Patents by Inventor James D. Chase
James D. Chase 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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Publication number: 20220073203Abstract: Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following xo) a region just ahead of the lip x1) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.Type: ApplicationFiled: August 30, 2010Publication date: March 10, 2022Inventors: James D. Chase, German Andres Garzon
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Patent number: 10724472Abstract: The present disclosure relates to a method of operating a supersonic aircraft comprising the steps of: at takeoff, positioning a slidable plug-cowl assembly disposed within a nozzle and behind an engine in an aft position such that a front surface of a plug is aft of an exit plane of a cowl, to thereby reduce noise during takeoff and maintain engine efficiency; and after takeoff, re-positioning the slidable plug-cowl assembly to a forward position such that the front surface of the plug is not disposed aft the exit plane of the cowl.Type: GrantFiled: June 16, 2017Date of Patent: July 28, 2020Assignee: AERION INTELLECTUAL PROPERTY MANAGEMENT CORPORATIONInventor: James D. Chase
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Patent number: 9233755Abstract: Improved supersonic laminar flow wing structure, on a supersonic aircraft, having strake extending forwardly of the wing inboard extent, and reversed fillet at strake junction with the wing leading edge. Plain and split flap structures may also be provided at each laminar flow wing.Type: GrantFiled: May 18, 2011Date of Patent: January 12, 2016Assignee: Aerion CorporationInventors: James D. Chase, Michael Henderson, Sturdza Peter
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Patent number: 8991768Abstract: Improved supersonic laminar flow wing structure, on a supersonic aircraft, having strake extending forwardly of the wing inboard extent, and reversed fillet at strake junction with the wing leading edge.Type: GrantFiled: May 18, 2011Date of Patent: March 31, 2015Assignee: Aerion CorporationInventors: James D. Chase, Michael Henderson, Sturdza Peter
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Patent number: 8882028Abstract: In combination, an aircraft and a rotatively combined electrical power/generator and hydraulic motor/pump configured to provide either hydraulic power from electrical power, or electrical power from hydraulic power, installed in said aircraft.Type: GrantFiled: August 9, 2010Date of Patent: November 11, 2014Assignee: Aerion CorporationInventor: James D. Chase
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Patent number: 8448893Abstract: Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.Type: GrantFiled: January 25, 2011Date of Patent: May 28, 2013Assignee: Aerion CorporationInventors: Richard R. Tracy, James D. Chase
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Patent number: 8371124Abstract: In a jet engine having a plug nozzle and a plug extending rearwardly from the nozzle exit, the improvement comprising a plug having successive cross sections spaced apart rearwardly of the nozzle exit, the cross sections transitioning from circular or near circular at the exit plane defined at the nozzle exit, to progressively non-circular, rearwardly.Type: GrantFiled: April 3, 2009Date of Patent: February 12, 2013Assignee: Aerion CorporationInventors: James D. Chase, German Andres Garzon
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Patent number: 8317128Abstract: On an aircraft designed for maximum efficient cruise speed in the range from about Mach 0.8 to about Mach 1.2, and having fuselage and wings with: (a) less than about 25 degrees of leading edge sweep, in combination with airfoil thickness to chord ratios between about 3% and about 8%, as an average along the wing semi-span outboard from the zone of substantial fuselage influence, and (b) wing leading edge sweep between about 20 degrees and about 35 degrees, in combination with airfoil thickness to chord ratios equal to or below about 3% as an average along the semi-span outboard from the zone of substantial fuselage influence to the wing tip.Type: GrantFiled: February 16, 2011Date of Patent: November 27, 2012Assignee: Aerion CorporationInventors: Richard R. Tracy, James D. Chase
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Patent number: 8272594Abstract: A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c).Type: GrantFiled: October 26, 2009Date of Patent: September 25, 2012Assignee: Aerion CorporationInventors: Richard R. Tracy, Peter Sturdza, James D. Chase
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Publication number: 20120043430Abstract: On an aircraft designed for maximum efficient cruise speed in the range from about Mach 0.8 to about Mach 1.2, and having fuselage and wings with: (a) less than about 25 degrees of leading edge sweep, in combination with airfoil thickness to chord ratios between about 3% and about 8%, as an average along the wing semi-span outboard from the zone of substantial fuselage influence, and (b) wing leading edge sweep between about 20 degrees and about 35 degrees, in combination with airfoil thickness to chord ratios equal to or below about 3% as an average along the semi-span outboard from the zone of substantial fuselage influence to the wing tip.Type: ApplicationFiled: February 16, 2011Publication date: February 23, 2012Inventors: Richard R. Tracy, James D. Chase
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Publication number: 20120043429Abstract: Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.Type: ApplicationFiled: January 25, 2011Publication date: February 23, 2012Inventors: Richard R. Tracy, James D. Chase
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Patent number: 7967241Abstract: Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following xo) a region just ahead of the lip xl) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.Type: GrantFiled: August 30, 2010Date of Patent: June 28, 2011Assignee: Aerion CorporationInventors: James D. Chase, German Andres Garzon
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Patent number: 7946535Abstract: An improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following: a strake extending forwardly of the wing inboard extent, a raked wing tip, a reversed fillet at the strake or fuselage junction, an inboard leading edge flap extending over less than about 15% of the inboard wing panel span, and a hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.Type: GrantFiled: October 16, 2007Date of Patent: May 24, 2011Assignee: Aerion CorporationInventors: James D. Chase, Michael Henderson, Peter Sturdza
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Publication number: 20110095137Abstract: A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c).Type: ApplicationFiled: October 26, 2009Publication date: April 28, 2011Inventors: Richard R. Tracy, Peter Sturdza, James D. Chase
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Publication number: 20110067393Abstract: In combination, an aircraft and a rotatively combined electrical power/generator and hydraulic motor/pump configured to provide either hydraulic power from electrical power, or electrical power from hydraulic power, installed in said aircraft.Type: ApplicationFiled: August 9, 2010Publication date: March 24, 2011Inventor: James D. Chase
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Publication number: 20110062290Abstract: Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following xo) a region just ahead of the lip x1) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.Type: ApplicationFiled: August 30, 2010Publication date: March 17, 2011Inventors: James D. Chase, German Andres Garzon
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Patent number: 7837142Abstract: Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following x0) a region just ahead of the lip x1) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.Type: GrantFiled: October 9, 2007Date of Patent: November 23, 2010Assignee: Aerion CorporationInventors: James D. Chase, German Andres Garzon
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Publication number: 20100139284Abstract: In a jet engine having a plug nozzle and a plug extending rearwardly from the nozzle exit, the improvement comprising a plug having successive cross sections spaced apart rearwardly of the nozzle exit, the cross sections transitioning from circular or near circular at the exit plane defined at the nozzle exit, to progressively non-circular, rearwardly.Type: ApplicationFiled: April 3, 2009Publication date: June 10, 2010Inventors: James D. Chase, German Andres Garzon
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Publication number: 20090206206Abstract: Improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following: strake extending forwardly of the wing inboard extent, raked wing tip, reversed fillet at strake or fuselage junction, inboard leading edge flap extending over less than about 15% of the inboard wing panel span, hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.Type: ApplicationFiled: October 16, 2007Publication date: August 20, 2009Inventors: James D. Chase, Michael Henderson, Peter Sturdza
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Publication number: 20090014597Abstract: Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following xo) a region just ahead of the lip x1) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.Type: ApplicationFiled: October 9, 2007Publication date: January 15, 2009Inventors: James D. Chase, German Andres Garzon