Abstract: Systems and methods are provided for storage in at least one on-board fuel tank of aircraft fuel under a predetermined pressure and at an internal ambient tank temperature. A passive heat exchanger having an exchanger inlet is fluid-connected to a propulsion engine of the aircraft to receive heated pressurized bleed air therefrom while an exchanger outlet is fluid connected to the fuel tank. The passive heat exchanger is configured to cool the heated pressurized bleed air from the engine by heat transfer to a surrounding environment by radiation and convection so as to supply pressurization air to the fuel tank at the predetermined internal tank pressure and the internal ambient tank temperature. A system controller is provided to provide the fuel tank with pressurized air at a predetermined temperature during various aircraft flight phases.

Abstract: A method for desaturating reaction wheels of a spacecraft having a magnetic dipole is provided. The method includes orienting the spacecraft relative to an external magnetic field to apply a torque to the spacecraft via the magnetic dipole in a direction opposing momentum stored in the reaction wheels; and using the applied torque to unload at least some of the momentum stored in the reaction wheels. A corresponding spacecraft and non-transitory computer-readable medium are also provided.

Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment and a second segment. The first segment is oriented along a fore-aft direction. The first segment is translatable relative to the nacelle along the fore-aft direction. The first segment includes one or more first airflow openings. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment includes one or more second airflow openings. The second segment is substantially coplanar with the first segment. Translation of the first segment adjusts the transverse alignment of the first airflow openings with the second airflow openings to vary an allowable airflow through the multi-segment chine.