at a first speed. A second propulsor from the plurality of propulsors comprises a second motor that drives a second fan of the second propulsor at a second speed that is different than the first speed.

Abstract: An exemplary vertical takeoff and landing includes a rotor driven by an electric motor, a generator located in a compartment and electrically connected to the electric motor, and an inlet formed through a side of the compartment to direct sideward airflow across the generator.

Abstract: An aircraft propulsor that includes a load bearing moveable panel is described herein. In one example, the moveable panel can be coupled to a propulsor structure to receive loads from the propulsor structure. Such loads can include roll and/or torque loads generated by rotation of a core engine of the aircraft propulsor. The moveable panel can be coupled to the propulsor structure through a plurality of coupling portions on one or both of the moveable panel and the propulsor structure.

Abstract: An unmanned aerial vehicle includes a fuselage, a motor mounted at the fuselage, and a control apparatus configured to control the motor. The control apparatus includes one or more processors configured to obtain a present electrical parameter of a battery configured to power the motor, calculate a compensation amount of a control signal of the motor according to the present electrical parameter, and modify the control signal according to the compensation amount.

Abstract: Embodiments described herein provide active dampening of flexible modes of a UAV during flight operations. During operation of a UAV having a flexible airframe, the thrust and/or torque of the motor(s) coupled to propellers can induce flexing in the airframe that reduces the flight performance of the UAV. Measurements of a linear acceleration and/or an angular rate at a location proximate to the motor are performed, and flexible modes in the airframe of the UAV are identified based on the measurements. An operation of the motor(s) is modified based on the measurements to dampen the flexible mode.

Abstract: Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor.

Abstract: Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor.

Abstract: Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor.

Abstract: Control systems and methods for controlling an engine. The control system includes a computation module and an input/output (I/O) module attached to the engine. The computation module is located in an area of the engine, or off-engine, that provides a more benign environment than the environment that the I/O module is subject to during operation of the engine. The I/O module includes a first processor and a first network interface device. The computation module includes a second processor with higher processing power than the first processor, and a second network interface device. The control system also includes a sensor configured to provide sensor readings to the first processor. The first processor transmits data based on the sensor readings to the second processor. The control system also includes an actuator operably coupled to the I/O module and that is controlled by the first processor based on commands from the second processor.

Abstract: A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

Abstract: A multi-engine power system is described that includes at least a first engine and a second engine configured to jointly provided mechanical power to the multi-engine power system. The multi-engine power system further includes a controller configured to estimate a deterioration factor of the first engine. The controller is further configured to adjust, based on the deterioration factor of the first engine, a first amount of mechanical power being provided by the first engine to increase a service time of the first engine, and adjust, based on the first amount of mechanical power being provided by the first engine, a second amount of mechanical power being provided by the second engine to compensate for the adjustment to the first amount of mechanical power.

Abstract: Various embodiments include a drive system for a vehicle, the system comprising: an internal combustion engine for converting chemical energy stored in a liquid fuel into mechanical energy; a fuel tank for storing fuel for use by the internal combustion engine; and an electric machine having a rotor, a stator, and a cooling system for cooling at least one component of the electric machine using a cooling liquid. The cooling liquid comprises the fuel.

Abstract: A fluid system includes a controller, a control valve, and a fluid manifold. At least one solenoid may be connected to the fluid manifold, the control valve, and/or the controller. A first pressure sensor may be in fluid communication with an output of the control valve. A second pressure sensor may be in fluid communication with the fluid manifold. The controller may be configured to control operation of the control valve via the at least one solenoid according to a first fluid pressure obtained via the first pressure sensor and according to a second fluid pressure obtained via the second pressure sensor.

Abstract: A noncombustible gas distribution method includes distributing noncombustible gas to a center wing tank throughout a continuous, first flight period and, as a result, reducing flammability exposure time during the first flight period or during a subsequent flight period. The method includes not distributing noncombustible gas to left and right main wing tanks while the noncombustible gas is distributed to the center wing tank throughout the first flight period and while the left and right main wing tanks are non-flammable. A noncombustible gas distribution system includes a noncombustible gas source and distribution tubing from the gas source to left and right main wing tanks and a center wing tank. A distribution mechanism yields a greater proportion of gas flow per tank unit volume distributed to an outboard section of the left and right main wing tanks compared to an inboard section during a climb phase of the aircraft's flight.

Abstract: Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.

Abstract: An electronic unit defines an interior and includes a circuit card assembly disposed in the interior. An enclosure surrounds five sides of the interior. A sixth side of the interior is closed by a circuit card assembly.

Abstract: A method of aircraft operation, the method comprising accepting a human pilot's selection of at least one checklist from among plural checklists stored in computer memory; and, responsive to the pilot's selection, using a processor for automatically performing all operations included in the individual checklist.

Abstract: In an example, a method for identifying associated events in an aircraft is described. The method includes obtaining sensor data, obtaining fault code data, generating a set of events, where each event occurs over a time interval over which either (i) the sensor data indicates an anomalous measurement or (ii) a fault code associated with a particular aircraft subsystem of the aircraft was signaled, calculating a value of statistical dependence between the set, based on the value exceeding a threshold, constructing a network representing the set as a sequence of related events and further representing a temporal order in which the sequence occurred, indexing, in a summary table stored in memory and separate from the sensor data and the fault code data, the sequence and the value, and controlling a display device to display the summary table and a visual representation of the network.

Abstract: An aircraft structure protected from collisions with foreign objects includes a first support proximate to an aircraft structure root; first sheets attached to the first support to form a first leading edge portion of the aircraft structure; a second support proximate to an outer end of the aircraft structure; second sheets attached to the second support to form a second leading edge portion; and a door including one or more ribs disposed between the first and second supports and configured to give shape to a third leading edge portion of the aircraft structure; and third sheets, attached to the ribs to form the third portion of the leading edge; wherein the first support, the first sheets, the second support, the second sheets, the one or more ribs, and the third sheets are disposed to mitigate damage from a foreign object collision by absorbing kinetic energy from a collision.