Patents by Inventor Mohammad Ali Heidari
Mohammad Ali Heidari has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10466187Abstract: 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.Type: GrantFiled: June 10, 2015Date of Patent: November 5, 2019Assignee: THE BOEING COMPANYInventors: Omid B. Nakhjavani, Mohammad Ali Heidari, Milan Stefanovic, Bradley A. Olmstead, Eric John Zimney, Naveena Mallikarjunaiah
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Patent number: 10118709Abstract: 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.Type: GrantFiled: February 8, 2018Date of Patent: November 6, 2018Assignee: The Boeing CompanyInventors: Omid B. Nakhjavani, Robert H. Willie, Paul S. Park, Mohammad Ali Heidari, Leonard J. Hebert, Milan Stefanovic, Parminder Singh, Naimishkumar B. Harpal, Andrew Y. Na
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Publication number: 20180170562Abstract: 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.Type: ApplicationFiled: February 8, 2018Publication date: June 21, 2018Inventors: Omid B. Nakhjavani, Robert H. Willie, Paul S. Park, Mohammad Ali Heidari, Leonard J. Hebert, Milan Stefanovic, Parminder Singh, Naimishkumar B. Harpal, Andrew Y. Na
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Patent number: 9896217Abstract: 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.Type: GrantFiled: January 7, 2016Date of Patent: February 20, 2018Assignee: The Boeing CompanyInventors: Omid B. Nakhjavani, Robert H. Willie, Paul S. Park, Mohammad Ali Heidari, Leonard J. Hebert, Milan Stefanovic, Parminder Singh, Naimishkumar B. Harpal, Andrew Y. Na
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Patent number: 9770873Abstract: A system and method for creating an optimized composite laminate structure containing a plurality of plies. The system has a processor and a memory, including an application interface. The application interface, when executed by the processor, is configured to operably: receive an input file having one or more of a maximum number of plies, design variables, material properties, and design constraints; determine an initial layup sequence defining parameters of a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle; iteratively adjust the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety, and that achieves optimization of the composite laminate structure; and generate an output file for creating a layup, according to the parameters. The system further has a layup system for creating the optimized composite laminate structure.Type: GrantFiled: August 22, 2014Date of Patent: September 26, 2017Assignee: The Boeing CompanyInventors: Anthony K. Gilbert, Omid B. Nakhjavani, Shahriar Khosravani, Mohammad Ali Heidari, James F. Ackermann, Mostafa Rassaian, Forouzan Behzadpour
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Patent number: 9754053Abstract: There is provided a system for reading geometric data from parametric model or a nonparametric model from a CAD model file. The system has a processor and an interface application, which when executed by the processor, is configured to operably receive automatically, using a first interface application, an input file that includes data representing one or more components of a three-dimensional model, and is further configured to operably determine, using the first interface application, a type of a part represented by the three-dimensional model. The first interface application has instructions, one or more algorithms, or a combination thereof, and is further configured to automatically operably identify, select, and group geometric data associated with specific geometric data of the three-dimensional model, based on a set of parametric rules. The processor writes extracted specific geometric data to a first geometry intermediate output file.Type: GrantFiled: August 11, 2014Date of Patent: September 5, 2017Assignee: The Boeing CompanyInventors: Mohammad Ali Heidari, Anthony K. Gilbert, James S. Lee, Omid B. Nakhjavani, Eric S. Lester, Arun Kannayiram Jeyavelu, Ayusman Tripathy
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Publication number: 20170197723Abstract: 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.Type: ApplicationFiled: January 7, 2016Publication date: July 13, 2017Inventors: Omid B. Nakhjavani, Robert H. Willie, Paul S. Park, Mohammad Ali Heidari, Leonard J. Hebert, Milan Stefanovic, Parminder Singh, Naimishkumar B. Harpal, Andrew Y. Na
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Publication number: 20160363546Abstract: 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.Type: ApplicationFiled: June 10, 2015Publication date: December 15, 2016Inventors: Omid B. Nakhjavani, Mohammad Ali Heidari, Milan Stefanovic, Bradley A. Olmstead, Eric John Zimney, Naveena Mallikarjunaiah
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Patent number: 9347321Abstract: Methods for balancing rotating machinery, such as gas turbine engines, to minimize vibrations. An optimal engine balance solution is obtained using a hybrid optimization technique based on vibration data from one or more vibration sensors and corresponding influence coefficients which quantify the change in vibration level at the vibration sensors due to a unit increase in unbalance level at unbalance source locations. More specifically, balance weight and angular position are determined based on multiple optimization methods which concurrently process the vibration data, the multiple optimization methods comprising local and global optimization algorithms.Type: GrantFiled: August 1, 2014Date of Patent: May 24, 2016Assignee: THe Boeing CompanyInventors: Mohammad Ali Heidari, Micah D. Druckman, Omid B. Nakhjavani
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Publication number: 20160052214Abstract: A system and method for creating an optimized composite laminate structure containing a plurality of plies. The system has a processor and a memory, including an application interface. The application interface, when executed by the processor, is configured to operably: receive an input file having one or more of a maximum number of plies, design variables, material properties, and design constraints; determine an initial layup sequence defining parameters of a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle; iteratively adjust the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety, and that achieves optimization of the composite laminate structure; and generate an output file for creating a layup, according to the parameters. The system further has a layup system for creating the optimized composite laminate structure.Type: ApplicationFiled: August 22, 2014Publication date: February 25, 2016Inventors: Anthony K. Gilbert, Omid B. Nakhjavani, Shahriar Khosravani, Mohammad Ali Heidari, James F. Ackermann, Mostafa Rassaian, Forouzan Behzadpour
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Publication number: 20160042094Abstract: There is provided a system for reading geometric data from a parametric model or a nonparametric model from a CAD model file. The system has a processor and an interface application, which when executed by the processor, is configured to operably receive automatically, using a first interface application, an input file that includes data representing one or more components of a three-dimensional model, and is further configured to operably determine, using the first interface application, a type of a part represented by the three-dimensional model. The first interface application has instructions, one or more algorithms, or a combination thereof, and is further configured to automatically operably identify, select, and group geometric data associated with specific geometric data of the three-dimensional model, based on a set of parametric rules. The processor writes extracted specific geometric data to a first geometry data intermediate output file.Type: ApplicationFiled: August 11, 2014Publication date: February 11, 2016Inventors: Mohammad Ali Heidari, Anthony K. Gilbert, James S. Lee, Omid B. Nakhjavani, Eric S. Lester, Arun Kannayiram Jeyavelu, Ayusman Tripathy
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Publication number: 20160032725Abstract: Methods for balancing rotating machinery, such as gas turbine engines, to minimize vibrations. An optimal engine balance solution is obtained using a hybrid optimization technique based on vibration data from one or more vibration sensors and corresponding influence coefficients which quantify the change in vibration level at the vibration sensors due to a unit increase in unbalance level at unbalance source locations. More specifically, balance weight and angular position are determined based on multiple optimization methods which concurrently process the vibration data, the multiple optimization methods comprising local and global optimization algorithms.Type: ApplicationFiled: August 1, 2014Publication date: February 4, 2016Applicant: THE BOEING COMPANYInventors: Mohammad Ali Heidari, Micah D. Druckman, Omid B. Nakhjavani
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Patent number: 8192102Abstract: An apparatus has a tubular body with a channel and a number of stiffeners. The number of stiffeners allows the tubular body to absorb additional mechanical energy through axial compression. Additionally, the number of stiffeners is located on a number of locations for the tubular body. The apparatus also has a plurality of hinges located in part between the number of locations of the number of stiffeners for the tubular body, and also located between end flanges at the end of the tubular body and a stiffener. The number of hinges further define deformable regions. At least one deformable region of the plurality of deformable regions is configured to expand away from the channel in response to the tubular body being compressed in the axial direction.Type: GrantFiled: November 26, 2008Date of Patent: June 5, 2012Assignee: The Boeing CompanyInventors: Mohammad Ali Heidari, Adrian Stanescu, Saba Mahanian
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Publication number: 20100129137Abstract: An apparatus comprises a tubular body with a channel and a number of stiffeners that allow the tubular body to absorb additional mechanical energy through axial compression. The number of stiffeners is located on a number of locations for the tubular body.Type: ApplicationFiled: November 26, 2008Publication date: May 27, 2010Inventors: Mohammad Ali Heidari, Adrian Stanescu, Saba Mahanian