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1. 发明授权

US5582001A Hybrid rocket combustion enhancement 失效
标题翻译：混合火箭燃烧增强
公开(公告)号：US5582001A
公开(公告)日：1996-12-10
申请号：US398140
申请日：1989-08-24
申请人： Michael D. Bradford , Roy J. Kniffen, Jr. , Bevin C. McKinney
发明人： Michael D. Bradford , Roy J. Kniffen, Jr. , Bevin C. McKinney
IPC分类号： F02K9/72 , F02K9/28
CPC分类号： F02K9/72
摘要： The combustion of a hybrid engine is improved by continuously injecting into a precombustion chamber a hypergolic fluid such as triethyl aluminum which exothermically reacts with and vaporizes the oxidizer such as liquid oxygen. The prevaporized oxidizer evenly combusts the solid propellant grain to develop thrust.
摘要翻译：混合发动机的燃烧通过连续地向预燃室中注入诸如三乙基铝的膨胀流体，与氧化剂如液氧放热反应并蒸发，从而提高燃烧。预蒸发的氧化剂均匀地燃烧固体推进剂颗粒以产生推力。

2. 发明授权

US5119627A Embedded pressurization system for hybrid rocket motor 失效
标题翻译：混合火箭发动机嵌入式加压系统
公开(公告)号：US5119627A
公开(公告)日：1992-06-09
申请号：US431660
申请日：1989-11-03
申请人： Michael D. Bradford , Bevin C. McKinney
发明人： Michael D. Bradford , Bevin C. McKinney
IPC分类号： F02K9/36 , F02K9/60 , F02K9/72
CPC分类号： F02K9/605 , F02K9/36 , F02K9/72
摘要： A solid propellant component grain is supported in a combustion chamber. A liquid propellant component container is mounted forward of the combustion chamber. The liquid propellant component is supplied through conduits from the container into the combustion chamber, and ignited to form combustion gas which is discharged out the rear of the combustion chamber to generate thrust for propelling a rocket. A high pressure tank containing a non-flammable gas such as helium is at least partially embedded in the grain. A conduit leads from the tank into the container, such that the high pressure gas pressurizes the container and urges the liquid propellant component to flow from the container into the combustion chamber. The tank provides internal structural support for the grain, with the wall of the combustion chamber constituting a safety barrier in the event of structural failure of the tank after the tank is filled with high pressure gas.
摘要翻译：固体推进剂组分颗粒被支撑在燃烧室中。液体推进剂组分容器安装在燃烧室的前方。液体推进剂组分通过管道从容器供入燃烧室，并被点燃以形成燃烧气体，其被排出到燃烧室后部以产生用于推进火箭的推力。含有诸如氦气的不易燃气体的高压罐至少部分地嵌入颗粒中。导管从罐引导到容器中，使得高压气体加压容器并促使液体推进剂组分从容器流入燃烧室。罐体为颗粒提供内部结构支撑，燃烧室的壁在罐被高压气体填充后，在罐体结构失效的情况下构成安全屏障。

3. 发明授权

US5842665A Launch vehicle with engine mounted on a rotor 失效
标题翻译：发动机搭载在转子上的发动机
公开(公告)号：US5842665A
公开(公告)日：1998-12-01
申请号：US711964
申请日：1996-09-09
申请人： Bevin C. McKinney , Gary C. Hudson
发明人： Bevin C. McKinney , Gary C. Hudson
IPC分类号： B64C27/18 , B64C29/02 , B64G1/00 , B64G1/14 , B64G1/40 , B64G1/62 , B64C39/00
CPC分类号： B64G1/401 , B64C27/18 , B64C29/02 , B64G1/002 , B64G1/14 , B64G1/62
摘要： A launch vehicle which employs a rotor similar to a helicopter. The vehicle has a four bladed rotor which is mounted on the vehicle body. The body of the vehicle includes propellant tanks and a payload compartment contained within an integral aeroshell. Rocket engines used to propel the vehicle into earth orbit are mounted at the ends of the rotor blades. The engines are connected by propellant feed lines to a propellant transfer hub surrounding the axis of rotation of the rotor. Propellants are fed from an oxidizer tank and a fuel tank through a propellant transfer coupling to oxidizer and fuel lines which extend to the engines at the rotor blades ends. The rotor blades incorporate air foils. To operate the vehicle the vehicle is positioned on a concrete or asphalt pad and fueled with liquid oxygen and kerosene. The engine are positioned tangent to the blade paths and ignited. The thrust of the engines which is tangent to the rotor causes the rotor to turn which accelerates the rotor thus increasing the pressure developed by the propellants as they flow towards the engines. When the rotor has reached operational speed the airfoil creates sufficient lift that the vehicle begins to ascend vertically. As the vehicle exits the atmosphere the rocket engines are aligned with the flight path of the vehicle. After reentry from earth orbit the vehicle utilizes the spun up rotor to fly the vehicle to a soft landing.
摘要翻译：使用类似于直升机的转子的运载火箭。车辆具有安装在车体上的四叶片转子。车辆的车身包括推进剂罐和包含在整体式气囊内的有效载荷舱。用于将车辆推进地球轨道的火箭发动机安装在转子叶片的端部。发动机通过推进剂进料管线连接到围绕转子旋转轴线的推进剂传递轮毂。推进剂从氧化剂罐和燃料箱通过推进剂传递耦合馈送到氧化剂和燃料管线，其在转子叶片端部延伸到发动机。转子叶片包含气翼。为了操作车辆，车辆定位在混凝土或沥青垫上，并用液氧和煤油燃料。发动机定位成与叶片路径相切并点燃。与转子相切的发动机的推力导致转子转动，从而加速转子，从而增加推进剂在向发动机流动时产生的压力。当转子达到操作速度时，机翼产生足够的升力，使车辆开始垂直上升。当车辆离开大气时，火箭发动机与车辆的飞行路线对准。在从地球轨道重新进入后，车辆利用旋转转子将车辆飞行到软着陆。

4. 发明授权

US6136418A Rapidly removable thermal protection system for reusable launch vehicle 有权
标题翻译：用于可重复使用的运载火箭的快速拆卸热保护系统
公开(公告)号：US6136418A
公开(公告)日：2000-10-24
申请号：US259763
申请日：1999-03-01
申请人： Anthony Martin , Bevin C. McKinney
发明人： Anthony Martin , Bevin C. McKinney
IPC分类号： B32B7/12 , B64G1/14 , B64G1/58 , B32B3/10 , B32B3/06
CPC分类号： B64G1/58 , B32B7/12 , B64G1/14 , Y10T428/24802 , Y10T428/2486 , Y10T428/24967 , Y10T428/2848
摘要： A thermal protection system is composed of multiple panels, each of which has an ablative layer of cork thermal protection which is adhesively bonded to a flexible film. The rear surface of the film is coated with two types of adhesive. A first, high strength adhesive is applied at the edges of the cork panel and where aerodynamic forces may be higher. A second, lower strength adhesive is applied to the remaining surface of the film. Following the return of the launch vehicle from space, the thermal protection panels are removed by peeling away the high strength attachment edges with a knife, or other blade tool, and then removing the remainder of the panel, which is only lightly attached to the vehicle skin, without the aid of tools.
摘要翻译：热保护系统由多个面板组成，每个面板具有粘结到柔性薄膜上的软木热保护的烧蚀层。膜的后表面涂覆有两种类型的粘合剂。在软木板的边缘处施加第一种高强度粘合剂，并且其中空气动力可能更高。将第二种较低强度的粘合剂施加到膜的剩余表面。在运载火箭从空间返回之后，用刀或其他刀片工具剥离高强度附着边缘去除热保护板，然后移除仅轻轻地附着在车辆上的其余部分皮肤，没有工具的帮助。

5. 发明授权

US5339625A Hybrid rocket motor solid fuel grain 失效
标题翻译：混合火箭发动机固体燃料颗粒
公开(公告)号：US5339625A
公开(公告)日：1994-08-23
申请号：US986087
申请日：1992-12-04
申请人： Bevin C. McKinney , Roy J. Kniffen, Jr.
发明人： Bevin C. McKinney , Roy J. Kniffen, Jr.
IPC分类号： C06D5/10 , F02K9/14 , F02K9/36 , F02K9/72 , F02K9/00
CPC分类号： C06D5/10 , F02K9/14 , F02K9/36 , F02K9/72
摘要： A hybrid rocket motor includes a solid propellant fuel grain component which incorporates fuel strengthening agents or mechanical retention devices. In one embodiment, the hybrid fuel formulation is a modified elastomeric polyurethane reaction product based on a liquid hydroxyl-terminated homopolymer of butadiene. A reinforcing agent is added which increases the tensile and tear strength of the grain by 50%. By so strengthening the grain, separation of the grain during the last portion of the burn is minimized. In a second exemplary embodiment, mechanical web stiffeners are provided in the form of a core configuration about which the fuel grain is cast. The web stiffeners are in the form of an open tetrahexagonal truss structure which mechanically traps and adheres to the fuel and becomes an integral part of the fuel grain geometry. In both embodiments, the integrity of the webs is maintained throughout the burn. Foam slivers may be added to the radially inner ends of web stiffeners to further inhibit undesired separation during the last part of the burn.
摘要翻译：混合火箭发动机包括固体推进剂燃料颗粒组分，其包含燃料强化剂或机械保持装置。在一个实施方案中，混合燃料制剂是基于液体羟基封端的丁二烯均聚物的改性弹性体聚氨酯反应产物。添加增强剂，将增强剂的抗拉强度和撕裂强度提高了50％。通过如此加强晶粒，在烧伤的最后部分期间颗粒的分离被最小化。在第二示例性实施例中，机械腹板加强件以核心构造的形式提供，燃料颗粒围绕其配置。腹板加强件是开放的四边形桁架结构的形式，其机械地捕获并粘附到燃料上并且成为燃料颗粒几何形状的组成部分。在两个实施例中，在整个烧伤过程中保持幅材的完整性。可以将泡沫条子添加到幅材加强件的径向内端，以进一步抑制在烧伤的最后部分期间的不期望的分离。

6. 发明授权

US07484692B1 Integrated abort rocket and orbital propulsion system 有权
标题翻译：综合中止火箭和轨道推进系统
公开(公告)号：US07484692B1
公开(公告)日：2009-02-03
申请号：US10987442
申请日：2004-11-12
申请人： Bevin C. McKinney , Gary C. Hudson
发明人： Bevin C. McKinney , Gary C. Hudson
IPC分类号： B64G1/40 , B64G1/00
CPC分类号： B64G1/002 , B64G1/005 , B64G1/12 , B64G1/401 , B64G1/402 , F02K9/50
摘要： An orbital stage system has an orbital stage and one or more launch stages. The orbital stage incorporates an orbital maneuvering system (OMS) and an abort propulsion system which both utilize the same propellants, propellant tankage, and propellant pressurization system, but which employ radically different engines. The OMS engines are comprised of at least two engines which have a combined thrust in the neighborhood of 1/10 the weight of the orbital stage, an area ratio of 50 or more and an operating life of many hundred seconds, preferably many thousands of seconds or more. The abort engine may be a single engine and typically has a thrust of three, four, or more times the weight of the vehicle and an area ratio in the neighborhood of two and an operating life of at most a few tens of seconds.
摘要翻译：轨道平台系统具有轨道平台和一个或多个发射阶段。轨道舞台包括轨道机动系统（OMS）和中止推进系统，它们都使用相同的推进剂，推进剂罐和推进剂加压系统，但采用完全不同的发动机。 OMS发动机由至少两个发动机组成，其具有在轨道平台重量的1/10附近的组合推力，面积比为50或更大，并且操作寿命为几百秒，优选数千秒或者更多。中止发动机可以是单个发动机，并且通常具有车辆重量的三倍，四倍或更多倍的推力，并且在两个附近的面积比和最多几十秒的使用寿命。

7. 发明授权

US06644015B2 Turbojet with precompressor injected oxidizer 失效
公开(公告)号：US06644015B2
公开(公告)日：2003-11-11
申请号：US10029760
申请日：2001-10-29
申请人： Bevin C. McKinney
发明人： Bevin C. McKinney
IPC分类号： F02K1100
CPC分类号： F02K9/78
摘要： A turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to be matched to varying flow conditions, allowing a greater mass of air to be ingested by the compressor section and results in a lower compressor outlet temperature. Increased mass flow, combined with more fuel results in higher exhaust gas temperatures and greater thrust. The addition of oxygen to the inlet air flow allows the engine to operate at higher altitudes by preventing flameout due to rarefied air.

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