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1. 发明授权

US5511745A Vectorable nozzle having jet vanes 失效
标题翻译：具有喷射叶片的可向量喷嘴
公开(公告)号：US5511745A
公开(公告)日：1996-04-30
申请号：US366848
申请日：1994-12-30
申请人： Lawrence C. Faupell , Steven R. Wassom , Joseph J. Kliger
发明人： Lawrence C. Faupell , Steven R. Wassom , Joseph J. Kliger
IPC分类号： F02K1/00 , F02K9/84 , F02K9/90 , F42B10/66
CPC分类号： F02K9/90 , F02K1/008 , F02K9/84 , F42B10/665
摘要： A system for providing pitch, yaw, and roll control during the flight of a rocket-propelled vehicle combines a vectorable nozzle with jet vanes. The vectorable nozzle provides yaw and pitch control, while the jet vanes provide roll control. Anti-rotation pins extend from the vehicle housing into longitudinal slots within the vectorable nozzle to allow vectoring movements and prevent rotation of the nozzle. The jet vanes are rotatably mounted on shafts within the nozzle exit cone to receive and guide combustion products passing through the nozzle. The jet vanes may be jettisoned after an initial high-angle-of-attack maneuver is completed and the vehicle gains speed, after which roll control is provided by aerodynamic fins. The jet vanes may also be formed of material which erodes after the initial maneuver, thereby reducing the loss of thrust caused by the jet vanes.
摘要翻译：在火箭推进车辆的飞行期间提供俯仰，偏航和滚动控制的系统将可向量喷嘴与喷射叶片组合。矢量喷嘴提供偏航和俯仰控制，而喷气叶片提供滚动控制。防旋转销从车辆壳体延伸到可向量喷嘴内的纵向槽中，以允许矢量运动并防止喷嘴旋转。喷射叶片可旋转地安装在喷嘴出口锥体内的轴上，以接收和引导通过喷嘴的燃烧产物。在最初的高角度攻击机动完成之后，喷射叶片可以被抛弃，并且车辆获得速度，之后由空气动力学翅片提供滚动控制。喷射叶片也可以由在初始操纵之后腐蚀的材料形成，从而减少由喷射叶片引起的推力损失。

2. 发明授权

US4867393A Reduced fin span thrust vector controlled pulsed tactical missile 失效
标题翻译：减少的翅片跨度推力矢量控制脉冲战术导弹
公开(公告)号：US4867393A
公开(公告)日：1989-09-19
申请号：US233069
申请日：1988-08-17
申请人： Lawrence C. Faupell , Steven R. Wassom
发明人： Lawrence C. Faupell , Steven R. Wassom
IPC分类号： F42B10/64 , B64C39/02 , B64D7/08 , B64G1/00 , F42B10/60
CPC分类号： F42B10/60
摘要： A tactical pulsed missile with a movable nozzle for thrust vector control and movable aerofins to provide greater maneuverability and flexibility. The first pulse is fired at launch and the later pulses are fired as needed whereby steerage may be provided by thrust vector control during the firing of the pulses. When none of the pulses are firing, steerage may be provided by the movable aerofins. The missile is provided with separate small electromechanical actuators for each of the aerofins and each of the movable nozzle axes which are preferably placed closely adjacent the respective aerofins and nozzle so that the weight and space of various linkages may be eliminated. The motors are provided with a source of high voltage so that their size may be reduced whereby they burn up when the high voltage is applied for a short period of time but not before their task has been achieved. The fin span is reduced to less than about four inches to enable the packaging of a greater number of such tactical missiles in the payload bay of an airplane. A flexible bearing may be provided between the nozzle and nozzle housing. An elastomeric material may be provided between and bonded to the nozzle and nozzle housing to prevent the ingestion of exhaust and debris into the space therebetween.

3. 发明授权

US4571800A Method for explosively forming an auxiliary exit cone for the nozzle of a rocket motor 失效
标题翻译：用于爆炸形成用于火箭发动机喷嘴的辅助出口锥体的方法
公开(公告)号：US4571800A
公开(公告)日：1986-02-25
申请号：US512274
申请日：1983-07-11
申请人： Lawrence C. Faupell
发明人： Lawrence C. Faupell
IPC分类号： B21D26/08 , F02K9/97 , B23P13/00
CPC分类号： B21D26/08 , F02K9/976 , Y10T29/49346 , Y10T29/49806
摘要： A method of and apparatus for forming with a minimum of labor, by explosive forming means, an automatically extendible auxiliary nozzle member or exit cone for a rocket motor, the member having tapered sinusoidal flutes with the stresses and thicknesses thereof being uniform whereby, when deployed, the resulting form of cone can be predicted with accuracy, and stresses being created such as to build a spring bias therein so that the member is bistable, that is, stable in both the stowed position and in the deployed position.
摘要翻译：一种用于通过爆炸形成装置形成用于火箭发动机的可自动延伸的辅助喷嘴构件或出口锥体的方法和装置，所述构件具有锥形的正弦斜槽，其应力和厚度是均匀的，由此当被部署时可以精确地预测所形成的锥体，并且产生应力，例如在其中形成弹簧偏压，使得构件是双稳态的，即在收起位置和展开位置两者都是稳定的。

4. 发明授权

US4970857A Energy absorber for translating portions of rocket motor cases using honeycomb 失效
标题翻译：用于使用蜂窝体平移火箭发动机壳体的部分的能量吸收器
公开(公告)号：US4970857A
公开(公告)日：1990-11-20
申请号：US308275
申请日：1989-02-09
申请人： Lawrence C. Faupell
发明人： Lawrence C. Faupell
IPC分类号： F02K9/92 , F02K9/97
CPC分类号： F02K9/92 , F02K9/97 , F05D2250/283 , F05D2250/34
摘要： For providing controllable thrust reversal or thrust termination of a rocket motor, a U-band retaining the nozzle assembly to the motor case is broken. This allows the internal motor pressure to move the nozzle assembly backward from the motor case to create a circumferential opening therebetween, through which opening gases can be expelled outward and/or in the forward direction to terminate or reverse the thrust. When the U-band is broken, the high internal motor pressure may exert such a high force on the nozzle assembly as it is moved backward that the bolts or other means attaching the nozzle assembly to the rest of the missile may be broken and cause uneven gas expulstion. Uneven gas expulsion may cause undesirable changes in trajectory. By the use of honeycomb structures in association with the bolts or other attachment means, the energy exerted on the nozzle assembly is gradually absorbed, preventing breakage of the connecting parts. The gradual absorption of energy ensures that nozzle assembly will be moved backward evenly and not become cocked on the bolts or other connecting means, which is essential for proper thrust termination or thrust reversal.
摘要翻译：为了提供火箭发动机的可控推力反向或推力端接，将喷嘴组件保持在电动机壳体上的U形带被破坏。这允许内部马达压力使喷嘴组件从马达壳体向后移动以在其间形成周向开口，通过该圆周开口，开口气体可以向外排出和/或向前排出以终止或反转推力。当U形带断裂时，高的内部电机压力可能在喷嘴组件向后移动时施加如此大的力，使得将喷嘴组件附接到导弹的其余部分的螺栓或其它装置可能被破坏并导致不均匀气体爆发不均匀的气体排出可能导致轨迹的不良变化。通过使用与螺栓或其他附接装置相关联的蜂窝结构，施加在喷嘴组件上的能量逐渐被吸收，防止连接部件断裂。能量的逐渐吸收确保喷嘴组件将均匀地向后移动，并且不会在螺栓或其他连接装置上被起动，这对于适当的推力终止或推力反转是至关重要的。

5. 发明授权

US4157788A Low friction, movable, rocket nozzle 失效
标题翻译：低摩擦，可动，火箭喷嘴
公开(公告)号：US4157788A
公开(公告)日：1979-06-12
申请号：US820954
申请日：1977-08-01
申请人： Alan R. Canfield , Lawrence C. Faupell , Stanley H. Cardall
发明人： Alan R. Canfield , Lawrence C. Faupell , Stanley H. Cardall
IPC分类号： F02K9/84 , B64C15/04 , B64C15/08
CPC分类号： F02K9/84
摘要： A ball-and-socket, thrust nozzle for rockets has a movable member retained by a stationary member attachable to a rocket. The movable member includes a venturi throat and an expansion cone for the propulsive gases. At least one of the nozzle members has a spherical surface concentric about the center of rotation of the movable member. The other member bears against this spherical surface via a bearing seal in the form of a thin, narrow ring of lubricous material. The bearing seal is located in a position to support the axial blow-out load imposed by the propulsive gases. It is made of fibers of lubricous material, filled with a solid, lubricous resin; and it is bonded to a nozzle member either with the filler resin or with some other bonding agent. The side of the bearing seal that is bonded to the nozzle member may be reinforced with fibers having high tensile strength, woven into the lubricous fibers, or with a thin sheet of metal. The unbonded surface of the bearing seal is convex to minimize its area of contact with the other nozzle member, while having a relatively large bonding surface. The bearing seal functions as a low-friction bearing and also as a seal for containing the hot, erosive, propulsive gases of the rocket.In a preferred embodiment, the fibers of the bearing seal are radially oriented by filament winding. This increases its strength by maximizing the density of the fibers therein and by orienting them so that they are always substantially paralell to the major travel of the surface against which it bears. For the latter reason, the coefficient of friction is also lowered; because the moving surface always moves esentially along the fibers.
摘要翻译：用于火箭的球形插座推力喷嘴具有由可附接到火箭的固定构件保持的可动构件。可动构件包括文丘里喉部和用于推进气体的膨胀锥。至少一个喷嘴构件具有围绕可移动构件的旋转中心同心的球面。另一个构件通过轴承密封件抵靠该球形表面，该轴承密封件呈薄而窄的润滑材料环形。轴承密封件位于支撑由推进气体施加的轴向吹出负载的位置。它由润滑材料纤维制成，填充有固体，润滑树脂; 并且用填料树脂或其它粘结剂与喷嘴构件接合。结合到喷嘴构件的轴承密封件的一侧可以用具有高拉伸强度的纤维，编织到该润滑纤维中的纤维或一薄层金属来增强。轴承密封件的未粘合表面是凸的，以使其与另一个喷嘴构件的接触面积最小化，同时具有相对较大的粘合表面。轴承密封件用作低摩擦轴承，也用作用于容纳火箭的热，腐蚀性推进气体的密封件。

6. 发明授权

US4506832A Antirotation linkage for rocket motor nozzles and other mechanisms 失效
标题翻译：火箭发动机喷嘴和其他机构的防旋转联动装置
公开(公告)号：US4506832A
公开(公告)日：1985-03-26
申请号：US453316
申请日：1982-12-27
申请人： Lawrence C. Faupell
发明人： Lawrence C. Faupell
IPC分类号： F02K9/84 , B64C15/00
CPC分类号： F02K9/84 , Y10T403/32172 , Y10T403/32606
摘要： An antirotation linkage that allows freedom of angular deflection in two coordinate directions of a first member, for example, a rocket motor nozzle, with respect to the primary axis of a second member, a rocket motor in which the nozzle is mounted for angular displacement of the thrust vector for steering control, but which restricts rotation of the first member about such primary axis.
摘要翻译：允许相对于第二构件的主轴线的第一构件例如火箭发动机喷嘴的两个坐标方向上的角度偏转自由度的旋转联动装置，其中安装喷嘴用于角位移的火箭发动机用于转向控制的推力矢量，但是限制第一构件围绕该主轴的旋转。

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