Abstract: Disclosed are systems and methods for network configuration management systems and methods. In some embodiments, the discloses systems and methods may involve receiving data from one or more nodes within a particular network. The data may include, for example, topology, telemetry, geographical, and other data relating to the nodes, the network, and/or the functionality of the nodes or network. Once received, such data may be cleaned and processing may be performed on the data. Such processing may involve clustering the data into groups based on various parameters and performing forecasting on the data to determine future usage rates and capacity information, for example. The clustering and forecasting results may be fed to a rules engine and/or an optimization engine, which may then determine appropriate actions to take on the network (e.g., changes to various nodes in terms of technology and/or number of nodes).

Abstract: Example notification management systems and methods are described. In one implementation, techniques identify multiple devices communicating using a carrier and identify a trigger associated with at least one of the multiple devices. Based on identifying the trigger, the techniques may apply at least one business rule associated with at least one of the multiple devices. The techniques may further generate at least one notification in response to applying the business rule.

Abstract: Example device management systems and methods are described. In one implementation, techniques identify a first plurality of devices communicating using a first rate plan associated with a carrier. The techniques further identify a second plurality of devices communicating using a second rate plan associated with the carrier. The techniques analyze the first rate plan and the second rate plan based on data usage. The techniques then identify at least one recommended rate plan change for at least one of the first plurality of devices or the second plurality of devices based on the analysis.

Abstract: Example bulk device processing systems and methods are described. In one implementation, techniques receive a plurality of application programming interface (API) requests, where each of the plurality of API requests is associated with a particular device. The techniques further sort the plurality of API requests based on an associated carrier. The techniques also create a first batch of API calls associated with devices using a first carrier and create a second batch of API calls associated with devices using a second carrier. The techniques then create multiple threads for parallel execution of the first batch of API calls and the second batch of API calls, and automatically execute the API calls associated with the plurality of threads.

Abstract: Example notification management systems and methods are described. In one implementation, techniques identify multiple devices communicating using a carrier and identify a trigger associated with at least one of the multiple devices. Based on identifying the trigger, the techniques may apply at least one business rule associated with at least one of the multiple devices. The techniques may further generate at least one notification in response to applying the business rule.

Abstract: Example bulk device processing systems and methods are described. In one implementation, techniques receive a plurality of application programming interface (API) requests, where each of the plurality of API requests is associated with a particular device. The techniques further sort the plurality of API requests based on an associated carrier. The techniques also create a first batch of API calls associated with devices using a first carrier and create a second batch of API calls associated with devices using a second carrier. The techniques then create multiple threads for parallel execution of the first batch of API calls and the second batch of API calls, and automatically execute the API calls associated with the plurality of threads.

Abstract: Example device management systems and methods are described. In one implementation, techniques identify a first plurality of devices communicating using a first rate plan associated with a carrier. The techniques further identify a second plurality of devices communicating using a second rate plan associated with the carrier. The techniques analyze the first rate plan and the second rate plan based on data usage. The techniques then identify at least one recommended rate plan change for at least one of the first plurality of devices or the second plurality of devices based on the analysis.

Abstract: A data network storing data relating to work done by vendors for clients is described. The network includes two or more servers, each server containing (1) an exhaustive vendor data base that contains client-independent vendor data for every vendor, and (2) one or more individual client databases, each containing client information for a single client. The exhaustive vendor data base is replicated between the servers, and the client information for each client is contained by one individual client data base on one server.

Abstract: Embodiments of a method to fabricate complex structures include making a pre-cured laminate template. The laminate template is first cured to the required shape, then surface prepared for joining to additional composite lamina. The laminate templates are used to position composite lamina in contact with one another. The composite lamina are then co-cured together to form one monolithic composite structure lacking bond lines or bonded joints. The laminate template supports additional composite lamina for formation of complex structures and replaces template tools from conventional methods.

Abstract: A data network storing data relating to work done by vendors for clients is described. The network includes two or more servers, each server containing (1) an exhaustive vendor data base that contains client-independent vendor data for every vendor, and (2) one or more individual client databases, each containing client information for a single client. The exhaustive vendor data base is replicated between the servers, and the client information for each client is contained by one individual client data base on one server.

Abstract: A method for making a fuselage section comprises the steps of assembling a support system. The support system comprises fiber reinforced composite material and includes at least three frames and six stringers. The support system is partially cured such that the support system attains about eighty percent of its fully cured strength. A skin comprising fiber reinforced composite material is globally positioned such that an inner surface of the skin corresponds to an outer surface of the support system. The skin and the support system are fully cured together. The support system is assembled on a skeleton assembly tool having a bonding surface corresponding to an inner surface of the skin.

Abstract: A data network storing data relating to work done by vendors for clients is described. The network includes two or more servers, each server containing (1) an exhaustive vendor data base that contains client-independent vendor data for every vendor, and (2) one or more individual client databases, each containing client information for a single client. The exhaustive vendor data base is replicated between the servers, and the client information for each client is contained by one individual client data base on one server.

Abstract: A fiber reinforced composite structure includes multiple plies of pre-impregnated fiber reinforced material. Consecutive plies are layered such that the fibers of one ply are at 90 degrees relative to the fibers of a proximate ply, and such that the fibers of each ply are oriented at positive or negative 45 degrees with respect to a reference plane of the fiber reinforced composite structure. In a method for fabricating a fiber reinforced composite structure, pre-impregnated fiber reinforced composite plies are layered into a tool layup. Each ply is cut on the bias at either plus 45 degrees or minus 45 degrees. The bias angles of the layered plies alternate one relative to the next. The layered plies are cured after layering.

Abstract: A method for fast curing a component made from composite laminate. The method rapidly raising the temperature of the component by applying heat at an accelerated temperature for a ramp time, holding the temperature of the component at a set temperature for a set dwell time, and removing heat from the component to slow curing process. The method may additionally include inspecting the component after removing the component from heat, and curing the component a final time to equivalent or better strength.

Abstract: A method for making a fuselage section comprises the steps of assembling a support system. The support system comprises fiber reinforced composite material and includes at least three frames and six stringers. The support system is partially cured via a fast cure process such that the support system attains about eighty percent of its fully cured strength. A skin comprising uncured fiber reinforced composite material is globally positioned such that an inner surface of the skin corresponds to an outer surface of the support system. The skin and the support system are fully cured together. The support system is assembled on a bonding tool having a bonding surface corresponding to an inner surface of the skin.

Abstract: An internally heated and pressurized system for fabricating a composite laminate structure and method for use thereof is disclosed. One of a plurality of thin, thermally conductive bond tools, prepreg fiber reinforced composite layers, and a pressure applying membrane are nested within a heated base, and then covered by a pressure sealed cover. The system is pressurized through the pressure sealed cover. The pressure causes the pressure applying membrane to force the prepreg fiber reinforced composite layers onto the upper surface of the bond tool. The heated base transfers heat to the composite layers via the bond tool, which heats and cures the composite layers together and to a shape determined by the upper surface of the bond tool. Each bond tool is formed with a generic lower surface for nesting within the heated base and an upper surface for forming composite layers into the shape of a specific part.

Abstract: A structure for use with an electrothermal heating element is disclosed comprising a heating element contained in a mat and heater supports attached to one surface of the mat. The heating element is disposed between the skin and internal structure of an aircraft with the heater supports disposed toward the internal structure thereof. The heater supports maintain an insulating layer of air between the mat and the internal structure of the aircraft.

Abstract: A fabrication process using an integrated form includes assembling at least two independent sections of composite laminate about a form, such that at least a portion of the sections overlap. A bonding agent is applied between the sections, at the overlap, and the form and laminate assembly are vacuum-bagged. The bag is sealed around a vent in the form, and about the laminate assembly. A vacuum is applied within the bag, to bond the sections, and the bagged assembly is autoclaved, to cure the bonded laminate sections. The vent allows equalization of autoclave pressures within and outside of the form, to prevent crushing or deformation of the form during cure. The form becomes an integral and permanent part of the final composite product.

Abstract: Sail deflection, from large resultant moments, creates excess aerodynamic twist and limits hang glider performance. Incorporating a rear spar and sail attachment system, as a design feature, allows control and definition of this critical performance component. Hang gliders with this design feature will produce more total lift which in turn will produce lower stall speeds and less drag.

Abstract: A process for bonding a vented hollow component includes placing a preformed component with an aircraft skin on a tool surface, with bonding agent applied between the component and the skin. A vacuum bag is sealed about a vent in the preformed component. The vent may be formed through the vacuum bag and the component, or the vent may be preexisting (i.e., an open end of the preformed component or an aperture through the component). The vacuum bag is sealed to the tool surface with a temporary seal or adhesive, to enclose the preformed component and the skin. A vacuum is applied within the bagging material, to compress the preformed component with the aircraft skin, and the bagged assembly is autoclaved to cure the bonding agent. The vent in the preformed component facilitates pressure equalization within and outside of the component to enhance compression against the aircraft skin.