A valve for a hydraulic circuit for an aircraft, the valve being configured to unite or separate multiple circuit portions in at least two configurations. More particularly, the valve allows to create one hydraulic circuit or two independent hydraulic circuits in order to circulate a coolant in two distinct manners and thus to adapt the function of the hydraulic circuit to any of two distinct phases of the functioning of an engine of the aircraft.

A chassis includes top rails extending along a top side of the chassis, bottom rails extending along a bottom side of the chassis, a fluid inlet connected to the chassis that is configured to receive a thermal transfer fluid, and a fluid outlet connected to the chassis that is configured to discharge the thermal transfer fluid. The chassis further includes a thermal transfer fluid path extending between and fluidly coupled to the fluid inlet and the fluid outlet, wherein the thermal transfer fluid is configured to flow through the thermal transfer fluid path, and wherein the thermal transfer fluid path extends in a serpentine pattern through at least one of the top rails and through at least one of the bottom rails.

A chassis includes top rails extending along a top side of the chassis, bottom rails extending along a bottom side of the chassis, a fluid inlet connected to the chassis that is configured to receive a thermal transfer fluid, and a fluid outlet connected to the chassis that is configured to discharge the thermal transfer fluid. The chassis further includes a thermal transfer fluid path extending between and fluidly coupled to the fluid inlet and the fluid outlet, wherein the thermal transfer fluid is configured to flow through the thermal transfer fluid path, and wherein the thermal transfer fluid path extends in a serpentine pattern through at least one of the top rails and through at least one of the bottom rails.

An electronics cooling system for an aircraft includes a heat exchanger comprising a coolant circuit, an air circuit, and a fuel circuit such that each of the circuits is in thermal communication with at least one of the other circuits. The coolant circuit is in thermal communication with one or more aircraft electronics. The air circuit is in fluid communication with at least one air source. The fuel circuit is in fluid communication with a fuel tank between the fuel tank and an engine of the aircraft.

An electronics cooling system for an aircraft includes a heat exchanger comprising a coolant circuit, an air circuit, and a fuel circuit such that each of the circuits is in thermal communication with at least one of the other circuits. The coolant circuit is in thermal communication with one or more aircraft electronics. The air circuit is in fluid communication with at least one air source. The fuel circuit is in fluid communication with a fuel tank between the fuel tank and an engine of the aircraft.

A method, system and apparatus are provided for generating and dispersing plumes of reflective aerosols. Methods include: supplying fuel to an engine of an aircraft for combustion; supplying an additive to the fuel, where the additive includes at least one of a reflective aerosol or a precursor thereof; combusting the fuel and the additive to the fuel in the engine; and generating, in the exhaust from the engine, a plume of reflective aerosol, where the reflective aerosol reflects sunlight.

A heat exchanger includes a first side of a heat exchanger layer with a first flow path, wherein the first flow path flows through a heat soak region and a flow region, and a second side of the heat exchanger layer with a second flow path in thermal communication with the first flow path, wherein an inlet of the first flow path and an inlet of the second flow path are proximate in the heat soak region.

A heat exchanger includes a first side of a heat exchanger layer with a first flow path, wherein the first flow path flows through a heat soak region and a flow region, and a second side of the heat exchanger layer with a second flow path in thermal communication with the first flow path, wherein an inlet of the first flow path and an inlet of the second flow path are proximate in the heat soak region.

A system for fuel and thermal management of fuel delivered to an engine is disclosed. The system includes a supply of fuel in fluid communication with a fuel inlet of the engine, and an oxygen sensor for measuring dissolved oxygen content in the fuel is in fluid communication with the fuel. The fuel is heated by transferring heat from engine oil in a heat exchanger. The temperature of the fuel is controlled by controlling engine oil flow and airflow through another heat exchanger upstream of the fuel/oil heat exchanger on the oil circulation path with engine oil.

A system for fuel and thermal management of fuel delivered to an engine is disclosed. The system includes a supply of fuel in fluid communication with a fuel inlet of the engine, and an oxygen sensor for measuring dissolved oxygen content in the fuel is in fluid communication with the fuel. The fuel is heated by transferring heat from engine oil in a heat exchanger. The temperature of the fuel is controlled by controlling engine oil flow and airflow through another heat exchanger upstream of the fuel/oil heat exchanger on the oil circulation path with engine oil.