Patents by Inventor Robert Henry Wille
Robert Henry Wille 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: 6375122Abstract: A reinforced elastomer panel (100) has a first rigid member (104) with an edge (116) attached to a first end of an elastomer panel (114). The first rigid member (104) has a removable plate (106) that provides access to a cavity (108). Attached to the first rigid member (104) is a reinforcing member (102) that extends through the elastomer panel (114). A second ridge member (118) has an edge attached to a second end of the elastomer panel (114).Type: GrantFiled: August 17, 1998Date of Patent: April 23, 2002Assignee: The Boeing CompanyInventors: Dean Emory Cameron, Paul Francis Geders, Michael Watson Geiger, Dennis Allan Roberts, Robert Henry Wille
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Patent number: 6349903Abstract: A control surface (152) for an aircraft has a reinforced elastomer surface (154) on a surface of the aircraft and has a perimeter (156) attached to the aircraft. An actuation mechanism (160) moves the reinforced elastomer surface (154) from a first position, substantially conforming to a moldline of the aircraft, to a second position, protruding from the moldline of the aircraft.Type: GrantFiled: February 15, 2001Date of Patent: February 26, 2002Assignee: The Boeing CompanyInventors: John Harold Caton, Michael James Hobey, John David Groeneveld, Jack Howard Jacobs, Robert Henry Wille, Lawrence Otto. Brase, Jr.
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Patent number: 6276026Abstract: A hinge (20) an an aircraft (24) has a first plurality of rigid tangs (22) attached to the aircraft (24). A second plurality of rigid tangs (26) are attached to a door (28) and a flexible cover (34) has a cover tang (44). A hinge pin (32) runs inside the first plurality of rigid tangs (22), the second plurality of rigid tangs (26) and the cover tang (44).Type: GrantFiled: March 10, 1997Date of Patent: August 21, 2001Assignee: The Boeing CompanyInventor: Robert Henry Wille
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Patent number: 6260567Abstract: A mission adaptive inlet (42) for an aircraft (40) has a rigid lip panel (56) pivotally attached to an inlet (42) of the aircraft (40). An actuation mechanism is coupled to the rigid lip panel (56) and causes the rigid lip panel (56) to pivot from a first position to a second position. A reinforced elastomer system (48) is connected the rigid lip panel and the inlet (42).Type: GrantFiled: March 28, 2000Date of Patent: July 17, 2001Assignee: The Boeing CompanyInventors: Cynthia Ann Gruensfelder, Robert Henry Wille
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Publication number: 20010006207Abstract: A control surface (152) for an aircraft has a reinforced elastomer surface (154) on a surface of the aircraft and has a perimeter (156) attached to the aircraft. An actuation mechanism (160) moves the reinforced elastomer surface (154) from a first position, substantially conforming to a moldline of the aircraft, to a second position, protruding from the moldline of the aircraft.Type: ApplicationFiled: February 15, 2001Publication date: July 5, 2001Inventors: John Harold Caton, Michael James Hobey, John David Groeneveld, Jack Howard Jacobs, Robert Henry Wille, Lawrence Otto Brase
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Patent number: 6231006Abstract: A mission adaptive inlet (42) for an aircraft (40) has a rigid lip panel (56) pivotally attached to an inlet (42) of the aircraft (40). An actuation mechanism is coupled to the rigid lip panel (56) and causes the rigid lip panel (56) to pivot from a first position to a second position. A reinforced elastomer system (48) is connected the rigid lip panel and the inlet (42).Type: GrantFiled: April 14, 2000Date of Patent: May 15, 2001Assignee: McDonnell Douglas CorporationInventors: Cynthia Ann Gruensfelder, Robert Henry Wille
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Patent number: 6209824Abstract: A control surface (152) for an aircraft has a reinforced elastomer surface (154) on a surface of the aircraft and has a perimeter (156) attached to the aircraft. An actuation mechanism (160) moves the reinforced elastomer surface (154) from a first position, substantially conforming to a moldline of the aircraft, to a second position, protruding from the moldline of the aircraft.Type: GrantFiled: March 2, 2000Date of Patent: April 3, 2001Assignee: The Boeing CompanyInventors: John Harold Caton, Michael James Hobey, John David Groeneveld, Jack Howard Jacobs, Robert Henry Wille, Lawrence Otto Brase, Jr.
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Patent number: 6092764Abstract: An interface seal (52) for an aircraft (50) has a first rigid structural beam (60) attached to a first portion of the aircraft (50). A second rigid structural beam (64) is attached to a second portion of the aircraft (50). An elastomer skin (62) is connected to the first rigid structural beam (60) and attached to the second rigid structural beam (64).Type: GrantFiled: July 21, 1997Date of Patent: July 25, 2000Assignee: McDonnell Douglas CorporationInventors: Paul Francis Geders, Robert Henry Wille
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Patent number: 6089505Abstract: A mission adaptive inlet (42) for an aircraft (40) has a rigid lip panel (56) pivotally attached to an inlet (42) of the aircraft (40). An actuation mechanism is coupled to the rigid lip panel (56) and causes the rigid lip panel (56) to pivot from a first position to a second position. A reinforced elastomer system (48) is connected the rigid lip panel and the inlet (42).Type: GrantFiled: July 22, 1997Date of Patent: July 18, 2000Assignee: McDonnell Douglas CorporationInventors: Cynthia Ann Gruensfelder, Robert Henry Wille
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Patent number: 6068215Abstract: An aircraft (50) with a variable cargo bay (52) includes a frame (60) having an inner surface and an outer skin (64) covering the frame (60). The frame (60) has a pair of faceted fairings (54, 56) coupled to the frame (60) and a door assembly (58) between the pair of faceted fairings (54, 56). The door assembly (58) has an inner surface connected to a linkage mechanism (66). The linkage mechanism (66) couples the inner surface of the frame (60) and the inner surface of the door assembly (58). A conformable surface (70) is connected between the skin (64) of the frame (60) and the door assembly (58).Type: GrantFiled: December 21, 1995Date of Patent: May 30, 2000Assignee: McDonnall DouglasInventors: Cynthia Ann Gruensfelder, Robert Henry Wille, James Richard Ellis, Joseph Brice Diller
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Patent number: 6027074Abstract: A reinforced elastomer panel (100) has a first rigid member (104) with an edge (116) attached to a first end of an elastomer panel (114). The first rigid member (104) has a removable plate (106) that provides access to a cavity (108). Attached to the first rigid member (104) is a reinforcing member (102) that extends through the elastomer panel (114). A second rigid member (118) has an edge attached to a second end of the elastomer panel (114).Type: GrantFiled: February 27, 1997Date of Patent: February 22, 2000Assignee: McDonnell DouglasInventors: Dean Emory Cameron, Paul Francis Geders, Michael Watson Geiger, Dennis Allan Roberts, Robert Henry Wille
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Patent number: 5988567Abstract: A conformable weapons platform (52) has a cavity (60) in a skin of an aircraft. A weapon launching system (62) is contained in the cavity (60). A pair of elastomer doors (56, 58) are attached to a perimeter of the cavity.Type: GrantFiled: June 30, 1997Date of Patent: November 23, 1999Assignee: McDonnell DouglasInventor: Robert Henry Wille
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Patent number: 5979828Abstract: An apparatus (30) for eliminating gaps (20) in a door of an airplane has an elastaueric bladder (32) bonding along an edge (24) of a door gap (20). The elastomeric bladder (32) includes a port providing for access to an interior cavity (34). A pneumatic actuator is coupled to the port.Type: GrantFiled: April 30, 1997Date of Patent: November 9, 1999Assignee: McDonnell DouglasInventors: Cynthia Ann Gruensfelder, Micael Watson Geiger, Jack Howard Jacobs, Robert Henry Wille
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Patent number: 5975463Abstract: An aircraft (50) with a variable cargo bay (52) includes a frame (60). A pair of fairing assemblies (54, 56) is coupled to the frame (60). Each of the pair of fairing assemblies (54, 56) has a ramp (100) connected to the frame (60) by a front sliding pivoting mechanism (106). A door assembly (58) is between the pair of fairing assemblies (54, 56) and is coupled to the frame (60).Type: GrantFiled: December 21, 1995Date of Patent: November 2, 1999Assignee: McDonnell DouglasInventors: Cynthia Ann Gruensfelder, Robert Henry Wille
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Patent number: 5947422Abstract: A tail (14) for an aircraft (10) has a center member (20) pivotally attached to the aircraft (10). A leading edge flap (22) extends along a length of the center member (20). An elastomeric skin (30) is connected between an exterior surface (26) of the center member (20) and an adjacent exterior surface (28) of the leading edge flap (22).Type: GrantFiled: April 29, 1997Date of Patent: September 7, 1999Assignee: McDonnell DouglasInventor: Robert Henry Wille
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Patent number: 5941480Abstract: A hinge line system (52) for an aircraft has a structural block (22) attached to a first edge of a hinge line. The structural block (22) has a flange (28) attached to a first end of an elastic sheet (32). A second structural block (24) is attached to a second edge of the hinge line. The second structural block (24) has a second flange (30) attached to a second end of the elastic sheet (32).Type: GrantFiled: May 8, 1997Date of Patent: August 24, 1999Assignee: McDonnell DouglasInventor: Robert Henry Wille
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Patent number: 5927651Abstract: An expandable fuel cell (72) for an aircraft (70) has a flexible structure (126) having a perimeter (124) attached to an airframe of the aircraft (70). The flexible structure (126) has an empty position, in which the flexible structure (126) approximately conforms to a moldline (76) of the aircraft (70), and a full position, in which the flexible structure (126) forms a smooth curvilinear protrusion from the moldline (76) of the aircraft (70). A fuel bladder (152) is positioned between the flexible structure (126) and the airframe.Type: GrantFiled: May 15, 1997Date of Patent: July 27, 1999Assignee: McDonnell DouglasInventors: Paul Francis Geders, John David Groeneveld, Robert Henry Wille
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Patent number: 5918834Abstract: A retractable sensor system (12) for an aircraft has a sensor (16) coupled to an actuation mechanism (18). The sensor (16) moves from a retracted position to an expanded position. A reinforced elastomer section (14) in an exterior surface (48) of the aircraft covers the sensor (16) and the actuation mechanism (18). The reinforced elastomer section (14) has an interior surface and an exterior surface and the sensor (16) has a portion adjacent to the interior surface. The reinforced elastomer section (14) has a flush position and an expanded position.Type: GrantFiled: February 27, 1997Date of Patent: July 6, 1999Assignee: McDonnell DouglasInventors: William Arthur Sommer, Robert Henry Wille
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Patent number: 5913494Abstract: A blade seal (20) for an aircraft has a mounting structure (22). A composite blade (26) is attached to the mounting structure (22). The composite blade (26) has a plurality of holes (28). An elastomer substance (30) is used to fill the plurality of holes (28).Type: GrantFiled: July 25, 1997Date of Patent: June 22, 1999Assignee: McDonnell DouglasInventors: Thomas Edward Burbridge, Harvey John Tomko, Robert Henry Wille
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Patent number: 5896191Abstract: A sensor system for a reinforced elastomer panel (100) has an optical source (104) emitting an optical signal. An optical strain sensor (102) is embedded in an elastomer sheet (40) of the reinforced elastomer panel (100) and receives the optical signal. A strain processing system (108) is optical coupled to the optically strain sensor (102).Type: GrantFiled: May 13, 1997Date of Patent: April 20, 1999Assignee: McDonnell DouglasInventors: Theodor Harry Beier, John Martin Haake, Robert Henry Wille, Jack Howard Jacobs