Search

Gordon A Dressler

from Manhattan Beach, CA
Age ~74
Get Report
Also known as:
Albert Dressler Gordon
Phone and address:
91 Village Cir, Manhattan Beach, CA 90266
(310) 545-9496
Related to:
Bryan J Kummer, 43Rosemary Herda, 69Valerie Wunch, 68Jennifer Kummer, 46
Connected to:
Brandon L Dressler, 38Brent Dressler, 43Carrie A Dressler, 49Chad A Dressler, 53Gene H Dressler, 100Haley J Dressler, 33Hope B Dressler, 33Jay A Dressler, 82Jeffrey K Dressler, 60Jeremy S Dressler, 44

Gordon Dressler Phones & Addresses

  • 91 Village Cir, Manhattan Beach, CA 90266 (310) 545-9496
  • Manhattan Bch, CA
  • Fernandina Beach, FL
  • 1491 Stonewood Ct, San Pedro, CA 90732

Work

Position: Professional/Technical

Education

Degree: High school graduate or higher

Emails

g***[email protected]

Industries

Aviation & Aerospace

Resumes

Resumes

Gordon Dressler Photo 1

Independent Aviation & Aerospace Professional

View page
Location:
Greater Los Angeles Area
Industry:
Aviation & Aerospace

Business Records

Name / Title
Company / Classification
Phones & Addresses
Gordon Dressler
Vice-President
California Traditional Music Society Inc
Civic/Social Association · Entertainer/Entertainment Group
16953 Ventura Blvd, Van Nuys, CA 91316
(818) 817-7756
Gordon A. Dressler
President, Treasurer, Secretary, Director
Florida Home Investments of Jacksonville, Inc
121 N 6 St, Fernandina, FL 32034
Gordon A. Dressler
Dressler Land Investments, Ltd
121 N 6 St, Fernandina, FL 32034

Publications

Us Patents

Pintle Injector Rocket With Expansion-Deflection Nozzle

View page
US Patent:
6591603, Jul 15, 2003
Filed:
Mar 8, 2001
Appl. No.:
09/802002
Inventors:
Gordon A. Dressler - Manhattan Beach CA
Thomas J. Mueller - Long Beach CA
Scott J. Rotenberger - Redondo Beach CA
Assignee:
TRW Inc. - Redondo Beach CA
International Classification:
B64C 1502
US Classification:
60258, 60239, 60259, 244 121
Abstract:
The present invention provides a rocket engine ( ) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine ( ) includes a combustion chamber ( ) having an injector end ( ) and a nozzle end ( ). A propellant injector ( ) is in fluid communication between a propellant line and an inside periphery of the combustion chamber injector end ( ). A nozzle throat ( ) is formed at the nozzle end ( ) of the combustion chamber ( ). A nozzle exit cone ( ) extends outwardly from the nozzle throat ( ). A plug support ( ) is coupled between a nozzle plug ( ) and the propellant injector ( ). The nozzle plug ( ) aerodynamically self-compensates for changes in ambient backpressure at the nozzle exit cone ( ) such that the nozzle thrust coefficient is maximized for any ambient backpressure.

Axisymmetric, Throttleable Non-Gimballed Rocket Engine

View page
US Patent:
6964154, Nov 15, 2005
Filed:
Mar 11, 2003
Appl. No.:
10/390253
Inventors:
Robert L. Sackheim - Madison AL, US
John J. Hutt - Decatur AL, US
William E. Anderson - West Lafayette IN, US
Gordon A. Dressler - Manhattan Beach CA, US
Assignee:
The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC
International Classification:
F02K003/00
F02K007/00
F02K009/00
F02K009/74
F02K009/76
US Classification:
60224, 60257, 60258, 60770
Abstract:
A rocket engine assembly is provided for a vertically launched rocket vehicle. A rocket engine housing of the assembly includes two or more combustion chambers each including an outlet end defining a sonic throat area. A propellant supply for the combustion chambers includes a throttling injector, associated with each of the combustion chambers and located opposite to sonic throat area, which injects the propellant into the associated combustion chamber. A modulator, which may form part of the injector, and which is controlled by a controller, modulates the flow rate of the propellant to the combustion chambers so that the chambers provide a vectorable net thrust. An expansion nozzle or body located downstream of the throat area provides expansion of the combustion gases produced by the combustion chambers so as to increase the net thrust.

System And Method For An Ambient Atmosphere Ion Thruster

View page
US Patent:
7270300, Sep 18, 2007
Filed:
Oct 30, 2003
Appl. No.:
10/698847
Inventors:
Gordon A. Dressler - Manhattan Beach CA, US
Assignee:
Northrop Grumman Corporation - Los Angeles CA
International Classification:
B64G 1/40
US Classification:
2441711, 60202
Abstract:
A system and a method for an ambient atmosphere ion thruster having a pair of permeable electrical members for accelerating ambient atmosphere ions which enter the thruster due to a craft's relative velocity. Neutral ambient atmosphere molecules in the intake mass flux may also be ionized and subsequently accelerated by the pair of permeable electrical members. Acceleration of any entering mass comprises an exhaust mass flux which then produces a net thrust. Such net thrust is then vectored by configuring and orienting the thrusters for imparting axial and lateral accelerations as well as pitch, yaw, and roll controls. The present invention is operational in proximity to any celestial body having a sensible atmosphere during a portion of the free trajectory or during orbiting at altitude. Useful net thrust is thereby produced without need for carrying reaction mass onboard a spacecraft.

System And Method For An Ambient Atmosphere Ion Thruster

View page
US Patent:
7306189, Dec 11, 2007
Filed:
Dec 11, 2006
Appl. No.:
11/609268
Inventors:
Gordon A. Dressler - Manhattan Beach CA, US
Assignee:
Northrop Grumman Space & Mission Systems Corp. - Redondo Beach CA
International Classification:
B64G 1/40
US Classification:
2441711, 60202
Abstract:
A system and a method for an ambient atmosphere ion thruster having a pair of permeable electrical members for accelerating ambient atmosphere ions which enter the thruster due to a craft's relative velocity. Neutral ambient atmosphere molecules in the intake mass flux may also be ionized and subsequently accelerated by the pair of permeable electrical members. Acceleration of any entering mass comprises an exhaust mass flux which then produces a net thrust. Such net thrust is then vectored by configuring and orienting the thrusters for imparting axial and lateral accelerations as well as pitch, yaw, and roll controls. The present invention is operational in proximity to any celestial body having a sensible atmosphere during a portion of the free trajectory or during orbiting at altitude. Useful net thrust is thereby produced without need for carrying reaction mass onboard a spacecraft.

Non-Propellant Fluid Cooled Space Craft Rocket Engine

View page
US Patent:
60529873, Apr 25, 2000
Filed:
Nov 14, 1997
Appl. No.:
8/970915
Inventors:
Gordon A. Dressler - Manhattan Beach CA
Assignee:
TRW Inc. - Redondo Beach CA
International Classification:
F02K 942
US Classification:
60260
Abstract:
A space craft's rocket engines are cooled by a recirculating cooling system containing a non-propellant coolant fluid, such as water and/or ethylene glycol. With that recirculating cooling system to maintain the rocket engine combustion chamber at a lower temperature, spacecraft rocket engines may be constructed less expensively and can operate with greater safety by employing the more common metals in their construction. The cooling system also provides an easy means to warm and/or vaporize a propellant.

Liquid Tripropellant Rocket Engine Coaxial Injector

View page
US Patent:
61859273, Feb 13, 2001
Filed:
Dec 22, 1997
Appl. No.:
8/995563
Inventors:
Constant J. Chrones - San Gabriel CA
Gordon A. Dressler - Manhattan Beach CA
Assignee:
TRW Inc. - Redondo Beach CA
International Classification:
F02K 952
US Classification:
60258
Abstract:
A tripropellant coaxial pintle injector for a rocket engine which enables smooth transitioning between two types of propellants that are adapted to be alternatively mixed with a third type of propellant in a combustion chamber of a rocket engine. The tripropellant coaxial injector includes a pintle for expelling a first propellant into a combustion chamber in a generally radial direction and two or more concentric metering sleeves which define orifices for expelling two or more different propellants into the combustion chamber in an axial direction thus, such a configuration allows for alternative mixing of two propellants with a third propellant in the combustion chamber of a rocket engine.
Control profile
Gordon A Dressler from Manhattan Beach, CA, age ~74 Get Report