Hybrid electric propulsion systems includes a combustion engine and an electric motor. The hybrid electric propulsion systems may include or utilize a non-transitory computer-readable medium comprising computer-executable instructions, which when executed by a processor associated with the hybrid electric propulsion system, cause the processor to perform a method that includes determining an occurrence of a thrust asymmetry in the hybrid electric propulsion system, and controlling the electric motor to decrease an efficiency of the electric motor for a transient time period sufficient to reduce a torque output of the combustion engine to match an electrical load on the combustion engine.

A touchscreen fuel panel with checklist automation is disclosed. In embodiments, the fuel panel includes a touchscreen display and a controller coupled to the touchscreen display. The controller is configured to generate a graphical user interface at the touchscreen display and receive user inputs via the touchscreen display. The controller is further configured to execute an automated set of fuel management checklist procedures in response to a user input. In some embodiments, the controller can be alternatively or additionally configured to execute other automated sets of checklist procedures, for example, pre-flight, in-flight, taxi/takeoff/landing (TTL), and/or post-flight procedures.

A touchscreen fuel panel with checklist automation is disclosed. In embodiments, the fuel panel includes a touchscreen display and a controller coupled to the touchscreen display. The controller is configured to generate a graphical user interface at the touchscreen display and receive user inputs via the touchscreen display. The controller is further configured to execute an automated set of fuel management checklist procedures in response to a user input. In some embodiments, the controller can be alternatively or additionally configured to execute other automated sets of checklist procedures, for example, pre-flight, in-flight, taxi/takeoff/landing (TTL), and/or post-flight procedures.

A support member configured to support a first structure within an aperture of a second structure is disclosed. The support member comprises a bracket for attaching the support member to the second structure; and a funnel part. The diameter of the base of the funnel is less than or equal to the diameter of the aperture, and is substantially equal to the diameter of a part of the first structure to be supported by the support member.

A support member configured to support a first structure within an aperture of a second structure is disclosed. The support member comprises a bracket for attaching the support member to the second structure; and a funnel part. The diameter of the base of the funnel is less than or equal to the diameter of the aperture, and is substantially equal to the diameter of a part of the first structure to be supported by the support member.

A system for power and data communications within a fuel tank and across a wall of the fuel tank includes an optical hybrid fuel height sensor and a sealed connector extending through a wall of the fuel tank. The system also includes an electric power connection between the optical hybrid fuel height sensor and the sealed connector. The electric power connection includes a resistive non-metallic wire. The system also includes a sealed optical connector extending through the wall of the fuel tank. The system further includes an internal data communications connection between the optical hybrid fuel height sensor and the sealed optical connector. The internal data communications connection includes an optical signal out connection.

Dual-walled fluid transportation systems and related methods. The systems comprise a dual-walled fluid conduit, comprising an outer duct comprising a pair of flared end regions and a central region extending therebetween that define an outer duct internal surface surrounding an outer duct internal volume, an inner duct defining a central conduit, extending within the outer duct internal volume, and comprising a pair of flared end regions and a central region extending therebetween that define an inner duct external surface. The inner duct and outer duct define interlocking geometries and are configured to be supported with an inner duct channel completely separating the inner duct external surface from the outer duct internal surface. The methods include additively forming an outer duct wall and additively forming an inner duct wall within an outer duct internal volume of the outer duct wall with an inner duct channel extending therebetween.

A ramjet including: a combustion area having an air inlet and an exhaust outlet; and a fuel cell in fluid communication with the air inlet and a fuel supply of the ramjet, wherein the fuel cell is in thermal communication with the combustion area.

A ramjet including: a combustion area having an air inlet and an exhaust outlet; and a fuel cell in fluid communication with the air inlet and a fuel supply of the ramjet, wherein the fuel cell is in thermal communication with the combustion area.

An aircraft with a fuselage that accommodates a floor panel and a fuel storage system, wherein the fuel storage system comprises a tank system with at least one main tank 5a that is arranged underneath the floor panel; a cross ventilation system with a plurality of ventilation lines for venting the tank system, wherein the plurality of ventilation lines comprises at least one crossing ventilation line 11a that is routed from a first lateral side of the tank system to an opposite second lateral side of the tank system; and wherein the at least one crossing ventilation line is routed underneath or in the floor panel from the first lateral side of the tank system to the second lateral side of the tank system.