Steven S Kim

US Patent:

6338242, Jan 15, 2002

Filed:

Jul 26, 2000

Appl. No.:

09/626070

Inventors:

Steven S. Kim - Crofton MD
John R. Luense - Accokeek MD

Assignee:

The United States of America as represented by the Secretary of the Navy - Washington DC

International Classification:

F02K 900

US Classification:

60204, 60223, 60254, 102377, 102481, 220 894

Abstract:

An ordnance venting system has an ordnance device having a casing with a vent opening, a dome plug fitted into the formed vent opening and an adapter fitted over the dome plug on the outside of the casing. The adapter connects sufficiently to the casing to retain the dome plug against the formed vent opening for given pressures. The adapter melts at high temperatures and releases the dome plug to reduce the danger of explosion from heat induced over-pressurization.

US Patent:

6363855, Apr 2, 2002

Filed:

Oct 27, 2000

Appl. No.:

09/697244

Inventors:

Steven S. Kim - Crofton MD
Chris M. Nugent - Bel Alton MD

Assignee:

The United States of America as represented by the Secretary of the Navy - Washington DC

International Classification:

F41A 900

US Classification:

102481, 102378, 60223, 60253, 60254

Abstract:

An ordnance venting system has a thermally initiated rapid deflagrating composition that detonates a high energy material. The high energy material is configured as a shaped charge and surrounds the ordnance housing of a rocket motor. During cook-off of the munition, the high energy material detonates, rupturing the structural integrity of the ordnance housing sufficiently to release pressure therefrom.

US Patent:

6450443, Sep 17, 2002

Filed:

Aug 17, 2000

Appl. No.:

09/639789

Inventors:

Steven S. Kim - Crofton MD

Assignee:

The United States of America as represented by the Secretary of the Navy - Washington DC

International Classification:

F42B 1026

US Classification:

244 323, 244 31, 23926515

Abstract:

A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible or retractable vanes inside of the nozzle. The vanes are removed from the rocket propelling thrust at rocket exit from the tube.

US Patent:

6666144, Dec 23, 2003

Filed:

Nov 13, 2002

Appl. No.:

10/292949

Inventors:

Steven S. Kim - Crofton MD
Eric J. Hawley - Alexandria VA

Assignee:

The United States of America as represented by the Secretary of the Navy - Washington DC

International Classification:

F42B 1536

US Classification:

102374, 102293, 244 323

Abstract:

The invention comprises an improved precision rocket motor and warhead system by increasing the spin rate of the rocket motor. The system comprises an outer housing segment attached to the end of a rocket motor tube and an annular sleeve placed within the end of the outer housing segment so that the end of the sleeve is aligned with the end of the segment. At least two annular bearings are placed around the outer surface of the sleeve. Normally the annular bearings will be made of a plastic type material that can be âstretchedâ around the outside of the sleeve prior to placing it within the outer housing segment. The inner surface of the sleeve will include a warhead attachment mechanism to secure the warhead to the inner surface. Finally, the invention includes a locking mechanism that locks the sleeve in place within the outer housing segment while attaching the warhead to the sleeve and unlocks to allow the sleeve to rotate independently of the rocket motor.

US Patent:

6668727, Dec 30, 2003

Filed:

Jun 18, 2003

Appl. No.:

10/463936

Inventors:

Steven S. Kim - Crofton MD
Christopher G. Melkonian - Alexandria VA
Michael P. Dunnigan - Bowie MD
Carl Gotzmer, Jr. - Accokeek MD
Joe Mayersak - Asburn VA

Assignee:

The United States of America as represented by the Secretary of the Navy - Washington DC

International Classification:

F42B 1210

US Classification:

102482, 102307, 102383, 102476, 102480, 102487, 86 50

Abstract:

An explosively driven impactor grenade includes a grenade body having a substantially spherical shape and a hollow central portion, the grenade body including a plurality of recesses formed on an external surface thereof with each recess including an opening into the hollow central portion of the grenade body, the grenade body including an opening on the exterior surface that connects with the hollow central portion; a fuze disposed in the hollow central portion of the grenade body; a fuze cap for closing the opening on the exterior surface that connects with the hollow central portion; and a plurality of explosively driven impactors respectively disposed in the plurality of recesses formed on the external surface of the grenade body, the explosively driven impactors being connected to the fuze through the recess openings into the hollow central portion of the grenade body.

US Patent:

6676072, Jan 13, 2004

Filed:

Nov 13, 2002

Appl. No.:

10/292948

Inventors:

Steven S. Kim - Crofton MD 21114
Eric Hawley - Alexandria VA 22304

International Classification:

F42B 1000

US Classification:

244 323, 244 322

Abstract:

A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned torque ring inside of the nozzle that is anchored with erodible tabs. The tabs erode as the rocket exits the launcher. With the erosion of the tabs, the torque ring is free to rotationally move, which eliminates any torque imparted onto the rocket while retaining the torque ring with the rocket. This increases the reliability of rocket precision.

US Patent:

6691948, Feb 17, 2004

Filed:

Apr 10, 2003

Appl. No.:

10/413182

Inventors:

Steven S. Kim - Crofton MD
Brian E. Krzewinski - Laurel MD

Assignee:

The United States of America as represented by the Secretary of the Navy - Washington DC

International Classification:

F42B 1000

US Classification:

244 323, 244 322

Abstract:

A high torque nozzle system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible vanes inside of the nozzle. The vanes erode as the rocket exits the launcher. The high torque nozzle system has a first section of a rocket nozzle body, a second section of the rocket nozzle body and a torque ring that contains erodible vanes. The torque ring is fitted into a groove formed by the first and second sections of the rocket nozzle body, which are threaded together.

US Patent:

6780260, Aug 24, 2004

Filed:

Dec 10, 2002

Appl. No.:

10/318673

Inventors:

David Goldstein - Potomac MD
Steven S. Kim - Crofton MD

Assignee:

The United Sates of America as represented by the Secretary of the Navy - Washington DC

International Classification:

C22F 110

US Classification:

148563, 148676

Abstract:

A method for producing a non-welded shape memory alloy ring, such as Nitinol, includes a wire segment. The alloy ring may be used in a venting mechanism for rocket motors or as a coupling device, such as for fitting piping.

Author:

Steven H. Kim

ISBN #:

0195060172

Author:

Steven H. Kim

ISBN #:

0195060164

Author:

Steven H. Kim

ISBN #:

0195072413

Author:

Steven H. Kim

ISBN #:

0262560666

Author:

Steven H. Kim

ISBN #:

0595213820

Author:

Steven H. Kim

ISBN #:

0442010060

Author:

Steven H. Kim

ISBN #:

0792330463