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Andrew Bernard Facciano

from Santa Fe, NM
Age ~62
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Also known as:
Andrew B Facciano, Andrew Tr Facciano, Andrew Facciano Separate, Acciaro F Andrew
Phone and address:
219 N El Rancho Rd, Santa Fe, NM 87501
(520) 275-9820
Related to:
Marilyn O O'Donnell, 77Gareth D Facciano, 31Bradley R Diller, 67Joseph J FaccianoGwendolyn Facciano, 31Gareth Facciano, 33Joseph FaccianoRuth Davey, 65Blanca R Facciano, 94
Connected to:
Leonard J Facciani, 67Jason Faccibene, 49Robert Faccidomo, 52Charlotte L Faccio, 65Stephanie Faccio, 35Jeremy J Face, 47Chris Facemire, 32Steve FacemireGeneva M Facemyer, 86Patricia M Facente, 57

Andrew Facciano Phones & Addresses

  • 219 N El Rancho Rd, Santa Fe, NM 87501 (520) 275-9820
  • Redwood City, CA
  • Burbank, CA
  • 11438 N Silver Pheasant Loop, Tucson, AZ 85737 (520) 742-3350
  • Oro Valley, AZ
  • Los Alamos, NM
  • 11438 N Silver Pheasant Loop, Tucson, AZ 85737 (520) 275-9820

Work

Position: Professional/Technical

Education

Degree: Associate degree or higher

Emails

a***[email protected]

Resumes

Resumes

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Andrew Facciano

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Andrew Facciano

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Location:
United States

Publications

Us Patents

Integral Missile Harness-Fairing Assembly

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US Patent:
6343954, Feb 5, 2002
Filed:
Jun 14, 2000
Appl. No.:
09/593204
Inventors:
Andrew B. Facciano - Tucson AZ
Steve E. Taylor - Tucson AZ
Assignee:
Raytheon Company - Lexington MA
International Classification:
H01R 1358
US Classification:
439604, 439606
Abstract:
The present invention relates to an improved electrical interconnection assembly adaptable for creating electrical connections between spaced-apart sections of a high performance missile assembly. Because the electrical connection must extend outside the missile, a plurality of electrical interconnections are integrally formed within a protective housing that is, itself of aerodynamic configuration. The cables may take the form of flat wires, or printed wire assemblies integral with the housing. Pre-stressed foam is formed in the housing to insulate the electrical interconnections. Wire mesh is preferably mounted in the housing between the interconnections and the outside of the housing to protect the interconnections from Electro-magnetic Interference (EMI).

Composite Concentric Launch Canister

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US Patent:
6526860, Mar 4, 2003
Filed:
Jun 19, 2001
Appl. No.:
09/884721
Inventors:
Andrew B. Facciano - Tucson AZ
Craig R. Adams - San Diego CA
Christine L. Benzie - Tucson AZ
Kelvin M. Jordan - Tucson AZ
Assignee:
Raytheon Company - Lexington MA
International Classification:
F41F 3052
US Classification:
89 1801, 89 1816, 89 1819, 89 1804
Abstract:
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.

Dissolvable Thrust Vector Control Vane

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US Patent:
6548794, Apr 15, 2003
Filed:
Mar 13, 2001
Appl. No.:
09/804897
Inventors:
Andrew B. Facciano - Oro Valley AZ
Paul Lehner - Green Valley AZ
Wayne N. Anderson - Tucson AZ
Assignee:
Raytheon Company - Lexington MA
International Classification:
F42B 1000
US Classification:
244 31, 244 325, 244 322, 244 52, 60230, 23926515
Abstract:
A dissolvable jet vane ( ) is a composite structure, having a support frame ( ), a plug leading edge ( ) connected to the forward edge ( ) of the frame ( ), and an insulation layer ( ) on the side walls of the support frame ( ). 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.

Missile With Multiple Nosecones

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US Patent:
7082878, Aug 1, 2006
Filed:
Nov 17, 2003
Appl. No.:
10/715176
Inventors:
Andrew B. Facciano - Oro Valley AZ, US
Robert T. Moore - Tucson AZ, US
James E. Parry - Suhuarita AZ, US
John Terry White - Oro Valley AZ, US
Assignee:
Raytheon Company - Waltham MA
International Classification:
F42B 15/00
US Classification:
102377
Abstract:
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.

Missile Control System And Method

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US Patent:
7108223, Sep 19, 2006
Filed:
Nov 7, 2002
Appl. No.:
10/289651
Inventors:
Daniel Chasman - Tucson AZ, US
Stephen D. Haight - Tucson AZ, US
Andrew B. Facciano - Oro Valley AZ, US
Assignee:
Raytheon Company - Lexington MA
International Classification:
F42B 10/66
F02K 9/80
US Classification:
244 322, 244 31, 244 315, 244 321
Abstract:
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.

Separable Structure Material

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US Patent:
7509903, Mar 31, 2009
Filed:
Jul 27, 2005
Appl. No.:
11/190297
Inventors:
Andrew B. Facciano - Oro Valley AZ, US
Robert T. Moore - Tucson AZ, US
Gregg J. Hlavacek - Tucson AZ, US
Assignee:
Raytheon Company - Waltham MA
International Classification:
B64G 1/64
US Classification:
89 114, 89 3601, 89 3602, 89 3617, 107377, 107378, 428 43, 109 36
Abstract:
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.

Composite Missile Nose Cone

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US Patent:
7681834, Mar 23, 2010
Filed:
Mar 31, 2006
Appl. No.:
11/395794
Inventors:
Andrew B. Facciano - Tucson AZ, US
Robert T. Moore - Tucson AZ, US
Gregg J. Hlavacek - Tucson AZ, US
Craig D. Seasly - Tucson AZ, US
Assignee:
Raytheon Company - Waltham MA
International Classification:
B64C 1/00
US Classification:
244119, 244120, 244121
Abstract:
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.

Piezoelectric Fiber, Active Damped, Composite Electronic Housings

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US Patent:
7767944, Aug 3, 2010
Filed:
Mar 7, 2007
Appl. No.:
11/715034
Inventors:
Andrew B. Facciano - Tucson AZ, US
Robert T. Moore - Tucson AZ, US
Gregg J. Hlavacek - Tucson AZ, US
Craig D. Seasly - Tucson AZ, US
Assignee:
Raytheon Company - Waltham MA
International Classification:
F41G 7/00
F42B 15/10
US Classification:
244 31, 244 315, 102293, 102374
Abstract:
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.
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Andrew Bernard Facciano from Santa Fe, NM, age ~62 Get Report