Patents by Inventor Gary H. Johnson
Gary H. Johnson 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: 9835425Abstract: A nosecone is provided and includes a ring that includes an angled surface, a nosecone tip, a double-walled shroud portion including inner and outer dome elements, a first end that interfaces with and is constrained by the nosecone tip and a second end that is connectable to the ring to define with the angled surface a sliding, resistive interface and a shim disposable in the double walled shroud portion to pre-load the sliding, resistive interface and to provide for separation distance between the inner and outer dome elements.Type: GrantFiled: August 14, 2015Date of Patent: December 5, 2017Assignee: RAYTHEON COMPANYInventors: Stephanie G. Rodriguez, Todd Kuhar, Thomas H. Penhollow, Brian B. Greer, Mark A. Hahn, Regina P. Reed, Richard M. Cordova, Patrick G. Dickerson, Kenneth G. Preston, Rick A. Ramos, Brady A. Hink, Gary H. Johnson
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Publication number: 20170045344Abstract: A nosecone is provided and includes a ring that includes an angled surface, a nosecone tip, a double-walled shroud portion including inner and outer dome elements, a first end that interfaces with and is constrained by the nosecone tip and a second end that is connectable to the ring to define with the angled surface a sliding, resistive interface and a shim disposable in the double walled shroud portion to pre-load the sliding, resistive interface and to provide for separation distance between the inner and outer dome elements.Type: ApplicationFiled: August 14, 2015Publication date: February 16, 2017Inventors: Stephanie G. Rodriguez, Todd Kuhar, Thomas H. Penhollow, Brian B. Greer, Mark A. Hahn, Regina P. Reed, Richard M. Cordova, Patrick G. Dickerson, Kenneth G. Preston, Rick A. Ramos, Brady A. Hink, Gary H. Johnson
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Patent number: 8931738Abstract: A protective cover (10) for an instrument dome (12) extending from a body (20) of a vehicle, such as a missile. The cover (10) includes multiple segments (14 and 16) having trailing ends (18) connectable to the body (20) at joints (22) that allow for rotational movement. The cover (10) further includes a releasable holder (26) that includes a retention device (28) that holds leading ends (24) of the segments (14 and 16) together, and a release mechanism (30) for causing the retention device (28) to release the leading ends (24). The joints (22) hold the trailing ends (18) of the segments (14 and 16) to the body (20) through a predetermined range of motion beyond which the segments (14 and 16) will be released to separate from the body (20) when the segments (14 and 16) rotate beyond the predetermined range.Type: GrantFiled: February 21, 2012Date of Patent: January 13, 2015Assignee: Raytheon CompanyInventors: Phillip Craige White, Robert L. Sisk, III, Brian S. Scott, Larry A. Coleman, Gary H. Johnson
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Patent number: 8567969Abstract: Optical systems configured to withstand operation in high acceleration and varying temperature environments, and methods of assembling the same. In one example, an imaging optical apparatus includes a primary minor made of an unreinforced polymer, a secondary mirror made of the unreinforced polymer and optically coupled to the primary minor, a field lens optically coupled to the secondary minor, and a strut having a plurality of cross-struts and mounting features configured to mount the primary minor, the secondary mirror and the field lens. In some examples, the imaging optical apparatus further includes an outer retainer disposed behind the primary minor and coupled to the strut, and an inner retainer disposed behind the field lens and coupled to the strut, the outer and inner retainers configured to structurally support the primary minor and the field lens and to accommodate deflections of the primary minor.Type: GrantFiled: February 10, 2012Date of Patent: October 29, 2013Assignee: Raytheon CompanyInventors: John A. Thomas, Thomas H. Lind, Ronald L. Roncone, Gary H. Johnson
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Publication number: 20130214093Abstract: A protective cover (10) for an instrument dome (12) extending from a body (20) of a vehicle, such as a missile. The cover (10) includes multiple segments (14 and 16) having trailing ends (18) connectable to the body (20) at joints (22) that allow for rotational movement. The cover (10) further includes a releasable holder (26) that includes a retention device (28) that holds leading ends (24) of the segments (14 and 16) together, and a release mechanism (30) for causing the retention device (28) to release the leading ends (24). The joints (22) hold the trailing ends (18) of the segments (14 and 16) to the body (20) through a predetermined range of motion beyond which the segments (14 and 16) will be released to separate from the body (20) when the segments (14 and 16) rotate beyond the predetermined range.Type: ApplicationFiled: February 21, 2012Publication date: August 22, 2013Applicant: RAYTHEON COMPANYInventors: Phillip Craige White, Robert L. Sisk, III, Brian S. Scott, Larry A. Coleman, Gary H. Johnson
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Publication number: 20130208367Abstract: Optical systems configured to withstand operation in high acceleration and varying temperature environments, and methods of assembling the same. In one example, an imaging optical apparatus includes a primary minor made of an unreinforced polymer, a secondary mirror made of the unreinforced polymer and optically coupled to the primary minor, a field lens optically coupled to the secondary minor, and a strut having a plurality of cross-struts and mounting features configured to mount the primary minor, the secondary mirror and the field lens. In some examples, the imaging optical apparatus further includes an outer retainer disposed behind the primary minor and coupled to the strut, and an inner retainer disposed behind the field lens and coupled to the strut, the outer and inner retainers configured to structurally support the primary minor and the field lens and to accommodate deflections of the primary minor.Type: ApplicationFiled: February 10, 2012Publication date: August 15, 2013Applicant: Raytheon CompanyInventors: John A. Thomas, Thomas H. Lind, Ronald L. Roncone, Gary H. Johnson
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Patent number: 7633691Abstract: An optical element mounting includes a frame, and a shuttle that is translatable relative to the frame. The shuttle includes inner and outer portions that are mechanically coupled together by a plurality of flexures that effectively bending and twisting of the shuttle from being transmitted to an optical element, such as an optical window, that is mounted on the inner portion of the shuttle. The flexures may be thin linking strips of material between the outer and inner portions. The flexures may have a thickness that is greater in an expected load direction, than in a direction perpendicular to the load direction. The optical mounting may include a locking mechanism, for example including a shape memory alloy wire, to lock the shuttle in a predetermined location relative to the frame.Type: GrantFiled: June 7, 2004Date of Patent: December 15, 2009Assignee: Raytheon CompanyInventors: Gary H. Johnson, John A. Thomas, John A. Winkler
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Patent number: 7566028Abstract: A guided projectile has a deployment system for deploying a deployable structure, such as a fin, another type of control surface, or an antenna. The deployment system includes a single-piece body that has a hub body and a resilient tab. The resilient tab presses against a stepped surface of a guided projectile body. As the deployable structure is extended, the deployable structure body rotates about a shaft in a central hole or aperture in the hub body. The resilient tab presses against the stepped surface on one side of an edge of the stepped surface during a first (relatively stowed) part of this deployment. At a certain point, as the contact between the tab and the stepped surfaces reaches the edge (the step of the stepped surface), the resilient tab changes position. The change in position of the resilient tab keeps the deployable structure from retracting again.Type: GrantFiled: October 26, 2006Date of Patent: July 28, 2009Assignee: Raytheon CompanyInventor: Gary H. Johnson
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Patent number: 7547865Abstract: An optical element mount is effective in high G environments to protect brittle optical elements in which tensile stresses are generated on surface S2 without degrading optical performance. A flexible spacer formed of a relatively low-stiffness material supports an optical element having a tapered outer periphery in an optical seat having a complementary tapered surface. When the optical assembly is exposed to the high G environment, the inertial loading drives the optical element in the aft direction into the flexible spacer and seat. This puts the optical element into a plate bending condition thereby inducing tensile stress on S2 which is at least partially offset by a compressive stress caused by the reaction force normal to the tapered interface. The stresses, both compressive and tensile, placed on the optical element in the high G environment can be very large.Type: GrantFiled: June 11, 2007Date of Patent: June 16, 2009Assignee: Raytheon CompanyInventors: Gary H. Johnson, Douglas M. Beard, John A. Thomas, Rene D. Perez
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Publication number: 20080302905Abstract: An optical element mount is effective in high G environments to protect brittle optical elements in which tensile stresses are generated on surface S2 without degrading optical performance. A flexible spacer formed of a relatively low-stiffness material supports an optical element having a tapered outer periphery in an optical seat having a complementary tapered surface. When the optical assembly is exposed to the high G environment, the inertial loading drives the optical element in the aft direction into the flexible spacer and seat. This puts the optical element into a plate bending condition thereby inducing tensile stress on S2 which is at least partially offset by a compressive stress caused by the reaction force normal to the tapered interface. The stresses, both compressive and tensile, placed on the optical element in the high G environment can be very large.Type: ApplicationFiled: June 11, 2007Publication date: December 11, 2008Inventors: Gary H. Johnson, Douglas M. Beard, John A. Thomas, Rene D. Perez
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Publication number: 20080099598Abstract: A guided projectile has a deployment system for deploying a deployable structure, such as a fin, another type of control surface, or an antenna. The deployment system includes a single-piece body that has a hub body and a resilient tab. The resilient tab presses against a stepped surface of a guided projectile body. As the deployable structure is extended, the deployable structure body rotates about a shaft in a central hole or aperture in the hub body. The resilient tab presses against the stepped surface on one side of an edge of the stepped surface during a first (relatively stowed) part of this deployment. At a certain point, as the contact between the tab and the stepped surfaces reaches the edge (the step of the stepped surface), the resilient tab changes position. The change in position of the resilient tab keeps the deployable structure from retracting again.Type: ApplicationFiled: October 26, 2006Publication date: May 1, 2008Inventor: Gary H. Johnson
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Patent number: 6764042Abstract: A tacital base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported for movement between a stowed position and a deployed position.Type: GrantFiled: May 12, 2003Date of Patent: July 20, 2004Assignee: Raytheon CompanyInventors: James L. Moore, Gary H. Johnson, William S. Peterson, Rajesh H. Shah, Richard Dryer
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Publication number: 20040108412Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported for movement between a stowed position and a deployed position.Type: ApplicationFiled: May 12, 2003Publication date: June 10, 2004Inventors: James L. Moore, Gary H. Johnson, William S. Peterson, Rajesh H. Shah, Richard Dryer
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Patent number: 6588700Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots, with a plurality of insert structures fitted into corresponding ones of the fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position.Type: GrantFiled: October 16, 2001Date of Patent: July 8, 2003Assignee: Raytheon CompanyInventors: James L. Moore, Gary H. Johnson, William S. Peterson, Rajesh H. Shah, Richard Dryer, Conlee O. Quortrup
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Publication number: 20030071166Abstract: A tactical base for a guided projectile includes a base structure, and an adaptor structure for securing the base structure to a forward section of the projectile. The base further includes a plurality of fin slots, with a plurality of insert structures fitted into corresponding ones of the fin slots. A plurality of deployable fins are pivotally mounted to the base structure and supported within the insert structures for movement between a stowed position and a deployed position.Type: ApplicationFiled: October 16, 2001Publication date: April 17, 2003Inventors: James L. Moore, Gary H. Johnson, William S. Peterson, Rajesh H. Shah, Richard Dryer, Conlee O. Quortrup
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Publication number: 20020166921Abstract: Accordingly, a shaft assembly for coupling a control fin to a missile includes outer and inner shaft portions which are detachably coupled together, allowing removal of one of the shaft portions while the other shaft portion remains in the missile. In an exemplary embodiment, the inner shaft portion, to which the control fin is coupled, is removable. The shaft assembly includes a pair of preload nuts to adjust the position of the control fin relative to the skin of the missile, the preload nuts being for example engaged on opposite threaded ends of the outer shaft portion.Type: ApplicationFiled: May 11, 2001Publication date: November 14, 2002Inventors: Gary H. Johnson, Christopher P. Owan, William M. Hatalsky, Wayne Lee Sunne
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Patent number: 6474594Abstract: Accordingly, a shaft assembly for coupling a control fin to a missile includes outer and inner shaft portions which are detachably coupled together, allowing removal of one of the shaft portions while the other shaft portion remains in the missile. In an exemplary embodiment, the inner shaft portion, to which the control fin is coupled, is removable. The shaft assembly includes a pair of preload nuts to adjust the position of the control fin relative to the skin of the missile, the preload nuts being for example engaged on opposite threaded ends of the outer shaft portion.Type: GrantFiled: May 11, 2001Date of Patent: November 5, 2002Assignee: Raytheon CompanyInventors: Gary H. Johnson, Christopher P. Owan, William M. Hatalsky, Wayne Lee Sunne