Professional Records
License Records
Alfred Alan Gates
Address:
16 W Cv Rd, Moodus, CT 06469
License #:
A2485306
Category:
Airmen
Alfred Gates Phones & Addresses
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16 Cove Rd, Moodus, CT 06469 (860) 873-3271 (860) 873-8883
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1 Cove Rd, Moodus, CT 06469
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124 Cattle Landing Rd, Meredith, NH 03253 (603) 279-4910
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East Wallingford, VT
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Mount Holly, VT
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New Britain, CT
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Colchester, CT
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East Haddam, CT
Resumes
Resumes
Alfred Gates
View pageLocation:
United States
Publications
Us Patents
Underwater Propulsion Device
View pageUS Patent:
56876718, Nov 18, 1997
Filed:
Apr 17, 1996
Appl. No.:
8/636999
Inventors:
Alfred A. Gates - Moodus CT
Assignee:
The United States of America as represented by the Secretary of the Navy - Washington DC
International Classification:
B63C 1146
US Classification:
114315
Abstract:
Disclosed is a water jet propulsion device for divers and diver equipment. forward pressurized air chamber and a rearward water containing chamber are positioned inside a cylindrical housing and are separated by a flexible membrane which is adjacent to a conical deformation plate. On opening a valve located in communication with the water containing housing, pressurized air in the air chamber forces water from the water chamber through a nozzle to the exterior of the housing until the flexible membrane expands to bear against the conical rearward deformation plate. The device is thus moved in a forward direction along with its attached swimmer or equipment.
Rotorcraft Control System For Rotorcraft With Two Or More Rotor Systems
View pageUS Patent:
20150037149, Feb 5, 2015
Filed:
Aug 1, 2013
Appl. No.:
13/956783
Inventors:
Alfred Alan Gates - Moodus CT, US
International Classification:
B64C 27/615
US Classification:
416 1, 416 23
Abstract:
A multirotor rotorcraft control system for effectuating flight control. The multirotor rotorcraft has at least two or more rotor assemblies. The control system preferably includes at least one flap for each rotor blade and at least one actuator for each rotor assembly. The rotor assemblies and the flap(s) and actuator(s) for each assembly are used for flight control. This invention does not require a complex fixed pitch control system or a high frequency servo control system. This invention can control blade angle of attack during autorotation.