公开(公告)号：US06688552B2

公开(公告)日：2004-02-10

申请号：US10170381

申请日：2002-06-14

申请人： Michel Franchet ,  Yann Laugier ,  Jean Loisy

发明人： Michel Franchet ,  Yann Laugier ,  Jean Loisy

IPC分类号： B64C1502

CPC分类号： F02K3/04 ,  F02C7/36 ,  F02K3/12 ,  Y02T50/671

摘要： A variable cycle propulsion system for a supersonic airplane comprises at least one engine capable of generating thrust for flight at supersonic speeds together with at least one auxiliary propulsion assembly that is separate from the engine and that is capable of generating additional thrust for takeoff, landing, and flight at subsonic speeds. The auxiliary propulsion assembly does not have a gas generator and means are provided for transmitting a fraction of the mechanical power produced by the engine to the auxiliary propulsion assembly in order to enable it to generate the additional thrust for takeoff, landing, and subsonic cruising flight. Means are provided for decoupling the mechanical transmission means for supersonic cruising flight.

摘要翻译： 用于超音速飞行器的可变循环推进系统包括至少一个能够以超声速度产生飞行的推力的发动机以及与发动机分离的至少一个辅助推进组件，并且能够产生额外的起飞，着陆， 并以亚音速飞行。 辅助推进组件没有气体发生器，并且提供了用于将由发动机产生的机械动力的一部分传递到辅助推进组件的装置，以使其能够产生用于起飞，着陆和亚音速巡航飞行的附加推力 。 提供了用于解耦用于超音速巡航飞行的机械传动装置的装置。

公开(公告)号：US06371407B1

公开(公告)日：2002-04-16

申请号：US09609484

申请日：2000-07-05

申请人： Kevin John Renshaw

发明人： Kevin John Renshaw

IPC分类号： B64C1502

CPC分类号： B64C15/02 ,  B64C29/0066

摘要： A mechanism and methods for directing the flow of exhaust gases associated with a V/STOL aircraft. A pair of constant area nozzles are associated with a plenum chamber that receives and contains exhaust gases. The nozzles are independently rotatable within circular exhaust openings in the plenum chamber to direct, or vector, exhaust exiting from the plenum chamber in preselected directions such as vertically downward or directions forward or aft of the vertical plane.

摘要翻译： 用于引导与V / STOL飞机相关的废气流的机构和方法。 一对恒定面积的喷嘴与容纳和包含废气的增压室相关联。 这些喷嘴可以在通风室中的圆形排气开口内独立地旋转，以引导或向量排出从预压方向（例如垂直向下或垂直平面的前后方向）排出的排气室。

公开(公告)号：US06591603B2

公开(公告)日：2003-07-15

申请号：US09802002

申请日：2001-03-08

申请人： Gordon A. Dressler ,  Thomas J. Mueller ,  Scott J. Rotenberger

发明人： Gordon A. Dressler ,  Thomas J. Mueller ,  Scott J. Rotenberger

IPC分类号： B64C1502

CPC分类号： F02K9/52 ,  F02K9/972

摘要： The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A propellant injector (20) is in fluid communication between a propellant line and an inside periphery of the combustion chamber injector end (14). A nozzle throat (18) is formed at the nozzle end (14) of the combustion chamber (12). A nozzle exit cone (22) extends outwardly from the nozzle throat (18). A plug support (30) is coupled between a nozzle plug (28) and the propellant injector (20). The nozzle plug (28) aerodynamically self-compensates for changes in ambient backpressure at the nozzle exit cone (22) such that the nozzle thrust coefficient is maximized for any ambient backpressure.

摘要翻译： 本发明提供了一种火箭发动机（10），其对于改变环境背压的喷嘴推力系数进行自补偿。 火箭发动机（10）包括具有喷射器端（14）和喷嘴端（16）的燃烧室（12）。 推进剂喷射器（20）在推进剂管线和燃烧室喷射器端部（14）的内周边之间流体连通。 在燃烧室（12）的喷嘴端（14）处形成喷嘴喉（18）。 喷嘴出口锥体（22）从喷嘴喉部（18）向外延伸。 插头支撑件（30）联接在喷嘴塞（28）和推进剂喷射器（20）之间。 喷嘴塞（28）在空气动力学上自我补偿喷嘴出口锥体（22）处的环境背压的变化，使得喷嘴推力系数对于任何环境背压最大化。

公开(公告)号：US06318668B1

公开(公告)日：2001-11-20

申请号：US09246426

申请日：1999-02-08

申请人： Michael S. Ulanoski ,  Jagdish S. Sokhey ,  Baily R. Vittal ,  Von D. Baker

发明人： Michael S. Ulanoski ,  Jagdish S. Sokhey ,  Baily R. Vittal ,  Von D. Baker

IPC分类号： B64C1502

CPC分类号： B64C29/0058 ,  B64C29/0066 ,  F01D17/162 ,  F02K1/002 ,  F02K1/006 ,  F02K3/025 ,  Y02T50/672

摘要： A thrust directing mechanism to vector thrust and control discharge throat area with a number of vanes mounted across the passage. The mechanism includes a control link pivotally coupled to each of the vanes. The control link is selectively movable to correspondingly pivot the vanes and has at least two degrees of freedom corresponding to a two coordinate position. A desired orientation of the vanes may be determined as a function of the two coordinate position. The discharge exit area is contracted by adjusting convergence of the vanes. During convergence, the vanes are pivoted to various pivot angles selected to optimize thrust efficiency when contracting the throat area.

摘要翻译： 一个推力引导机构，用于矢量推力和控制排放喉部区域，并安装了跨越通道的多个叶片。 该机构包括枢转地联接到每个叶片的控制连杆。 控制链路可选择性地可移动以相应地枢转叶片并且具有至少两个对应于两个坐标位置的自由度。 可以根据两个坐标位置来确定叶片的期望取向。 排出口区域通过调整叶片的收敛而收缩。 在收敛期间，叶片枢转到各种枢转角度，以在收缩喉部区域时优化推力效率。