A propulsion system for an aircraft includes a gas turbine engine and a fuel tank, wherein the fuel includes at least a proportion of a sustainable aviation fuel—SAF—having a density between 90% and 98% of the density, ρ.sub.K, of kerosene and a calorific value between 101% and 105% the calorific value CV.sub.K, of kerosene. The engine includes a combustor; and a fuel pump arranged to supply a fuel thereto at an energy flow rate, C, the pump being arranged to output fuel at a volumetric flow rate, Q, the percentage of fuel passing through the pump not provided to the combustor being referred to as a spill percentage. The fuel include X % SAF, where X % is in the range from 5% to 100%, and has a density, ρ.sub.F, and a calorific value CV.sub.F. The propulsion system is arranged so: the fuel-change spill ratio, R.sub.s, of: $R_s=\frac{\mathrm{spill}\mathrm{percentage}\mathrm{at}\mathrm{cruise}\mathrm{using}\mathrm{kerosene}}{\mathrm{spill}\mathrm{percentage}\mathrm{at}\mathrm{cruise}\mathrm{using}\mathrm{the}\mathrm{fuel}\mathrm{with}X\%SAF}$ is equal to: $\frac{Q-\left(C/\left({\mathrm{CV}}_K\times {\rho }_K\right)\right)}{Q-(C/({\mathrm{CV}}_F\times {\rho }_{}}$

A fuel gauging sensing device for a fuel tank for aircrafts includes an optical fiber harness along the internal surface of the tank, a master optical controller connected to a first terminal of the optical fiber harness, a slave optical controller connected to a second terminal of the optical fiber harness, wherein the optical fiber harness includes Fiber Bragg Grating (FBG) sensors spaced in the optical fiber harness between 1 mm and 25 mm to provide temperature gradients inside the tank and wherein the master and slave optical controllers are configured to obtain the fuel gauging of the tank based on the output from the FBG sensors.

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.

The present application relates to a method of forming a structural portion of a fuel tank for an aircraft in which the structural portion is formed from a fibre reinforced polymer and a sensor is integrated in the structural portion. The method includes providing a fibre ply which acts as a structural component, and embroidering an electrically conductive wire in a predetermined pattern on the fibre ply to form the sensor. The fibre ply acts as a sensor substrate. Furthermore, the method includes applying a polymer matrix to the fibre ply so that the fibre ply and electrically conductive wire are covered by the polymer matrix. The present application also relates to a fuel tank for an aircraft, a fuel quantity indicating system, and an aircraft.

An expandable fuel line section for an aircraft, a fuel line for an aircraft, and a method for fabricating an expandable fuel line section for an aircraft are provided. In one non-limiting example, the expandable fuel line section includes a first inner tube section subassembly. A second inner tube section subassembly is in fluid communication with the first inner tube section subassembly. An outer tube subassembly has an outer tube wall surrounding an outer tube channel. The first and second inner tube section subassemblies are slidingly disposed in the outer tube channel to move between retracted positions and extended positions.

Systems and methods for communicating a signal over a fuel line in a vehicle are provided. In one embodiment, a system can include a fuel line. The fuel line can include at least one communication medium for propagating a communication signal. The system can also include at least one signal communication device configured to receive the communication signal communicated over the fuel line. The system can also include at least one vehicle component in communication with the at least one signal communication device.

Systems and methods for communicating a signal over a hydraulic line in a vehicle are provided. In one embodiment, a system can include a hydraulic line. The hydraulic line can include at least one communication medium for propagating a communication signal. The system can also include at least one signal communication device configured to receive the communication signal communicated over the hydraulic line. The system can also include at least one vehicle component in communication with the at least one signal communication device.

A method of generating a maintenance schedule for an aircraft including one or more gas turbine engines powered by an aviation fuel. The method includes: determining one or more fuel characteristics of the fuel; and generating a maintenance schedule according to the one or more fuel characteristics. Also disclosed is a method of maintaining an aircraft, a maintenance schedule generation system and an aircraft.

In an aircraft duct formed with pipes connected in pairs via connectors in which the pipes are mounted with the possibility of axial displacement, there exists a risk that a pipe of the duct, with a dimension greater that the dimension of the nominal pipe, is mounted instead and in place of the latter. In this case, the wrongly mounted pipe would risk not having sufficient clearance in axial translation. In order to solve this problem, it is disclosed to equip one of the relevant connectors with an obstacle limiting the travel of the nominal pipe and preventing the mounting of a pipe with a greater dimension belonging to the duct. A method for assembling an aircraft portion is also proposed, in order to benefit from the particularities of the duct.

This invention, the Motor-wing Gimbal Aircraft (MGA) is an aerial vehicle and waterborne craft. It launches and lands vertically from the ground and water. In flight, it transitions from vertical, hovering and forward flight to horizontal flight. The MGA embodies multiple configurations and arrangements of motor-wings, propulsion systems and hybrid engine combinations. The MGA uses a fly-by-light system for flight maneuvering and controlling the motorized multi-axis gimbal cockpit. The MGA uses cellular communications together with the Global Positioning System (GPS) for navigation, collision avoidance and restricted airspace avoidance. The MGA uses visible lights to signal its elevation and flight maneuvers. The MGA is constructed of modular apparatuses and assemblies that are interchangeable and work in concert to power and maneuver the vehicle. This invention includes: the method of construction, the method of control, the method of visual light signaling, the method of electronic mapping of airspace (EMA) and the method of navigation. This invention includes flight operation applications and military applications.