公开(公告)号：US5422443A

公开(公告)日：1995-06-06

申请号：US80601

申请日：1993-06-24

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: B64F1/26 ,  F02K9/92 ,  F02K9/96

CPC classification number: F02K9/96 ,  B64F1/26 ,  F02K9/92 ,  Y10T137/87652

Abstract: Apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A pair of wedge-shaped pieces comprise a disrupter positioned on opposite sides of the central longitudinal axis of the rocket exhaust plume in order to disrupt and disperse the plume concentration. The positioning of these pieces is such that at least a portion of the exhaust gas plume may pass between them. The disrupter defines a flow area normal to the central axis of the exhaust flow which is less than the cross sectional area of the exhaust plume at the position of the disrupter pieces. The reduced flow area causes the exhaust flow to undergo a normal shock wave adjacent the position of the disrupter device before the exhaust gases pass between the disrupter body pieces at subsonic velocity. The presence and configuration of the disrupter device disrupts and disperses the plume concentration, and the reduced flow velocity significantly reduces downstream pressure and thermal effects of the exhaust gas plume.

Abstract translation: 用于降低从火箭发动机喷嘴发出的超音速废气羽流的压力和热冲击效应的装置。 一对楔形件包括位于火箭排气羽流的中心纵向轴线的相对侧上的扰流器，以便破坏和分散羽流浓度。 这些零件的定位使得废气羽流的至少一部分可以在它们之间通过。 破坏器限定了与排气流的中心轴线垂直的流动区域，该流动区域小于在破碎器件的位置处的排气羽流的横截面面积。 减少的流动面积导致废气流在邻近破坏器装置的位置之前经历正常的冲击波，然后废气以亚音速通过破碎体体部件。 破坏装置的存在和配置破坏和分散羽流浓度，并且减小的流速显着降低排气烟羽的下游压力和热效应。

公开(公告)号：US4545284A

公开(公告)日：1985-10-08

申请号：US489876

申请日：1983-04-29

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F41F3/04 ,  F41F7/00

CPC classification number: F41F3/0406

Abstract: Apparatus for preventing a missile's rocket exhaust gases from contacting and adversely affecting, such as by overheating, the launch rails from which a missile may be launched. Such apparatus includes an angled member having first and second leg portions, the end of the first leg portion being pivotably secured to the rail. A member having an angled surface is mounted to the second leg portion. Prior to the launching of said missile, the apparatus is in a first operative position such that it is out of contact with said launch rail. When the exhaust gases are emitted from said missile, a portion of the exhaust is incident upon the angled surface which causes the apparatus to rotatably pivot into contact with the launch rail, whereby portions of two surfaces of the launch rail are protected from the exhaust. In alternative arrangements, springs or counterweights are provided to hold the protective apparatus open to facilitate loading of a missile on the launch rails while permitting the apparatus to close around the rails when the missile is being launched. Other arrangements provide for translation as well as rotation of a pair of angled members in a clam shell configuration for protection of particularly shaped launch rails.

Abstract translation: 用于防止导弹的火箭废气接触并不利地影响（例如由于过热）可以发射导弹的发射轨的装置。 这种装置包括具有第一和第二腿部的倾斜构件，第一腿部的端部可枢转地固定到轨道。 具有倾斜表面的构件安装到第二腿部。 在发射所述导弹之前，所述装置处于第一操作位置，使得其与所述发射轨道不接触。 当废气从所述导弹发射时，排气的一部分入射到成角度的表面上，这使得装置可旋转地枢转成与发射轨接触，由此将发射轨的两个表面的一部分保护不被排放。 在替代布置中，提供弹簧或配重以将保护装置保持开放以便于在发射导轨上装载导弹，同时允许装置在导弹发射时围绕导轨关闭。 其他布置提供翻转以及以蛤壳构造的一对倾斜构件的旋转，以保护特别形状的发射轨。

公开(公告)号：US4373420A

公开(公告)日：1983-02-15

申请号：US194533

申请日：1980-10-06

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F41F3/04

CPC classification number: F41F3/0413

Abstract: Method and apparatus for preventing combustion of exhaust gases in rocket launch systems using a plurality of launch tubes connected to a plenum including pressure sensors in each launch tube, a control system sensitive to atmospheric pressure and launch tube pressure which provides a signal to an inert gas supply flow controller to initiate flow of gas into the plenum when pressure in a launch tube, after launch of a rocket, reaches a predetermined level.

Abstract translation: 使用连接到包括每个发射管中的压力传感器的增压室的多个发射管来防止火箭发射系统中的废气燃烧的方法和装置，对大气压敏感的控制系统和向惰性气体提供信号的发射管压力 供应流量控制器以在发射管中的发射管中的压力达到预定水平之后启动气体流入气室。

公开(公告)号：US5136922A

公开(公告)日：1992-08-11

申请号：US698696

申请日：1991-05-13

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F41A13/00 ,  F41F3/04 ,  F41F3/077

CPC classification number: F41F3/0413

Abstract: An exhaust gas management system for missile launch arrangements having multiple launch cells exhausting into a common plenum includes automatic aft closure members which serve to close off the flow passages to inactive cells while providing an open passage for exhaust gases from an active cell undergoing a missile firing. This arrangement prevents back flow or recirculation of exhaust gases into the volume in the cell which is upstream of the rocket nozzle exit.

公开(公告)号：US4733751A

公开(公告)日：1988-03-29

申请号：US814138

申请日：1985-12-27

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: B64F1/26 ,  F02K9/96

CPC classification number: F02K9/96 ,  B64F1/26

Abstract: An apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A disrupter body positioned within the exhaust plume along the central longitudinal axis thereof disrupts and disperses the plume concentration. The body has a central passage through which a portion of the exhaust may pass. The body and passage are sized and shaped to provide a flow area normal to the exhaust flow less than the cross-sectional area of the exhaust plume at the position of the body. The reduced flow area causes the exhaust flow to undergo a normal shock wave upstream of the body before passing through and around the body at a subsonic velocity. The presence and configuration of the body disrupts and disperses the plume concentration, and the reduced flow velocity significantly reduces the downstream pressure and thermal effects of the exhaust gas plume.

Abstract translation: 一种用于降低从火箭发动机喷嘴发出的超音速废气羽流的压力和热冲击效应的装置。 沿着中心纵向轴线位于排气羽流内的破坏器主体破坏和分散羽流浓度。 主体具有中央通道，排气的一部分可以通过该通道。 主体和通道的尺寸和形状被设计成在身体的位置处提供与排气羽流的横截面面积小于排气流的流动面积。 减小的流动面积导致排气流在身体之前和之后以亚音速通过身体前方的正常冲击波。 身体的存在和结构破坏和分散羽流浓度，并且减小的流速显着降低排气烟羽的下游压力和热效应。

公开(公告)号：US4685533A

公开(公告)日：1987-08-11

申请号：US814139

申请日：1985-12-27

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F01N1/08 ,  F02K1/40 ,  F02K9/96 ,  F02K9/97 ,  F02K1/44

CPC classification number: F02K1/40 ,  F01N1/08 ,  F02K9/96 ,  F02K9/97 ,  F01N2470/14 ,  F01N2470/18 ,  F01N2470/30 ,  F01N2490/16

Abstract: An exhaust dissipator device for a rocket exhaust has an inlet for connection to the exhaust and a plurality of smaller exhaust orifices spaced around its surface to dissipate the flow into a plurality of smaller jets. A deflector surface in the direction of exhaust flow into the container acts to further dissipate the flow and deflect it out of its original path. This may comprise an internal surface of the container, or a separate deflector plate spaced from the container surface.

Abstract translation: 用于火箭排气的排气消散器装置具有用于连接到排气口的入口和在其表面上间隔开的多个较小的排气孔，以将流分解成多个较小的喷射。 排气流入容器方向的偏转器表面用于进一步消散流动并使其偏离其原始路径。 这可以包括容器的内表面或与容器表面间隔开的单独的导流板。

公开(公告)号：US4134327A

公开(公告)日：1979-01-16

申请号：US860039

申请日：1977-12-12

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F41F3/04 ,  F41F3/077

CPC classification number: F41F3/077 ,  F41F3/0413

Abstract: A rear door for a rocket launch tube provided to prevent rocket exhaust gas flow into an empty launch tube from an associated multiple-rocket plenum chamber. The door is maintained in a stored position while a missile is in the launch tube and is activated when the missile leaves the launcher. The door may be latched open and released by a sensor device at a selected position of the missile as it is leaving the launch tube. Preferably, gases from the launching missile power closure of the door, once the door is released from its open latched position. Once the door closes, a second latch locks it in place to seal off the launch tube from the plenum chamber.

Abstract translation: 用于火箭发射管的后门，用于防止火箭废气从相关联的多火箭增压室流入空的发射管。 当导弹在发射管中时，门保持在存储位置，并且当导弹离开发射器时被激活。 当导弹离开发射管时，门可以被锁定在导弹的选定位置处由传感器装置释放。 优选地，一旦门从其打开的锁定位置释放，来自门的发射导弹动力闭合的气体。 一旦门关闭，第二个闩锁将其锁定就位，以将发射管从增压室密封。

公开(公告)号：US4796510A

公开(公告)日：1989-01-10

申请号：US118674

申请日：1987-11-09

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F41F3/04 ,  F41F3/073

CPC classification number: F41F3/0413 ,  F41F3/073

Abstract: A rocket exhaust recirculation obturator or cover member is designed to extend across the base of a missile in a launch tube between the exit nozzle of the missile rocket exhaust and the walls of the launch tube. The cover member has a central opening which seals against the rocket motor nozzle exit, and an outer periphery which seals against the launch tube walls. During launch, pressure of exhaust gases recirculating back up the launch tube will urge the obturator against the base of the missile, and both the missile and obturator will accelerate together up the launch tube. A release assembly is provided at the upper end of the launch tube which engages corresponding release devices at the outer periphery of the obturator. The engagement releases the pressure bond between the obturator, the missile base, and the launch tube. This allows the rocket exhaust to impinge upon the upper surface of the obturator in opposition to the obturator's momemtum. The exhaust impingement forces the obturator back down the launch tube, eliminating debris outside the launch tube.

Abstract translation: 火箭排气再循环闭塞器或盖构件被设计成在导弹火箭排气口的出口喷嘴与发射管的壁之间的发射管中延伸穿过导弹的基座。 盖构件具有密封抵靠火箭发动机喷嘴出口的中心开口和密封发射管壁的外周。 在发射期间，再循环发射管的废气压力将促使闭孔器抵靠导弹的基部，导弹和闭孔器将一起加速发射管。 释放组件设置在发射管的上端，其接合在闭塞器的外周边处的相应释放装置。 接合释放了闭孔器，导弹座和发射管之间的压力。 这允许火箭排气与闭塞器的母体相反地撞击闭塞器的上表面。 排气冲击迫使闭塞器向下推动发射管，消除发射管外的碎片。

公开(公告)号：US4686884A

公开(公告)日：1987-08-18

申请号：US813906

申请日：1985-12-27

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F41F3/04

CPC classification number: F41F3/0413

Abstract: Pivotable deflector panels are installed in the transition sections between a plurality of rocket storage and launch chambers and a lower plenum or manifold chamber which is provided to dispose of the exhaust gases from missile firings. The deflector panels are in addition to the sets of doors which are provided to close off the missile storage chambers upon the firing of a missile in another chamber in order to prevent recirculation of exhaust gases into the closed off chambers. The deflector panels act with the doors to control exhaust gas flow, thereby improving the effectiveness of the gas plug which is formed by exhaust gases within a transition section.

Abstract translation: 枢轴转向板安装在多个火箭储存和发射室之间的过渡部分中，以及设置成处理来自导弹发射的废气的下部增压室或歧管室。 偏转板是除了设置成在另一个室中的导弹发射之后关闭导弹存储室以防止废气再循环到封闭的室中的门组之外的。 偏转板与门一起作用以控制排气流动，从而提高由过渡段内的废气形成的气塞的有效性。

公开(公告)号：US4327624A

公开(公告)日：1982-05-04

申请号：US162290

申请日：1980-06-23

Applicant: Edward T. Piesik

Inventor： Edward T. Piesik

IPC: F41A21/36 ,  F41F3/045 ,  F41F3/04

CPC classification number: F41F3/0455 ,  F41A21/36

Abstract: Disclosed is a launcher-missile system with the launcher tube provided with a configuration on its aft end so as to reduce the tip-off rates of the system. The configuration comprises the formation of an open sector in the flared end of the launcher tube so that a portion of the exhaust gases exiting from the tube, as the missile is fired, does not impinge on that sector of the flared end and thus an impulse caused by the impinging of the gases on the remainder of the flared end reduces the tip-off rate.Also disclosed is a means in which the size and location of the open sector can be selected depending upon the desired change in magnitude and direction of the tip-off rate.

Abstract translation: 公开了一种发射导弹系统，其发射管在其后端具有一个配置，以便降低系统的提升速率。 该构造包括在发射管的扩口端中形成开放扇区，使得当作为导弹被点燃时从管中排出的废气的一部分不会撞击扩口端的该扇区，因此冲击 由于气体在其余的扩口上的撞击引起的减少了脱落率。 还公开了一种装置，其中可以根据期望的切断速率的大小和方向的变化来选择开放扇区的大小和位置。