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公开(公告)号：US20240199237A1
公开(公告)日：2024-06-20
申请号：US17909824
申请日：2021-04-05
发明人： Aharon Yifrach
摘要： A launch system is provided, including a composite vehicle and a carrier vehicle. The composite vehicle includes a payload vehicle, a booster vehicle and a first coupling system. The payload vehicle is configured for powered spaceflight at least in a space medium, and includes a rocket driven propulsion system. The booster vehicle is configured for powered supersonic/hypersonic aerodynamic flight, includes a ramjet propulsion system, and is configured for transporting the composite vehicle between a first altitude and a second altitude under propulsive power provided by the ramjet propulsion system. The first coupling system is configured for selectively coupling and decoupling the payload vehicle with respect to the booster vehicle. The carrier vehicle is configured at least for powered subsonic/transonic/supersonic aerodynamic flight, and for transporting the composite vehicle to at least the first altitude from a ground location. The launch system also includes a second coupling system for selectively coupling and decoupling the composite vehicle with respect to the carrier aircraft.
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公开(公告)号：US11891951B1
公开(公告)日：2024-02-06
申请号：US18104327
申请日：2023-02-01
发明人： Robert Mercier , Mark Gruber , Ryan Milligan
CPC分类号： F02C7/04 , F02K7/14 , F05D2250/14
摘要： A scramjet engine with a novel isolator is disclosed herein. The scramjet includes an air inlet configured to receive and direct air into the engine and a combustor operable to receive air from the air inlet and combust fuel therein as is conventional. An isolator is positioned between the air inlet and the combustor. The isolator includes a primary flow path separated into a plurality of separate secondary flow channels formed therethrough. The smaller secondary flow channels prevent shockwaves from propagating upstream from the combustor to the inlet that can occur during some operating conditions of a supersonic combustion flow process.
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3.发明授权Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance 有权紧凑型轻型冲压喷气发动机，结合旋转增强燃烧，性能提高公开(公告)号：US06968695B2
公开(公告)日：2005-11-29
申请号：US10360469
申请日：2003-02-06
申请人： Stephen N. Schmotolocha , Robert J. Pederson , Calvin Q. Morrison, Jr. , Raymond B. Edelman , Donald H. Morris
发明人： Stephen N. Schmotolocha , Robert J. Pederson , Calvin Q. Morrison, Jr. , Raymond B. Edelman , Donald H. Morris
CPC分类号： F23C7/006 , F23C9/006 , F23C2900/09002 , F23R3/14 , F23R3/20 , F23R3/22 , F23R3/286 , Y02T50/675
摘要： A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and an inner central recirculation zone, both of which are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers and stabilizes flame propagation and accelerates combustion throughout the entire combustor. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor. Other benefits include simplicity, reliability, wide flammability limits and high combustion efficiency and thrust performance.
摘要翻译： 一种冲压喷气发动装置，其利用新颖的涡流发生器，根据需要快速有效地雾化，蒸发并将燃料混合到氧化剂中。 涡流发生器将氧化剂流转化为引入燃料的湍流三维流场。 涡流发生器影响环形外再循环区域和内中心再循环区域，两者都以向后流动的方式构造，其将热和燃烧副产物运送到上游，在其上用于连续点燃相邻剪切中的可燃燃料/氧化剂混合物 层并稳定火焰传播并加速整个燃烧室的燃烧。 涡流发生器提供平稳的燃烧，没有不稳定性和最小的总压力损失，并且能够显着降低燃烧器的L / D比。 其他优点包括简单性，可靠性，广泛的可燃性极限和高燃烧效率和推力性能。
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公开(公告)号：US06883330B2
公开(公告)日：2005-04-26
申请号：US10264172
申请日：2002-10-02
CPC分类号： F02K7/14
摘要： The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading edge and the leading edges of the sidewalls intersect the leading edge of the cowl flap.
摘要翻译： 本发明涉及一种用于具有至少一个燃烧器模块的冲击式发动机的改进的可变几何入口。 可变几何入口包括具有两个侧壁的每个燃烧器模块。 每个侧壁具有中心部分，该中心部分具有中心部分的前方的厚度和锥形轮廓。 锥形轮廓终止于锋利的前缘。 可变几何形状入口还包括每个模块，其具有位于下壁前方的下壁和可移动整流罩。 可移动整流罩具有前缘，并且侧壁的前缘与整流罩的前缘相交。
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公开(公告)号：US5485787A
公开(公告)日：1996-01-23
申请号：US264207
申请日：1994-06-21
申请人： Kevin G. Bowcutt , Harry Shortland
发明人： Kevin G. Bowcutt , Harry Shortland
摘要： A gas gun-launched, propulsion-assisted scramjet projectile adapted to be fired from a gun, preferably at velocities greater than Mach 5, includes a body with an external compression section, an internal compression section, a combustion section, a nozzle section, and means for channeling ambient fluid to an engine in one of the sections of the body, the channeling means and the body cooperating with the engine to produce thrust greater than drag when the projectile travels at velocities greater than Mach 5. The projectile further includes a plurality of circumferentially spaced stabilization fins located at the nozzle region of the body and a sabot assembly releasably secured to the rear portion of the body, where the sabot assembly includes a plurality of elements joined together about the body rear portion to form a housing for protecting the body rear portion from explosive gases in the barrel of the gun.
摘要翻译： 一种气枪发射的推进辅助冲击射弹，适于从枪射出，优选速度大于5马赫，包括具有外部压缩部分，内部压缩部分，燃烧部分，喷嘴部分和 用于将环境流体引导到身体，引导装置和与发动机配合的主体中的一个部分中的发动机的装置，以在弹丸以大于5马赫的速度行进时产生大于阻力的推力。射弹还包括多个 位于主体的喷嘴区域处的周向间隔开的稳定翼片，以及可释放地固定到主体后部的破坏组件，其中膛体组件包括围绕主体后部部分连接在一起的多个元件，以形成用于保护 枪身后部爆炸性气体的身体后部。
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公开(公告)号：US5085048A
公开(公告)日：1992-02-04
申请号：US486640
申请日：1990-02-28
CPC分类号： F02K7/10 , Y02T50/671
摘要： A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scamjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween. Means for injecting fuel into the inlet-combustor at the step are provided for mixing fuel with supersonic airflow for generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel injecting means is effective for injecting fuel to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in a conventional scramjet engine.
摘要翻译： 公开了一种有效用于超音速飞机作为飞行器集成的scamjet发动机的冲击式发动机。 发动机包括具有后向后台阶的第一表面和与第一表面间隔开的整流罩上表面，以在它们之间限定一体的入口 - 燃烧器。 提供了在步骤中将燃料喷入入口 - 燃烧器的装置，用于将燃料与用于在入口 - 燃烧器中产生超音速燃烧气体的超音速气流混合。 在本发明的优选实施例中，燃料喷射装置有效地喷射燃料以产生限定亚音速燃料区和超音速流体区的流体边界。 流体边界是可变的，并且消除了在常规冲击式喷气发动机中需要可变入口几何形状的起动和不起动问题。
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公开(公告)号：US4903480A
公开(公告)日：1990-02-27
申请号：US245181
申请日：1988-09-16
CPC分类号： F23R3/28 , F02K7/10 , F02K9/52 , F05D2260/20
摘要： A hypersonic scramjet engine fuel injector and a hypersonic scramjet engine having such a fuel injector. The engine has a serially connected inlet, combustor, and exhaust nozzle. Multiple, horizontally-spaced-apart fuel injectors are positioned in and connected to the combustor's top portion. Each fuel injector has a hollow wedge shape housing. To improve fuel-air mixing for better combustion, the housing's end wall has multiple, discrete, convergent-divergent fuel outlet nozzles and its side walls have horizontally-extending exterior grooves. Fuel is used to cool the fuel injector housing with the housing's bottom and side walls having fuel-exit holes and the housing having an interior serpentine fuel passageway.
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公开(公告)号：US4821512A
公开(公告)日：1989-04-18
申请号：US46072
申请日：1987-05-05
申请人： Roy N. Guile , William T. Peschke
发明人： Roy N. Guile , William T. Peschke
CPC分类号： F02K7/10 , F23R3/20 , F05D2260/20 , Y02T50/675
摘要： A piloting fuel injector assembly for a supersonic ramjet engine has a cowl 24, 70 confining a pilot air portion of the airstream. A conical member 34, 74 produces a subsonic recirculation zone 30, 76 and a shock wave falling within the cowl. Pilot fuel injected 40, 82 upstream of the recirculation zone burns stoichiometrically. The exhaust 38, 86 from the cowl is sonic, producing a shock wave which facilitates ignition of the main fuel injected 46, 84 upstream of the cowl exhaust.
摘要翻译： 用于超音速冲压喷气发动机的驾驶式燃料喷射器组件具有限制气流的先导空气部分的整流罩24,70。 圆锥形构件34,74产生亚音速再循环区域30,76和落在整流罩内的冲击波。 在再循环区上游40,82的先导燃料以化学计量燃烧。 来自整流罩的排气38,86是声波的，产生冲击波，这促使在整流罩排气上游喷射的主燃料46,84点燃。
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公开(公告)号：US4170875A
公开(公告)日：1979-10-16
申请号：US694262
申请日：1976-06-10
申请人： Lawrence J. Edwards
发明人： Lawrence J. Edwards
CPC分类号： F02K7/14 , Y02T50/671
摘要： A "caseless" rocket having a solid propellant grain body which as a result of its shape and surface burning creates, in effect, an outer case or barrier formed by the surrounding airstream and the burning propellant. An exhaust "nozzle" is generated as an annulus in which the air stream serves as one surface while the propellant grain serves as the other. Stores or a payload are enclosed within the propellant body.
摘要翻译： 由于其形状和表面燃烧，具有固体推进剂颗粒体的“无形”火箭实际上形成了由周围的气流和燃烧的推进剂形成的外壳或屏障。 产生排气“喷嘴”作为其中空气流用作一个表面的环形空间，而推进剂颗粒用作另一个表面。 商店或有效载荷包围在推进剂体内。
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10.发明授权Spindle-shaped supersonic projectile with additional propulsion by sternfiring 失效通过STERNIRIR附加额外推力的主轴超级项目
公开(公告)号：US3545212A
公开(公告)日：1970-12-08
申请号：US3545212D
申请日：1967-12-14
申请人： DYNAMIT NOBEL AG
发明人： LUDWIG GUNTER
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