CLIFFORD D HEATON
Broker in Ware, MA
License number
Massachusetts 140231
Issued Date
Feb 15, 1996
Expiration Date
Oct 23, 2002
Type
Broker
Address
Address
Ware, MA 01082
Professional information
Split-Cycle Aircraft Engine
US Patent:
7513224, Apr 7, 2009
Filed:
Sep 11, 2006
Appl. No.:
11/518828
Inventors:
Clifford D. Heaton - Ware MA, US
Assignee:
The Scuderi Group, LLC - West Springfield MA
International Classification:
F01B 7/12
US Classification:
123 51R, 60 3962
Abstract:
A split-cycle aircraft engine includes a crankshaft rotatable about a crankshaft axis. A power piston is slidably received within a power cylinder and is operatively connected to the crankshaft such that the power piston reciprocates through an expansion stroke and an exhaust stroke during a single rotation of the crankshaft. A compression piston is slidably received within a compression cylinder and is operatively connected to the crankshaft such that the compression piston reciprocates through an intake stroke and a compression stroke during a single rotation of the crankshaft. A gas crossover passage operatively interconnects the compression cylinder and the power cylinder. An air reservoir is operatively connected to the gas crossover passage by a reservoir passage. The air reservoir is selectively operable to receive and deliver compressed air. The engine is mounted to an aircraft and the air reservoir is disposed within the aircraft.
Split-Cycle Aircraft Engine
US Patent:
2009014, Jun 11, 2009
Filed:
Feb 13, 2009
Appl. No.:
12/370644
Inventors:
Clifford D. Heaton - Ware MA, US
Assignee:
The Scuderi Group, LLC - West Springfield MA
International Classification:
F01B 29/04, B64C 3/34
US Classification:
60712, 701102, 2441231, 244119
Abstract:
A split-cycle aircraft engine includes a crankshaft rotatable about a crankshaft axis. A power piston is slidably received within a power cylinder and is operatively connected to the crankshaft such that the power piston reciprocates through an expansion stroke and an exhaust stroke during a single rotation of the crankshaft. A compression piston is slidably received within a compression cylinder and is operatively connected to the crankshaft such that the compression piston reciprocates through an intake stroke and a compression stroke during a single rotation of the crankshaft. A gas crossover passage operatively interconnects the compression cylinder and the power cylinder. An air reservoir is operatively connected to the gas crossover passage by a reservoir passage. The air reservoir is selectively operable to receive and deliver compressed air. The engine is mounted to an aircraft and the air reservoir is disposed within the aircraft.
Split-Cycle Aircraft Engine
US Patent:
2009025, Oct 15, 2009
Filed:
Feb 5, 2009
Appl. No.:
12/366048
Inventors:
Clifford D. Heaton - Ware MA, US
Assignee:
THE SCUDERI GROUP, LLC - West Springfield MA
International Classification:
F02B 75/22, F02B 25/00
US Classification:
123 542, 123 71 R
Abstract:
A split-cycle aircraft engine includes a crankshaft rotatable about a crankshaft axis. A power piston is slidably received within a power cylinder and is operatively connected to the crankshaft such that the power piston reciprocates through an expansion stroke and an exhaust stroke during a single rotation of the crankshaft. A compression piston is slidably received within a compression cylinder and is operatively connected to the crankshaft such that the compression piston reciprocates through an intake stroke and a compression stroke during a single rotation of the crankshaft. A gas crossover passage operatively interconnects the compression cylinder and the power cylinder. An air reservoir is operatively connected to the gas crossover passage by a reservoir passage. The air reservoir is selectively operable to receive and deliver compressed air. The engine is mounted to an aircraft and the air reservoir is disposed within the aircraft.
Airplane Wing
US Patent:
2012007, Mar 29, 2012
Filed:
Sep 22, 2011
Appl. No.:
13/240293
Inventors:
Clifford D. Heaton - Ware MA, US
International Classification:
B64C 39/12, B64C 3/48, B23P 11/00, B64C 3/50
US Classification:
244213, 244 45 R, 244201, 29428
Abstract:
An airplane wing configuration includes a first wing positioned above and forward of a second wing on an airplane fuselage. The first wing is operable to direct airflow over an upper surface of the second wing, whereby the first and second wings are capable of generating greater lift than a sum of their individual lifts. The first wing may include an adjustable wing flap that redirects airflow over the upper surface of the second wing, and the second wing may include a rotatable portion that pivots to vary the angle of attack of the second wing independent of the first wing.