Patents by Inventor Ramesh Thiagarajan
Ramesh Thiagarajan 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: 11396372Abstract: Embodiments are directed to systems and methods for providing a control link for an aircraft in which the control link comprises an impact-resistant structure with a redundant load path. The control link has an inner structure that is sized to carry the anticipated load of the flight control system and to meet all safety factors. The control link also has an outer structure that is sacrificial and configured to absorb impact damage during operation, thereby protecting the inner structure. The outer structure is also designed to carry the anticipated load of the flight control system on its own, independent of the inner structure, and to meet all safety factors. If the outer structure fails, the inner structure allows for continued safe operation of the flight control system. The space or cavity between the inner and outer structures may be filled with a material, such as a closed-cell foam, to improve the impact resistance of the outer structure.Type: GrantFiled: August 30, 2018Date of Patent: July 26, 2022Assignee: Textron Innovations Inc.Inventors: John Benjamin Osborne, Ramesh Thiagarajan, Charles Joseph Kilmain
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Patent number: 11097507Abstract: A structure includes a skin and a foam member. The foam member has a molded contour, the mold contour being configured to provide tooled surface for the skin. When the skin is a composite skin, the foam member provides support for the skin so that the skin can be cured under heat and pressure. A method of making the foam member for a foam stiffened structure includes creating a mold having an interior cavity which resembles a desired shape the foam member. A subsequent step involves introducing a foam mixture into the mold. Next, the foam mixture is allowed to polymerize so as to expand and distribute within the cavity of the mold. The method further includes selectively controlling a density of the foam member in the mold. The foam member is at least partially cured. The foam member is assembled with a skin to produce the foam stiffened structure.Type: GrantFiled: June 28, 2016Date of Patent: August 24, 2021Assignee: Textron Innovations Inc.Inventors: Ramesh Thiagarajan, Suvankar Mishra, Mark Chris, William Evans, III, Mike Mikel
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Publication number: 20200070967Abstract: Embodiments are directed to systems and methods for providing a control link for an aircraft in which the control link comprises an impact-resistant structure with a redundant load path. The control link has an inner structure that is sized to carry the anticipated load of the flight control system and to meet all safety factors. The control link also has an outer structure that is sacrificial and configured to absorb impact damage during operation, thereby protecting the inner structure. The outer structure is also designed to carry the anticipated load of the flight control system on its own, independent of the inner structure, and to meet all safety factors. If the outer structure fails, the inner structure allows for continued safe operation of the flight control system. The space or cavity between the inner and outer structures may be filled with a material, such as a closed-cell foam, to improve the impact resistance of the outer structure.Type: ApplicationFiled: August 30, 2018Publication date: March 5, 2020Applicant: Bell Helicopter Textron Inc.Inventors: John Benjamin Osborne, Ramesh Thiagarajan, Charles Joseph Kilmain
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Patent number: 10317323Abstract: Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.Type: GrantFiled: October 12, 2017Date of Patent: June 11, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Ramesh Thiagarajan, Suvankar Mishra
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Publication number: 20190113426Abstract: Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.Type: ApplicationFiled: October 12, 2017Publication date: April 18, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Ramesh Thiagarajan, Suvankar Mishra
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Publication number: 20160303818Abstract: A structure includes a skin and a foam member. The foam member has a molded contour, the mold contour being configured to provide tooled surface for the skin. When the skin is a composite skin, the foam member provides support for the skin so that the skin can be cured under heat and pressure. A method of making the foam member for a foam stiffened structure includes creating a mold having an interior cavity which resembles a desired shape the foam member. A subsequent step involves introducing a foam mixture into the mold. Next, the foam mixture is allowed to polymerize so as to expand and distribute within the cavity of the mold. The method further includes selectively controlling a density of the foam member in the mold. The foam member is at least partially cured. The foam member is assembled with a skin to produce the foam stiffened structure.Type: ApplicationFiled: June 28, 2016Publication date: October 20, 2016Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Ramesh Thiagarajan, Suvankar Mishra, Mark Chris, William Evans, III, Mike Mikel
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Patent number: 9333684Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: GrantFiled: October 30, 2012Date of Patent: May 10, 2016Assignee: Bell Helicopter Textron Inc.Inventors: Ramesh Thiagarajan, Robert Mark Chris, John R. McCullough, Suvankar Mishra
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Patent number: 9149999Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: GrantFiled: October 30, 2012Date of Patent: October 6, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Ramesh Thiagarajan, Theodore W. Ingram, III, John R. McCullough, Suvankar Mishra, Carl May
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Patent number: 9015941Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: GrantFiled: October 30, 2012Date of Patent: April 28, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Ramesh Thiagarajan, Robert Mark Chris, John R. McCullough, Suvankar Mishra
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Publication number: 20140120305Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: ApplicationFiled: October 30, 2012Publication date: May 1, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Ramesh Thiagarajan, Robert Mark Chris, John R. McCullough, Suvankar Mishra
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Publication number: 20140119930Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: ApplicationFiled: October 30, 2012Publication date: May 1, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Ramesh Thiagarajan, Robert Mark Chris, John R. McCullough, Suvankar Mishra
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Publication number: 20140120298Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: ApplicationFiled: October 30, 2012Publication date: May 1, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Ramesh Thiagarajan, Theodore W. Ingram, III, John R. McCullough, Suvankar Mishra, Carl May
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Publication number: 20140115853Abstract: A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.Type: ApplicationFiled: October 30, 2012Publication date: May 1, 2014Applicant: BELL HELICOPTER TEXTRON INC.Inventors: Ramesh Thiagarajan, Robert Mark Chris, John R. McCullough, Suvankar Mishra
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Publication number: 20120114897Abstract: A structure includes a skin and a foam member. The foam member has a molded contour, the mold contour being configured to provide tooled surface for the skin. When the skin is a composite skin, the foam member provides support for the skin so that the skin can be cured under heat and pressure. A method of making the foam member for a foam stiffened structure includes creating a mold having an interior cavity which resembles a desired shape the foam member. A subsequent step involves introducing a foam mixture into the mold. Next, the foam mixture is allowed to polymerize so as to expand and distribute within the cavity of the mold. The method further includes selectively controlling a density of the foam member in the mold. The foam member is at least partially cured. The foam member is assembled with a skin to produce the foam stiffened structure.Type: ApplicationFiled: September 2, 2011Publication date: May 10, 2012Inventors: Ramesh Thiagarajan, Suvankar Mishra, Mark Chris, William Evans, III, Mike Mikel
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Patent number: 6427942Abstract: A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffniess of the cross members may be performed independently of the optimization of the vertical stiffniess and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life.Type: GrantFiled: June 8, 2001Date of Patent: August 6, 2002Assignee: Bell Helicopter Textron Inc.Inventors: John V. Howard, Ramesh Thiagarajan, Michael R. Smith, Ashish K. Sareen
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Publication number: 20020008175Abstract: A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffness of the cross members may be performed independently of the optimization of the vertical stiffness and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life.Type: ApplicationFiled: June 8, 2001Publication date: January 24, 2002Applicant: Bell Helicopter Textron Inc.Inventors: John V. Howard, Ramesh Thiagarajan, Michael R. Smith, Ashish K. Sareen
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Patent number: 6244538Abstract: A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffness of the cross members may be performed independently of the optimization of the vertical stiffness and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life.Type: GrantFiled: May 19, 1999Date of Patent: June 12, 2001Assignee: Bell Helicopter Textron Inc.Inventors: John V. Howard, Ramesh Thiagarajan, Michael R. Smith, Ashish K. Sareen