A bracket manifold for a landing gear assembly is disclosed. In various embodiments, the bracket manifold includes a mounting plate having a central portion and a first wing portion extending from the central portion; and a first manifold section integrated monolithically into at least one of the central portion and the first wing portion of the mounting plate.

Fault prediction improvements are provided herein via pruning a dataset by selecting a subset of the dataset for use as a pruned dataset, wherein the pruned dataset includes pressure data for a hydraulic system correlated in time with command signals for a plurality of deployment events of the hydraulic system, and in response to determining that a given pressure value for a given deployment event in the pruned dataset satisfies a low pressure threshold and that a change in pressure values over time during the given deployment event satisfies a pressure slope threshold, generating a service message for the hydraulic system that indicates that the hydraulic system is in a prefault state.

Disclosed is an aircraft piston assembly, having: a piston housing fluid port formed in a piston housing; a piston shaft, disposed within the piston housing, configured for translation in either forward or aft directions when fluid is respectively supplied to or removed from the piston housing; a screw shaft, disposed within the piston housing, that includes a first gear that rotates without translation while the piston shaft translates; and a slider, disposed within the piston housing, that includes a second gear, and that is configured for translation without rotation, wherein: the slider moves between a first position where the first gear and the second gear are separated from one another to allow the piston shaft to translate and a second position where the second gear surrounds the first gear so that the first and second gears are engaged with one another and the piston shaft is prevented from translating.

A poppet of a check valve includes a base, a shaft extending from the base, and a sealing head coupled to the shaft and extended away from the base by the shaft. A flow channel is defined between the base, the shaft, and the sealing head. The base includes a plurality of holes.

A poppet of a check valve includes a base, a shaft extending from the base, and a sealing head coupled to the shaft and extended away from the base by the shaft. A flow channel is defined between the base, the shaft, and the sealing head. The base includes a plurality of holes.

A thermal actuator includes a piston slidingly within a cylinder. The piston cooperates with the cylinder to define a cavity. The piston also includes a rod extending away from the cavity. A magnetic field generator selectively imparts an alternating magnetic field to the cylinder, and inductively heats a heating element mounted within the cavity. The cavity also includes a volume of a phase-change material, which is melted by the heating element. The melting phase-change material expands to drive the rod from a retracted position to an extended position.

The present disclosure provides an aircraft thermal management system. The aircraft thermal management system includes a first hydraulic system for circulating a first hydraulic fluid, a second hydraulic system for circulating a second hydraulic fluid, and a third hydraulic system for circulating a third hydraulic fluid. The aircraft thermal management system also includes a controller configured to: (i) determine a temperature of the first hydraulic fluid, a temperature of the second hydraulic fluid, and a temperature of the third hydraulic fluid, and (ii) based on the determined temperature of the first hydraulic fluid, utilize the second hydraulic fluid and/or the third hydraulic fluid to modify an operational temperature of the first hydraulic fluid.

A sub-system 200 for an aircraft hydraulic system 20 that includes a first inlet 202 for receiving fluid from a supply 22 of hydraulic fluid, a system valve 210 for controlling fluid flow from the sub-system 200 to a hydraulically-operable system 24 of the aircraft hydraulic system 20, a check valve 220 for permitting fluid flow from the sub-system 200 and preventing or hindering fluid flow into the sub-system 200, a second inlet 240 for receiving fluid from a second supply 28 of hydraulic fluid, and a selector 230. The selector 230 configured to place the system valve 210 in fluid communication with the first inlet 202 when the selector 230 is in a first state, and to place the system valve 210 in fluid communication with the check valve 220 and the second inlet 240 when the selector 230 is in a second state different from the first state.

A sub-system 200 for an aircraft hydraulic system 20 that includes a first inlet 202 for receiving fluid from a supply 22 of hydraulic fluid, a system valve 210 for controlling fluid flow from the sub-system 200 to a hydraulically-operable system 24 of the aircraft hydraulic system 20, a check valve 220 for permitting fluid flow from the sub-system 200 and preventing or hindering fluid flow into the sub-system 200, a second inlet 240 for receiving fluid from a second supply 28 of hydraulic fluid, and a selector 230. The selector 230 configured to place the system valve 210 in fluid communication with the first inlet 202 when the selector 230 is in a first state, and to place the system valve 210 in fluid communication with the check valve 220 and the second inlet 240 when the selector 230 is in a second state different from the first state.

A method of supplying hydraulic power via a zonal hydraulic system to an aircraft having a plurality of operating phases includes determining a current operating phase of the aircraft and setting a power limit (e.g., a pressure set point and/or flow limitation) for at least one hydraulic power unit based on the current operating phase. The hydraulic system includes a plurality of hydraulic zones. Each of the hydraulic zones includes a local controller, a hydraulic power unit controlled by the local controller, and at least one actuator powered by the hydraulic power unit. Energy savings may be realized by altering the pressure set point for and/or limiting the flow to hydraulic systems in inactive and/or less active zones. The zonal hydraulic system may be reconfigured for safety based on sensed failures and/or during emergency or alternate power conditions with limited available power. Duty cycles for multiple electric motor driven pumps of the system may be balanced. Dependency on a central hydraulic system controller may be minimized or eliminated by providing default power limit (e.g., pressure setting) reversion logic at the local controller.