Patents by Inventor Andrew B. Facciano
Andrew B. Facciano 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: 7989744Abstract: Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.Type: GrantFiled: February 1, 2008Date of Patent: August 2, 2011Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek, Michael D. Do
-
Patent number: 7980057Abstract: An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.Type: GrantFiled: November 27, 2007Date of Patent: July 19, 2011Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Kelly J. Sinnock, Scott T. Caldwell
-
Patent number: 7819048Abstract: A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.Type: GrantFiled: November 20, 2008Date of Patent: October 26, 2010Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek
-
Publication number: 20100264251Abstract: Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.Type: ApplicationFiled: June 25, 2010Publication date: October 21, 2010Applicant: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek, Craig D. Seasly
-
Patent number: 7800032Abstract: Provided is a detachable aerodynamic missile stabilizing system for a missile flying at low flight speeds. The system includes a housing adapted to couple to couple to the missile. Extending outward from the housing is at least one grid fin. Specifically the grid fin extends from the housing such that it is transverse to a longitudinal axis of the housing and the missile. The grid fin provides a plurality of apertures. The apertures are parallel to the longitudinal axis of the housing and the missile. A coupler is adapted to detachably couple the housing to the missile. A method of use is also provided.Type: GrantFiled: November 30, 2006Date of Patent: September 21, 2010Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Craig D. Seasly, Richard A. McClain, Raymond J. Spall
-
Publication number: 20100219285Abstract: Provided is a detachable aerodynamic missile stabilizing system for a missile flying at low flight speeds. The system includes a housing adapted to couple to couple to the missile. Extending outward from the housing is at least one grid fin. Specifically the grid fin extends from the housing such that it is transverse to a longitudinal axis of the housing and the missile. The grid fin provides a plurality of apertures. The apertures are parallel to the longitudinal axis of the housing and the missile. A coupler is adapted to detachably couple the housing to the missile. A method of use is also provided.Type: ApplicationFiled: November 30, 2006Publication date: September 2, 2010Inventors: Andrew B. Facciano, Robert T. Moore, Craig D. Seasly, Richard A. McClain, Raymond J. Spall
-
Patent number: 7767944Abstract: A vibration controlled housing. The novel housing includes a housing structure and a mechanism for receiving a control signal and in accordance therewith electronically tuning a structural response of the structure. In an illustrative embodiment, the housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.Type: GrantFiled: March 7, 2007Date of Patent: August 3, 2010Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek, Craig D. Seasly
-
Patent number: 7681834Abstract: A missile includes a radome-seeker airframe assembly that has a single-piece composite material forebody. The forebody is made of a high-temperature composite material that can withstand heat with little or no ablation. The forebody has a front part with an ogive shape and an aft part that has a cylindrical shape. The front part acts as a radome for a seeker located within the forebody. Patch antennas are attached to an inside surface of the cylindrical aft part. The aft part acts as a radome for the patch antennas, allowing signals to be sent and received by the patch antennas without a need for cutouts. A single seal may be used to seal the guidance system and seeker within the forebody, allowing the equipment to be hermetically sealed within the forebody.Type: GrantFiled: March 31, 2006Date of Patent: March 23, 2010Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek, Craig D. Seasly
-
Publication number: 20090320589Abstract: Methods and apparatus for non-axisymmetric radome according to various aspects of the present invention include a non-symmetric housing for a forward portion of a projectile. Multiple sensors may be positioned in an off-axis configuration within the non-symmetric housing reducing the possibility of one sensor interfering with the operation of another sensor. The non-symmetric housing may also be configured with a strengthening member suitably adapted to provide additional resistance to bending moments caused by external loading along a surface of the non-symmetric housing.Type: ApplicationFiled: February 27, 2009Publication date: December 31, 2009Inventors: Andrew B. Facciano, Brian J. Gowler, James L. Kinzie, Quenten E. Duden, Blake R. Tennison, Adam P. Cherrill
-
Publication number: 20090194632Abstract: Methods and apparatus for a missile having an external system operate in conjunction with an airframe and a fluid transfer system. The airframe includes an interior surface defining a substantially enclosed internal chamber. The fluid transfer system selectively connects the internal chamber to the external system, for example to provide pressurant or coolant to the external system.Type: ApplicationFiled: February 1, 2008Publication date: August 6, 2009Inventors: ANDREW B. FACCIANO, Robert T. Moore, Gregg J. Hlavacek, Michael D. Do
-
Patent number: 7509903Abstract: A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.Type: GrantFiled: July 27, 2005Date of Patent: March 31, 2009Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek
-
Publication number: 20090071320Abstract: A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.Type: ApplicationFiled: November 20, 2008Publication date: March 19, 2009Inventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek
-
Publication number: 20080290191Abstract: An integral composite rocket motor nozzle. The novel nozzle includes a first layer of a first reinforcement material, a second layer of a second reinforcement material, and a common matrix material surrounding the first and second reinforcement materials such that the reinforcement materials and matrix material form a single integral composite structure. In an illustrative embodiment, the first reinforcement material includes graphite fibers for providing structural support, and the second reinforcement material includes glass or quartz fibers for providing thermal insulation on a first side of the first layer. The nozzle may also include a third layer of a third reinforcement material for providing thermal insulation on a second side of the first layer. In a preferred embodiment, the first layer is shaped to form an integrated dome and nozzle structure.Type: ApplicationFiled: November 27, 2007Publication date: November 27, 2008Inventors: Andrew B. Facciano, Robert T. Moore, Kelly J. Sinnock, Scott T. Caldwell
-
Publication number: 20080217465Abstract: A vibration controlled housing. The novel housing includes a housing structure and a mechanism for receiving a control signal and in accordance therewith electronically tuning a structural response of the structure. In an illustrative embodiment, the housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.Type: ApplicationFiled: March 7, 2007Publication date: September 11, 2008Inventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek, Craig D. Seasly
-
Publication number: 20080163748Abstract: A separable structure includes composite material that is separated or severed by a reactive pyrotechnic material. According to one embodiment, the structure includes a pair of composite laminate structural portions, each including multiple layers of composite material. The portions each extend into an overlap region, within which the composite layers of the two structural portions may be alternately placed, overlapping one another. A reactive material is also placed within this overlap region, for instance being in layers between pairs of the composite material layers. The reactive material may be ignited to cause destruction of the pyrotechnic material, and a matrix or resin material of the composite materials layers in the overlap region. This causes the structure to sever or separate along a line of separation within the overlap region. The separation may occur without need to sever fibers of the composite material.Type: ApplicationFiled: July 27, 2005Publication date: July 10, 2008Inventors: Andrew B. Facciano, Robert T. Moore, Gregg J. Hlavacek
-
Patent number: 7108223Abstract: A missile includes a tail section having a multi-nozzle grid with both fixed nozzlettes, and movable, thrust vector nozzlettes. The movable nozzlettes may be configured in a number of discrete array bars, each containing multiple of the movable nozzlettes. Movement of one or more array bars may be used to vector the thrust of the missile, providing roll, yaw, or spinning of the missile, for example.Type: GrantFiled: November 7, 2002Date of Patent: September 19, 2006Assignee: Raytheon CompanyInventors: Daniel Chasman, Stephen D. Haight, Andrew B. Facciano
-
Patent number: 7082878Abstract: A missile includes a payload assembly that has a pair of nosecones. The nosecones may be optimized for different environments and/or phases of flight, for example, having different shapes, different shell materials, different types of seals, and/or different separation mechanisms. The first (outer) nosecone may have a more streamlined shape, be made of more thermally-protective material, and may meet less stringent sealing requirements, than the second (inner) nosecone. Separation of the outer nosecone from the payload assembly may cause backward movement of a center of pressure of the payload assembly, bringing the center of pressure of the assembly closer to a center of gravity of the assembly. This may make the payload assembly easier to maneuver, for example, reducing or eliminating the need for intervention by an attitude control system, to maintain the payload assembly on a desired course.Type: GrantFiled: November 17, 2003Date of Patent: August 1, 2006Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Robert T. Moore, James E. Parry, John Terry White
-
Patent number: 6548794Abstract: A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable jet vane materials withstand the pressure and thermal loads associated with missile steering during the first few seconds of rocket boost until the missile attains sufficient speed to use conventional external aerodynamic control fins for steering control. Once control passes to the external fins, the jet vanes rapidly and uniformly dissolve in the exhaust stream. The dissolvable jet vane provides a lightweight, reliable means of removing steering jet vanes from the exhaust stream of a solid rocket motor nozzle.Type: GrantFiled: March 13, 2001Date of Patent: April 15, 2003Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Paul Lehner, Wayne N. Anderson
-
Patent number: 6526860Abstract: A launch canister for a missile, including an outer canister shell and a concentric inner liner. The inner liner augments the canister shell with structural load capability and bending inertia to enhance canister stiffness. The inner liner can be constructed from structural load carrying composite materials, and also acts as a thermal and ablative insulator to enable vertical plume venting away from the enveloped missile. A shock and vibration isolation layer can be laminated between the inner liner and canister shell.Type: GrantFiled: June 19, 2001Date of Patent: March 4, 2003Assignee: Raytheon CompanyInventors: Andrew B. Facciano, Craig R. Adams, Christine L. Benzie, Kelvin M. Jordan
-
Publication number: 20020189432Abstract: A launch canister for a missile, including an outer canister shell and a concentric inner liner. The inner liner augments the canister shell with structural load capability and bending inertia to enhance canister stiffness. The inner liner can be constructed from structural load carrying composite materials, and also acts as a thermal and ablative insulator to enable vertical plume venting away from the enveloped missile.Type: ApplicationFiled: June 19, 2001Publication date: December 19, 2002Inventors: Andrew B. Facciano, Craig R. Adams, Christine L. Benzie, Kelvin M. Jordan