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1. 发明授权

US5927653A Two-stage reusable earth-to-orbit aerospace vehicle and transport system 失效
标题翻译：两级可重用地球对轨道航空航天车辆和运输系统
公开(公告)号：US5927653A
公开(公告)日：1999-07-27
申请号：US632786
申请日：1996-04-17
申请人： George E. Mueller , Walter P. Kistler , Thomas G. Johnson , Henry O. Pohl , Chris McLain , Allan S. Hill , Jason E. Andrews , Thomas C. Taylor , Aaron Cohen , Dale Myers , Adam P. Bruckner , Steven C. Knowles , Richard Warwick
发明人： George E. Mueller , Walter P. Kistler , Thomas G. Johnson , Henry O. Pohl , Chris McLain , Allan S. Hill , Jason E. Andrews , Thomas C. Taylor , Aaron Cohen , Dale Myers , Adam P. Bruckner , Steven C. Knowles , Richard Warwick
IPC分类号： B64G1/00 , B64G1/14 , B64G1/40 , B64G1/62 , B64G1/64 , B64G5/00
CPC分类号： B64G1/401 , B64G1/14 , B64G1/402 , B64G1/62 , B64G1/641 , B64G5/00
摘要： A two-stage wingless reusable aerospace vehicle having upper and lower stages that take off from a take-off area and separate at a separation point along a first trajectory. The separation forces are generated by air retained between the upper and lower stages, which is at a pressure higher than ambient pressure at the separation point. The lower stage is then propelled along a return trajectory to a landing area. After separation from the lower stage, the upper stage continues to an Earth orbit for deployment of a payload. After deploying the payload, the upper stage moves out of the Earth orbit, re-enters the Earth's atmosphere, and returns to the take-off and landing area. The upper and lower stages are powered by liquid oxygen and kerosene engines. The aerospace vehicle is transported to a take-off area by a transport vehicle having a first fixed carriage and a second translatable carriage that is adapted to move the upper stage relative to the lower stage for assembly of the aerospace vehicle while in the horizontal position. The transport vehicle then pivots the aerospace vehicle from the horizontal to the vertical position for launching.
摘要翻译：一种两级无翼可重复使用的航空航天器，具有从起飞区域起飞并且沿着第一轨迹在分离点分离的上段和下段。分离力由保持在上部和下部之间的空气产生，其处于高于分离点处的环境压力的压力。然后，下阶段沿着返回轨迹被推进到着陆区域。在与下级分离之后，上级继续到地球轨道，用于部署有效载荷。部署有效载荷后，上级移出地球轨道，重新进入地球大气层，返回起飞和着陆区域。上层和下层由液氧和煤油发动机提供动力。航空航天车辆通过具有第一固定支架和第二可平移滑架的运输车辆被运送到起飞区域，该第二可平移滑架适于在水平位置组装航空航天器时相对于下部台阶移动。然后，运输车辆将航空航天器从水平轴枢转到用于发射的垂直位置。

2. 发明授权

US4727930A Heat transfer and storage system 失效
标题翻译：传热和储存系统
公开(公告)号：US4727930A
公开(公告)日：1988-03-01
申请号：US293196
申请日：1981-08-17
申请人： Adam P. Bruckner , Abraham Hertzberg , David J. Shaw
发明人： Adam P. Bruckner , Abraham Hertzberg , David J. Shaw
IPC分类号： F02C1/05 , F02C1/10 , F02C6/14 , F03G6/06 , F24S20/20 , F28C3/14 , F28D20/00 , F28D19/02
CPC分类号： F24J2/07 , F02C1/05 , F02C1/10 , F02C6/14 , F03G6/064 , F24J2/4649 , F28C3/14 , F28D20/0056 , F28D2020/006 , Y02E10/41 , Y02E10/46 , Y02E60/142 , Y02E70/30
摘要： An energy storage and conversion system utilizes unique heat exchange media for storing and transferring heat. In one embodiment, a refractory material is heated to the molten state by a solar furnace. The refractory material is stored in its molten form and metered to a direct-contact heat exchanger. It is fed into the heat exchanger in a plurality of streams that break into a plurality of droplets. The droplets flow through the heat exchanger in countercurrent relationship with a relatively inert gas such as argon or nitrogen. The gas is heated and expanded through an expansion engine to convert the thermal energy to mechanical energy which in turn can be utilized to produce electricity, for example. The refractory can be sufficiently cooled in the heat exchanger to fuse into beads, which can be easily recycled to the solar furnace.
摘要翻译：能量储存和转换系统利用独特的热交换介质来储存和传递热量。在一个实施例中，通过太阳能炉将耐火材料加热至熔融状态。耐火材料以其熔融形式储存并计量加入直接接触热交换器。它以多个流进入热交换器，其分成多个液滴。液滴与相对惰性气体如氩气或氮气呈逆流关系流过热交换器。气体通过膨胀发动机被加热和膨胀，以将热能转化为机械能，其又可以用于产生电。耐火材料可以在热交换器中充分冷却以熔化成珠，这可以容易地再循环到太阳能炉中。

3. 发明授权

US4938112A Apparatus and method for the acceleration of projectiles to hypervelocities 失效
标题翻译：将射弹加速到高空的装置和方法
公开(公告)号：US4938112A
公开(公告)日：1990-07-03
申请号：US946439
申请日：1986-12-23
申请人： Abraham Hertzberg , Adam P. Bruckner , David W. Bogdanoff
发明人： Abraham Hertzberg , Adam P. Bruckner , David W. Bogdanoff
IPC分类号： F41A1/02
CPC分类号： F41A1/02
摘要： A projectile is initially accelerated to a supersonic velocity and then injected into a launch tube filled with a gaseous propellant. The projectile outer surface and launch tube inner surface form a ramjet having a diffuser, a combustion chamber and a nozzle. A catalytic coated flame holder projecting from the projectile ignites the gaseous propellant in the combustion chamber thereby accelerating the projectile in a subsonic combustion mode zone. The projectile then enters an overdriven detonation wave launch tube zone wherein further projectile acceleration is achieved by a formed, controlled overdriven detonation wave capable of igniting the gaseous propellant in the combustion chamber. Ultrahigh velocity projectile accelerations are achieved in a launch tube layered detonation zone having an inner sleeve filled with hydrogen gas. An explosive, which is disposed in the annular zone between the inner sleeve and the launch tube, explodes responsive to an impinging shock wave emanating from the diffuser of the accelerating projectile thereby forcing the inner sleeve inward and imparting an acceleration to the projectile. For applications wherein solid or liquid high explosives are employed, the explosion thereof forces the inner sleeve inward, forming a throat behind the projectile. This throat chokes flow behind, thereby imparting an acceleration to the projectile.
摘要翻译：抛射体最初被加速到超音速，然后注入到装有气体推进剂的发射管中。射弹外表面和发射管内表面形成具有扩散器，燃烧室和喷嘴的冲压喷气发动机。从抛射体突出的催化涂层火焰保持器点燃燃烧室中的气体推进剂，从而在亚音速燃烧模式区域加速射弹。然后射弹进入过驱动的爆轰波发射管区域，其中通过能够点燃燃烧室中的气体推进剂的形成的受控过驱动爆震波来实现进一步的射弹加速。在具有填充有氢气的内套筒的发射管分层爆轰区中实现超高速射弹加速度。设置在内套筒和发射管之间的环形区域中的爆炸物响应于从加速抛射体的扩散器发出的冲击波，从而迫使内套筒向内并对射弹施加加速度。对于使用固体或液体高爆炸物的应用，其爆炸迫使内套筒向内，在射弹后面形成喉部。这个喉咙阻塞在后面，从而赋予射弹加速度。

4. 发明授权

US5097743A Method and apparatus for zero velocity start ram acceleration 失效
标题翻译：用于零速起动压头加速的方法和装置
公开(公告)号：US5097743A
公开(公告)日：1992-03-24
申请号：US628420
申请日：1990-12-14
申请人： Abraham Hertzberg , Adam P. Bruckner , Carl Knowlen , Keith A. McFall
发明人： Abraham Hertzberg , Adam P. Bruckner , Carl Knowlen , Keith A. McFall
IPC分类号： F41A1/02
CPC分类号： F41A1/02
摘要： A method and apparatus for initiating a ram acceleration of a projectile that is at rest. A projectile (34) is positioned in a starting chamber (14) of a launch tube (12). Starting chamber (14) is either filled with a gas at a relatively low pressure or is substantially evacuated. A wave reflection disk (42/42') is positioned a short distance behind the projectile. Downstream of the starting chamber are a plurality of segments, including a first segment (16), which is filled with a combustible gas mixture at a substantially higher pressure than that in the starting chamber. The first segment is separated from the starting chamber by a pair of thin membranes (20a and 20b). These membranes have a characteristic burst pressure that is about midway between the differential pressure in the first segment and the starting chamber. To initiate the ram acceleration process, fluid between the two membranes is exhausted to the atmosphere, sequentially exposing them to a differential pressure that exceeds their burst pressure. Bursting of these membranes enables the combustible gas mixture to expand unsteadily from the first segment into the starting chamber. An expansion wave produced by the expanding combustible gas mixture passes the projectile and reflects from the wave reflection disk as a shock wave. The wave reflection disk converts the kinetic energy of the expanding gas into thermal energy, at a temperature sufficient to initiate combustion of the mixture. The shock wave propagates downstream from the wave reflection disk, attaches to the projectile, and establishes a stable, thermally choked ram acceleration of the projectile down the launch tube. As the combustible gas mixture burns behind the projectile, the resulting pressure wave accelerates the projectile down the bore of the tube into successive combustible gas-filled segments.
摘要翻译：一种用于启动静止的弹丸的冲压加速的方法和装置。射弹（34）位于发射管（12）的起动室（14）中。起始室（14）或者填充有相对较低压力的气体或基本排空。波浪反射盘（42/42'）位于射弹后面很短距离。起动室的下游是多个段，包括第一段（16），其以比起动室中的压力明显更高的压力填充可燃气体混合物。第一段通过一对薄膜（20a和20b）与起始室分开。这些膜具有大约在第一段中的压差和起始室之间的中间的特征性爆破压力。为了启动压头加速过程，两个膜之间的流体排放到大气中，依次将它们暴露于超过其爆破压力的压差。这些膜的破裂使得可燃气体混合物从第一段不稳定地扩展到起始室。由膨胀的可燃气体混合物产生的膨胀波通过射弹并从波反射盘反射为冲击波。波形反射盘在足以引发混合物燃烧的温度下将膨胀气体的动能转换成热能。冲击波从波浪反射盘的下游传播，附着在抛射体上，并在发射管下方建立稳定的热扼流器加速度的弹丸。当可燃气体混合物在射弹后面燃烧时，所产生的压力波将射弹从管的孔向下加速成连续的可燃气体填充段。

5. 发明申请

US20190195579A1 BAFFLED-TUBE RAM ACCELERATOR 审中-公开
公开(公告)号：US20190195579A1
公开(公告)日：2019-06-27
申请号：US16165687
申请日：2018-10-19
申请人： Carl Knowlen , Adam P. Bruckner , Andrew J. Higgins , Viggo Hansen
发明人： Carl Knowlen , Adam P. Bruckner , Andrew J. Higgins , Viggo Hansen
IPC分类号： F41A1/02 , F41F1/00
CPC分类号： F41A1/02 , F41F1/00 , F41F3/00
摘要： A baffled ram accelerator system includes a ram accelerator tube with an inner surface and an outer surface and a plurality of baffles disposed on the inner surface. The plurality of baffles forms a sequential series of propellant chambers along the longitudinal axis of the ram accelerator tube. An accelerator gun is also disposed on an input end of the ram accelerator tube, and the accelerator gun is positioned to fire a projectile into the ram accelerator tube.

6. 发明授权

US4982647A Method and apparatus for initating stable operation of a ram accelerator 失效
标题翻译：用于启动冲压加速器稳定运行的方法和装置
公开(公告)号：US4982647A
公开(公告)日：1991-01-08
申请号：US207706
申请日：1988-06-16
申请人： Abraham Hertzberg , Adam P. Bruckner , David W. Bogdanoff , Carl Knowlen
发明人： Abraham Hertzberg , Adam P. Bruckner , David W. Bogdanoff , Carl Knowlen
IPC分类号： F41A1/04 , F42B35/00
CPC分类号： F41A1/04 , F42B35/00
摘要： A method and apparatus for supersonically accelerating a projectile in a thermally choked subsonic combustion mode. A projectile (50) is initially preaccelerated using either a tank (24) of compressed helium or a chemical propellant charge preaccelerator (152). The projectile enters a portion of a tube (22) filled with a combustible mixture (54) of a gaseous fuel and an oxidizer and is propelled by a ram acceleration process as the mixture burns. In several different embodiments, various devices are used to control the velocity of a shock wave generated as the projectile enters the combustible mixture and the dynamic impulse pressure immediately behind the projectile, so that the shock wave attaches to the projectile along an aft portion, thereby establishing a stable subsonic combustion zone along the aft end (64) of the projectile, in which combustion of the gaseous fuel accelerates the projectile down the bore of the tube. In one embodiment, a perforated sabot (52) is used to propel the projectile during preacceleration. The sabot has a plurality of passages (114) extending longitudinally between its front and rear surfaces, which are initially closed with a thin plate (110) during the preacceleration of the projectile. However, the plate is dislodged as the projectile enters the combustible mixture, allowing the dynamic pressure of the shock wave caused by the sabot to dissipate through the open passages.
摘要翻译：一种用于在热窒息的亚音速燃烧模式下超弹加速射弹的方法和装置。最初使用压缩氦气罐（24）或化学推进剂充电预加速器（152）对射弹（50）进行预加速。弹丸进入填充有气体燃料和氧化剂的可燃混合物（54）的管（22）的一部分，并随着混合物燃烧而通过冲压加速过程推进。在几个不同的实施例中，使用各种装置来控制当射弹进入可燃混合物时产生的冲击波的速度和紧随射弹的动态脉冲压力，使得冲击波沿着后部附接到射弹，从而沿着射弹的后端（64）建立稳定的亚音速燃烧区，其中气体燃料的燃烧将射弹沿管的孔加速。在一个实施例中，穿孔式炮（52）用于在预加速期间推进射弹。该膛具有在其前表面和后表面之间纵向延伸的多个通道（114），其在弹丸预加速期间由薄板（110）开始封闭。然而，当弹丸进入可燃混合物时，板被移动，允许由破坏引起的冲击波的动态压力通过开放通道消散。

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