Abstract: A bluff body adaptive wake reduction system includes a series of fairings mounted to outer surfaces of the aft end of the road vehicle. The fairings are streamlined in geometry with an outer surface, a partially hollow core, and with a rear end surface curved such that left and right hand sides are convergent behind the vehicle. The fairings are coupled to at least one ram air inlet and also include at least one blown slot positioned on the rear end of the fairings enabling air flow to exit the fairings tangent to the rear end surface of the fairings. Air flow enters the system through the ram air inlets and exits through the blown slots. Air flow exiting the blown slots promotes flow traveling over the outer surface to remain attached to the outer surface and thus to the rear end surface. The rear end surface then deflects air flow to follow a convergent trajectory behind the vehicle in such a fashion as to reduce the size of the wake, and as a result reduce the aerodynamic drag.

Abstract: A bluff body adaptive wake reduction system includes a series of fairings mounted to outer surfaces of the aft end of the road vehicle. The fairings are streamlined in geometry with an outer surface, a partially hallow core, and with a rear end surface curved such that left and right hand sides are convergent behind the vehicle. The fairings are coupled to at least one ram air inlet and also include at least one blown slot positioned on the rear end of the fairings enabling air flow to exit the fairings tangent to the rear end surface of the fairings. Air flow enters the system through the ram air inlets and exits through the blown slots. Air flow exiting the blown slots promotes flow traveling over the outer surface to remain attached to the outer surface and thus to the rear end surface. The rear end surface then deflects air flow to follow a convergent trajectory behind the vehicle in such a fashion as to reduce the size of the wake, and as a result reduce the aerodynamic drag.

Abstract: An aircraft includes a housing and a powerplant coupled to the housing and configured to rotate a drive shaft around its longitudinal axis. The aircraft may include at least one lift fan assembly coupled to its housing and including a gearbox and at least one lift fan. The gearbox is coupled to the drive shaft and configured to transfer rotational energy from the drive shaft to the lift fan or fans. The lift fan assembly or assemblies may include at least two pivot assemblies, the first pivot assembly configured to pivot the lift fan assembly on a first axis and the second pivot assembly configured to pivot the lift fan assembly on a second axis that is substantially perpendicular to the first axis.

Abstract: A rotating launcher system includes a plurality of rocket or missile housing tubes arranged in a circular pattern within a carousel, a set of frames, a cylindrical protective skin, an aerodynamically optimized nose cone with a bore, and an optional door covering the bore, enabling rockets or missiles to exit the launcher. The rotating launcher system may also include an aerodynamically optimized tail cone with a bore, and an optional door covering the bore, enabling exhaust from the rockets or missiles to exit the launcher. The rotating launcher system also includes an integral controller for an indexing motor, and an indexing motor enabling the bores of the nose and tail cones to align with different rockets or missiles in the carousel by either rotating the nose and tail cones, or by rotating the carousel.

Abstract: An aircraft includes a housing and a powerplant coupled to the housing and configured to rotate a drive shaft around its longitudinal axis. The aircraft may include at least one lift fan assembly coupled to its housing and including a gearbox and at least one lift fan. The gearbox is coupled to the drive shaft and configured to transfer rotational energy from the drive shaft to the lift fan or fans. The lift fan assembly or assemblies may include at least two pivot assemblies, the first pivot assembly configured to pivot the lift fan assembly on a first axis and the second pivot assembly configured to pivot the lift fan assembly on a second axis that is substantially perpendicular to the first axis.

Abstract: A rotating launcher system includes a plurality of rocket or missile housing tubes arranged in a circular pattern within a carousel, a set of frames, a cylindrical protective skin, an aerodynamically optimized nose cone with a bore, and an optional door covering the bore, enabling rockets or missiles to exit the launcher. The rotating launcher system may also include an aerodynamically optimized tail cone with a bore, and an optional door covering the bore, enabling exhaust from the rockets or missiles to exit the launcher. The rotating launcher system also includes an integral controller for an indexing motor, and an indexing motor enabling the bores of the nose and tail cones to align with different rockets or missiles in the carousel by either rotating the nose and tail cones, or by rotating the carousel.