Abstract: A user interface for performing load analysis on various geometries is provided. The user interface is especially useful for performing load analysis operations on mobile platforms, for example an aircraft. The user interface includes an object display that lists a plurality of load objects that include object data. A plurality of menu displays list a plurality of load operations. A data display displays the object data associated with the plurality of load objects.

Abstract: A computer program product, system, and method for performing load analysis on various geometries is provided. The system is especially useful for performing load analysis on various portions of a mobile platform, for example an aircraft. The computer program product includes a computer readable medium bearing software instructions for enabling predetermined operations. The predetermined operations include generating an object command; generating at least one load object from at least one predefined object class definition based on the object command, where each load object includes at least one interface to a load operation and object data; generating an operation command based on the at least one interface; and performing the load operation on the object data based on the operation command.

Abstract: A user interface for performing load analysis on various geometries is provided. The user interface is especially useful for performing load analysis operations on mobile platforms, for example an aircraft. The user interface includes an object display that lists a plurality of load objects that include object data. A plurality of menu displays list a plurality of load operations. A data display displays the object data associated with the plurality of load objects.

Abstract: In various embodiment of the present invention, a method for determining a mass distribution solution for a mathematical model of a part to be structurally analyzed is provided. The method includes utilizing a finite element modeling (FEM) device to generate a nodal data of a part to be structurally analyzed. The nodal data is exported into a mass distribution solution (MDS) generating device where a three dimensional graphical illustration of the nodal data is rendered on a monitor of the MDS generating device. Mass properties data relating to the part to be analyzed is then imported into the MDS generating device from a weight accounting data source (WAD). The MDS generating device includes a processor that executes a MDS algorithm to thereby generate a MDS for the nodal data based on the imported mass properties data. A three dimensional graphical illustration of the weight distribution across selected nodes of the nodal data in accordance with of the mass distribution solution is rendered on the monitor.

Abstract: A system allowing for an integrated flight loads balancing process at one or more time instances of a flight maneuver of an aircraft includes a processor and a plurality of resources. Additionally, the system includes a resource integration program that is executable by the processor. Upon execution by the processor, the resource integration program operates to integrate the plurality of resources so that the integrated resources are accessible to the system while balancing the flight loads at the one or more time instances.

Abstract: A system allowing for an integrated flight loads balancing process at one or more time instances of a flight maneuver of an aircraft includes a processor and a plurality of resources. Additionally, the system includes a resource integration program that is executable by the processor. Upon execution by the processor, the resource integration program operates to integrate the plurality of resources so that the integrated resources are accessible to the system while balancing the flight loads at the one or more time instances.

Abstract: A system allowing for an integrated flight loads balancing process at one or more time instances of a flight maneuver of an aircraft includes a processor and a plurality of resources. Additionally, the system includes a resource integration program that is executable by the processor. Upon execution by the processor, the resource integration program operates to integrate the plurality of resources so that the integrated resources are accessible to the system while balancing the flight loads at the one or more time instances.

Abstract: A system allowing for an integrated flight loads balancing process at one or more time instances of a flight maneuver of an aircraft includes a processor and a plurality of resources. Additionally, the system includes a resource integration program that is executable by the processor. Upon execution by the processor, the resource integration program operates to integrate the plurality of resources so that the integrated resources are accessible to the system while balancing the flight loads at the one or more time instances.