Abstract: An aerial vehicle includes a housing, a propulsion system supported within the housing, and an inlet assembly supported by an outer surface of the housing. The inlet assembly includes: at least one fluid channel in fluid communication with the propulsion system; and a first scoop pivotably coupled to the housing and movable between a stowed position and a deployed position. The first scoop is aligned with the housing in the stowed position to prevent air from entering the propulsion system, and the first scoop projects from the outer surface of the housing in the deployed position to direct air through the at least one fluid channel and into the propulsion system to generate thrust. The inlet assembly includes a compression ramp integrally formed with and extending forward from the first scoop. The compression ramp includes an upstream end disposed below the upstream end of the first scoop.

Abstract: An aerial vehicle includes a housing, a propulsion system supported within the housing, and an inlet assembly supported by an outer surface of the housing. The inlet assembly includes: at least one fluid channel in fluid communication with the propulsion system; and a first scoop pivotably coupled to the housing and movable between a stowed position and a deployed position. The first scoop is aligned with the housing in the stowed position to prevent air from entering the propulsion system, and the first scoop projects from the outer surface of the housing in the deployed position to direct air through the at least one fluid channel and into the propulsion system to generate thrust. The inlet assembly includes a compression ramp integrally formed with and extending forward from the first scoop. The compression ramp includes an upstream end disposed below the upstream end of the first scoop.

Abstract: An aerial vehicle includes a housing, a propulsion system supported within the housing, and an inlet assembly supported by an outer surface of the housing. The inlet assembly includes: at least one fluid channel in fluid communication with the propulsion system; and a first scoop coupled to the housing and movable between a stowed position and a deployed position. The first scoop is aligned with the housing in the stowed position to prevent air from entering the propulsion system, and the first scoop projects from the outer surface of the housing in the deployed position to direct air through the at least one fluid channel and into the propulsion system to generate thrust. The inlet assembly includes a flap disposed upstream of the first scoop. The flap is moveable between a flap stowed position and a flap deployed position.

Abstract: An aerial vehicle includes a housing, a propulsion system supported within the housing, and an inlet assembly supported by an outer surface of the housing. The inlet assembly includes: at least one fluid channel in fluid communication with the propulsion system; and a first scoop coupled to the housing and movable between a stowed position and a deployed position. The first scoop is aligned with the housing in the stowed position to prevent air from entering the propulsion system, and the first scoop projects from the outer surface of the housing in the deployed position to direct air through the at least one fluid channel and into the propulsion system to generate thrust. The inlet assembly includes a flap disposed upstream of the first scoop. The flap is moveable between a flap stowed position and a flap deployed position.

Abstract: A solid fuel propulsion system includes a housing, an air inlet configured to enable air to flow into the housing, an air duct, a rotation detonation chamber, and a nozzle assembly. The air duct is disposed in the housing and is in fluid communication with the air inlet. The air duct is configured to supply air for combustion of a solid fuel configured to sublimate into a gaseous fuel mixture. The rotation detonation chamber is disposed in the housing aft of the air duct and is configured to combust the gaseous fuel mixture and air to generate a rotating detonation wave. The nozzle assembly is configured to expand and exhaust the flow prompted by the rotating detonation wave to generate thrust.