Patents by Inventor Todd H. Ashton
Todd H. Ashton 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).
-
Patent number: 11279474Abstract: A main landing gear assembly for an aircraft has an upper beam and a lower beam. The proximal ends of the upper and lower beams are each connected to a trunnion assembly that is mounted on the fuselage or wing of the aircraft. The distal ends of the upper and lower beams are each affixed to an axel support structure on which a main wheel of the landing gear assembly is mounted. In the gear assembly, the upper beam and the lower beam are coplanar and act together, in combination, to accommodate a planar flexure of the gear assembly during aircraft takeoffs and landings.Type: GrantFiled: May 30, 2019Date of Patent: March 22, 2022Assignee: CTLP, LLCInventors: Todd H. Ashton, Easton D. Smith, James S. Winegar, Austin J. N. Blue, Linden S. Blue
-
Publication number: 20210316845Abstract: A main landing gear assembly for an aircraft has an upper beam and a lower beam. The proximal ends of the upper and lower beams are each connected to a trunnion assembly that is mounted on the fuselage or wing of the aircraft. The distal ends of the upper and lower beams are each affixed to an axel support structure on which a main wheel of the landing gear assembly is mounted. In the gear assembly, the upper beam and the lower beam are coplanar and act together, in combination, to accommodate a planar flexure of the gear assembly during aircraft takeoffs and landings.Type: ApplicationFiled: May 30, 2019Publication date: October 14, 2021Inventors: Todd H. Ashton, Easton D. Smith, James S. Winegar, Austin J. N. Blue, Linden S. Blue
-
Publication number: 20200377202Abstract: A main landing gear assembly for an aircraft has an upper beam and a lower beam. The proximal ends of the upper and lower beams are each connected to a trunnion assembly that is mounted on the fuselage or wing of the aircraft. The distal ends of the upper and lower beams are each affixed to an axel support structure on which a main wheel of the landing gear assembly is mounted. In the gear assembly, the upper beam and the lower beam are coplanar and act together, in combination, to accommodate a planar flexure of the gear assembly during aircraft takeoffs and landings.Type: ApplicationFiled: May 30, 2019Publication date: December 3, 2020Inventors: Todd H. Ashton, Easton D. Smith, James S. Winegar, Austin J. N. Blue, Linden S. Blue
-
Patent number: 9586367Abstract: A method is provided for the non-contact measurement of variations in thickness of composite materials and structures prepared from composite parts. Metrologic methods are employed to provide a 3D image of the structure or part. Variations that are greater than an acceptable amount can be corrected by adding a compensation layer to the surface of the structure or part.Type: GrantFiled: November 4, 2008Date of Patent: March 7, 2017Assignee: LOCKHEED MARTIN CORPORATIONInventors: Jeffrey T. Drewett, Paul T. Briney, Grady L. White, Gary L. Kelly, Michael L. Hestness, Todd H. Ashton, Peter L. Morken
-
Publication number: 20100186893Abstract: Composite structures are fabricated and cured without applying external heat from an autoclave or oven. This technique uses composite preforms to form high strength, three-dimensional co-bonded joints, and thermoplastic conformal mandrels such as rota-molded vacuum bags. The bags form internal tooling within the structure and provide molding with integral fittings that circulate heated air within the bags. The exteriors of the bags are simultaneously under vacuum and exert pressure on the composite elements of the structure that are being cured. This internally-applied heat initially causes to the bags to soften and fully conform to the internal shapes of the structure that are being co-bonded. The heat then transfers into the uncured materials, causing them to cure without unnecessarily heating the entire structure or any required tooling.Type: ApplicationFiled: January 29, 2009Publication date: July 29, 2010Applicant: Lockheed Martin CorporationInventors: Todd H. Ashton, Ron P. Schmidt, Scott McKee, Ross A. Benson
-
Publication number: 20100112190Abstract: A method is provided for the non-contact measurement of variations in thickness of composite materials and structures prepared from composite parts. Metrologic methods are employed to provide a 3D image of the structure or part. Variations that are greater than an acceptable amount can be corrected by adding a compensation layer to the surface of the structure or part.Type: ApplicationFiled: November 4, 2008Publication date: May 6, 2010Inventors: Jeffrey T. Drewett, Paul T. Briney, Grady L. White, Gary L. Kelly, Michael L. Hestness, Todd H. Ashton, Peter L. Morken
-
Patent number: 7625510Abstract: Composite tooling is fabricated with low cost dry fabrics and a neat resin instead of expensive prepregs. Dry, three-dimensional woven joint preforms are placed on a dry tool substrate and dry, 3D preforms are also placed between pre-cured egg crate-like junctions. The entire tool substrate and substrate-to-support structure joints are then resin-infused simultaneously through the use of rota-molded tooling aids, providing an additional reduction in cost. Tight control of resin content and distribution with vacuum infusion is thereby provided. This process eliminates the primary cause of structural weakness and cooling distortion, which typically occur at the attachment interface when existing methods are used. The preforms provide significantly greater pull-off strengths at interfaces than do hand-laid tie plies. Issues with tool surface durability are addressed through the use of ceramic-filled face coat.Type: GrantFiled: November 29, 2005Date of Patent: December 1, 2009Assignee: Lockheed Martin CorporationInventors: Todd H. Ashton, Richard R. Batzer, Ronald P. Schmidt
-
Patent number: 6849323Abstract: A composite panel waffle stiffener has fabric plies pre-cut to a selected pattern and laid on a tool having a waffle configuration. The plies overlap each other to maintain continuity of the structure. The resulting waffle stiffener is then bonded to a panel requiring stiffening. The stiffener is flexible and may be bonded to curved panels. Holes in the stiffener allow access to the volume between the stiffener and the panel for minimizing volume loss within, for example, a wing structure containing fuel and for ventilating air or moisture trapped in the volume.Type: GrantFiled: October 30, 2003Date of Patent: February 1, 2005Assignee: Lockheed Martin CorporationInventors: Ross A. Benson, Terrance R. Burd, Todd H. Ashton
-
Publication number: 20040091676Abstract: A composite panel waffle stiffener has fabric plies pre-cut to a selected pattern and laid on a tool having a waffle configuration. The plies overlap each other to maintain continuity of the structure. The resulting waffle stiffener is then bonded to a panel requiring stiffening. The stiffener is flexible and may be bonded to curved panels. Holes in the stiffener allow access to the volume between the stiffener and the panel for minimizing volume loss within, for example, a wing structure containing fuel and for ventilating air or moisture trapped in the volume.Type: ApplicationFiled: October 30, 2003Publication date: May 13, 2004Inventors: Ross A. Benson, Terrance R. Burd, Todd H. Ashton
-
Patent number: 6649006Abstract: An apparatus and method for stiffening a panel provides a composite waffle stiffener and the method for constructing the stiffener. A plurality of fabric plies pre-cut to a selected pattern are laid on a tool having a waffle configuration, the plies overlapping each other to maintain continuity of the structure. The resulting waffle stiffener is then bonded to a panel requiring stiffening. The stiffener is flexible and may be bonded to curved panels. Holes in the stiffener allow access to the volume between the stiffener and the panel for minimizing volume loss within, for example, a wing structure containing fuel and for ventilating air or moisture trapped in the volume.Type: GrantFiled: October 9, 2001Date of Patent: November 18, 2003Assignee: Lockheed Martin CorporationInventors: Ross A. Benson, Terrance R. Burd, Todd H. Ashton
-
Patent number: 6589472Abstract: A thermoplastic conformal tool/vacuum bag that is structured to substantially conform to a surface or a cavity in a composite structure is placed proximate to a uncured composite member to fabricate a composite structure. External heat and external pressure are applied to cure the member. The conformal thermoplastic tool/vacuum bag is removed from the cured assembly by reheating, if necessary, to facilitate removal of the tool/vacuum bag.Type: GrantFiled: May 31, 2001Date of Patent: July 8, 2003Assignee: Lockheed Martin CorporationInventors: Ross A. Benson, Todd H. Ashton
-
Publication number: 20030068472Abstract: An apparatus and method for stiffening a panel provides a composite waffle stiffener and the method for constructing the stiffener. A plurality of fabric plies pre-cut to a selected pattern are laid on a tool having a waffle configuration, the plies overlapping each other to maintain continuity of the structure. The resulting waffle stiffener is then bonded to a panel requiring stiffening. The stiffener is flexible and may be bonded to curved panels. Holes in the stiffener allow access to the volume between the stiffener and the panel for minimizing volume loss within, for example, a wing structure containing fuel and for ventilating air or moisture trapped in the volume.Type: ApplicationFiled: October 9, 2001Publication date: April 10, 2003Inventors: Ross A. Benson, Terrance R. Burd, Todd H. Ashton
-
Patent number: 5137071Abstract: An apparatus used to form a three-dimensional composite structure is disclosed having an initially rigid heat-softenable layer of ABS plastic wherein uncured portions of the composite structure are first assembled between the layer of ABS plastic and a hard mold surface. Prior to curing of the composite structure, pressure and heat are applied to the ABS layer to soften the layer and thereafter compact the uncured portions of the structure against the hard mold surface. The ability to pre-shape the ABS layer allows stiffening beams to be incorporated into the structure so as to yield a lightweight, strong composite structure that can be used as a pressure vessel in an aerospace vehicle.Type: GrantFiled: July 21, 1989Date of Patent: August 11, 1992Assignee: Chemicals & Materials Enterprise Assoc.Inventors: Larry Ashton, Todd H. Ashton
-
Patent number: 5059377Abstract: A method of forming a three-dimensional composite structure. Uncured portions of the composite structure are first assembled between a initially rigid heat-softening inner layer of ABS plastic and a hard outer mold surface. Prior to curing of the composite structure, pressure and heat is applied to the ABS layer to soften the layer. Thereafter, pressure is applied to the side of the ABS layer opposite from the composite structure, thereby to compact the uncured portions of the composite structure against the hard outer mold. Stiffening beams may be incorporated into the composite structure, so as to yield a lightweight, strong composite structure that can be used as a pressure vessel in an aerospace vehicle.Type: GrantFiled: July 21, 1989Date of Patent: October 22, 1991Assignee: Aerotrans CorporationInventors: Larry J. Ashton, Todd H. Ashton