Patents by Inventor Donald C. Howe
Donald C. Howe has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11208969Abstract: An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.Type: GrantFiled: November 25, 2015Date of Patent: December 28, 2021Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Patent number: 10731556Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, 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 overall engine performance.Type: GrantFiled: May 25, 2016Date of Patent: August 4, 2020Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Patent number: 9714084Abstract: Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when the 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 there between 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.Type: GrantFiled: November 8, 2013Date of Patent: July 25, 2017Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Donald C. Howe
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Patent number: 9482155Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, 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 overall engine performance.Type: GrantFiled: September 27, 2012Date of Patent: November 1, 2016Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Publication number: 20160265433Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, 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 overall engine performance.Type: ApplicationFiled: May 25, 2016Publication date: September 15, 2016Inventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Patent number: 9353704Abstract: An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.Type: GrantFiled: July 3, 2012Date of Patent: May 31, 2016Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Patent number: 9334801Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, 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 overall engine performance.Type: GrantFiled: August 2, 2012Date of Patent: May 10, 2016Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
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Publication number: 20160076448Abstract: An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.Type: ApplicationFiled: November 25, 2015Publication date: March 17, 2016Inventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Patent number: 9121369Abstract: A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.Type: GrantFiled: July 3, 2012Date of Patent: September 1, 2015Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Publication number: 20140306058Abstract: Method and arrangement for reducing the effects of a some 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 there between 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.Type: ApplicationFiled: November 8, 2013Publication date: October 16, 2014Applicant: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Donald C. Howe
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Patent number: 8789789Abstract: Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when the 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 there between 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.Type: GrantFiled: May 23, 2011Date of Patent: July 29, 2014Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Donald C. Howe, Robert R. Wolz, Jimmy L. Hancock, Jr.
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Publication number: 20130112776Abstract: A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.Type: ApplicationFiled: July 3, 2012Publication date: May 9, 2013Applicant: GULFSTREAM AEROSPACE CORPORATIONInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Publication number: 20130048098Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, 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 overall engine performance.Type: ApplicationFiled: August 2, 2012Publication date: February 28, 2013Applicant: GULFSTREAM AEROSPACE CORPORATIONInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
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Publication number: 20130042922Abstract: An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.Type: ApplicationFiled: July 3, 2012Publication date: February 21, 2013Applicant: GULFSTREAM AEROSPACE CORPORATIONInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe
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Patent number: 8333076Abstract: 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.Type: GrantFiled: December 15, 2006Date of Patent: December 18, 2012Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Donald C. Howe, Preston A. Henne
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Patent number: 8327645Abstract: 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.Type: GrantFiled: December 27, 2011Date of Patent: December 11, 2012Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
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Patent number: 8286434Abstract: 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.Type: GrantFiled: December 27, 2011Date of Patent: October 16, 2012Assignee: Gulfstream Aerospace CorporationInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
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Publication number: 20120199212Abstract: 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.Type: ApplicationFiled: December 27, 2011Publication date: August 9, 2012Applicant: GULFSTREAM AEROSPACE CORPORATIONInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
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Publication number: 20120091286Abstract: 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.Type: ApplicationFiled: December 27, 2011Publication date: April 19, 2012Applicant: GULFSTREAM AEROSPACE CORPORATIONInventors: Preston A. Henne, Timothy R. Conners, Donald C. Howe
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Patent number: RE47304Abstract: A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.Type: GrantFiled: August 31, 2017Date of Patent: March 19, 2019Assignee: Gulfstream Aerospace CorporationInventors: Timothy R. Conners, Preston A. Henne, Donald C. Howe