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1. 发明申请

US20170191450A1 SOLID PROPELLANT ROCKET MOTOR 审中-公开
公开(公告)号：US20170191450A1
公开(公告)日：2017-07-06
申请号：US15129396
申请日：2015-04-02
申请人： AVIO S.P.A.
发明人： Paolo Bellomi , Vincenzo Mancini
IPC分类号： F02K9/36 , F02K9/34
CPC分类号： F02K9/36 , F02K7/105 , F02K9/10 , F02K9/26 , F02K9/32 , F02K9/34 , F02K9/343 , F02K9/38 , F02K9/86 , F05D2220/80 , F05D2250/411 , F05D2260/30 , F05D2300/501
摘要： A solid propellant rocket motor (1) has a tubular casing (3) accommodating a mass (5) of solid propellant material and at least one opening (10) for the space in the casing (3) to communicate with the outside closed by a closing head (11); the closing head (11) being coupled to the casing (3) by means of one or the other of two blocking portions (28) (21A) with different strength both carried by a movement device (21,35) which can be elastically deformed and operated from the outside.

2. 发明申请

US20110314791A1 METHOD FOR COMBUSTION SYSTEM 审中-公开
标题翻译：燃烧系统方法
公开(公告)号：US20110314791A1
公开(公告)日：2011-12-29
申请号：US12823701
申请日：2010-06-25
申请人： Jeffrey D. Haynes , James T. Beals , Paul Sheedy
发明人： Jeffrey D. Haynes , James T. Beals , Paul Sheedy
IPC分类号： F02K9/00 , B05D1/36 , B05D1/12
CPC分类号： F02K9/12 , C06B21/0083 , C23C24/04 , F02K7/105 , F02K9/95 , F05D2220/10
摘要： A method of fabricating a combustion system includes cold depositing a starting material onto a substrate as a solid metal fuel to produce a combustion structure.
摘要翻译：制造燃烧系统的方法包括将起始材料作为固体金属燃料冷沉积到基底上以产生燃烧结构。

3. 发明授权

US4760695A Acoustic oscillatory pressure control for ramjet 失效
标题翻译：压路机的声振荡压力控制
公开(公告)号：US4760695A
公开(公告)日：1988-08-02
申请号：US65483
申请日：1987-06-23
申请人： Robert S. Brown , Roger Dunlap
发明人： Robert S. Brown , Roger Dunlap
IPC分类号： F02K7/10 , F02K9/26
CPC分类号： F02K7/105 , F02K9/26
摘要： The periodic shedding of vortices produced in a highly sheared gas flow, such as that encountered at the grain transition boundary in a solid propellant rocket motor or at the combustor inlet to a ramjet engine, is a significant source of acoustic instability which may result in unstarting of the ramjet engine or excessive vibration of the rocket motor. By restricting the transition boundary or combustor inlet at the sudden expansion dump plane (5), such as by locating an orifice plate (13) at the dump plane, the gas flow is separated upstream and produces a vena contracta downstream of the orifice, inhibiting the feedback of acoustic pressure to the point of flow separation and preventing the formation of organized oscillations. Incorporation of such a simple thin plate orifice at the dump plane reduces the periodic acoustic oscillations and thereby controls the detrimental oscillatory pressure fluctuations.
摘要翻译：在高度剪切的气流中产生的涡流的周期性脱落，例如在固体推进剂火箭发动机中或在燃烧器入口处在冲压喷气发动机处遇到的涡流，是声学不稳定的重要来源，这可能导致不起动的冲压发动机或火箭发动机的过度振动。通过在突出膨胀倾卸平面（5）处限制过渡边界或燃烧器入口，例如通过在排放平面处设置孔板（13），气流在上游被分离，并在孔的下游产生静脉收缩，抑制声压反馈到流动分离点，防止形成有组织的振荡。这种简单的薄板孔口在转储平面处的结合减少了周期性声振荡，从而控制了有害的振荡压力波动。

4. 发明授权

US4502649A Gun-launched variable thrust ramjet projectile 失效
标题翻译：枪式推力可变推力冲击射弹
公开(公告)号：US4502649A
公开(公告)日：1985-03-05
申请号：US495203
申请日：1983-05-16
申请人： Leo Botwin , John A. Simpson
发明人： Leo Botwin , John A. Simpson
IPC分类号： F02C7/057 , F02K7/10 , F42B10/38 , F42B15/00 , F42B15/10
CPC分类号： F02C7/057 , F02K7/105 , F42B10/38 , F42B15/00
摘要： A gun-launched ramjet projectile follows a classical vacuum ballistic trajectory by maintaining a thrust-drag balance. The thrust of the ramjet is varied by an air door which bleeds air from the duct that leads from the supersonic diffuser at the front of the projectile to the combustion chamber. The control system for the air door includes an actuator and a pair of accelerometers, the output of which is integrated to provide an indication of velocity. The first accelerometer operates during the launching of the projectile in the gun to measure the launch velocity. A second, and more sensitive, accelerometer measures in-flight velocity changes due to atmospheric conditions. Both of the measured velocities are compared with prerecorded standards and error signals are derived representing any velocity deviations. These error signals are combined and then used to drive the air doors which varies the thrust of the ramjet so that it follows the classical vacuum ballistic trajectory.
摘要翻译：喷枪式冲压射弹遵循经典的真空弹道轨迹，通过保持推力 - 阻力平衡。冲压喷气机的推力由一个空气门变化，空气门将导管的空气从喷射器前部的超音速扩散器引导到燃烧室。用于空气门的控制系统包括致动器和一对加速度计，其输出被一体化以提供速度指示。第一个加速度计在炮弹发射时测量发射速度。第二个更敏感的加速度计测量由于大气条件的飞行中速度变化。将所测量的速度与预先记录的标准进行比较，并且导出代表任何速度偏差的误差信号。将这些误差信号组合起来，然后用于驱动改变冲压喷气机推力的气门，使其符合经典的真空弹道轨迹。

5. 发明授权

US4124976A Method for reducing the critical injection parameter in a solid fuel ramjet 失效
标题翻译：降低固体燃料冲压喷气机中临界注入参数的方法
公开(公告)号：US4124976A
公开(公告)日：1978-11-14
申请号：US813044
申请日：1977-07-05
申请人： Allen L. Holzman
发明人： Allen L. Holzman
IPC分类号： F02K7/10 , F02K9/04 , F02K9/06
CPC分类号： F02K7/105 , Y10S60/917
摘要： A method and system for reducing the critical injection parameter (h/D.su) in a solid fuel ramjet (SFRJ) by using a low h/D.sub.p fuel within the recirculation region of the grain and a higher h/D.sub.p fuel for the majority of the grain to reduce the injector pressure drop, allow higher chamber pressure and higher performance and achieve flame stabilization.
摘要翻译：一种用于通过在颗粒的再循环区域内使用低h / Dp燃料来减少固体燃料冲压式喷气发动机（SFRJ）中的临界注入参数（h / Dp）的方法和系统，以及用于大多数颗粒减少喷油器压降，允许更高的室压力和更高的性能并实现火焰稳定。

6. 发明授权

US3754511A Fuel and fuel igniter for ram jet and rocket 失效
标题翻译：燃油和燃油IGNITER用于RAM喷射器和ROCKET
公开(公告)号：US3754511A
公开(公告)日：1973-08-28
申请号：US3754511D
申请日：1959-03-26
申请人： US NAVY
发明人： DAMON G , RIBOVICH J , HERICKES J
IPC分类号： F02K7/10 , F42B1/00 , F02K7/08
CPC分类号： F02K7/105 , Y10S60/917
摘要： 1. A fuel unit for forced air flow ram jet combustion chambers comprising a briquet of compressed mixed powdered oxidants and reductants, a magnesium shell encasing said briquet, and a film of plasticized nitrocellulose consisting of 25 percent by weight of alcohol-wet nitrocellulose in 75 percent by weight of Dibutylphthallate between the briquet and shell.
摘要翻译： 1.一种用于强制空气流动冲击式喷气燃烧室的燃料单元，其包括压缩的混合粉末状氧化剂和还原剂的块状物，包含所述团块的镁壳和由75重量％的75重量％的醇 - 湿硝化纤维素组成的增塑硝化纤维膜在块状和壳状物之间的二丁基 - 邻苯二甲酸酯的重量百分比。

7. 发明授权

US3004841A Jet or rocket fuel 失效
标题翻译：喷气或火箭燃料
公开(公告)号：US3004841A
公开(公告)日：1961-10-17
申请号：US81065359
申请日：1959-05-04
申请人： OHIO COMMW ENG CO
发明人： TOULMIN JR HARRY A
IPC分类号： C06B27/00 , F02C3/26 , F02K7/10 , F02K9/42
CPC分类号： C06B27/00 , F02C3/26 , F02K7/105 , F02K9/425 , Y10S149/114

8. 发明授权

US2684570A Rocket-engine and reaction-motor missile 失效
标题翻译：火箭发动机和反应运动导弹
公开(公告)号：US2684570A
公开(公告)日：1954-07-27
申请号：US16659450
申请日：1950-06-07
申请人： BOFORS AB
发明人： MARTIN NORDFORS KURT
IPC分类号： F02K7/10 , F02K7/18 , F42B15/00 , H01L39/24
CPC分类号： H01L39/2493 , F02K7/10 , F02K7/105 , F02K7/18 , F42B15/00 , Y10S60/917

9. 发明授权

US06968676B1 Propulsion from combustion of solid propellant pellet-projectiles 失效
标题翻译：固体推进剂丸粒喷射燃烧的推进
公开(公告)号：US06968676B1
公开(公告)日：2005-11-29
申请号：US10280968
申请日：2002-10-25
申请人： Vinu B. Krishnan
发明人： Vinu B. Krishnan
IPC分类号： C06B45/00 , C06B47/02 , F02C3/26 , F02K7/10 , F02K9/10 , F02K9/72 , F02K9/95
CPC分类号： F02K9/10 , C06B45/00 , C06B47/02 , F02C3/26 , F02K7/105 , F02K9/72 , F02K9/95
摘要： Propulsion from combustion of solid propellant pellet-projectiles for providing a useful propulsion that has the advantages of both solid and liquid propulsion engines, and also can make use of either solid chemical propellants or fissionable nuclear material as the fuel. Preferred methods and systems can include a storage chamber for storing solid propellant pellets, a feeding system having a pellet feeding channel and a pellet feeding mechanism connected to the storage chamber and to a gun assembly, which is positioned along a longitudinal axis to eject the pellets at a certain velocity. A triggering system positioned between gun assembly and thrust chamber can initiate the propellant pellet-projectile, and a thrust chamber having a combustion chamber for combustion of propellant pellet-projectile with an exhaust nozzle. Additionally, an auxiliary power system can be used to power the components and various electrical and electronic systems that may be present in the invention for controlling the engine components. The gun assembly may include an ejector mechanism for ejecting the propellant pellets through at least one barrel. The triggering system can produce a medium creating an ambience for the initiation of propellant pellet-projectiles. Methods and systems can be used for space and rocket crafts, turbojets and ramjets.
摘要翻译：用于提供固体和液体推进发动机优点的有用推进剂的固体推进剂丸粒 - 射弹的燃烧推进，也可以利用固体化学推进剂或可裂变核材料作为燃料。优选的方法和系统可以包括用于储存固体推进剂颗粒的储存室，具有颗粒进料通道的进料系统和连接到储存室的颗粒进料机构和沿着纵向轴线定位以喷射颗粒的喷枪组件以一定的速度。位于枪组件和推力室之间的触发系统可以启动推进剂丸粒抛射体，以及具有用于燃烧推进剂丸粒 - 抛射体与排气喷嘴的燃烧室的推力室。此外，可以使用辅助动力系统为组件以及本发明中可能存在的用于控制发动机部件的各种电气和电子系统供电。枪组件可以包括用于通过至少一个筒喷射推进剂丸粒的喷射器机构。触发系统可以产生介质，为引发推进剂丸粒射弹创造一个氛围。方法和系统可用于太空和火箭工艺，涡轮喷气发动机和雷击。

10. 发明授权

US5067406A Supersonic, low-drag, solid fuel ramjet tubular projectile 失效
标题翻译：超音速，低阻力，固体燃料冲压喷管
公开(公告)号：US5067406A
公开(公告)日：1991-11-26
申请号：US608915
申请日：1990-11-05
申请人： Donald N. Olson , Joseph Huerta
发明人： Donald N. Olson , Joseph Huerta
IPC分类号： F02K7/10 , F42B10/34
CPC分类号： F42B10/34 , F02K7/105
摘要： A low-drag supersonic tubular projectile with self-contained thrust augmetion and capable of simultaneous dual internal air flows. One is a centrally located supersonic flow for providing low-drag characteristics, and the other a subsonic flow annularly arranged about the supersonic flow path, comprising a ramjet structure with solid fuel for deriving thrust augmentation enabling the projectile to achieve a terminal velocity which is substantially the same as or exceeding muzzle velocity.
摘要翻译：一种具有独立推力增加并能够同时进行双内部空气流动的低阻力超音速管状弹丸。一个是用于提供低阻力特性的中心位置的超音速流，另一个是围绕超音速流动路径环形布置的亚音速流，包括具有固体燃料的冲压喷射结构，用于导出推力增加，使得射弹能够实现基本上等于或超过枪口速度。

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