An apparatus and method that improves the operation of aerospace planes or rockets having an integrated flute and hat components whereby the flute functions as a hypersonic refrigeration engine and the hat as a flat plate heat exchanger to achieve an isothermal compression of the incipient hypersonic air in front of the nosecone to reduce hypersonic vibrations during flight, these improvements allow for the reduction in temperature during flight operation allowing for improved cooling of the aerospace plane or rocket.

Various techniques provide a heat shield assembly and mounting thereof on an aircraft. In one example, a heat shield assembly may include flexible member. The heat shield assembly may further include a plurality of frame members disposed on the flexible member. The heat shield assembly may further include a plurality of mounting structures configured to directly mount the heat shield assembly to a strut of an airplane. Each of the plurality of mounting structures may be disposed on one of the plurality of frame members. Related methods are also provided.

Various techniques provide a heat shield assembly and mounting thereof on an aircraft. In one example, a heat shield assembly may include flexible member. The heat shield assembly may further include a plurality of frame members disposed on the flexible member. The heat shield assembly may further include a plurality of mounting structures configured to directly mount the heat shield assembly to a strut of an airplane. Each of the plurality of mounting structures may be disposed on one of the plurality of frame members. Related methods are also provided.

A skin assembly that includes a first ceramic-matrix-composite skin panel including one or more first fingers extending along a first direction. The skin assembly further includes a second ceramic-matrix-composite skin panel including one or more second fingers extending along the first direction. The one or more second fingers interdigitated with the one or more first fingers to define a plurality of staggered expansion gaps between the first ceramic-matrix-composite skin panel and the second ceramic-matrix-composite skin panel wherein the plurality of staggered expansion gaps are configured to accommodate thermal expansion of at least a portion of the skin assembly.

A system that optimizes the shape or configuration of an aircraft to minimize ground overpressure shock strength while in supersonic flight over speed restricted terrain and to morph to an optimized configuration for drag minimization while over unrestricted terrain.

A system that optimizes the shape or configuration of an aircraft to minimize ground overpressure shock strength while in supersonic flight over speed restricted terrain and to morph to an optimized configuration for drag minimization while over unrestricted terrain.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35 C. to 1,650 C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35 C. to 1,650 C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

The antenna (3) cover (1) for a vehicle is designed to cover at least one antenna (3) mounted on the vehicle, the cover (1) being made of composite material with a ceramic matrix reinforced by oxide fibers. The antenna cover (1) is resistant to high temperatures while not posing any sealing problem and remaining transparent to the frequencies used for the antennas (3) of the vehicle.

The antenna (3) cover (1) for a vehicle is designed to cover at least one antenna (3) mounted on the vehicle, the cover (1) being made of composite material with a ceramic matrix reinforced by oxide fibers. The antenna cover (1) is resistant to high temperatures while not posing any sealing problem and remaining transparent to the frequencies used for the antennas (3) of the vehicle.