Methods and apparatus to cool a vehicle heat source are disclosed herein. An example apparatus includes a first tank and a second tank. The first tank and the second tank are disposed on a vehicle. The second tank is in fluid communication with the first tank. An engine of the vehicle is to be supplied with fuel from at least one of the first tank or the second tank. The example apparatus also includes a cooling system disposed on the vehicle to cool the fuel flowing from the first tank to the second tank. The example apparatus further includes a heat exchanger operatively coupled to a heat source disposed on the vehicle. The fuel from the second tank is to flow to the first tank via the heat exchanger to cool the heat source.

Methods and apparatus to cool a vehicle heat source are disclosed herein. An example apparatus includes a first tank and a second tank. The first tank and the second tank are disposed on a vehicle. The second tank is in fluid communication with the first tank. An engine of the vehicle is to be supplied with fuel from at least one of the first tank or the second tank. The example apparatus also includes a cooling system disposed on the vehicle to cool the fuel flowing from the first tank to the second tank. The example apparatus further includes a heat exchanger operatively coupled to a heat source disposed on the vehicle. The fuel from the second tank is to flow to the first tank via the heat exchanger to cool the heat source.

A vacuum assembly includes a housing and a movable assembly positioned within the housing. Movement of the movable assembly relative to the housing creates a low pressure area. A fluid flow conduit is in fluid communication with the low pressure area. A leakage valve is disposed within the fluid flow conduit and is movable between a first position and a second position to restrict a flow through the fluid flow conduit upon detection of an undesired fluid within the low pressure area.

A system for purging an aircraft fuel reservoir includes a body (48) configured to be assembled on the aircraft fuel reservoir (16) and a valve (50), received in the body (48), and having a released configuration of an outlet channel (70) and a tight closed configuration of the outlet channel (70). The system further comprises a transport pipe (44) secured to the body (48), the transport pipe (44) being configured to be fluidly connected to a fuel supply pipe (20) configured to supply an energy producing device. The transport pipe (44) extends at least between a fuel suction inlet (52) and a discharge outlet (54), the suction inlet (52) being configured to emerge in the aircraft fuel reservoir (16) and the discharge outlet (54) being configured to emerge in the supply pipe (20) when the body (48) is mounted on the aircraft fuel reservoir (16).

The present invention relates to a fire fighting system for transporting a nozzle of a fire hose coupled to a drone to a high place. The fire fighting system includes a fire hose (10) having a fire hose (10) having a nozzle (11) for injecting a fire extinguishing liquid; a fire-extinguishing-liquid supply source (2) which is coupled to the fire hose (10), and supplies the fire extinguishing liquid to the fire hose (10); a top drone (1) coupled to the nozzle (11); a wired cable (4) coupled to the top drone (1); and a power supply unit (3) which supplies power or fuel for flying the top drone (1) through the wired cable (4).

Gaskets, including aircraft gaskets, are disclosed, the gaskets having an elastomeric gel body and substantially incompressible skeletons. The bodies may be pliable and deformable and, in one example, may be comprised of a two-part chemically cured polyurethane that sets up as a gel after mixing with the web so that it is fully integral with the web and so that there is substantially no air bubbles or air pockets left in the web. The web may be a regular shaped web and made of nylon.

Described are systems and methods for a segmented aircraft refueling tube with a tube interface that includes a plurality of seals configured to deform while allowing relative movement between tube segments. The systems described herein include a tube interface that includes a first ring, a second ring, a first seal disposed between a first ferrule and the first ring, a second seal disposed between a second ferrule and the second ring, a third seal disposed between the first ring and a sleeve, and a fourth seal disposed between the second ring and the sleeve. The plurality of seals per ring allow for misalignment between the ferrules to be accommodated by two or more seals. Thus, the amount of deformation per seal for any given misalignment is lower and easy to install seals such as O-rings are used.

Systems and method for filling a fuel manifold comprising at least a primary and a second manifold of a gas turbine engine are described. The method comprises providing fuel flow to the secondary manifold of the gas turbine engine, the secondary manifold being partly or completely empty; monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary manifold; and accelerating the engine when a transition threshold is reached, the transition threshold being associated with the engine operational parameter and indicative that fuel has reached the combustor.

Systems and method for filling a fuel manifold comprising at least a primary and a second manifold of a gas turbine engine are described. The method comprises providing fuel flow to the secondary manifold of the gas turbine engine, the secondary manifold being partly or completely empty; monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary manifold; and accelerating the engine when a transition threshold is reached, the transition threshold being associated with the engine operational parameter and indicative that fuel has reached the combustor.

A method of fuelling an aircraft for a flight to a predetermined destination in which the aircraft is loaded, the actual zero fuel weight of the loaded aircraft is determined, the fuel requirement of the loaded aircraft for that destination is calculated by fuel calculation software on the basis of operational flight plan data, said actual zero fuel weight, and further data relevant to fuel consumption for that instance of the flight to the predetermined destination, said further data being processed interactively by the user by means of a user interface to said fuel calculation software, and subsequently fuel to meet said fuel requirement is uplifted to the aircraft under the control of said user.