Patents by Inventor Melvin J. Bulman
Melvin J. Bulman 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: 10690424Abstract: A modified projectile includes a projectile, a container, and a liquid propellant in the container. The container is detachably attached to the projectile.Type: GrantFiled: May 31, 2017Date of Patent: June 23, 2020Assignee: Aerojet Rocketdyne, Inc.Inventor: Melvin J. Bulman
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Patent number: 10308133Abstract: A transport and power system having a plurality of tubes or tunnels, a magnetic levitation and linear motor train, and a superconducting power cable. One of the tubes can be an escape, power distribution, and maintenance tunnel. These tubes can be above ground, below ground, at ground, or under water.Type: GrantFiled: April 27, 2016Date of Patent: June 4, 2019Inventors: Victor B. Kley, Melvin J. Bulman
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Publication number: 20190107346Abstract: A modified projectile includes a projectile, a container, and a liquid propellant in the container.Type: ApplicationFiled: May 31, 2017Publication date: April 11, 2019Inventor: Melvin J. Bulman
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Publication number: 20170080823Abstract: A transport and power system having a plurality of tubes or tunnels, a magnetic levitation and linear motor train, and a superconducting power cable. One of the tubes can be an escape, power distribution, and maintenance tunnel. These tubes can be above ground, below ground, at ground, or under water.Type: ApplicationFiled: April 27, 2016Publication date: March 23, 2017Applicant: Metadigm LLCInventors: Victor B. Kley, Melvin J. Bulman
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Patent number: 9291124Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of the DMRJ functioning as an aerodynamic choke.Type: GrantFiled: March 6, 2014Date of Patent: March 22, 2016Assignee: AEROJET ROCKETDYNE, INC.Inventor: Melvin J. Bulman
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Publication number: 20160010485Abstract: A combined cycle propulsion system includes a low-speed propulsion engine and a high-speed propulsion engine that has a compression zone. A non-propulsion turbine is connected with the compression zone. An accessory drive gearbox is mechanically coupled with the low-speed engine and mechanically coupled with the non-propulsion turbine. For example, the low-speed propulsion engine is a turbine engine and the high-speed propulsion engine is a ramjet or scramjet engine.Type: ApplicationFiled: July 2, 2015Publication date: January 14, 2016Inventors: Jon Volkmann, Melvin J. Bulman, Adam Siebenhaar
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Publication number: 20150007550Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of the DMRJ functioning as an aerodynamic choke.Type: ApplicationFiled: March 6, 2014Publication date: January 8, 2015Inventor: Melvin J. Bulman
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Patent number: 8763361Abstract: High thrust at sea level and high Isp at high altitudes with low ambient pressure are obtained in a vehicle with an engine of fixed geometry including an exit of non-changing cross section, by incorporating a series of propellant injectors in a divergent section of the engine, spaced apart along the engine axis at points of different engine cross section. At takeoff, the injectors at sites with a large cross section are used, and as the vehicle climbs, these injectors are successively closed leaving injectors activated at sites of successively smaller cross sections. The injectors establish thermal choke points, and the area ratio of the cross section at the exit to the cross section at the thermal choke point thus increases as the vehicle climbs from low to high altitudes.Type: GrantFiled: January 6, 2009Date of Patent: July 1, 2014Assignee: Aerojet-General CorporationInventor: Melvin J Bulman
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Patent number: 8701379Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.Type: GrantFiled: January 19, 2011Date of Patent: April 22, 2014Assignee: Aerojet-General CorporationInventor: Melvin J. Bulman
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Patent number: 8601787Abstract: Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.Type: GrantFiled: May 3, 2012Date of Patent: December 10, 2013Assignee: Aerojet—General CorporationInventor: Melvin J. Bulman
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Publication number: 20120233983Abstract: Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.Type: ApplicationFiled: May 3, 2012Publication date: September 20, 2012Applicant: AEROJET-GENERAL CORPORATIONInventor: Melvin J. Bulman
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Patent number: 8186145Abstract: Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.Type: GrantFiled: February 26, 2008Date of Patent: May 29, 2012Assignee: Aerojet-General CorporationInventor: Melvin J. Bulman
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Publication number: 20120089525Abstract: A transport and power system having a plurality of tubes or tunnels, a magnetic levitation and linear motor train, and a superconducting power cable. One of the tubes can be an escape, power distribution, and maintenance tunnel. These tubes can be above ground, below ground, at ground, or under water.Type: ApplicationFiled: October 20, 2009Publication date: April 12, 2012Applicant: Metadigm LLCInventors: Victor B. Kley, Melvin J. Bulman
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Patent number: 8056319Abstract: An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A first conduit has a first valve communicating the fuel and the oxidizer and a second conduit, spatially removed from the first conduit, has a second valve communicating the fuel and the oxidizer. An inlet system for delivering atmospheric oxygen for combustion with the fuel rich gases generated within the missile and a nozzle exhausts combustion products that result from combustion of the fuel, the liquid and solid oxidizers, and air.Type: GrantFiled: November 8, 2007Date of Patent: November 15, 2011Assignee: Aerojet—General CorporationInventors: Melvin J. Bulman, Adam Siebenhaar
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Publication number: 20110107738Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.Type: ApplicationFiled: January 19, 2011Publication date: May 12, 2011Applicant: Aerojet-General CorporationInventor: Melvin J. Bulman
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Patent number: 7886516Abstract: An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of said DMRJ functioning as an aerodynamic choke.Type: GrantFiled: December 18, 2006Date of Patent: February 15, 2011Assignee: Aerojet-General CorporationInventor: Melvin J. Bulman
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Publication number: 20110023451Abstract: High thrust at sea level and high Isp at high altitudes with low ambient pressure are obtained in a vehicle with an engine of fixed geometry including an exit of non-changing cross section, by incorporating a series of propellant injectors in a divergent section of the engine, spaced apart along the engine axis at points of different engine cross section. At takeoff, the injectors at sites with a large cross section are used, and as the vehicle climbs, these injectors are successively closed leaving injectors activated at sites of successively smaller cross sections. The injectors establish thermal choke points, and the area ratio of the cross section at the exit to the cross section at the thermal choke point thus increases as the vehicle climbs from low to high altitudes.Type: ApplicationFiled: January 6, 2009Publication date: February 3, 2011Inventor: Melvin J. Bulman
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Patent number: 7823376Abstract: Thrust augmentation in a rocket nozzle is achieved by incorporating injectors for the introduction of unburnt fuel and oxidizer into a nozzle to combust in the nozzle and thereby supplement the primary thrust that is supplied by fuel and oxidizer that are combusted prior to entry into the nozzle. These secondary injectors are incorporated into the design of expansion-deflection nozzles and plug nozzles. In expansion-deflection nozzles, the injectors are either in the flow deflector itself or in the wall of the divergent section of the nozzle. In plug nozzles, the injectors are either in a shell of the nozzle surrounding the forward end of the centerbody or in the centerbody itself.Type: GrantFiled: September 13, 2005Date of Patent: November 2, 2010Assignee: Aerojet-General CorporationInventors: Merlyn Lausten, Melvin J. Bulman
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Patent number: 7797943Abstract: A pilot for a scramjet provides a flame front whose arrival at the wall of the scramjet combustor is delayed thereby reducing combustor heat load. By combining in-stream injection of fuel with an interior pilot and a lean (fuel-poor) outer annulus, the bulk of combustion is confined to the scramjet combustor center. This concept, referred to as “core-burning,” further reduces combustor heat load. One such pilot is for a two dimensional scramjet effective to propel a vehicle. This pilot includes a plurality of spaced apart struts separated by ducts and a strut pilot contained within each strut. A second such pilot is for an axisymmetric scramjet engine has, in sequence and in fluid communication, an air intake, an open bore scramjet isolator and a scramjet combustor. This centerbody pilot pod includes a pilot isolator disposed between the air intake and a pilot diffuser, the pilot diffuser disposed between the pilot isolator and a pilot with the pilot disposed between the pilot diffuser and a pilot combustor.Type: GrantFiled: October 18, 2006Date of Patent: September 21, 2010Assignee: Aerojet-General CorporationInventor: Melvin J. Bulman
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Patent number: RE43731Abstract: An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.Type: GrantFiled: August 30, 2010Date of Patent: October 16, 2012Assignee: Aerojet-GeneralInventors: Melvin J. Bulman, Frederick S. Billig, Linda A. Baumler, legal representative