Donald C Howe

US Patent:

6698684, Mar 2, 2004

Filed:

Mar 22, 2002

Appl. No.:

10/104403

Inventors:

Preston A. Henne - Hilton Head IS. SC
Donald C. Howe - Savannah GA
Robert R. Wolz - Savannah GA

Assignee:

Gulfstream Aerospace Corporation - Savannah GA

International Classification:

B64C 3000

US Classification:

244 1N, 244119, 181211

Abstract:

An aircraft includes a spike projecting forward from the leading end of the fuselage and/or rearward from the trailing end of the fuselage. The spike can include a single section or two or more sections of varying cross-sectional area. Transition regions between sections of varying cross-sectional area are located and shaped to reduce coalescence of shock waves created thereby during supersonic flight. The spike can be collapsible and can be retracted into the fuselage. The spike can have a cross-sectional shape wherein the nose thereof lies on a line formed by the intersection of the bottom of the spike with a plane tangent to the bottom of the spike. A spike thus shaped causes an asymmetric pressure distribution during supersonic flight, wherein the ground-directed pressure contour is of lesser magnitude than the pressure contour propagating in other directions.

US Patent:

7634941, Dec 22, 2009

Filed:

Jan 18, 2008

Appl. No.:

12/010042

Inventors:

Preston A. Henne - Hilton Head Island SC, US
Donald C. Howe - Savannah GA, US
Robert R. Wolz - Savannah GA, US

Assignee:

Gulfstream Aerospace Corporation - Savannah GA

International Classification:

G01M 9/00

US Classification:

73147

Abstract:

A method for modeling the acoustic signature produced by an aircraft of interest flying at a particular supersonic Mach number/altitude operating point of interest. The method includes operating a sub-scale aircraft that is a sub-scale version of the aircraft of interest at a supersonic Mach number and at an altitude that are respectively different from the Mach number and the altitude associated with the operating point of interest. The Mach number and altitude at which the sub-scale aircraft is operated is selected such that peak overpressure generated by the sub-scale aircraft and time to rise to peak overpressure are the same as peak overpressure and time to rise to peak overpressure caused by operating the aircraft of interest at the operating point of interest.

US Patent:

8083171, Dec 27, 2011

Filed:

May 26, 2007

Appl. No.:

11/754276

Inventors:

Preston A. Henne - Hilton Head Island SC, US
Donald C. Howe - Savannah GA, US
Robert R. Wolz - Savannah GA, US

Assignee:

Gulfstream Aerospace Corporation - Savannah GA

International Classification:

B64C 23/04

US Classification:

244 1N, 244 13, 244130

Abstract:

Method for configuring and operating an aircraft for minimizing sonic boom effects at ground level during supersonic flight of the aircraft. The method includes configuring an aircraft and flying the aircraft at supersonic speed so that in the supersonic flight, a lower profile of the aircraft is presented and generally groundwardly directed; and generating multiple different magnitude pressure disturbances below the aircraft, and radiating therebelow, and controlling the different magnitude pressure disturbances generated below the aircraft so that differentials thereamong are sufficiently minimized that ground level sonic boom effects are minimized during the supersonic flight.

US Patent:

8286434, Oct 16, 2012

Filed:

Dec 27, 2011

Appl. No.:

13/338010

Inventors:

Preston A. Henne - Hilton Head SC, US
Timothy R. Conners - Statesboro GA, US
Donald C. Howe - Savannah GA, US

Assignee:

Gulfstream Aerospace Corporation - Savannah GA

International Classification:

F02C 7/04

US Classification:

60767, 60768, 60204, 137 151, 244 53 B

Abstract:

A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

US Patent:

8327645, Dec 11, 2012

Filed:

Dec 27, 2011

Appl. No.:

13/338005

Inventors:

Preston A. Henne - Hilton Head SC, US
Timothy R. Conners - Statesboro GA, US
Donald C. Howe - Savannah GA, US

Assignee:

Gulfstream Aerospace Corporation - Savannah GA

International Classification:

F02C 7/04

US Classification:

60767, 60768, 60204, 137 151, 244 53 B

Abstract:

A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

US Patent:

8333076, Dec 18, 2012

Filed:

Dec 15, 2006

Appl. No.:

11/639339

Inventors:

Timothy R. Conners - Statesboro GA, US
Donald C. Howe - Savannah GA, US
Preston A. Henne - Hilton Head SC, US

Assignee:

Gulfstream Aerospace Corporation - Savannah GA

International Classification:

F02C 7/04

US Classification:

60767, 137 151, 244 53 B, 60204, 60768

Abstract:

A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

US Patent:

20050224630, Oct 13, 2005

Filed:

Mar 1, 2004

Appl. No.:

10/708404

Inventors:

Preston Henne - Hilton Head Island SC, US
Donald Howe - Savannah GA, US
Robert Wolz - Savannah GA, US
Jimmy Hancock - Savannah GA, US

Assignee:

GULFSTREAM AEROSPACE CORPORATION - Savannah GA

International Classification:

B64C001/00

US Classification:

24400100N, 244119000

Abstract:

Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.

US Patent:

20070145192, Jun 28, 2007

Filed:

Jan 30, 2006

Appl. No.:

11/307280

Inventors:

Preston Henne - Hilton Head Island SC, US
Donald Howe - Savannah GA, US
Robert Wolz - Savannah GA, US
Jimmy Hancock - Savannah GA, US

Assignee:

GULFSTREAM AEROSPACE CORPORATION - Savannah GA

International Classification:

B64D 17/00

US Classification:

244139000

Abstract:

Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle with a first spike extending from the nose thereof substantially in the direction of normal flight of the aerospace vehicle, the first spike having a second section aft of a first section that is aft of a leading end portion, the first and second sections having a second transition region therebetween and each of the sections having different cross-sectional areas, the leading end portion of the first spike tapering toward a predetermined cross-section with a first transition region between the predetermined cross-section and the first section. The first transition region is configured so as to reduce the coalescence of shock waves produced by the first spike during normal supersonic flight of the aerospace vehicle. A spike may also be included that extends from the tail of the aerospace vehicle to reduce the coalescence of shock waves produced by the spike during normal supersonic flight of the aerospace vehicle.