-
公开(公告)号：US06308408B1
公开(公告)日：2001-10-30
申请号：US09690123
申请日：2000-10-05
IPC分类号： B23P1500
CPC分类号： F02K9/62 , F02K9/974 , Y10T29/49346 , Y10T29/49885 , Y10T29/49982
摘要： An integral, lightweight combustion chamber/nozzle assembly for a rocket engine has a refractory metal shell defining a chamber of generally frusto-conical contour. The shell communicates at its smaller end with a rocket body, and terminates at its larger end in a generally contact contour, which is open at its terminus and which serves as a nozzle for the rocket engine. The entire inner surface of the refractory metal shell has a thermal and oxidation barrier layer applied thereto. An ablative silica phenolic insert is bonded to the exposed surface of the thermal and oxidation barrier layer. The ablative phenolic insert provides a chosen inner contour for the combustion chamber and has a taper toward the open terminus of the nozzle. A process for fabricating the integral, lightweight combustion chamber/nozzle assembly is simple and efficient, and results in economy in respect of both resources and time.
摘要翻译： 用于火箭发动机的整体轻质的燃烧室/喷嘴组件具有限定大致截头圆锥形轮廓的腔室的难熔金属壳体。 壳体的较小端部与火箭体连通，并且在其较大端部以大致接触的轮廓终止，轮廓在其终点处是开放的，并且用作火箭发动机的喷嘴。 难熔金属壳体的整个内表面具有施加到其上的热和氧化阻挡层。 烧蚀的二氧化硅酚醛嵌段结合到热和氧化阻挡层的暴露表面。 烧蚀性酚醛树脂插入件为燃烧室提供了选定的内部轮廓，并且具有朝向喷嘴的开口端的锥形。用于制造整体轻质燃烧室/喷嘴组件的方法简单而有效，并且导致经济性 资源和时间。
-
公开(公告)号：US5412981A
公开(公告)日：1995-05-09
申请号：US117587
申请日：1993-09-07
CPC分类号： F02M65/00
摘要： An apparatus for testing and evaluating the spray pattern of high pressure fuel injector elements for use in supplying fuel to combustion engines. Prior art fuel injector elements were normally tested by use of low pressure apparatuses which did not provide a purge to prevent mist from obscuring the injector element or to prevent frosting of the view windows; could utilize only one fluid during each test; and had their viewing ports positioned one hundred eighty (180.degree.) apart, thus preventing optimum use of laser diagnostics. The high pressure fluid injector test apparatus includes an upper hub, an upper weldment or housing, a first clamp and stud/nut assembly for securing the upper hub to the upper weldment, a standoff assembly within the upper weldment, a pair of window housings having view glasses within the upper weldment, an injector block assembly and purge plate within the upper weldment for holding an injector element to be tested and evaluated, a lower weldment or housing, a second clamp and stud/nut assembly for securing the lower weldment to the upper weldment, a lower hub, a third clamp and stud/nut assembly for securing the lower hub to the lower weldment, mechanisms for introducing fluid under high pressure for testing an injector element, and mechanisms for purging the apparatus to prevent frosting of view glasses within the window housings and to permit unobstructed viewing of the injector element.
摘要翻译： 一种用于测试和评估用于向燃烧发动机供应燃料的高压燃料喷射器元件的喷射模式的装置。 现有技术的燃料喷射器元件通常通过使用不提供吹扫以防止雾遮挡喷射器元件或防止视窗结霜的低压设备来测试; 每次测试中只能使用一种流体; 并且它们的观察端口位于距离180°（180°）的位置，从而防止最佳地使用激光诊断。 高压流体注射器测试装置包括上部轮毂，上部焊件或壳体，用于将上部轮毂固定到上部焊件的第一夹具和螺栓/螺母组件，上部焊件内的支座组件，一对窗口壳体， 在上部焊件内观察玻璃，在上部焊件内的用于保持要测试和评估的注射器元件的喷射器组件和吹扫板，下部焊件或壳体，第二夹具和螺柱/螺母组件，用于将下部焊件固定到 上部焊接件，下部轮毂，第三夹具和用于将下部轮毂固定到下部焊件的螺柱/螺母组件，用于在高压下引入流体以测试喷射器元件的机构，以及用于清洁设备以防止观察眼镜结霜的机构 在窗户外壳内，并且能够不间断地观察注射器元件。
-
公开(公告)号：US06330792B2
公开(公告)日：2001-12-18
申请号：US09747979
申请日：2000-12-22
申请人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
发明人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
IPC分类号： F02K900
CPC分类号： F02K9/974 , B29C53/585 , B29L2031/3097 , F02K9/62 , F02K9/97 , Y10S60/909
摘要： A thrust chamber assembly for liquid fueled rocket engines and the method of making it wherein a two-piece mandrel wrapped with a silica tape saturated with a phenolic resin, the tape extending along the mandrel and covering the combustion chamber portion of the mandrel to the throat portion. The phenolic in the tape is cured and the end of the wrap is machined. The remainder of the mandrel is wrapped with a third silica tape. The resin in the third tape is cured and the assembly is machined. The entire assembly is then wrapped with a tow of graphite fibers wetted with an epoxy resin and, after the epoxy resin is cured, the graphite is machined to final dimensions.
摘要翻译： 用于液体燃料火箭发动机的推力室组件及其制造方法，其中包裹有用酚醛树脂饱和的二氧化硅胶带的两件式心轴，所述带沿心轴延伸并将心轴的燃烧室部分覆盖至喉部 一部分。 胶带中的酚醛固化，并且机器的末端被加工。 心轴的其余部分用第三个硅胶带包裹。 第三带中的树脂被固化并且组装被加工。 然后将整个组件用用环氧树脂润湿的石墨纤维丝束包裹，并且在环氧树脂固化之后，将石墨加工成最终尺寸。
-
公开(公告)号：US06845605B1
公开(公告)日：2005-01-25
申请号：US10288800
申请日：2002-11-04
CPC分类号： F02K9/95
摘要： An ignitor for use with the MC-1 rocket engine has a cartridge bounded by two end caps with rupture disc assemblies connected thereto. A piston assembly within the cartridge moves from one end of the cartridge during the ignition process. The inlet of the ignitor communicates with a supply taken from the discharge of the fuel pump. When the pump is initially started, the pressure differential bursts the first rupture disc to begin the movement of the piston assembly toward the discharge end. The pressurization of the cartridge causes the second rupture disc to rupture and hypergolic fluid contained within the cartridge is discharged out the ignitor outlet.
摘要翻译： 与MC-1火箭发动机一起使用的点火器具有由两个连接有破裂盘组件的端盖限定的盒。 在点火过程中，墨盒内的活塞组件从墨盒的一端移动。 点火器的入口与从燃料泵的排出口获取的供应物相通。 当泵初始启动时，压力差使第一破裂盘爆裂，开始活塞组件向排出端移动。 筒的加压导致第二破裂盘破裂，并且包含在盒内的高压流体被排出到点火器出口。
-
公开(公告)号：US06497091B1
公开(公告)日：2002-12-24
申请号：US09877800
申请日：2001-06-06
IPC分类号： F02C724
CPC分类号： F02K9/95
摘要： An ignitor for use with the MC-1 rocket engine has a cartridge bounded by two end caps with rupture disc assemblies connected thereto. A piston assembly within the cartridge moves from one end of the cartridge during the ignition process. The inlet of the ignitor communicates with a supply taken from the discharge of the fuel pump. When the pump is initially started, the pressure differential bursts the first rupture disc to begin the movement of the piston assembly toward the discharge end. The pressurization of the cartridge causes the second rupture to rupture and hypergolic fluid contained within the cartridge is discharged out the outlet. Once the piston assembly reaches the discharge end of the cartridge, purge grooves allow for fuel and remaining hypergolic fluid, to be discharged out the ignitor outlet into the combustion chamber to purge the ignitor of any remaining hypergolic fluid.
摘要翻译： 与MC-1火箭发动机一起使用的点火器具有由两个连接有破裂盘组件的端盖限定的盒。 在点火过程中，墨盒内的活塞组件从墨盒的一端移动。 点火器的入口与从燃料泵的排出口获取的供应物相通。 当泵初始启动时，压力差使第一破裂盘爆裂，开始活塞组件向排出端移动。 筒的加压导致第二次破裂破裂，并且包含在筒内的高压流体排出出口。 一旦活塞组件到达料筒的排放端，净化槽允许燃料和剩余的高沸点流体被排放到燃烧室内的点火器出口，以清除任何剩余的高沸点流体的点火器。
-
公开(公告)号：US06195984B1
公开(公告)日：2001-03-06
申请号：US09228034
申请日：1998-12-10
申请人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
发明人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
IPC分类号： F02K900
CPC分类号： F02K9/974 , B29C53/585 , B29L2031/3097 , F02K9/62 , F02K9/97 , Y10S60/909
摘要： A thrust chamber assembly for liquid fueled rocket engines and the method of making it wherein a two-piece mandrel having the configuration of an assembly having a combustion chamber portion connected to a nozzle portion through a throat portion is wrapped with a silica tape saturated with a phenolic resin, the tape extending along the mandrel and covering the combustion chamber portion of the mandrel to the throat portion. The width of the tape is positioned at an angle of 30 to 50° to the axis of the mandrel such that one edge of the tape contacts the mandrel while the other edge is spaced from the mandrel. The phenolic in the tape is cured and the end of the wrap is machined to provide a frustoconical surface extending at an angle of 15 to 30° with respect to the axis of the mandrel for starting a second wrap on the mandrel to cover the throat portion. The remainder of the mandrel is wrapped with a third silica tape having its width positioned at a angle of 5 to 20° from the axis of the mandrel. The resin in the third tape is cured and the assembly is machined to provide a smooth outer surface. The entire assembly is then wrapped with a tow of graphite fibers wetted with an epoxy resin and, after the epoxy resin is cured, the graphite is machined to final dimensions.
-
公开(公告)号：US4836707A
公开(公告)日：1989-06-06
申请号：US93417
申请日：1987-09-04
申请人： W. Neill Myers
发明人： W. Neill Myers
CPC分类号： B25J15/028 , B25B5/08 , B64G1/641 , B64G1/645 , E05C3/34 , Y10T24/45634 , Y10T292/0829 , Y10T292/0837 , Y10T403/595 , Y10T403/599 , Y10T403/604
摘要： In accordance with this invention, a releasable clamping apparatus (10) is constructed having an opening or slot (14) within which a lifting handle (28 or 30) is clamped between retaining latch portions (62, 64) and a clamp assembly (34). The latch portions (62, 64) are supported by openings (56, 58) and are retracted and extended into a slot (14) by spring biased linkage members (78, 80). These members (78, 80) are acted upon by similarly profiled cam lobes (116, 116a, 118, 118a). Dissimilarly profiled cam lobes (126, 128) of the cam member (110) act upon the clamp assembly (34), clamping a handle (28 or 30) against faces (68) of the latch portions (62, 64). The cam member (110) is coupled to a shaft (162) having an operating handle (32), with the shaft (32) also being provided with a detent assembly (202). This detent assembly (202) locks the handle (32) and the shaft (162) in "locked" positions (38 or 40) in the surface (198) of the apparatus (10), which clamps a handle (28 or 30) as described. When the handle (32) is rotated to position the detent assembly (202) in one of the "release" openings (42, 44), the clamp assembly (34) and the latch portions (62, 64) are withdrawn into their respective openings, releasing the handle (28 or 30).
摘要翻译： 根据本发明，一种可释放的夹紧装置（10）被构造成具有开口或狭槽（14），提升把手（28或30）夹在其中，夹紧部分（62,64）和夹紧组件（34） ）。 闩锁部分（62,64）由开口（56,58）支撑，并且通过弹簧偏压连杆构件（78,80）缩回并延伸到狭槽14中。 这些构件（78,80）由类似的凸轮凸角（116,116a，118,118a）作用。 凸轮构件（110）的不同类型的凸轮凸角（126,128）作用在夹紧组件（34）上，将手柄（28或30）夹在闩锁部分（62,64）的表面（68）上。 凸轮构件（110）联接到具有操作手柄（32）的轴（162），轴（32）还设置有制动组件（202）。 该止动组件（202）将手柄（32）和轴（162）锁定在装置（10）的表面（198）中的“锁定”位置（38或40）中，夹紧手柄（28或30） 如上所述。 当手柄（32）旋转以将定位组件（202）定位在“释放”开口（42,44）之一中时，夹紧组件（34）和闩锁部分（62,64）被撤回到它们各自的 开口，释放把手（28或30）。
-
公开(公告)号：US4718709A
公开(公告)日：1988-01-12
申请号：US942159
申请日：1984-12-16
申请人： W. Neill Myers , John C. Forbes , Wayne L. Barnes
发明人： W. Neill Myers , John C. Forbes , Wayne L. Barnes
CPC分类号： B25J15/103 , B64G1/646 , B64G4/00
摘要： An end effector device (A) for grasping and holding an article such as a handle (18) of a space telescope is disclosed. The device includes a V-shaped capture window (74) defined as inclined surfaces (76, 78) in parallel face plates (22, 24) which converge toward a retainer recess (54) in which the handle is retained. A pivotal finger (30) meshes with a pair of pivoted fingers (26, 28) which rotate in counterrotation. The fingers rotate to pull a handle within the capture window into recess (54) where latches (50) lock handle (18) in the recess. To align the capture window, plates (22, 24) may be cocked plus or minus five degrees on base (64).
摘要翻译： 公开了一种用于抓握和保持诸如空间望远镜的手柄（18）的物品的端部执行器装置（A）。 该装置包括被定义为平行面板（22,24）中的倾斜表面（76,78）的V形捕获窗口（74），其朝向保持手柄的保持器凹部（54）会聚。 枢轴指（30）与一对旋转的转动的手指（26,28）啮合，其旋转。 手指旋转以将捕获窗口内的手柄拉入到凹部（54）中，其中闩锁（50）将手柄（18）锁定在凹部中。 为了对齐捕获窗口，板（22,24）可以在基部（64）上被加压或减小五度。
-
公开(公告)号：US06860099B1
公开(公告)日：2005-03-01
申请号：US10263297
申请日：2003-01-09
摘要： An injector for use with the rocket thruster has a plurality of fuel ports separated from a plurality of oxidizer ports. The oxidizer and fuel ports are paired together directing their respective fluids along a path with radial and tangential components so that the two fluids impinge at a predetermined spaced apart distance from the chamber wall of the combustion chamber at an impingement track. By providing the fuel at a steeper angle relative to the chamber walls than the oxidizer, the fuel can be utilized to provide a fuel rich zone near the chamber walls to assist in cooling the chamber walls during operation.
摘要翻译： 与火箭推进器一起使用的喷射器具有与多个氧化剂口分离的多个燃料口。 氧化剂和燃料端口配对在一起，沿着具有径向和切向部件的路径引导它们各自的流体，使得两个流体在冲击轨道处以与燃烧室的室壁预定间隔开的距离冲击。 通过以比氧化器相对于室壁更陡的角度提供燃料，燃料可以用于在室壁附近提供富燃区，以在操作期间帮助冷却室壁。
-
公开(公告)号：US06189315B1
公开(公告)日：2001-02-20
申请号：US09350412
申请日：1999-06-18
IPC分类号： F02K942
摘要： A gas generator and ignitor assembly for powering a turbine of a turbopump assembly for a rocket engine comprises an injector and a combustion chamber, the injector having a body member including a fuel inlet and an oxidizer inlet spaced one from the other and communicating with respective radially spaced apart annular members in the body member. Three annuli communicate with the fuel inlet and two annuli communicate with the oxidizer inlet, the annuli which communicates with the oxidizer being positioned between pairs of the other annuli. The body member is enclosed by a plate having an array of bores arranged in two series with three radially spaced apart groups of circular rows in each series. The outer series has 28 groups of triplet bores while the inner series has 14 groups of triplet bores. The annuli which communicate with oxidizer feed bores of each series that are between the other bores of a triplet, the latter bores communicating with annuli that communicate with fuel. The inner and outer bores of the triplets of each series are inclined relatively to each other and to the third bore of the triplet so that fuel and oxidizer atomizes as it is sprayed into the inlet of the combustion chamber where the propellants are mixed, and burned. The burning of the propellants is effected by ignition of a plug of solid propellant fuel mounted to communicate with the interior of the combustion chamber.
摘要翻译： 用于为涡轮发动机的涡轮泵组件的涡轮机供电的气体发生器和点火器组件包括喷射器和燃烧室，所述喷射器具有主体构件，该主体构件包括彼此间隔开并与径向相连的燃料入口和氧化剂入口 间隔开的环形构件在主体构件中。 三个环与燃料入口连通，两个环与氧化剂入口连通，与氧化剂连通的环与位于另一个环之间。 主体部件由具有排列成两个系列的孔阵列的板包围，每个系列具有三个径向间隔开的圆形排的组。 外部系列具有28组三重孔，而内部系列具有14组三重孔。 与三联体的其他孔之间的每个系列的氧化剂进料孔进行通气的环路，后者孔与与燃料连通的环路连通。 每个系列的三联体的内孔和外孔相对于彼此倾斜并相对于三联体的第三孔倾斜，使得燃料和氧化剂在其被喷射到燃烧室的入口处时雾化，其中推进剂被混合并燃烧 。 推进剂的燃烧通过点燃安装成与燃烧室内部连通的固体推进剂燃料的塞子来实现。
-
-
-
-
-
-
-
-
-
搜索结果
14 条记录 (耗时 0.013 秒)
