Abstract: 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.

Abstract: A lightning strike protection (LSP) system minimizes or eliminates both the direct and indirect effects of lightning strikes on aircraft with composite fuselages without adding excessive weight to the aircraft. The LSP system comprises an external current return network and an internal current return network. The internal current return network comprises a wide plane of conductive foil material adhered to, or embedded within, an innermost surface of the fuselage and other portions of the aircraft formed primarily of composite materials. The conductive foil material is provided in wide planar sheets, and in one embodiment, is formed of expanded copper foil mesh. The internal current return network is installed in all areas or zones of the aircraft where cables and wires are routed.

Abstract: An aircraft maintenance system for improving updates and maintenance of computing devices and software systems of aircraft includes an onboard maintenance device, a centralized configuration server, and a master server. The onboard maintenance device is disposed in an aircraft. The centralized configuration server is communicatively coupled with the onboard maintenance device via satellite communication. The centralized configuration server is configured to wirelessly receive a current configuration report from the onboard maintenance device while the aircraft is in flight. The master server is disposed behind a firewall and is configured to send a set of up-to-date configuration data to the centralized configuration server such that the centralized configuration server can determine compliance by the aircraft.

Abstract: An aircraft body section comprises a first layer of composite material, a first group of conductive traces, a second layer of composite material, and a first group of conductive connectors. The first layer of composite material has an upper surface and a lower surface, with the lower surface forming an exterior surface of a body of the aircraft. The first group of conductive traces are formed on the upper surface of the first layer of composite material. The second layer of composite material is positioned on the first layer of composite material and has an upper surface and a lower surface, with the upper surface forming an interior surface of a body of the aircraft. The first group of conductive connectors is formed on the upper surface of the second layer of composite material and is configured to provide electrical connection from external conductors to the conductive traces.

Abstract: An aircraft maintenance system for improving updates and maintenance of computing devices and software systems of aircraft includes an onboard maintenance device, a centralized configuration server, and a master server. The onboard maintenance device is disposed in an aircraft. The centralized configuration server is communicatively coupled with the onboard maintenance device via satellite communication. The centralized configuration server is configured to wirelessly receive a current configuration report from the onboard maintenance device while the aircraft is in flight. The master server is disposed behind a firewall and is configured to send a set of up-to-date configuration data to the centralized configuration server such that the centralized configuration server can determine compliance by the aircraft.

Abstract: A lightning strike protection (LSP) system minimizes or eliminates both the direct and indirect effects of lightning strikes on aircraft with composite fuselages without adding excessive weight to the aircraft. The LSP system comprises an external current return network and an internal current return network. The internal current return network comprises a wide plane of conductive foil material adhered to, or embedded within, an innermost surface of the fuselage and other portions of the aircraft formed primarily of composite materials. The conductive foil material is provided in wide planar sheets, and in one embodiment, is formed of expanded copper foil mesh. The internal current return network is installed in all areas or zones of the aircraft where cables and wires are routed.

Abstract: A method for determining a Mach cutoff flight profile for an aircraft comprises receiving a flight origination and destination; receiving an initial atmospheric profile forecast; receiving user preferences on flight parameters to be optimized; computing a user cost function; determining a flight profile which implements Mach cutoff; receiving updates on the atmospheric profile forecast; determining potential sonic boom incidents; determining one or more sonic boom avoidance modifications to the flight profile that will avoid sonic boom incidents and not exceed the user cost function if potential sonic boom incidents are determined; presenting one or more sonic boom avoidance modifications to a pilot of the aircraft if potential sonic boom incidents are determined; receiving selection of one of the sonic boom avoidance modifications if potential sonic boom incidents are determined; and updating the flight profile with the selected sonic boom avoidance modification if potential sonic boom incidents are determin

Abstract: The present disclosure relates to a method of operating a supersonic aircraft comprising the steps of: at takeoff, positioning a slidable plug-cowl assembly disposed within a nozzle and behind an engine in an aft position such that a front surface of a plug is aft of an exit plane of a cowl, to thereby reduce noise during takeoff and maintain engine efficiency; and after takeoff, re-positioning the slidable plug-cowl assembly to a forward position such that the front surface of the plug is not disposed aft the exit plane of the cowl.

Abstract: In accordance with embodiments disclosed herein, there are provided methods, systems, and apparatuses for predicting whether a point on a computer-generated aircraft or vehicle surface is adjacent to laminar or turbulent flow is made using a transition prediction technique. A plurality of boundary-layer properties at the point are obtained from a steady-state solution of a fluid flow in a region adjacent to the point. Included in the list of boundary-layer properties are computed coefficients or weights of mode shapes that describe the boundary-layer profiles. A plurality of instability modes are obtained, each defined by one or more mode parameters. A vector of regressor weights is obtained for the known instability growth rates in a training dataset. For each instability mode in the plurality of instability modes, a covariance vector is determined, which is the covariance of a predicted local growth rate with the known instability growth rates.

Abstract: This disclosure provides a method for providing spatial gradients of 3D CAD models of solid objects with respect to various parameters used in defining the solid object. A modeler is designed and implemented to provide spatial gradients of solid objects (when represented on a computer as 3D CAD models) with respect to the various parameters that define the objects. Although primarily based on finite difference operations, several additional steps are performed to ensure that the gradients computed are correct and valid for a general class of solid objects and the parameters that define the objects. No commercially available 3D CAD tool provides such ability for a general class of solid objects.