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Alfred Alan Gates
Address:
16 W Cv Rd, Moodus, CT 06469
Licenses:
License #: A2485306
Category: Airmen
Category: Airmen
Alfred A Gates, 642328 Vt Route 103 N, East Wallingford, VT 05742
Alfred Gates Phones & Addresses
16 Cove Rd, Moodus, CT 06469 860-8733271 860-8738883
1 Cove Rd, Moodus, CT 06469
124 Cattle Landing Rd, Meredith, NH 03253 603-2794910
East Wallingford, VT
Mount Holly, VT
New Britain, CT
Colchester, CT
East Haddam, CT
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Alfred Gates
Location:
United States
Publications & IP owners
Us Patents
Underwater Propulsion Device
US Patent:
5687671, 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
US Patent:
2015003, 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.
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