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1. 发明申请

US20230012171A1 PROPELLANT INJECTOR FOR HYBRID ROCKET ENGINES 有权
公开(公告)号：US20230012171A1
公开(公告)日：2023-01-12
申请号：US17367627
申请日：2021-07-06
申请人： AT SPACE PTY LTD
发明人： Yen-Sen CHEN
IPC分类号： F02K9/52 , F02K9/72
摘要： A propellant injector is adapted to be installed to a hybrid rocket engine and includes an injector casing, a tube and a plurality of blades. The tube is arranged along a center axis of the propellant injector in an inner space of the injector casing. The plurality of blades is disposed to and evenly distributed over an outer surface of the tube, and is configured to cause vortices toward a combustion chamber of the hybrid rocket engine when being driven to rotate.

2. 发明授权

US11408376B2 Thrust augmentation of an additively manufactured hybrid rocket system using secondary oxidizer injection 有权
公开(公告)号：US11408376B2
公开(公告)日：2022-08-09
申请号：US16990586
申请日：2020-08-11
申请人： Stephen Whitmore , Mark C. Heiner
发明人： Stephen Whitmore , Mark C. Heiner
IPC分类号： F02K9/72 , F02K9/26 , F02K9/52 , F02K9/14
摘要： A hybrid rocket includes a housing having first and second ends, a solid-grain fuel material in the housing and defining a bore extending from end to end, two electrodes positioned adjacent to the fuel material to ignite the fuel material at the first end, a primary oxidizer port positioned at the first end to inject a primary oxidizer to flow in a downstream direction from the first end to the second end, a nozzle positioned at the second end and having a converging portion and a diverging portion, and a secondary oxidizer port to inject a secondary oxidizer downstream of the converging portion. The bore has a geometry configured to produce a hot-gas, fuel-rich mixture at the nozzle as the fuel material and primary oxidizer burn while flowing downstream. The diverging portion of the nozzle is configured to spontaneously combust the secondary oxidizer and the hot-gas, fuel-rich mixture.

3. 发明申请

US20200370513A1 THRUST AUGMENTATION OF AN ADDITIVELY MANUFACTURED HYBRID ROCKET SYSTEM USING SECONDARY OXIDIZER INJECTION 审中-公开
公开(公告)号：US20200370513A1
公开(公告)日：2020-11-26
申请号：US16990586
申请日：2020-08-11
申请人： Stephen Whitmore , Mark C. Heiner
发明人： Stephen Whitmore , Mark C. Heiner
IPC分类号： F02K9/72
摘要： A hybrid rocket includes a housing having first and second ends, a solid-grain fuel material in the housing and defining a bore extending from end to end, two electrodes positioned adjacent to the fuel material to ignite the fuel material at the first end, a primary oxidizer port positioned at the first end to inject a primary oxidizer to flow in a downstream direction from the first end to the second end, a nozzle positioned at the second end and having a converging portion and a diverging portion, and a secondary oxidizer port to inject a secondary oxidizer downstream of the converging portion. The bore has a geometry configured to produce a hot-gas, fuel-rich mixture at the nozzle as the fuel material and primary oxidizer burn while flowing downstream. The diverging portion of the nozzle is configured to spontaneously combust the secondary oxidizer and the hot-gas, fuel-rich mixture.

4. 发明授权

US10815935B2 Throttleable propulsion launch escape systems and devices 有权
公开(公告)号：US10815935B2
公开(公告)日：2020-10-27
申请号：US15729554
申请日：2017-10-10
申请人： Earl W. Renaud , Patrick R. E. Bahn
发明人： Earl W. Renaud , Patrick R. E. Bahn
IPC分类号： F02K9/60 , B64G1/40 , B64G1/52 , F02K9/08 , F02K9/46 , F02K9/72 , B64G1/00 , F02K9/96
摘要： The present invention relates to throttleable propulsion launch escape systems and devices. In one embodiment, the system includes a tower and at least one throttleable motor secured to the tower. The throttleable motor is able to throttle to a reduced power setting during flight. In another embodiment, the system includes at least one throttleable motor and a space vehicle unit that includes a containing structure. In a further embodiment, the throttleable motor may be secured about a boost escape system of a space vehicle unit. In an additional embodiment, the present invention is a three-dimensional nozzle.

5. 发明申请

US20200291899A1 HYBRID ROCKET ENGINE WITH IMPROVED SOLID FUEL SEGMENT 审中-公开
公开(公告)号：US20200291899A1
公开(公告)日：2020-09-17
申请号：US16351179
申请日：2019-03-12
申请人： TAIWAN INNOVATIVE SPACE, INC.
发明人： Yen-Sen CHEN
IPC分类号： F02K9/32 , F02K9/72 , F02K9/52
摘要： A rocket engine with an improved solid fuel segment mainly comprises a combustion chamber, a solid fuel segment installed in the combustion chamber, and an oxidizer injector installed at one end of the combustion chamber. The solid fuel segment surrounds and forms a trajectory to allow the oxidizer injector to inject oxidizer into the trajectory, in particular, on the solid fuel segment is formed with a plurality of protrusions, between the each two protrusions are defined a recess, a flame holding hot-gas region is formed between the protrusion and the recess, so as to produce eddy current in the flame holding hot-gas region when the propellant mixture is burned inside the trajectory, such that the whole solid fuel segment can produce even regression rate and high combustion efficiency.

6. 发明申请

US20200063692A1 LINEAR THROTTLING HIGH REGRESSION RATE VORTEX FLOW FIELD INJECTION SYSTEM WITHIN A HYBRID ROCKET ENGINE 审中-公开
公开(公告)号：US20200063692A1
公开(公告)日：2020-02-27
申请号：US16550063
申请日：2019-08-23
申请人： ROCKET CRAFTERS PROPULSION LLC
发明人： Kineo M. WALLACE
IPC分类号： F02K9/72
摘要： A hybrid rocket engine with a vortex flow field injection system that produces a high-speed sustained vortex flow field is described. The hybrid rocket engine includes a generally cylindrical injection chamber with an inner circumference to comprise an outer edge of a solid propellant grain in the hybrid rocket engine. The engine also includes an injection system that has a throttle valve and an injector that injects injection fluid into the engine and produces a vortex flow-field for the injected fluid. The injector includes at least one primary feed line that distributes the injection fluid throughout a pre-swirl chamber and multiple orifices along an inner edge of the injection chamber. The pre-swirl chamber connects to the injection chamber and at least one of the primary feed lines and redirects a primary fluid flow of the injected fluid from a primary axial direction to a centrifugal direction.

7. 发明申请

US20170234268A1 HYBRID ROCKET MOTOR WITH INTEGRAL OXIDIZER TANK 审中-公开
公开(公告)号：US20170234268A1
公开(公告)日：2017-08-17
申请号：US15044490
申请日：2016-02-16
申请人： Raytheon Company
发明人： Matt H. Summers , Jeremy C. Danforth
IPC分类号： F02K9/72 , B33Y80/00 , B33Y10/00
摘要： A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.

8. 发明申请

US20110314790A1 HYBRID PROPULSION SYSTEM 有权
标题翻译：混合推进系统
公开(公告)号：US20110314790A1
公开(公告)日：2011-12-29
申请号：US12404977
申请日：2009-03-16
申请人： Frank MacKlin , Chris Grainger
发明人： Frank MacKlin , Chris Grainger
IPC分类号： F02K9/72
CPC分类号： F02K9/72 , F02K9/343
摘要： Disclosed is a propulsion system having a structural configuration that provides easy and convenient access to the interior regions of a liquid fuel tank and a hybrid rocket motor case. In one embodiment, the propulsion system comprises: a hybrid rocket motor case and a fuel tank coupled to the hybrid motor case. The motor case is configured to hold solid rocket fuel and the fuel tank defines an internal volume configured to hold a fluid oxidizer. A bulkhead is interposed between the motor case and the fuel tank, wherein at least one access passageway extends through the bulkhead. The access passageway provides exterior access to the interior volume of the motor case or the internal volume of the storage tank while the hybrid rocket motor is coupled to the fuel tank.
摘要翻译：公开了具有结构构造的推进系统，其提供容易且方便地进入液体燃料箱和混合火箭发动机壳体的内部区域。在一个实施例中，推进系统包括：混合火箭发动机壳体和联接到混合动力马达壳体的燃料箱。电动机壳被配置为保持固体火箭燃料，并且燃料箱限定配置成保持流体氧化器的内部容积。在电动机外壳和燃料箱之间设置隔板，其中至少一个进入通道延伸穿过隔板。进入通道在混合式火箭发动机联接到燃料箱的同时，提供对电动机壳体的内部容积或储罐的内部容积的外部通路。

9. 发明申请

US20090211226A1 HYBRID ROCKET MOTOR WITH ANNULAR, CONCENTRIC SOLID FUEL ELEMENTS 有权
标题翻译：混合式摇臂电机，带有环形固体燃料元件
公开(公告)号：US20090211226A1
公开(公告)日：2009-08-27
申请号：US11764677
申请日：2007-06-18
申请人： Frank Macklin
发明人： Frank Macklin
IPC分类号： F02K9/72 , F02K9/28
CPC分类号： F02K9/28 , F02K9/72
摘要： A hybrid rocket motor includes a supply of oxidizer, a first solid fuel element positioned around the supply of oxidizer, a second solid fuel element positioned concentrically around the first solid fuel element, and a combustion port positioned between the first and second solid fuel elements. The oxidizer interacts with the first and second solid fuel elements within the combustion port to produce a combustion product. A nozzle is in communication with the combustion port for combustion discharge of the combustion product.
摘要翻译：混合式火箭发动机包括供给氧化剂，围绕氧化剂供应的第一固体燃料元件，位于第一固体燃料元件周围同心定位的第二固体燃料元件和位于第一和第二固体燃料元件之间的燃烧口。氧化剂与燃烧口内的第一和第二固体燃料元件相互作用以产生燃烧产物。喷嘴与燃烧口连通，用于燃烧产物的燃烧排放。

10. 发明授权

US07194853B1 Pressurizer for a rocket engine 失效
标题翻译：用于火箭发动机的加压器
公开(公告)号：US07194853B1
公开(公告)日：2007-03-27
申请号：US10852761
申请日：2004-05-25
申请人： Andrew F. Knight
发明人： Andrew F. Knight
IPC分类号： F02K9/00 , F02K9/42 , F02K9/72
CPC分类号： F02K9/46 , F02K9/50 , F04B9/133 , F04F13/00
摘要： A pump for pressurizing a fluid includes an engine portion including a first pressure vessel, a first piston movable inside the first pressure vessel, at least two pressurant entrance valves connected to the first pressure vessel, and at least two pressurant exit valves connected to the first pressure vessel. The valves are configured to be opened and closed automatically and directly as a function of a position of the first piston inside the first pressure vessel. The valves are also configured to be automatically opened and closed out of phase with each other. The pump also includes a pump portion including a second pressure vessel, a second piston connected to the first piston and movable inside the second pressure vessel, at least two fluid entrance valves connected to the second pressure vessel, and at least two fluid exit valves connected to the second pressure vessel.
摘要翻译：用于对流体加压的泵包括发动机部分，其包括第一压力容器，可在第一压力容器内运动的第一活塞，连接到第一压力容器的至少两个加压入口阀以及连接到第一压力容器的至少两个加压排出阀压力容器。阀构造成根据第一活塞在第一压力容器内部的位置自动和直接地打开和关闭。这些阀也被配置成彼此自动打开和关闭。所述泵还包括泵部分，所述泵部分包括第二压力容器，连接到所述第一活塞并可在所述第二压力容器内移动的第二活塞，连接到所述第二压力容器的至少两个流体入口阀以及连接到所述第二压力容器的至少两个流体出口阀到第二压力容器。

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