Daniel C Dombrowski

US Patent:

6651438, Nov 25, 2003

Filed:

Aug 29, 2001

Appl. No.:

09/941397

Inventors:

David K. McGrath - Elkton MD
Daniel C. Dombrowski - Elkton MD

Assignee:

Alliant Techsystems Inc. - Edina MN

International Classification:

F02K 980

US Classification:

60771, 23926519

Abstract:

A rocket nozzle assembly is provided for operatively coupling to a rocket motor. The assembly includes a nozzle insert structure having a converging-diverging passageway with a throat region. First and second thrust control cylinders are parallel to each other and rotatable about respective axes transverse to the passageway central axis. The first and second thrust control cylinders intersect the throat region and include respective grooves. A thrust control cylinder-rotating subassembly is operatively associated with the first and second thrust control cylinders to rotate the cylinders about their respective axes and move the grooves relative to the throat region. Movement of the grooves changes the effective cross-sectional throat area of the converging/diverging passageway at the throat region for controlling the thrust when the rocket nozzle assembly is operatively engaged with an operating rocket motor.

US Patent:

7568348, Aug 4, 2009

Filed:

Nov 28, 2005

Appl. No.:

11/287297

Inventors:

Andrew C. McAllister - Manassas VA, US
Daniel C. Dombrowski - Marshall VA, US

Assignee:

Aerojet-General Corporation - Sacramento CA

International Classification:

F02K 1/00

US Classification:

60771, 60770

Abstract:

A nozzle assembly for thrust or thrust vector control of a rocket or ramjet, comprising an elongated nozzle housing and a pair of vane members mounted for pivotal movement within a central portion of the nozzle housing. The vane members extend vertically or transversely between the upper and lower portions of the nozzle housing near the forward portion thereof, and extend longitudinally in the nozzle housing from the forward end portion thereof to a point near the rear end portion thereof. The vane members are pivotable about axes disposed between the forward and rear ends thereof, and are movable between an open position wherein they are in substantially parallel relation and a closed position wherein their forward ends are in engagement with each other and their rear ends are in engagement with the adjacent inner surface of the nozzle housing. An operating mechanism is operatively connected to the vane members to move them simultaneously or individually between the open and closed positions for thrust control or thrust vector control.

US Patent:

56009461, Feb 11, 1997

Filed:

Jun 6, 1995

Appl. No.:

8/469759

Inventors:

Daniel C. Dombrowski - Elkton MD
Thomas J. Frey - Elkton MD
Andrew G. Nevrincean - Elkton MD
Clyde E. Carr - Lincoln University PA

Assignee:

Thiokol Corporation - Ogden UT

International Classification:

F02K 900

US Classification:

60253

Abstract:

A solid propellant dual pulse rocket motor has a pressure vessel containing two pulse grains separated by a barrier insulator. An igniter assembly disposed at a fore end of the pressure vessel selectively ignites a first pulse grain from a central channel within the grain. The igniter assembly also ignites a second pulse grain by ejecting hot combustion gases onto the fore end of the grain. Using such an ignition arrangement, a dual pulse rocket motor may be constructed using standard off-the-shelf ignition components.

US Patent:

56759665, Oct 14, 1997

Filed:

Sep 7, 1995

Appl. No.:

8/525336

Inventors:

Daniel C. Dombrowski - Elkton MD
Thomas J. Frey - Wilmington DE
Andrew G. Nevrincean - Oxford PA

Assignee:

Thiokol Corporation - Ogden UT

International Classification:

F02K 928

US Classification:

60204

Abstract:

A solid propellant dual pulse rocket motor has a pressure vessel containing two pulse grains separated by a barrier insulator. An igniter assembly disposed at a fore end of the pressure vessel selectively ignites a first pulse grain from a central channel within the grain. The igniter assembly also ignites a second pulse grain by ejecting hot combustion gases onto the fore end of the grain. Using such an ignition arrangement, a dual pulse rocket motor may be constructed using standard off-the-shelf ignition components.