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公开(公告)号：US20200024210A1
公开(公告)日：2020-01-23
申请号：US16226741
申请日：2018-12-20
申请人： Raytheon Company
IPC分类号： C06B21/00 , B29C64/165 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B33Y70/00 , B33Y80/00 , B29B7/00
摘要： A system is used for additively manufacturing propellant elements, such as for rocket motors, includes partially curing a propellant mixture before extruding or otherwise dispensing the material, such that the extruded propellant material is deposited on the element in a partially-cured state. The curing process for the partially-cured extruded material may be completed shortly after the material is put into place, for example by the material being heated at or above its cure temperature, such that it finishes curing before it fully cools. The propellant material may be prepared by first mixing together, a fuel, an oxidizer, and a binder, such as in an acoustic mixer. After that mixing a curative may be added to the mixture. The propellant mixture may then be directed to an extruder (or other dispenser), in which the mixture is heated to or above a cure temperature prior to the deposition, and then deposited.
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公开(公告)号：US10046409B2
公开(公告)日：2018-08-14
申请号：US15259921
申请日：2016-09-08
申请人： Raytheon Company
发明人： Matthew H. Summers , Jeremy C. Danforth , David G. Garrett , Dmitry V. Knyazev , Stephen M. Bagg , Gaines S. Gibson
IPC分类号： B23K31/02 , B23K1/00 , B33Y10/00 , B33Y80/00 , B23K35/02 , F42B10/66 , H01R4/02 , H01R12/51 , H01R12/57 , H01R43/02 , B23K101/36 , H01R13/66 , H05K1/02 , H05K3/34
摘要： A method of making an electrical connection includes soldering using channels in a receptacle to direct hot air (or another hot gas) to effect soldering where the electrical connection is to be made. The connection may be made between device electrical contacts of an electrical device, and other contacts, such as receptacle contacts of the receptacle. The connection may be a blind connection, one in which the connected ends of the contacts are hidden or unable to be directly physically accessed, when the connection is made. The electrical connection may be made between device contacts of an electrical device that is inserted into the receptacle, and receptacle electrical contacts that are part of the receptacle. The channels for directing the hot gas to where the soldering occurs may be parts of the receptacle, for example being produced during additive manufacture of the receptacle.
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公开(公告)号：US20180106218A1
公开(公告)日：2018-04-19
申请号：US15259945
申请日：2016-09-08
申请人： Raytheon Company
发明人： Matthew H. Summers , Jeremy C. Danforth , David G. Garrett , Dmitry V. Knyazev , Stephen M. Baggs , Gaines S. Gibson
摘要： A thruster has an additively-manufactured housing that includes an integrally-formed nozzle with a burst disk in it. The housing is part of a casing that surrounds and encloses a propellant that is burned to produce pressurized gases that burst the burst disk and produce thrust. The thruster may be placed in a receptacle that defines a recess for receiving the thruster. The receptacle also may be additively manufactured. The thruster and the recess both may be cylindrical, with the housing being closely fit with the cylindrical walls of the receptacle. This may allow some of the structural loads on the housing, such as loads produced by the combustion of the propellant, to be transferred to the adjoining walls of the receptacle. This enables the housing to have less structural strength than if it were to have to contain the pressure from the propellant all on its own.
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公开(公告)号：US20180073842A1
公开(公告)日：2018-03-15
申请号：US15217482
申请日：2016-07-22
申请人： Raytheon Company
CPC分类号： F42B10/661 , B33Y80/00 , F02K9/425 , F02K9/97 , F42B6/006 , F42B10/663
摘要： A projectile, such as a railgun-launched projectile, includes a single-piece body that is additively manufactured. The single piece body includes fuel within it, and one or more cavities for receiving an oxidizer. The body also defines one or more combustion chambers therein for combustion of the fuel and oxidizer as part of a divert thruster system. Thus the projectile is able to fully contain the divert thruster system within the single-piece body without using any hot gas seals as part of the system. The body may also define a cavity for receiving a pressurized fluid, used as part of a cold-gas attitude control system of the projectile. The body may also define passages between the pressurized fluid cavity and other parts of the attitude control system, such as valves and/or nozzles that are outside of the body, for example being aft of the one-piece body.
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公开(公告)号：US20170284339A1
公开(公告)日：2017-10-05
申请号：US15091245
申请日：2016-04-05
申请人： Raytheon Company
发明人： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
IPC分类号： F02K9/28
摘要： A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments into engagement with the electrodes. The segments may be configured to provide equal increments of thrust, or different amounts of thrust. The segments may each include an electrically-operated propellant material surrounded by a sealing material, so as to keep the propellant material away from moisture and other contaminants (and/or the vacuum of space) before each individual segment is to be used. The thruster may be included in any of a variety of flight vehicles, for example in a small satellite such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
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公开(公告)号：US20160355447A1
公开(公告)日：2016-12-08
申请号：US14729429
申请日：2015-06-03
申请人： Raytheon Company
CPC分类号： C06B45/10 , B33Y10/00 , B33Y80/00 , C06B21/0033 , F02K9/12 , F05D2230/31
摘要： A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element. The combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited. The fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate.
摘要翻译： 可燃元件包括散布有氧化剂材料区域的燃料材料区域。 该元件可以通过添加剂制造工艺（例如三维印刷）制成，其中燃料材料区域和氧化剂材料区域放置在可燃元件的层中的适当位置。 例如，可以使用不同的挤出机来挤出和沉积燃料丝和氧化剂丝的部分在可燃元件的每层中的不同位置。 可燃元件可以在元件内限定燃烧室，其中当可燃元件被点燃时发生燃烧。 可以选择燃料材料和氧化剂材料，并且可以控制它们的相对量，使得燃烧所需的相对量的燃料和氧化剂存在于具有所需特性如燃烧速率的燃烧中。
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公开(公告)号：US10654762B2
公开(公告)日：2020-05-19
申请号：US16125871
申请日：2018-09-10
申请人： Raytheon Company
摘要： A combustible element includes regions of fuel material interspersed with regions of oxidizer material. The element may be made by additive manufacturing processes, such as three-dimensional printing, with the fuel material regions and the oxidizer material regions placed in appropriate locations in layer of the combustible element. For example, different extruders may be used to extrude and deposit portions of a fuel filament and an oxidizer filament at different locations in each layer of the combustible element. The combustible element may define a combustion chamber within the element, where combustion occurs when the combustible element is ignited. The fuel material and the oxidizer material may be selected, and their relative amounts may be controlled, such that desired relative amounts of fuel and oxidizer are present for combustion with desired characteristics, such as combustion rate.
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公开(公告)号：US10518908B2
公开(公告)日：2019-12-31
申请号：US14921545
申请日：2015-10-23
申请人： Raytheon Company
摘要： A spacecraft, such as a satellite, uses a shape memory polymer actuator to deploy one or more deployable parts. The shape memory polymer actuator may be formed integrally with a deployable part and/or with a fuselage or other structure of the spacecraft, with the shape memory polymer actuator being for example a relatively thin portion of the shape memory polymer material of the integral structure. The shape memory actuator allows deployment of the deployable part(s) upon heating of the shape memory polymer material of the actuator, such as after the satellite has been launched into space. The heating may be caused by a heat source that is part of the spacecraft itself, or may be merely the result of exposing the spacecraft to solar heating after launch. The deployable part of the spacecraft may include any of a wide variety of parts that are used after launch.
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公开(公告)号：US10287218B2
公开(公告)日：2019-05-14
申请号：US15232339
申请日：2016-08-09
申请人： Raytheon Company
IPC分类号： C06B21/00 , B33Y10/00 , B33Y30/00 , B33Y40/00 , B33Y70/00 , B33Y80/00 , B29B7/00 , B29C67/00 , B29K23/00 , B29K505/00 , B29L31/20 , B29L31/30
摘要： A method of additively manufacturing propellant elements, such as for rocket motors, includes partially curing a propellant mixture before extruding or otherwise dispensing the material, such that the extruded propellant material is deposited on the element in a partially-cured state. The curing process for the partially-cured extruded material may be completed shortly after the material is put into place, for example by the material being heated at or above its cure temperature, such that it finishes curing before it fully cools. The propellant material may be prepared by first mixing together, a fuel, an oxidizer, and a binder, such as in an acoustic mixer. After that mixing a curative may be added to the mixture. The propellant mixture may then be directed to an extruder (or other dispenser), in which the mixture is heated to or above a cure temperature prior to the deposition, and then deposited.
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公开(公告)号：US10220966B2
公开(公告)日：2019-03-05
申请号：US15091008
申请日：2016-04-05
申请人： Raytheon Company
发明人： Frederick B. Koehler , Jeremy C. Danforth , Ward D. Lyman , Mark T. Langhenry , Matt H. Summers , Paul E. Pontius , Brian M. Pape , Jared D. Stallings , James K. Villarreal , Thomas Villarreal
摘要： A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.
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