Abstract: A computer-implemented method is executed using a threat assessment server that is communicatively coupled via one or more networks to one or more different cloud computing service providers and comprises receiving first input data specifying a first cloud service account that is associated with two or more cloud computing instances and/or two or more cloud storage instances, the cloud computing instances or cloud storage instances being hosted at a first cloud computing service provider, the first cloud service account being from among one or more different cloud service accounts that are associated with the one or more different cloud computing service providers each hosting respective cloud computing instances and/or cloud storage instances; receiving second input data specifying an entry point identifier of a particular cloud resource from among the two or more cloud computing instances and/or two or more cloud storage instances; using a plurality of first network calls from the threat assessment server t

Abstract: Aerospace vehicle leading edge slat devices and corresponding methods are generally disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes an airfoil having a leading edge. The system further includes a first flow body fixedly coupled to the airfoil to form at least one gap between the leading edge of the airfoil and the first flow body. A second flow body can be coupled to the airfoil and can be movable between at least a retracted position where the second flow body is positioned to at least approximately aerodynamically seal the at least one gap, and an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.

Abstract: An apparatus and a method for reducing drag over an aircraft wing assembly in operational angle of attack situations are disclosed. The aircraft wing assembly includes a wing and an engine nacelle mounted to the wing. A nacelle chine is mounted on an outboard side of the engine nacelle, and the nacelle chine is configured to reduce drag by redirecting at least a portion of fluid striking a forward end of the aircraft wing assembly such that a vortex is formed over the forward end of the aircraft wing assembly. The chine is coupled to a mounting base configured to be secured to an outer surface of the engine nacelle at a mounting position along an outer surface of the engine nacelle.