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Hermann L Miskelly

from New Market, AL
Age ~66
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Also known as:
Hermann Karen Miskelly, Herman L Miskelly, Hermann L Miskelley, Hermann L Dawson, Janis Miskelly
Phone and address:
3234 Hurricane Rd, New Market, AL 35761
(256) 379-2075
Related to:
Natasha MiskellyNina R Miskelly, 41Karen A Dawson, 66James Putt, 42Margie R SherwoodMichelle P Dawson, 35Jason P Pitruzzello, 48Anne Paelian, 100Lucile C Dawson, 99Michael A Izzo, 28Bo DavisMichael A Izzo, 60Cody L Izzo, 34Miskelly PaelianJanis L Miskelly, 71Luanne D Kirkland, 69Lori A Dawson, 68
Connected to:
Branden D Miskell, 37Erica L Miskelly, 47Hanbit Miskell, 41James B Miskelly, 80Jennifer A Miskell, 41John L Miskelly, 60Julie Miskelley, 40Larry P Miskell, 78Molly M Miskelly, 50Rachel D Miskell, 46

Hermann Miskelly Phones & Addresses

  • 3234 Hurricane Rd, New Market, AL 35761 (256) 379-2075
  • 7509 Amanda Cir, Huntsville, AL 35802 (256) 881-1956
  • Gurley, AL
  • Tampa, FL
  • 6997 Meaghan Ln, Warrenton, VA 20187 (540) 341-3024
  • Gainesville, VA
  • Manassas, VA
  • Madison, AL

Resumes

Resumes

Hermann Miskelly Photo 1

Vice President Of Quality

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Location:
7509 Amanda Cir southwest, Huntsville, AL 35802
Industry:
Chemicals
Work:
Matheson ... the Gas Professionals (Tm)
Vice President of Quality
Global Productivity Solutions Feb 2002 - Dec 2008
Senior Consultant
Atlantic Research Corporation 1996 - 2003
Engineering Manager
Thiokol Corporation 1978 - 1996
Engineering Group Leader
Education:
The University of Alabama In Huntsville 1993 - 1996
Masters, Management, Engineering Southeastern Institute of Technology 1991 - 1992
Masters, Design The University of Alabama In Huntsville 1976 - 1981
Bachelor of Science In Engineering, Bachelors, Mechanical Engineering
Skills:
Six Sigma
Continuous Improvement
Lean Manufacturing
Quality Management
Operational Excellence
Manufacturing
Process Improvement
Cross Functional Team Leadership
Quality System
Process Engineering
Operations Management
Engineering Management
Root Cause Analysis
Iso 9000
Iso
Project Management
Leadership
Engineering
Supply Chain Management
Business Process Improvement
Design of Experiments
Supply Chain
Spc
Dmaic
Strategy
Kanban
Manufacturing Operations Management
Process Simulation
Kaizen
Fmea
Smed
5S
Toyota Production System
Problem Solving
Statistics
Metric Development
Quality Assurance
Value Stream Mapping
Tqm
Team Leadership
Business
Industrial Engineering
Automotive
R&D
Design For Six Sigma
Management of Change
Testing
Product Design
Software Documentation
Business Metric Development
Interests:
Mathematics
Politics
Live Music
Philosophy and Fiction
Motorcycles
Reading
Cosmology
Movies
Buddhism
Hermann Miskelly Photo 2

Hermann Miskelly

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Publications

Us Patents

Destroying Airborne Biological And/Or Chemical Agents With Solid Propellants

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US Patent:
20030233956, Dec 25, 2003
Filed:
Mar 4, 2003
Appl. No.:
10/377773
Inventors:
Hermann Miskelly - Warrenton VA, US
Assignee:
Atlantic Research Corporation
International Classification:
C06B047/00
F42C001/00
US Classification:
102/293000
Abstract:
High temperature incendiary (HTI) devices and methods destroy biological and/or chemical agents. Preferably, such HTI devices include dual modal propellant compositions having low burn rate propellant particles dispersed in a matrix of a high burn rate propellant. Most preferably, the HTI device includes a casing which contains the dual modal propellant and a nozzle through which combustion gases generated by the ignited high burn rate propellant may be discharged thereby entraining ignited particles of the low burn rate propellant. In use, therefore, the high burn rate propellant will be ignited using a conventional igniter thereby generating combustion gases which are expelled through the nozzle of the HTI device. As the ignition face of the propellant composition regresses, the low burn rate particles will similarly become ignited. Since the low burn rate particles burn at a lesser rate as compared to the high burn rate propellant in which such particles are dispersed, the ignited particles per se will be expelled through the nozzle and will therefore continue to burn in the ambient environment. Such continued burning of the particles will thereby be sufficient to destroy chemical and/or biological agents that may be present in the ambient environment.

Solid Propellant Formulations And Methods And Devices Employing The Same For The Destruction Of Airborne Biological And/Or Chemical Agents

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US Patent:
20040025990, Feb 12, 2004
Filed:
Mar 4, 2003
Appl. No.:
10/377775
Inventors:
Hermann Miskelly - Warrenton VA, US
Assignee:
Atlantic Research Corporation
International Classification:
C06B047/00
US Classification:
149/001000
Abstract:
High temperature incendiary (HTI) devices and methods destroy biological and/or chemical agents. Preferably, such HTI devices include dual modal propellant compositions having low burn rate propellant particles dispersed in a matrix of a high burn rate propellant. Most preferably, the HTI device includes a casing which contains the dual modal propellant and a nozzle through which combustion gases generated by the ignited high burn rate propellant may be discharged thereby entraining ignited particles of the low burn rate propellant. In use, therefore, the high burn rate propellant will be ignited using a conventional igniter thereby generating combustion gases which are expelled through the nozzle of the HTI device. As the ignition face of the propellant composition regresses, the low burn rate particles will similarly become ignited. Since the low burn rate particles burn at a lesser rate as compared to the high burn rate propellant in which such particles are dispersed, the ignited particles per se will be expelled through the nozzle and will therefore continue to burn in the ambient environment. Such continued burning of the particles will thereby be sufficient to destroy chemical and/or biological agents that may be present in the ambient environment.

Solid Propellant Formulations And Methods And Devices Employing The Same For The Destruction Of Airborne Biological And/Or Chemical Agents

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US Patent:
20040112487, Jun 17, 2004
Filed:
May 15, 2002
Appl. No.:
10/145540
Inventors:
Hermann Miskelly - Warrenton VA, US
International Classification:
C06B047/00
C06B045/10
US Classification:
149/019400
Abstract:
High temperature incendiary (HTI) devices and methods destroy biological and/or chemical agents. Preferably, such HTI devices include dual modal propellant compositions having low burn rate propellant particles dispersed in a matrix of a high burn rate propellant. Most preferably, the HTI device includes a casing which contains the dual modal propellant and a nozzle through which combustion gases generated by the ignited high burn rate propellant may be discharged thereby entraining ignited particles of the low burn rate propellant. In use, therefore, the high burn rate propellant will be ignited using a conventional igniter thereby generating combustion gases which are expelled through the nozzle of the HTI device. As the ignition face of the propellant composition regresses, the low burn rate particles will similarly become ignited. Since the low burn rate particles burn at a lesser rate as compared to the high burn rate propellant in which such particles are dispersed, the ignited particles per se will be expelled through the nozzle and will therefore continue to burn in the ambient environment. Such continued burning of the particles will thereby be sufficient to destroy chemical and/or biological agents that may be present in the ambient environment.

Safety Mechanism For Rendering A Rocket Motor Non-Propulsive

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US Patent:
50441540, Sep 3, 1991
Filed:
Nov 27, 1989
Appl. No.:
7/441830
Inventors:
R. Hill English - Huntsville AL
Hermann L. Miskelly - Huntsville AL
Assignee:
Thiokol Corporation - Ogden UT
International Classification:
F02K 900
US Classification:
60223
Abstract:
A rocket motor having case segments which are attached together. A retaining member extends circumferentially thereabout to maintain attachment of the segments together. The retaining member is characterized by sensitivity to a predetermined temperature greater than ambient temperature and less than the ignition temperature of propellant material in the rocket motor to lose strength whereby the retaining member is released and the rocket motor may safely be rendered non-propulsive during a hazard such as a fuel fire or slow cook-off.

Pyrotechnically Driven Nozzle Restrictor

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US Patent:
54351286, Jul 25, 1995
Filed:
Nov 15, 1993
Appl. No.:
8/152865
Inventors:
Hermann L. Miskelly - Huntsville AL
R. Lance Alldredge - Arab AL
Thomas F. Owens - Huntsville AL
Assignee:
Thiokol Corporation - Ogden UT
International Classification:
F02K 130
US Classification:
60271
Abstract:
A pyrotechnically driven device for restricting the area of the nozzle throat in a solid propellant rocket motor is disclosed. In one embodiment, the device includes a piston support mounted to the rocket motor in the exit cone. A restrictor is attached to a piston which is supported by the piston support. The restrictor is movable from a retracted position outside the nozzle throat to a restricting position within the throat upon actuation of the device. The piston and attached restrictor are driven by a pyrotechnic driving means that is actuatable separately from the solid propellant of the rocket motor. A locking means locks the restrictor in its restricting position.

Distributed Erosion Region Rocket Motor Nozzle

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US Patent:
55796354, Dec 3, 1996
Filed:
Nov 18, 1994
Appl. No.:
8/342146
Inventors:
Hermann L. Miskelly - Huntsville AL
Mark C. Horton - Huntsville AL
Sheryl H. Hepler - Huntsville AL
Assignee:
Thiokol Corporation - Ogden UT
International Classification:
F02K 118
US Classification:
60242
Abstract:
A rocket motor nozzle has a nozzle core that defines a nozzle passage through which combustion products travel during flight. The erosive forces created by the combustion products are longitudinally distributed over the nozzle core so that the nozzle's smallest area remains substantially constant in spite of the erosion. An inner surface of the nozzle core defines the nozzle passage. The inner surface includes an entry region which defines a nozzle entry, an exit region which defines an exit, and an elongate erosion region which defines an erosion passage between the entry and exit. The erosion region length is greater than the average smallest passage diameter, thereby allowing the location of the erosion focus along the erosion region to vary over time as a result of erosion of the erosion region. The nozzle core is formed of a fibrous composite material which is selected according to the type of propellant used and which includes fibers oriented transverse to the erosion passage to resist erosion.

Supercavitating Underwater Projectile

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US Patent:
6405653, Jun 18, 2002
Filed:
Oct 26, 2000
Appl. No.:
09/696688
Inventors:
Hermann L Miskelly - Warrenton VA
Assignee:
Atlantic Research Corporation - Gainesville VA
International Classification:
F42B 1520
US Classification:
102374, 102399, 102490, 89 1807, 89 1809
Abstract:
A supercavitating underwater projectile adapted to be fired from a gun or the like, comprising a front end or nose portion and a rear end portion. An auxiliary rocket motor is disposed within the rear end portion of the projectile for providing additional thrust after the projectile has been fired. Vents are disposed within the projectile and are in communication with the rocket motor and the exterior of the projectile for venting some of the combustion gases from the rocket motor to the exterior of the projectile near the nose portion thereof to increase the size of the cavitation bubble formed as the projectile travels through the water and thereby reduce hydrodynamic drag on the projectile.
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Hermann L Miskelly from New Market, AL, age ~66 Get Report