| Patent Number |
Title Of Patent |
Date Issued |
| 7331292 |
Venting system for explosive warheads |
February 19, 2008 |
| An ordnance venting system has one or more adapters that separate the warhead section from other sections of a rocket, or submunition compartments within the warhead itself. The adapters structurally fail at given temperatures and pressures to reduce the danger of explosion from heat |
| 6945175 |
Biological and chemical agent defeat system |
September 20, 2005 |
| The present invention comprises a kinetic energy penetrator warhead that may engage both surface and buried soft and hardened targets. The warhead contains a high-temperature incendiary (HTI) fill capable of destroying chemical and biological agents in such a manner to minimize dispersal |
| 6780260 |
Non-welded shape memory alloy rings produced from roll flattened wire |
August 24, 2004 |
| 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. |
| 6691948 |
High torque rocket nozzle |
February 17, 2004 |
| 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 |
| 6676072 |
Short duration, high-torque rocket nozzle |
January 13, 2004 |
| 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 |
| 6668727 |
Explosively driven impactor grenade |
December 30, 2003 |
| 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 p |
| 6666144 |
Warhead decoupling bearing |
December 23, 2003 |
| 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 seg |
| 6450443 |
High torque 2.75-inch rocket nozzle |
September 17, 2002 |
| 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. |
| 6363855 |
Solid propellant rocket motor thermally initiated venting device |
April 2, 2002 |
| 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 |
| 6338242 |
Vented MK 66 rocket motor tube with a thermoplastic warhead adapter |
January 15, 2002 |
| 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 agains |
| 6230626 |
Flashless MK 66 rocket motor |
May 15, 2001 |
| A flashless rocket propellent has a continuous potassium sulfate rod extending though the length of the propellent component. The flashless rocket propellent is particularly useful in the MK 66 Rocket Motor. |
