An example method for installing optical sensors for a fuel level measurement system includes mounting a plurality of fittings through a wall of a fuel tank, positioning a plurality of optical sensors within the plurality of fittings and a respective optical sensor includes a first pressure sensing end inserted through the fitting and internally into the fuel tank and a second end extending externally from the fuel tank, and mounting an optical fiber bundle external to the fuel tank. The optical fiber bundle has an optical fiber connected to each of the plurality of optical sensors for guiding light to each of the plurality of optical sensors.

An aircraft fuel system includes a fuel tank and at least one electrically-operated sensor arranged within the fuel tank. The at least one electrically-operated sensor is configured to measure a property of fuel in the fuel tank. At least one wireless power transmission device is arranged relative to the fuel tank, the at least one power transmission device is configured to wirelessly transmit electric power to the at least one electrically-operated sensor.

A dual use UAV or “drone” can include a battery and primary processor located at a fuselage, as well as two separate modular units removably coupled to the fuselage and in communication with the primary processor. The two separate modular units can interact with each other to provide an enhanced operation while the drone is in flight. One modular unit can be an ISR unit having a video camera, and the other modular unit can be a cargo unit. The enhanced operation can involve the ISR unit using its video camera to identify a delivery location for a cargo pod of the cargo unit. Alternative modular units can include a secondary ISR unit, a cargo fuel pod unit, or a robotic arm assembly. Standardized interfaces coupled to the fuselage can enable the ready removal of one modular unit and installation of another one.

A composite fluid transfer conduit is provided. The conduit includes a first end portion, a second end portion and a main body portion between the first and second end portions. At least one of the first and second end portions is an end portion comprising a circumferential groove in a radially outer surface of the fluid transfer conduit, an axial end face, and a transition surface between the axial end face and the circumferential groove. The transition surface is configured such that, for any angle of impact of the end portion with a planar impact surface, a resultant impact force on the end portion is directed away from the circumferential groove.

A battery thermal management system for an air vehicle includes a first heat exchange circuit, a battery in thermal communication with the first heat exchange circuit, and a heat exchanger positioned on the first heat exchange circuit. The heat exchanger is operatively connected to a second heat exchange circuit. The system includes a controller operatively connected to the second heat exchange circuit. The controller is configured to variably select whether heat will be rejected to the second heat exchange circuit. A method for controlling a thermal management system for an air vehicle includes determining an expected fluid temperature of fluid in a fluid heat exchange circuit. The method includes commanding a flow restrictor at least partially closed or commanding the flow restrictor at least partially open.

Aircraft fuel ice capturing filter device housings, aircraft fuel ice capturing filter devices, and methods of use are provided.

An apparatus and method for installing an aircraft bulkhead connector with a bulkhead is disclosed where access to only one side of the bulkhead is required. The disclosure is also applicable to installation of bulkhead connectors in aircraft fuel tanks. An aircraft bulkhead connector and installation tool is also disclosed. The bulkhead connector includes a female end portion and the installation tool includes a male end portion. The male end portion of the installation tool is removably engaged with the female end portion of the bulkhead connector, such that the installation tool protrudes beyond the female end portion of the bulkhead connector. The installation tool may be inserted through an aperture in a bulkhead and used to both position and hold the bulkhead connector during the installation process.

A method of joining an interior wall and a composite channel together is disclosed. The method includes wrapping one or more first composite plies around a first end portion of a first mandrel and wrapping one or more second composite plies around a second end portion of a second mandrel. The method includes positioning the one or more first composite plies located on the first end portion of the first mandrel against the one or more second composite plies located on the second end portion of the second mandrel to create the interior wall, and inserting the first mandrel and the second mandrel into a passageway of a composite channel. The interior wall created by the one or more first composite plies and the one or more second composite plies creates a barrier to block a flow of fluid within the passageway of the composite channel.

A support assembly may include a support structure and a P-clamp attached to the support structure. The P-clamp may include a clamp body defining an opening, a mounting base structured and arranged to engage the support structure, and a connecting section interconnecting the clamp body and the mounting base. The P-clamp may be arranged in an inverted upright position where the mounting base is attached to the support structure underneath the clamp body relative to a direction of gravity. The P-clamp may yield at the connecting section upon an application of a load for to the clamp body that is equal to or greater than a predetermined applied load three threshold. The support assembly may be useful in an aircraft fuel line installation for supporting a fuel line from the support structure.

A dual pump fuel delivery system for an aircraft includes a fixed displacement fuel pump including an inlet and an outlet. The fixed displacement fuel pump is configured to supply a first portion of a fuel demand for the aircraft. A variable displacement fuel pump including an inlet portion and an outlet portion includes a selectively adjustable pump actuator configured to supply a second portion of the fuel demand. The second portion is variable. A fuel demand sensor operates to detect a selected fuel demand. A control member is operatively connected to the fuel demand sensor and the variable displacement fuel pump. The control member being configured to operate to adjust the variable displacement fuel pump to output the second portion of the fuel demand to satisfy the selected fuel demand.