Kevin R Greenwood

US Patent:

6571715, Jun 3, 2003

Filed:

Mar 11, 2002

Appl. No.:

10/095208

Inventors:

Stephen E. Bennett - Tucson AZ
Chris E. Geswender - Tucson AZ
Kevin R. Greenwood - Tucson AZ

Assignee:

Raytheon Company - Lexington MA

International Classification:

F42B 3930

US Classification:

102439, 102374, 244 327

Abstract:

A projectile ( ) with extensible fins ( ) is designed to be lightweight by removing material unnecessary to structural strength and filling the resulting voids with a non-metallic filler material ( ). Although particularly suited where the extensible fins ( ) are mounted behind the obturator ( ) and that are therefore subjected to turbulent, destructive shock waves when the projectile is accelerated down the gun barrel, the method and apparatus can be used elsewhere as well. The filler material ( ) may be high temperature grease, an epoxy, a silicone or other similar materials. The filler material ( ) may be designed to fall away as soon as the projectile ( ) exits the gun barrel, or it may be permanently adhered to the material of the projectile. The filler may be surrounded by a frangible boot ( â) to protect the filler during storage, shipment and loading into the gun.

US Patent:

7185847, Mar 6, 2007

Filed:

May 13, 2004

Appl. No.:

10/845700

Inventors:

Mark L. Bouchard - Tucson AZ, US
Purna Gogineni - Tucson AZ, US
Rudolph A. Eisentraut - Tucson AZ, US
Juan A. Perez - Tucson AZ, US
Kevin Greenwood - Tucson AZ, US

Assignee:

Raytheon Company - Waltham MA

International Classification:

B64C 3/40

US Classification:

244 46, 244 328

Abstract:

A winged vehicle includes an elongated fuselage, and a wing mechanism affixed to the fuselage. The wing mechanism has a wing-support-body track affixed to and extending lengthwise along the fuselage, a translating wing-support body engaged to and translatable along the wing-support-body track, and exactly two deployable cantilevered wings. Each deployable cantilevered wing has a wing pivot mounted to the translating wing-support body so that the deployable cantilevered wing is pivotable about the translating wing-support body. The two deployable cantilevered wings are each pivotable between a stowed position and a deployed position. An actuation mechanism is operable to controllably move the translating wing-support body along the wing-support-body track and to controllably move the two deployable cantilevered wings between the stowed position and the deployed position.

US Patent:

7997205, Aug 16, 2011

Filed:

May 8, 2009

Appl. No.:

12/463260

Inventors:

Kevin R. Greenwood - Tucson AZ, US
James D. Streeter - Oro Valley AZ, US
Jeremy C. Danforth - Tucson AZ, US
Timothy A. Yoder - Sahuarita AZ, US

Assignee:

Raytheon Company - Waltham MA

International Classification:

F42B 15/01

US Classification:

102490, 244 33, 102501

Abstract:

A projectile may include a base drag reduction fairing preform adapted to be plastically deformed into a base drag reduction fairing after the projectile is launched from a gun barrel.

US Patent:

8312813, Nov 20, 2012

Filed:

Jul 30, 2010

Appl. No.:

12/847722

Inventors:

Brian K. McDermott - Woodinville WA, US
Kevin R. Greenwood - Tucson AZ, US
James D. Streeter - Tucson AZ, US

Assignee:

Raytheon Company - Waltham MA
General Dynamics Ordnance and Tactical Systems - Bothell WA

International Classification:

F42B 10/44

US Classification:

102490, 244 327, 244 324, 102473

Abstract:

A deployable fairing is driven off of high-pressure gun gases to reduce aerodynamic drag and extend the range of the artillery shell. An artillery shell is provided with a fabric fairing and a piston attached thereto in a rear section of the shell in a stowed state and a chamber. During launch high-pressure gun gasses are captured and stored in the chamber. Once the shell clears the end of the artillery tube, the pressure aft of the shell drops from the high pressure inside the tube to atmospheric pressure outside the tube. The high pressure gun gasses stored in the chamber act over the top surface of the piston to drive the piston aft against the much lower pressure behind the projectile to deploy the fabric fairing attached thereto to reduce the base area of the projectile creating or extending the boat-tail of the shell, hence reduce aerodynamic drag. The aft driven piston engages a locking mechanism that locks the piston in a deployed position.

US Patent:

20110024550, Feb 3, 2011

Filed:

Aug 2, 2010

Appl. No.:

12/848956

Inventors:

Brian K. McDermott - Woodinville WA, US
Kevin R. Greenwood - Tucson AZ, US
James D. Streeter - Tucson AZ, US

International Classification:

F42B 10/00

US Classification:

244 327

Abstract:

In accordance with one aspect of the invention, a system, method and apparatus for a boat-tail device is described herein. A body section for a projectile having a deployable portion is provided. Gun gases may pass through an orifice at an aft end of a piston and pressurize a volume in a plenum within the body section. Depressurization at muzzle exit may allow the gas pressurized in the plenum to push the piston aft deploying the deployable portion. A stopping and locking mechanism such as a complementarily tapered piston and opening may engage at the end of the stroke of the piston to stop and lock the piston at a predetermined location. A releasable protective cover may be used to protect the structure of the deployable element and other elements from gun gases and launch loads.

US Patent:

20120312092, Dec 13, 2012

Filed:

Aug 31, 2011

Appl. No.:

13/222508

Inventors:

Shawn A. Miller - Oro Valley AZ, US
Mark A. Scott - Corona AZ, US
Douglas J. Eliason - Saint David AZ, US
Kevin R. Greenwood - Tucson AZ, US

Assignee:

Raytheon Company - Waltham MA

International Classification:

G01L 5/14

US Classification:

73167

Abstract:

Some embodiments pertain to a projectile that includes a casing and a sensor that is wrapped around the casing. As an example, the sensor may be wrapped around a longitudinal axis of the casing. The sensor obtains environmental data that the projectile is exposed to when the projectile is inside a cannon tube. As an example, the sensor may obtain pressure data that the projectile is exposed to during launch of the projectile when the projectile is inside the cannon tube. The sensor may include a plurality of segments that at least partially surround the casing. In some embodiments, the segments may be separated from the casing due to pressure that the projectile is exposed to during launch.