A fuel freeze mitigation and/or prevention system includes a power generator configured and adapted to be positioned within a fuel storage tank. A fluid mover device is in electrical communication with the power generator. The fluid mover device is configured and adapted to be positioned within a fuel storage tank to mitigate or prevent fuel freeze in the fuel storage tank. A method for mitigating or preventing fuel freeze in a fuel storage tank includes harvesting energy with a power generator positioned within the fuel storage tank, charging a battery with the harvested energy, monitoring a fuel temperature inside the fuel storage tank, and turning a fluid mover device positioned within the fuel storage tank ON or OFF depending on at least one of a manual command or the fuel temperature inside the fuel storage tank to mitigate or prevent fuel freeze in the fuel storage tank.

A cooling system includes a thermal engine having a fluid output, and a motor drive having a fluid inlet in fluid communication with the fluid output of the thermal engine. The fluid inlet of the motor drive is downstream from the fluid output of the thermal engine. The system includes a fluid storage downstream from the motor drive and a fluid output of the motor drive. A method of cooling a motor drive includes outputting a cooling fluid from a fluid output of a thermal engine, receiving the cooling fluid from the fluid output of the thermal engine in a fluid inlet of a motor drive, passing the cooling fluid through the motor drive to a fluid output of the motor drive, receiving the cooling fluid in a fluid storage.

An aircraft includes an engine, a fuel tank, a chamber, a system, and an introduction line. The chamber is located in the tank, occupies only a part of the tank, and includes a sensor for measuring a property of the fuel. The system injects fuel into the line. The introduction line introduces fuel from the injection system into the chamber. The introduction line includes a valve capable of preventing an introduction of fuel from the injection system into the chamber via the line.

An aircraft includes an engine, a fuel tank, a chamber, a system, and an introduction line. The chamber is located in the tank, occupies only a part of the tank, and includes a sensor for measuring a property of the fuel. The system injects fuel into the line. The introduction line introduces fuel from the injection system into the chamber. The introduction line includes a valve capable of preventing an introduction of fuel from the injection system into the chamber via the line.

A fuel tank system is disclosed that includes a fuel tank and a first fluid flow path between a gas space in the fuel tank and outside of the fuel system. A gas separation membrane is disposed with a first side in communication with the first fluid flow path and a second side in communication with a second fluid flow path. A fluid control device is in communication with the second fluid flow path and is configured to provide fluid flow from the second fluid flow path to a liquid space in the fuel tank or to outside of the fuel system. A prime mover is disposed in communication with the second fluid flow path, and is configured to move fluid on the second fluid flow path from the second side of the separation membrane to the fuel tank liquid space or to outside of the fuel system.

A fuel tank system is disclosed that includes a fuel tank and a first fluid flow path between a gas space in the fuel tank and outside of the fuel system. A gas separation membrane is disposed with a first side in communication with the first fluid flow path and a second side in communication with a second fluid flow path. A fluid control device is in communication with the second fluid flow path and is configured to provide fluid flow from the second fluid flow path to a liquid space in the fuel tank or to outside of the fuel system. A prime mover is disposed in communication with the second fluid flow path, and is configured to move fluid on the second fluid flow path from the second side of the separation membrane to the fuel tank liquid space or to outside of the fuel system.

An ergonomic method for working in confined work spaces is disclosed. The method, in some cases, includes the steps of: a) providing a support structure that is generally in the configuration of a rectangular prism having six faces, a length, width, and a height in which the length, width, and height differ from one another so that the structure provides three different height positions when the support structure is placed on the floor of the workspace; b) placing the support structure with one of its faces in contact with a contoured floor surface in a confined work space; and c) sitting or standing on the support structure.

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 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.

The present application relates to a fuel flow system. In particular, the application relates to a fuel flow system for an aircraft. The fuel flow system has a fuel conduit having a fuel inflow and a fuel outflow along which a fuel/water mix is configured to flow from the fuel inflow to the fuel outflow. The fuel conduit is fluidly communicable with a fuel tank. A peripheral conduit surrounds at least part of the fuel conduit. A water-permeable member is disposed between the fuel conduit and the peripheral conduit. The water-permeable member enables water from the fuel/water mix to flow through the water-permeable member from the fuel conduit into the peripheral conduit, but at least substantially prevents liquid fuel from the fuel/water mix from doing so.