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公开(公告)号：US11028803B2
公开(公告)日：2021-06-08
申请号：US16126225
申请日：2018-09-10
Applicant: Raytheon Company
Inventor： Matt H. Summers , David M. Case , John J. Raymond, IV , Gray Fowler , Mark T. Langhenry
Abstract: A rocket motor has a nozzle that is reconfigurable by erosion or ablation of the material around the throat of the nozzle. The nozzle throat has layers of materials with different erosion characteristics, with the erosion occurring so as to achieve the desired nozzle characteristics (configurations) during different parts of the fuel burn. The nozzle throat includes relatively-high-erosion material layers and relatively-low-erosion material layers, with some layers of the throat resisting erosion, while other of the layers erode or ablate relatively quickly. The relatively-low-erosion material layers may act as thermal barriers to fix the throat at relatively stable geometry for long periods of time, such as during most of the burn of different fuel segments, with the relatively-high-erosion material layers allowing rapid transition of the throat from one geometry to the next. The layers may be made by resin transfer molding (RTM).
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公开(公告)号：US10093592B2
公开(公告)日：2018-10-09
申请号：US14729429
申请日：2015-06-03
Applicant: Raytheon Company
Inventor： Jeremy C. Danforth , Mark T. Langhenry , Matt H. Summers , Teresa Perdue
Abstract: 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：US20170283095A1
公开(公告)日：2017-10-05
申请号：US15091008
申请日：2016-04-05
Applicant: Raytheon Company
Inventor： 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
CPC classification number: B64G1/403 , B33Y70/00 , B33Y80/00 , B64G1/10 , B64G1/26 , F02K9/80 , F02K99/00 , F05D2210/20 , F05D2230/31
Abstract: 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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公开(公告)号：US20160356245A1
公开(公告)日：2016-12-08
申请号：US14729390
申请日：2015-06-03
Applicant: Raytheon Company
Inventor： Jeremy C. Danforth , Teresa Perdue , Mark T. Langhenry , Matt H. Summers
IPC: F02K9/95
Abstract: A nozzleless hybrid rocket motor includes a fuel element that defines a combustion chamber therewithin, in which combustion of the fuel and an oxidizer occurs. The combustion gases produced by the combustion between the fuel and the oxidizer transition to supersonic flow before leaving the fuel element, eliminating the need for a separate nozzle. The fuel element may be a part of a structural element of a vehicle, for example being a part of a fuselage, wing, fairing, or other part of a space vehicle or an air vehicle, with the fuel element an integral and continuous part of the structural element. Combustion of part of the fuel element may allow vehicle structure to be used to provide thrust, such as for maneuver, consuming part of the structure. The fuel element may be made by an additive manufacturing process.
Abstract translation: 无喷嘴混合火箭发动机包括在其中限定燃烧室的燃料元件，其中发生燃料和氧化剂的燃烧。 由燃料和氧化剂之间的燃烧产生的燃烧气体在离开燃料元件之前转变为超音速流动，消除了对单独喷嘴的需要。 燃料元件可以是车辆的结构元件的一部分，例如是机身，机翼，整流罩或空间飞行器或空中交通工具的其他部分的一部分，其中燃料元件是整体和连续的部分 结构元素。 燃料元件的一部分的燃烧可以允许车辆结构用于提供推力，例如用于操纵，消耗部分结构。 燃料元件可以通过添加剂制造工艺制成。
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公开(公告)号：US09457761B2
公开(公告)日：2016-10-04
申请号：US14289513
申请日：2014-05-28
Applicant: Raytheon Company
Inventor： James K. Villarreal , Thomas M. Deppert , Mark T. Langhenry , Matt H. Summers
CPC classification number: B60R21/2644 , B60R21/00 , C06B33/06 , C06C9/00 , C06D5/06 , F42B3/04 , F42B3/128 , F42B3/14 , F42C19/0823 , F42C19/12
Abstract: The rate of combustion of an electrically operated propellant having self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.
Abstract translation: 控制具有至少1,000psi的自持阈值的电动推进剂的燃烧速率以产生足以在气囊中产生所需压力分布的腔室压力，以适应一系列人为因素和碰撞条件，但从未超过 自我维持的门槛。 推进剂的燃烧熄灭，以控制输送到气囊的总压力脉冲。 用离子高氯酸盐基氧化剂形成的推进剂已经证实超过1500psi或更高的阈值。
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Patent Agency Ranking
公开(公告)号：US20200080518A1
公开(公告)日：2020-03-12
申请号：US16126225
申请日：2018-09-10
Applicant: Raytheon Company
Inventor： Matt H. Summers , David M. Case , John J. Raymond, IV , Gray Fowler , Mark T. Langhenry
Abstract: A rocket motor has a nozzle that is reconfigurable by erosion or ablation of the material around the throat of the nozzle. The nozzle throat has layers of materials with different erosion characteristics, with the erosion occurring so as to achieve the desired nozzle characteristics (configurations) during different parts of the fuel burn. The nozzle throat includes relatively-high-erosion material layers and relatively-low-erosion material layers, with some layers of the throat resisting erosion, while other of the layers erode or ablate relatively quickly. The relatively-low-erosion material layers may act as thermal barriers to fix the throat at relatively stable geometry for long periods of time, such as during most of the burn of different fuel segments, with the relatively-high-erosion material layers allowing rapid transition of the throat from one geometry to the next. The layers may be made by resin transfer molding (RTM).
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公开(公告)号：US10563617B2
公开(公告)日：2020-02-18
申请号：US15274669
申请日：2016-09-23
Applicant: Raytheon Company
Inventor： James K. Villarreal , Mark T. Langhenry , Matt H. Summers
IPC: F02K9/24 , F02K9/12 , F02K9/95 , F02K9/86 , F02K9/82 , B64G1/40 , F02K9/08 , F02K9/94 , F02K9/26 , F02K9/28 , F02K9/34 , F02K9/97
Abstract: Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.
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公开(公告)号：US10378483B2
公开(公告)日：2019-08-13
申请号：US14938952
申请日：2015-11-12
Applicant: Raytheon Company
Inventor： James Kendall Villarreal , Mark T. Langhenry , Jeremy C. Danforth
IPC: F02K9/97 , F02K9/90 , F02K9/10 , F02K9/34 , F02K9/24 , F02K9/36 , F42B30/08 , F42B30/12 , F42B30/10 , F02K9/95 , F42B15/01 , F42B15/10 , F42B15/36 , F02K9/18 , F41A1/00 , F42B15/00 , F41F3/04
Abstract: A motor assembly is provided for use with projectiles, such as munitions, having relatively low length to diameter ratios. The motor assembly has an aerospike nozzle and a casing disposed about the aerospike nozzle, where interior aerospike volume contains propellant and where walls of both the cowl of the casing and of the aerospike nozzle jointly define a combustion chamber.
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公开(公告)号：US20190002362A1
公开(公告)日：2019-01-03
申请号：US16125871
申请日：2018-09-10
Applicant: Raytheon Company
Inventor： Jeremy C. Danforth , Mark T. Langhenry , Matt H. Summers , Teresa Perdue
Abstract: 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：US10145337B2
公开(公告)日：2018-12-04
申请号：US15197421
申请日：2016-06-29
Applicant: Raytheon Company
Inventor： Matt H. Summers , James K. Villarreal , Mark T. Langhenry , Jeremy C. Danforth , John W. Walter
Abstract: Electrical ignition of electrically operated propellant in a gas generation system provides an ignition condition at an ignition surface between a pair of electrodes that satisfies three criteria of a current density J that exhibits a decreasing gradient along an axis normal to an ignition surface, is substantially constant across the ignition surface and exceeds an ignition threshold at the ignition surface. These criteria may be satisfied by one or more of an angled electrode configuration, a segmented electrode configuration or an additive to the electrically operated propellant that modifies its conductivity. These configurations improve burn rate control and consumption of the available propellant and are scalable to greater propellant mass to support larger gas generation systems.
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