Abstract: A method, system, and apparatus for managing a part design. The method comprises processing, by a computer system, a finite element model for a part to refine a part topology and generate a number of configurations, in which each configuration has a part weight and a number of different parameters that change the part weight and meet a specification for the part. The method analyzes a part geometry model and a selected manufacturing process to estimate a resource use for manufacturing the part. In response to determining that the part weight or the resource use for a configuration is unacceptable, the method iteratively edits the configuration, refines the part topology to generate an updated configuration, and analyzes the selected manufacturing process to estimate the resource use, until an optimized configuration is identified. The method outputs a file for the optimized configuration, enabling manufacturing of the part using the part design.

Abstract: A method comprises mapping a plurality of variable values of a database in a multi-dimensional search space, each dimension corresponding to a variable of the database. The method comprises defining a surface within the multi-dimensional search space based on a plurality of search points defined by values for at least a pair of variables, the surface comprising a closed-loop, convex shape that defines an area of the multi-dimensional search space that has been searched. The method comprises repositioning at least one search point of the plurality of search points within the multi-dimensional search space based on a target objective, the at least one search point of the plurality of search points moved a predefined distance in a direction of the target objective such that the shape of the surface is changed while maintaining a closed-loop, convex shape. The method comprises reporting the variable values for the plurality of search points.

Abstract: Disclosed herein is a method that comprises determining one or more structural constraints for a structural design of a flexure mechanism. The method also comprises optimizing a level-set formula describing the structural design of the flexure mechanism subject to the one or more structural constraints for manufacturing the structural design of the flexure mechanism. The method further comprises outputting the structural design of the flexure mechanism based on the optimized level-set formula for manufacturing.

Abstract: Example systems and methods to optimize and integrate of thermal and structural analyses are described herein. An example method includes performing a thermal analysis of a component using a first mesh representing the component to produce a thermal distribution across the component. The first mesh has first nodes based on a first element size. The example method includes using a first mapping file to assign temperature values to second nodes of a second mesh representing the component based on the thermal distribution. The second nodes are based on a second element size different than the first element size. The example method also includes performing a structural analysis of the component using the second mesh and the assigned temperature values to produce gauge sizes for the component and using a second mapping file to assign gauge values to the first nodes of the first mesh based on the gauge sizes.

Abstract: Methods for balancing aircraft turbofan engines using an artificial neural network and a global optimization algorithm, which are configured as a loop in which: the global optimization algorithm inputs to the artificial neural network data representing proposed changes in the balance weight attached to the engine; the artificial neural network outputs data estimating changes in engine vibration in response to input of the data representing the proposed changes in balance weight; and the global optimization algorithm outputs an optimum influence coefficient calculated using a minimum predicted change in engine vibration. This process can be repeated multiple times to derive a multiplicity of optimum influence coefficients which are used to determine an optimal balance solution for the engine. The balance weights attached to the engine are then reconfigured in accordance with the optimal balance solution.

Abstract: A diagnostic system for a closed fluid system is provided. The closed fluid system includes a first fluid subsystem and a second fluid subsystem connected using a valve or valve/actuator. The diagnostic system includes a first sensor disposed in the first fluid subsystem, a second sensor disposed in the second fluid subsystem and a computer. The computer receives first time-ordered fluid level measurements and second time-ordered fluid level measurements from respectively the first sensor and the second sensor and performs a comparison of first fluid level of the first fluid subsystem and second fluid level of the second fluid subsystem. The computer produces a notification indicating a predicted transfer of hydraulic fluid when the first time-ordered fluid level measurements and the second time-ordered fluid level measurements have at least a threshold divergence and outputs the notification for display to a user.

Abstract: A method for balancing an aircraft turbofan engine using a respective artificial neural network for each flight of multiple reference aircraft to predict the engine vibrations that would be produced in response to input of flight parameter and balance weight data acquired from a flight of a test aircraft of the same type. The resulting sets of predicted vibrations are then processed to identify and collect those engine vibration predictions which match or nearly match the engine vibration measurements acquired from the test aircraft during its flight test. For each matching modeled flight of the reference aircraft, the magnitude and phase angle of the mass vector for any commonly used balance weight configurations are determined and included in a list of recommended balance weight configurations. A technician can then reconfigure the balance weights attached to the engine on the test aircraft in accordance with a selected recommendation.

Abstract: A method to find and report an available parking space in a parking lot, where a software application is installed on a memory device coupled to a processor on a dedicated computing platform in an automobile. The dedicated computing platform further including a geographic localizing program, a mapping software providing a digital parking space map superimposed on a real map of the parking lot, a statistical analysis software calculating probability of occupied or available status of a parking space based on data provided by the dedicated computing platform, a transceiver transmitting availability status of the parking space in the parking lot to a central processing unit. Where the central processing unit further transmits availability status of the parking spaces in the parking lots to the dedicated computing platform, thus enabling the dedicated computing platform to report on available parking spaces in the parking lots.

Abstract: A method, system, and apparatus for managing a part design. The method comprises processing, by a computer system, a finite element model for a part to refine a part topology and generate a number of configurations, in which each configuration has a part weight and a number of different parameters that change the part weight and meet a specification for the part. The method analyzes a part geometry model and a selected manufacturing process to estimate a resource use for manufacturing the part. In response to determining that the part weight or the resource use for a configuration is unacceptable, the method iteratively edits the configuration, refines the part topology to generate an updated configuration, and analyzes the selected manufacturing process to estimate the resource use, until an optimized configuration is identified. The method outputs a file for the optimized configuration, enabling manufacturing of the part using the part design.

Abstract: Methods for balancing aircraft turbofan engines using an artificial neural network and a global optimization algorithm, which are configured as a loop in which: the global optimization algorithm inputs to the artificial neural network data representing proposed changes in the balance weight attached to the engine; the artificial neural network outputs data estimating changes in engine vibration in response to input of the data representing the proposed changes in balance weight; and the global optimization algorithm outputs an optimum influence coefficient calculated using a minimum predicted change in engine vibration. This process can be repeated multiple times to derive a multiplicity of optimum influence coefficients which are used to determine an optimal balance solution for the engine. The balance weights attached to the engine are then reconfigured in accordance with the optimal balance solution.

Abstract: A method for balancing an aircraft turbofan engine using a respective artificial neural network for each flight of multiple reference aircraft to predict the engine vibrations that would be produced in response to input of flight parameter and balance weight data acquired from a flight of a test aircraft of the same type. The resulting sets of predicted vibrations are then processed to identify and collect those engine vibration predictions which match or nearly match the engine vibration measurements acquired from the test aircraft during its flight test. For each matching modeled flight of the reference aircraft, the magnitude and phase angle of the mass vector for any commonly used balance weight configurations are determined and included in a list of recommended balance weight configurations. A technician can then reconfigure the balance weights attached to the engine on the test aircraft in accordance with a selected recommendation.

Abstract: A parking exchange application method and system for securing an available parking space on a street corner. A responding driver in a car temporarily occupies an available parking space and informs a central processing database of the address of the available parking space. A requesting driver searching for an available parking space in a location vicinity, transmits a request to the central processing database. The central processing database compiles a list of available parking spaces addresses, and the requesting driver selects one of the available parking spaces, and drives toward the selected available parking space. Upon arrival, the central processing database makes payments of a transfer fee to the requesting drive, in exchange for the selected available parking space, and a commission fee to the parking exchange application, from an authorized fee payment from the requesting drivers, and the requesting driver occupies the available parking space.

Abstract: In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: Methods and apparatus for analyzing fatigue of a structure and optimizing a characteristic of the structure based on the fatigue analysis are disclosed herein. An example method disclosed herein includes obtaining mass and unit stress values of a plurality of details of interest of a structural component, calculating fatigue margins for each of the details of interest, identifying among the calculated fatigue margins any negative fatigue margins associated with one or more of the details of interest, and adjusting, via a processor, a dimensional characteristic of each detail of interest associated with the negative fatigue margin(s) until positive fatigue margin(s) at each detail of interest is obtained.

Abstract: An apparatus is provided for implementation of a mid-surface modeler including a receiver, selector, clusterer and mid-surface constructor. The receiver is to receive a solid model of a structural product composed of structural components, with the solid model representing the components by a collection of geometry. The selector is to select a group of geometry from the geometry in the solid model, with the group of geometry having approximately the same shape, and being perpendicular to an axis of a local coordinate system. The clusterer is to cluster geometry of the group of geometry into one or more clusters of geometry based on a relationship between the geometry, with each cluster of the cluster(s) representing a component of the component(s). And the mid-surface constructor is to construct a mid-surface model of the product, including computation of respective one or more mid-surfaces for the cluster(s).

Abstract: Methods and apparatus to vary reverse thrust of aircraft engines are disclosed. An example cascade apparatus disclosed herein includes a cascade frame having a first end, a second end, and a fixed structure extending between the first end and second end, where the cascade frame defines a slot. A cascade forms a reverse thrust flow path and at least a portion of the cascade is slidably coupled to the frame via the slot. The cascade slides relative the frame between a first position to produce a first reverse thrust and a second position to produce a second reverse thrust, where the first reverse thrust is different than the second reverse thrust.

Abstract: In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: Variable incident nacelle apparatus and methods are disclosed herein. An apparatus for varying an incident angle of a nacelle of an aircraft engine relative to an aircraft wing comprises a pylon frame member to be rigidly coupled to the aircraft engine. The pylon frame member is to be pivotable about a first axis of rotation. The apparatus further comprises a diagonal brace including a first end defining an aperture to receive a portion of a drive member. The portion of the drive member is to be rotatable relative to the aperture about a second axis of rotation. The drive member includes a pin positioned eccentrically relative to the second axis of rotation. The pin is to be coupled to the pylon frame member to pivot the pylon frame member in response to rotation of the portion of the drive member.

Abstract: In one example embodiment, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and comprising front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.

Abstract: Methods and apparatus to vary reverse thrust of turbofans are disclosed. An example cascade apparatus disclosed herein includes a fixed frame having a plurality of fixed vanes coupled to the frame, where each of the fixed vanes defines a plurality of slots. A plurality of movable vanes intersects the fixed vanes to form a reverse thrust flow path and slidably coupled to the fixed vanes via the slots. The movable vanes slide relative to the fixed vanes between a first position to provide a first reverse thrust and a second position to provide a second reverse thrust different from the first reverse thrust.