Abstract: An aircraft wing, including a fixed wing an outboard wing section, and a hinge assembly connecting the outboard wing section to the fixed wing. The aircraft wing is configurable between a flight configuration and a ground configuration. The hinge assembly includes a fore set of interleaving lugs and an aft set of interleaving lugs, an actuator, such as a Geared Rotary Actuator (GRA), located between the fore set of lugs and the aft set of lugs. The aircraft wing also includes a latch assembly, located in the fixed wing and inboard of the actuator, a fore latching arm and an aft latching arm. The latch assembly includes an aft latch pin, deployable in the aft direction to latch the aft latching arm, and a fore latch pin, deployable in a forward direction, to latch the fore latching arm.

Abstract: An aircraft wing including a fixed wing, an outboard wing section outboard of the fixed wing, and a hinge assembly connecting the outboard wing section to the fixed wing. The aircraft wing is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. The wing further includes a Geared rotary Actuator (GRA) configured to rotate the outboard wing section about the hinge axis to move the wing between the flight configuration and the ground configuration; an axial-flux motor configured to drive the GRA, the axial-flux motor being located inboard of the GRA, and a GRA transmission coupling the GRA to the axial-flux motor, to transfer a rotary output of the axial-flux motor into the GRA.

Abstract: An aircraft wing having a fixed wing and an outboard wing section including a powered system. The aircraft wing is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations by rotating the outboard wing section about a hinge axis of a hinge assembly. The aircraft wing also includes a power transmission conduit extending across the hinge assembly from the fixed wing to the outboard wing section, the first power transmission conduit being configured to power the powered system. The power transmission conduit extends across the hinge assembly along either a leading edge space or a trailing edge space.

Abstract: A high lift arrangement for a folding aircraft wing having a wing body with a folding wing tip including a high lift element arranged to have a deployed position in front of the leading edge of the folding wing tip, and an actuator for deploying the element. The actuator is mounted to the wing body such that there is no need for electrical or hydraulic cables to cross the wing fold line.

Abstract: A high lift arrangement for an aircraft wing includes a high lift element arranged to have a deployed position wherein the high lift element extends in front of at least an inboard portion of a leading edge of the wing tip. The high lift element has a sweep angle which is less than the sweep angle of the wing tip, such that a gap is formed between the element and the wing tip. A vortex is generated at the tip of the high lift element to energize the wing tip upper surface boundary layer. The gap accelerates the flow, improving low speed performance of the wing.

Abstract: A method of applying an ice-removal fluid (113) to a folding wing aircraft (100) is described, the method comprising applying the ice-removal fluid (113) to the folding wing portion (103) and holding the folding wing portion in an over-folded position (111) once the ice-removal fluid (113) has been applied. A method of operating an aircraft (100) during ground based operations is further described using the method of applying an ice-removal fluid (113).

Abstract: A method of applying an ice-removal fluid (113) to a folding wing aircraft (100) is described, the method comprising applying the ice-removal fluid (113) to the folding wing portion (103) and holding the folding wing portion in an over-folded position (111) once the ice-removal fluid (113) has been applied. A method of operating an aircraft (100) during ground based operations is further described using the method of applying an ice-removal fluid (113).

Abstract: A method of actuating a wing tip device on an aircraft, from a flight configuration to a ground configuration in which the span is reduced. The method includes receiving data indicative of a condition, such as the location or speed of the aircraft, and determining an actuation profile in dependence on the condition. The actuation profile may include determining a time period, and/or speed profile of the wing tip actuation over that time period. In this manner the actuation of the wing tip device can be tailored to minimize loads and wear on the actuator assembly.

Abstract: An interface for a wing folding mechanism of an aircraft. The interface has a central region comprising an internal surface, the internal surface being suitable for engaging a driven gear of a rotary actuator, and an attachment pad extending away from the central region in a first direction for attaching a surface to the interface. The interface can be used as part of the casing of a Geared Rotary Actuator. Also described are related wing assemblies, and aircraft and related methods.

Abstract: An interactive planning system is provided to allow a user to create and manage plans in online, offline, and intermittent connectivity environments. In some embodiments, the interactive planning system comprises a mobile, web-based application with an in-browser database configured to allow the user to create and manage plans in an offline environment and synchronize the plan when online connectivity is restored. In some embodiments, the interactive planning system comprises a fitness planning system configured to allow users to create and manage physical fitness plans in online, offline, and intermittent connectivity environments; to provide instructors the ability to enter fitness plan attributes, detail focus areas and timeframe for fitness plans; to provide instructors the ability to highlight macro-level phases to inform plan analytics; and to provide an ability to share programs to groups.

Abstract: A double coating, curing method, cured coating, and kit are provided. A first layer of the double coating can be a first cure coating composition, which has a first hydroxy-functional resin, a first crosslinking agent, and a non-polar catalyst. A second layer of a second cure coating composition can have a second hydroxy-functional resin, a second crosslinking agent, and a polar catalyst. The non-polar catalyst catalyzes crosslinking between the second hydroxy-functional resin and crosslinking agent, and not between the first hydroxy-functional resin and crosslinking agent. The polar catalyst catalyzes crosslinking between the first hydroxy-functional resin and crosslinking agent, and not between the second hydroxy-functional resin and crosslinking agent. The polarity of the catalysts can facilitate catalyst migration from one layer to the other. The separate compositions can be shelf-stable and/or the curing can occur at low temperature.

Abstract: A double coating, curing method, cured coating, and kit are provided. A first layer of the double coating can be a first cure coating composition, which has a first hydroxy-functional resin, a first crosslinking agent, and a first catalyst. A second layer of a second cure coating composition can have a low hydrophilicity acrylic resin as a second hydroxy-functional resin, a second crosslinking agent, and a second catalyst. The first catalyst catalyzes crosslinking between the second hydroxy-functional resin and crosslinking agent, and not between the first hydroxy-functional resin and crosslinking agent. The second catalyst catalyzes crosslinking between the first hydroxy-functional resin and crosslinking agent, and not between the second hydroxy-functional resin and crosslinking agent. The first and/or second hydroxy functional resins can facilitate catalyst migration from one layer to the other. The separate compositions can be shelf-stable and/or the curing can occur at low temperature.

Abstract: Example implementations relate to maintaining service availability. According to an example, a distributed system including multiple nodes establishes a number of the nodes to operate as voters in a quorum evaluation process for a service supported by the nodes. A first proper subset of the nodes is identified to operate as the voters and the remainder of the nodes do not vote in the quorum evaluation process. Responsive to detecting, by a voter, existence of a failure that results in the voter being part of a second proper subset of the nodes and that calls for a quorum evaluation, the voter determines whether the second proper subset of nodes has a quorum by initiating the quorum evaluation process. When the determining is affirmative, the second proper subset continues to support the service; otherwise, the second proper subset discontinues to make progress on behalf of the service.

Abstract: Methods and systems are provided for adjusting operation of a split exhaust engine system based on a total flow of gases through a scavenge exhaust gas recirculation system of the split exhaust engine system. In one example, a method may include adjusting engine operation in response to a flow of gases to an intake passage, upstream of a compressor, from a scavenge manifold coupled to scavenge exhaust valves, the flow of gases determined based on a valve opening overlap between the scavenge exhaust valves and intake valves of an engine, the scavenge exhaust valves opened at a different time than blowdown exhaust valves coupled to a blowdown manifold coupled to a turbine.

Abstract: Methods and systems are provided for adjusting operation of a split exhaust engine system based on a total flow of gases through a scavenge exhaust gas recirculation system of the split exhaust engine system. In one example, a method may include adjusting engine operation in response to a flow of gases to an intake passage, upstream of a compressor, from a scavenge manifold coupled to scavenge exhaust valves, the flow of gases determined based on a valve opening overlap between the scavenge exhaust valves and intake valves of an engine, the scavenge exhaust valves opened at a different time than blowdown exhaust valves coupled to a blowdown manifold coupled to a turbine.

Abstract: Methods and systems are provided for determining a dilution of recirculated gases, including blowthrough air, combusted exhaust gas, and fuel vapor, in a split exhaust engine. In one example, the dilution rate may be calculated using a feedforward model that includes determining a pressure differential across a region in an intake passage, mapped engine parameters such as gas temperature, and exhaust valve timing. Engine operations such as spark advance and fuel injection may be adjusted according to the modeled rate to reduce engine knock and improve combustion efficiency.

Abstract: The present disclosure generally pertains to novel water soluble oligomeric and polymeric additives derived from oligomeric and polymeric amines; esters or halides of twin tail alkyl group comprising acids with intervening quaternary ammonium groups; optionally and preferably hydrophilic group comprising compounds capable of reacting with primary, secondary or tertiary amino groups; and optionally hydrophobic group comprising compounds. The compounds of the invention are useful as additives for aqueous film forming foam agents, and can perform as partial or complete replacements for fluorosurfactants and/or fluorinated foam stabilizers in foams.

Abstract: A double coating, curing method, cured coating, and kit are provided. A first layer of the double coating can be a first cure coating composition, which has a first hydroxy-functional resin, a first crosslinking agent, and a non-polar catalyst. A second layer of a second cure coating composition can have a second hydroxy-functional resin, a second crosslinking agent, and a polar catalyst. The non-polar catalyst catalyzes crosslinking between the second hydroxy-functional resin and crosslinking agent, and not between the first hydroxy-functional resin and crosslinking agent. The polar catalyst catalyzes crosslinking between the first hydroxy-functional resin and crosslinking agent, and not between the second hydroxy-functional resin and crosslinking agent. The polarity of the catalysts can facilitate catalyst migration from one layer to the other. The separate compositions can be shelf-stable and/or the curing can occur at low temperature.

Abstract: Methods and systems are provided for determining a dilution of recirculated gases, including blowthrough air, combusted exhaust gas, and fuel vapor, in a split exhaust engine. In one example, the dilution rate may be calculated using a feedforward model that includes determining a pressure differential across a region in an intake passage, mapped engine parameters such as gas temperature, and exhaust valve timing. Engine operations such as spark advance and fuel injection may be adjusted according to the modeled rate to reduce engine knock and improve combustion efficiency.

Abstract: A double coating, curing method, cured coating, and kit are provided. A first layer of the double coating can be a first cure coating composition, which has a first hydroxy-functional resin, a first crosslinking agent, and a first catalyst. A second layer of a second cure coating composition can have a low hydrophilicity acrylic resin as a second hydroxy-functional resin, a second crosslinking agent, and a second catalyst. The first catalyst catalyzes crosslinking between the second hydroxy-functional resin and crosslinking agent, and not between the first hydroxy-functional resin and crosslinking agent. The second catalyst catalyzes crosslinking between the first hydroxy-functional resin and crosslinking agent, and not between the second hydroxy-functional resin and crosslinking agent. The first and/or second hydroxy functional resins can facilitate catalyst migration from one layer to the other. The separate compositions can be shelf-stable and/or the curing can occur at low temperature.