Patents by Inventor Frank O. Chandler
Frank O. Chandler 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: 9759161Abstract: A rocket engine having a co-axial, bidirectional flow arrangement is described herein. The rocket engine receives fuel and an oxidizer into the rocket engine in a first direction, whereby a portion of the fuel is combusted in a pre-burner. The flow direction of the partially combusted fuel/oxidizer mixture is reversed, whereby the mixture is introduced into a combustion chamber. The fuel and oxidizer are combusted in the combustion chamber. The combustion products exit a throat and an expansion plenum in a direction similar to the first direction, whereby the combustion products exit a nozzle of the rocket engine, providing thrust.Type: GrantFiled: March 28, 2014Date of Patent: September 12, 2017Assignee: The Boeing CompanyInventors: James S. Herzberg, Robert J. Budica, Frank O. Chandler
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Patent number: 9493228Abstract: A system and methods for high heat transfer rate reusable thermal protection are presented. A porous skin comprises an exposed exterior surface and a non-exposed surface, and a coolant reservoir comprises perforations coupled to the non-exposed surface, and valves. The valves regulate a flow of coolant from the coolant reservoir to the porous skin in response to a temperature of the porous skin.Type: GrantFiled: November 28, 2012Date of Patent: November 15, 2016Assignee: The Boeing CompanyInventors: James S. Herzberg, Robert J. Budica, Frank O. Chandler, Joseph W. Haney
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Publication number: 20150354907Abstract: A system and methods for high heat transfer rate reusable thermal protection are presented. A porous skin comprises an exposed exterior surface and a non-exposed surface, and a coolant reservoir comprises perforations coupled to the non-exposed surface, and valves. The valves regulate a flow of coolant from the coolant reservoir to the porous skin in response to a temperature of the porous skin.Type: ApplicationFiled: November 28, 2012Publication date: December 10, 2015Inventors: James S. Herzberg, Robert J. Budica, Frank O. Chandler, Joseph W. Haney
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Publication number: 20150275823Abstract: A rocket engine having a co-axial, bidirectional flow arrangement is described herein. The rocket engine receives fuel and an oxidizer into the rocket engine in a first direction, whereby a portion of the fuel is combusted in a pre-burner. The flow direction of the partially combusted fuel/oxidizer mixture is reversed, whereby the mixture is introduced into a combustion chamber. The fuel and oxidizer are combusted in the combustion chamber. The combustion products exit a throat and an expansion plenum in a direction similar to the first direction, whereby the combustion products exit a nozzle of the rocket engine, providing thrust.Type: ApplicationFiled: March 28, 2014Publication date: October 1, 2015Applicant: The Boeing CompanyInventors: James S. Herzberg, Robert J. Budica, Frank O. Chandler
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Patent number: 9068562Abstract: A propulsion apparatus includes a propellant, at least one laser, and a thrust member. The propellant includes a solid surface having a hollow core disposed within the solid surface and a thrust-producing medium disposed within the hollow core. The at least one laser is positioned to vaporize the propellant with at least one laser-beam into a thrust-producing flow. The thrust member is for flowing within the thrust member a thrust-producing flow created by vaporization of the propellant.Type: GrantFiled: October 5, 2012Date of Patent: June 30, 2015Assignee: The Boeing CompanyInventors: Robert J. Budica, James S. Herzberg, Frank O. Chandler
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Patent number: 8091835Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).Type: GrantFiled: July 1, 2009Date of Patent: January 10, 2012Assignee: The Boeing CompanyInventors: John W. Behrens, Frank O. Chandler, Jeffrey J. Cronick
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Patent number: 8006938Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.Type: GrantFiled: September 23, 2010Date of Patent: August 30, 2011Assignee: The Boeing CompanyInventors: John W. Behrens, Thomas L. Kessler, Leora Peltz, Jeffrey J. Cronick, Glenn N. Caplin, Frank O. Chandler, Robert V. Frampton, Daniel E. Rivera
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Publication number: 20110031352Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.Type: ApplicationFiled: September 23, 2010Publication date: February 10, 2011Applicant: THE BOEING COMPANYInventors: John W. Behrens, Thomas L. Kessler, Leora Peltz, Jeffrey J. Cronick, Glenn N. Caplin, Frank O. Chandler, Robert V. Frampton, Daniel E. Rivera
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Patent number: 7861975Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.Type: GrantFiled: March 31, 2006Date of Patent: January 4, 2011Assignee: The Boeing CompanyInventors: John W. Behrens, Thomas L. Kessler, Leora Peltz, Jeffrey J. Cronick, Glenn N. Caplin, Frank O. Chandler, Robert V. Frampton, Daniel E. Rivera
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Patent number: 7823837Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.Type: GrantFiled: March 31, 2006Date of Patent: November 2, 2010Assignee: The Boeing CompanyInventors: John W. Behrens, Thomas L. Kessler, Leora Peltz, Jeffrey J. Cronick, Glenn N. Caplin, Frank O. Chandler, Robert V. Frampton, Daniel E. Rivera
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Publication number: 20100012788Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).Type: ApplicationFiled: July 1, 2009Publication date: January 21, 2010Applicant: THE BOEING COMPANYInventors: John W. Behrens, Frank O. Chandler, Jeffrey J. Cronick
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Patent number: 7575200Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).Type: GrantFiled: September 7, 2005Date of Patent: August 18, 2009Assignee: The Boeing CompanyInventors: John W. Behrens, Frank O. Chandler, Jeffrey J. Cronick
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Patent number: 7413148Abstract: A cryocooler is located on a spacecraft bus, such as a bus box, separate from the cryogenic propellant tanks disposed on a separable and distinct propellant cartridge system spacecraft docked to the spacecraft bus. In operation, propellant may be continuously pumped from the tanks through the cryocooler cold heat exchanger and then back to the tanks on the separable propellant cartridge system spacecraft through temporarily couplable lines. After the propellant tanks are depleted, the propellant cartridge system is then undocked from the bus and typically discarded. A new propellant cartridge system spacecraft comprising a full set of tanks may then be docked to the bus and the cryocooler supply/return lines coupled. The remote cryocooler may function as part of a larger space depot for spacecraft resupply, although it is not limited to such applications.Type: GrantFiled: April 5, 2006Date of Patent: August 19, 2008Assignee: The Boeing CompanyInventors: John W. Behrens, Frank O. Chandler, Jeffrey J. Cronick, Alfredo Lopez
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Publication number: 20080121759Abstract: A cryocooler is located on a spacecraft bus, such as a bus box, separate from the cryogenic propellant tanks disposed on a separable and distinct propellant cartridge system spacecraft docked to the spacecraft bus. In operation, propellant may be continuously pumped from the tanks through the cryocooler cold heat exchanger and then back to the tanks on the separable propellant cartridge system spacecraft through temporarily couplable lines. After the propellant tanks are depleted, the propellant cartridge system is then undocked from the bus and typically discarded. A new propellant cartridge system spacecraft comprising a full set of tanks may then be docked to the bus and the cryocooler supply/return lines coupled. The remote cryocooler may function as part of a larger space depot for spacecraft resupply, although it is not limited to such applications.Type: ApplicationFiled: April 5, 2006Publication date: May 29, 2008Applicant: The Boeing CompanyInventors: John W. Behrens, Frank O. Chandler, Jeffrey J. Cronick, Alfredo Lopez