Patents by Inventor Moushumi Shome
Moushumi Shome 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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Publication number: 20170120512Abstract: A method of bonding materials may comprise defining a bond interface between two materials in a cure zone on a surface of an object, and non-conductively heating the bond interface without directly heating the surface outside of the cure zone. Non-conductively heating the bond interface may involve applying microwave radiation to the bond interface.Type: ApplicationFiled: January 16, 2017Publication date: May 4, 2017Applicant: The Boeing CompanyInventors: Moushumi Shome, Adriana Willempje Blom, Sahrudine Apdalhaliem, Waeil M. Ashmawi
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Patent number: 9581146Abstract: A system for heating a shape memory alloy (SMA) actuator may include an SMA actuator, a smart susceptor, a plurality of induction coils, and a control module. The SMA actuator may have at least one layup. The SMA actuator may be selectively heated to a transition temperature. The smart susceptor may be in thermal contact with the at least one layup of the SMA actuator. The induction heating coils may be configured to receive an alternating current and generate a magnetic field based on the alternating current. The magnetic field may create an eddy current in at least one of the SMA actuator and the smart susceptor to heat the SMA actuator to the transition temperature. The control module may be configured to drive the alternating current supplied to the induction heating coils.Type: GrantFiled: October 3, 2013Date of Patent: February 28, 2017Assignee: The Boeing CompanyInventors: Moushumi Shome, Frederick T. Calkins, Stephen R. Amorosi, Flint M. Jamison, Sahrudine Apdalhaliem, Robert James Miller
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Patent number: 9545782Abstract: A method of bonding materials may comprise defining a bond interface between two materials in a cure zone on a surface of an object, and non-conductively heating the bond interface without directly heating the surface outside of the cure zone. Non-conductively heating the bond interface may involve applying microwave radiation to the bond interface.Type: GrantFiled: May 13, 2014Date of Patent: January 17, 2017Assignee: The Boeing CompanyInventors: Moushumi Shome, Adriana Willempje Blom, Sahrudine Apdalhaliem, Waeil M. Ashmawi
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Patent number: 9527126Abstract: A system for manufacturing a composite tubular structure. The system includes an outer tube configured to remain rigid up to at least a first threshold pressure. The system includes an inner tube internal to the outer tube and substantially coaxial with the outer tube. The inner tube has a first outer surface and a first inner surface. The inner tube is configured to remain rigid up to a second threshold pressure that is less than the threshold first pressure. The system includes a composite tubular layup laid on the first outer surface of the inner tube. The system includes an assembly of a plurality of separate segments disposed inside the inner tube, each segment adjacent to two other segments, to form a segmented inner cylinder having a second outer surface of a cylindrical shape and an inner channel of a first conical shape.Type: GrantFiled: July 11, 2014Date of Patent: December 27, 2016Assignee: THE BOEING COMPANYInventors: Sahrudine Apdalhaliem, Waeil M. Ashmawi, Moushumi Shome, Jeffery Lee Marcoe
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Patent number: 9457494Abstract: Method and apparatus for curing a composite laminate. The apparatus comprising an electromagnetic radiation source creating electromagnetic microwave energy in an enclosed volume and a heating source for providing a convective airflow in the enclosed volume. A composite laminate assembly comprising a composite laminate is placed in the enclosed volume, wherein the composite laminate of the composite laminate assembly is cured by both the electromagnetic microwave energy created by the electromagnetic radiation source, and the convective airflow provided by the heating source. A vacuum bag may be placed over the composite laminate assembly. A source may be activated such that a vacuum within the vacuum bag is created according to design specifications.Type: GrantFiled: September 9, 2014Date of Patent: October 4, 2016Assignee: The Boeing CompanyInventors: Moushumi Shome, Janet Mary Layng, Waeil M. Ashmawi, Sahrudine Apdalhaliem
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Publication number: 20160201654Abstract: Aspects of the present disclosure generally relate to an SMA actuator that includes a cooling device disposed within a torque tube. In one aspect, the cooling device includes a sliding sleeve, an expandable sleeve, and plurality of cooling fins coupled to the expandable sleeve. Axial movement of the sliding sleeve relative to the expandable sleeve facilitates radial expansion of the expandable sleeve and urges the cooling fins into contact with the torque tube. The cooling fins function as heat sinks when in contact with the torque tube to facilitate the removal of heat from the torque tube to increase the cooling rate of the torque tube. During heating of the torque tube, the cooling fins may be spaced apart from the torque tube to reduce the thermal mass that is heated, thus increasing the heating rate of the torque tube.Type: ApplicationFiled: January 9, 2015Publication date: July 14, 2016Inventors: Sahrudine APDALHALIEM, Moushumi SHOME, Kimberly D. MEREDITH, Waeil M. ASHMAWI, Morteza SAFAI, Frederick T. CALKINS
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Publication number: 20160067888Abstract: Method and apparatus for curing a composite laminate. The apparatus comprising an electromagnetic radiation source creating electromagnetic microwave energy in an enclosed volume and a heating source for providing a convective airflow in the enclosed volume. A composite laminate assembly comprising a composite laminate is placed in the enclosed volume, wherein the composite laminate of the composite laminate assembly is cured by both the electromagnetic microwave energy created by the electromagnetic radiation source, and the convective airflow provided by the heating source. A vacuum bag may be placed over the composite laminate assembly. A source may be activated such that a vacuum within the vacuum bag is created according to design specifications.Type: ApplicationFiled: September 9, 2014Publication date: March 10, 2016Inventors: Moushumi Shome, Janet Mary Layng, Waeil M. Ashmawi, Sahrudine Apdalhaliem
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Publication number: 20160023406Abstract: In one or more aspects of the present disclosure, a mandrel is disclosed. The mandrel having a shape memory alloy (SMA) shell having a longitudinal axis, an interior extending along the longitudinal axis and an exterior contour, the SMA shell being configured to interface with a structure to be cured, and at least one SMA actuation member disposed within the interior and connected to the SMA shell, where the at least one SMA actuation member is configured to exert pressure against the SMA shell effecting an interface pressure between the exterior contour of the SMA shell and the structure to be cured where the exterior contour has a predetermined actuated shape that corresponds to a predetermined cured shape of the structure to be cured.Type: ApplicationFiled: July 25, 2014Publication date: January 28, 2016Inventors: Moushumi Shome, Sahrudine Apdalhaliem, Frederick T. Calkins, Waeil M. Ashmawi, Kimberly Meredith
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Publication number: 20160016355Abstract: Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.Type: ApplicationFiled: July 16, 2014Publication date: January 21, 2016Applicant: THE BOEING COMPANYInventors: Jeffery L. Marcoe, Sahrudine Apdalhaliem, Moushumi Shome
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Publication number: 20160008868Abstract: A system for manufacturing a composite tubular structure. The system includes an outer tube configured to remain rigid up to at least a first threshold pressure. The system includes an inner tube internal to the outer tube and substantially coaxial with the outer tube. The inner tube has a first outer surface and a first inner surface. The inner tube is configured to remain rigid up to a second threshold pressure that is less than the threshold first pressure. The system includes a composite tubular layup laid on the first outer surface of the inner tube. The system includes an assembly of a plurality of separate segments disposed inside the inner tube, each segment adjacent to two other segments, to form a segmented inner cylinder having a second outer surface of a cylindrical shape and an inner channel of a first conical shape.Type: ApplicationFiled: July 11, 2014Publication date: January 14, 2016Inventors: Sahrudine Apdalhaliem, Waeil M. Ashmawi, Moushumi Shome, Jeffery Lee Marcoe
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Publication number: 20160003280Abstract: Provided are assemblies having composite structures interlocked with shape memory alloy structures and methods of fabricating such assemblies. Interlocking may involve inserting an interlocking protrusion of a shape memory alloy structure into an interlocking opening of a composite structure and heating at least this protrusion of the shape memory alloy structure to activate the alloy and change the shape of the protrusion. This shape change engages the protrusion in the opening such that the protrusion cannot be removed from the opening. The shape memory alloy structure may be specifically trained prior to forming an assembly using a combination of thermal cycling and deformation to achieve specific pre-activation and post-activation shapes. The pre-activation shape allows inserting the interlocking protrusion into the opening, while the post-activation shape engages the interlocking protrusion within the opening. As such, activation of the shape memory alloy interlocks the two structures.Type: ApplicationFiled: July 3, 2014Publication date: January 7, 2016Applicant: The Boeing CompanyInventors: Waeil M. Ashmawi, Jaime C. Garcia, Sahrudine Apdalhaliem, Jeffery L. Marcoe, Moushumi Shome
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Publication number: 20150328877Abstract: A method of bonding materials may comprise defining a bond interface between two materials in a cure zone on a surface of an object, and non-conductively heating the bond interface without directly heating the surface outside of the cure zone. Non-conductively heating the bond interface may involve applying microwave radiation to the bond interface.Type: ApplicationFiled: May 13, 2014Publication date: November 19, 2015Applicant: THE BOEING COMPANYInventors: Moushumi Shome, Adriana Willempje Blom, Sahrudine Apdalhaliem, Waeil M. Ashmawi
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Publication number: 20150321441Abstract: Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting.Type: ApplicationFiled: August 22, 2014Publication date: November 12, 2015Inventors: Jeffery Lee Marcoe, Marc Rollo Matsen, Waeil M. Ashmawi, Jaime C. Garcia, Sahrudine Apdalhaliem, John B. Moser, Brett I. Lyons, Moushumi Shome, Kay Y. Blohowiak
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Patent number: 9145198Abstract: A system for varying a camber of an airfoil may include an airfoil having an upper surface and a lower surface meeting to form a leading edge and a trailing edge, the lower surface having a first actuator including shape memory alloy sheet, a controller including a plurality of heating elements attached to the shape memory alloy sheet for selectively heating the sheet to a temperature above ambient to deform the upper and lower surfaces to morph a geometry of a camber of the airfoil thereby, a computer control connected to selectively control individual activation of the heating elements to heat the shape memory alloy sheet to a selected temperature to effect a selected deflection, and a cooling device to allow ambient air to enter the wing and exit over the actuator to resume a non-morphed state.Type: GrantFiled: January 4, 2013Date of Patent: September 29, 2015Assignee: THE BOEING COMPANYInventors: Moushumi Shome, Frederick T. Calkins, Sahrudine Apdalhaliem
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Patent number: 9120554Abstract: A system and methods for configuring a fluid-dynamic body is disclosed. A camber of a fluid-dynamic body is configured by activating a shape memory alloy actuator coupled to the fluid-dynamic body.Type: GrantFiled: August 16, 2011Date of Patent: September 1, 2015Assignee: The Boeing CompanyInventors: Moushumi Shome, Frederick T. Calkins, James Henry Mabe, Matthew Todd Grimshaw
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Publication number: 20150240793Abstract: Described herein is an apparatus for controlling an actuator made from a shape-memory alloy includes a first layer made from a thermally conductive material and a second layer. The second layer is made from a thermally conductive material. The apparatus also includes at least one thermoelectric heater positioned between the first and second layers. Additionally, the apparatus includes at least one thermoelectric cooler positioned between the first and second layers.Type: ApplicationFiled: February 21, 2014Publication date: August 27, 2015Applicant: THE BOEING COMPANYInventors: Morteza Safai, Kimberly D. Meredith, Sahrudine Apdalhaliem, Moushumi Shome, Frederick T. Calkins
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Patent number: 9010688Abstract: Apparatus and methods provide for a structural joint utilizing overlapping blade stringers coupled to opposing sides of a continuous skin. According to embodiments described herein, a structural joint includes a number of inside blade stringers associated with a first component are coupled to an inside surface of a continuous skin. A number of outside blade stringers associated with a second component may be coupled to an outside surface of the continuous skin. The inside blade stringers and outside blade stringers may overlap on opposing surfaces of the continuous skin.Type: GrantFiled: February 7, 2012Date of Patent: April 21, 2015Assignee: The Boeing CompanyInventor: Moushumi Shome
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Publication number: 20150096293Abstract: A system for heating a shape memory alloy (SMA) actuator may include an SMA actuator, a smart susceptor, a plurality of induction coils, and a control module. The SMA actuator may have at least one layup. The SMA actuator may be selectively heated to a transition temperature. The smart susceptor may be in thermal contact with the at least one layup of the SMA actuator. The induction heating coils may be configured to receive an alternating current and generate a magnetic field based on the alternating current. The magnetic field may create an eddy current in at least one of the SMA actuator and the smart susceptor to heat the SMA actuator to the transition temperature. The control module may be configured to drive the alternating current supplied to the induction heating coils.Type: ApplicationFiled: October 3, 2013Publication date: April 9, 2015Applicant: The Boeing CompanyInventors: Moushumi Shome, Frederick T. Calkins, Stephen R. Amorosi, Flint M. Jamison, Sahrudine Apdalhaliem, Robert James Miller
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Publication number: 20130200215Abstract: Apparatus and methods provide for a structural joint utilizing overlapping blade stringers coupled to opposing sides of a continuous skin. According to embodiments described herein, a structural joint includes a number of inside blade stringers associated with a first component are coupled to an inside surface of a continuous skin. A number of outside blade stringers associated with a second component may be coupled to an outside surface of the continuous skin. The inside blade stringers and outside blade stringers may overlap on opposing surfaces of the continuous skin.Type: ApplicationFiled: February 7, 2012Publication date: August 8, 2013Inventor: Moushumi Shome
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Patent number: 8434293Abstract: A shape memory alloy (SMA) actuated aerostructure operable to dynamically change shape according to flight conditions is disclosed. Deformable structures are actuated by SMA actuators that are coupled to face sheets of the deformable structures. Actuating the SMA actuators produces complex shape changes of the deformable structures by activating shape changes of the SMA actuators. The SMA actuators are actuated via an active or passive temperature change based on operating conditions. The SMA actuated aerostructure can be used for morphable nozzles such as a variable area fan nozzle and/or a variable geometry chevron of a jet engine to reduce engine noise during takeoff without degrading fuel burn during cruise.Type: GrantFiled: August 6, 2009Date of Patent: May 7, 2013Assignee: The Boeing CompanyInventors: Richard D. Widdle, Jr., Matthew T. Grimshaw, Kava S. Crosson-Elturan, James H. Mabe, Frederick T. Calkins, Lynn M. Gravatt, Moushumi Shome