A battery containment pod including a body formed of a lightweight material. The body has an aerodynamic exterior shape and an interior cavity formed in the lightweight material, the size and shape of the interior cavity designed to accommodate one or more battery packs. A smooth exterior coating covers the exterior shape of the body, and an attachment structure formed in or on the body allows the body to be coupled to a flight vehicle. Other implementations are disclosed and claimed.

A battery containment pod including a body formed of a lightweight material. The body has an aerodynamic exterior shape and an interior cavity formed in the lightweight material, the size and shape of the interior cavity designed to accommodate one or more battery packs. A smooth exterior coating covers the exterior shape of the body, and an attachment structure formed in or on the body allows the body to be coupled to a flight vehicle. Other implementations are disclosed and claimed.

A low drag surface is provided for a fluid washed object, the low drag surface comprising an aerodynamic surface comprising a cut-out region, and a continuously translatable surface comprising a surface portion. The surface portion is positioned in the cut-out region such that the aerodynamic surface and the surface portion form a fluidwash surface, and the surface portion is translatable relative to the aerodynamic surface.

A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

An anterior part of a nacelle of a propulsion assembly of an aircraft, having an air intake lip and a front frame disposed at the rear of the air intake lip that connects an outer part to an inner part of the air intake lip. A de-icing duct is formed in front of the front frame. The front frame is shaped so that the de-icing duct has a main cavity and a thermal transition region formed behind the main cavity between an internal face of the outer part of the air intake lip and the front frame. The thermal transition region extends over a longitudinal dimension greater than its average radial dimension, the front frame forming, with respect to the internal face of the outer part of the air intake lip, an angle, measured longitudinally, of between −20° and +10° over the majority of the thermal transition region.

A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

A platform-mounted radome which includes: a low-profile aerodynamic canopy made of a radio frequency (RF) transparent material, wherein the canopy has a leading edge and a trailing edge and is suitable to accommodate a flat panel satellite communication (SATCOM) antenna; an air-cooling duct connecting an inlet at the leading edge of the canopy and an outlet at the trailing edge of the canopy, wherein the air-cooling duct is designed to transfer naturally cool air collected by the inlet across the canopy when flying; means for transferring heat thermally coupled to heat-generating elements of the SATCOM antenna and the air-cooling duct; and one or more heat sinks located within the air-cooling duct and thermally coupled thereto.

A vertical take-off and landing (VTOL) aircraft is provided. The aircraft includes a wing, nacelles supportively disposed at opposite ends of the wing, proprotors respectively attached to each of the nacelles with each of the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and a delta-wing shaped fuselage disposed along the wing between the nacelles.

A vertical take-off and landing (VTOL) aircraft is provided. The aircraft includes a wing, nacelles supportively disposed at opposite ends of the wing, proprotors respectively attached to each of the nacelles with each of the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and a delta-wing shaped fuselage disposed along the wing between the nacelles.