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1. 发明申请

US20120048991A1 TAIL THRUSTER CONTROL FOR PROJECTILES 有权
标题翻译：用于项目的TAIL THRUSTER控制
公开(公告)号：US20120048991A1
公开(公告)日：2012-03-01
申请号：US13319777
申请日：2011-03-09
申请人： Robert D. Frey, JR.
发明人： Robert D. Frey, JR.
IPC分类号： F42B15/01 , F42B10/26 , F42D99/00 , F42B10/02
CPC分类号： F42B10/663 , F41G7/2246 , F42B10/06 , F42B10/66 , F42B10/666
摘要： A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.
摘要翻译：介绍了一种引导弹丸的系统和方法。喷嘴系统包括可附接到射弹的后端的吊杆组件主体。起重臂组件中的气罐包含加压气体。叉子连接到悬臂组件体上以引导抛射体。阀门将气体脉冲从气罐中排出。喷嘴排出气体脉冲以控制射弹的迎角和升力，以将射弹引导到目标。

2. 发明授权

US06315239B1 Variable coupling arrangement for an integrated missile steering system 失效
标题翻译：用于集成导弹转向系统的可变联轴器布置
公开(公告)号：US06315239B1
公开(公告)日：2001-11-13
申请号：US08935571
申请日：1997-09-23
申请人： Allan A. Voigt
发明人： Allan A. Voigt
IPC分类号： F41G700
CPC分类号： F42B10/666 , F42B10/64 , F42B10/663
摘要： An integrated system for missile steering, which uses both jet reaction control (JRC) and aerofin control systems, is provided with a variable coupling mechanism for adjusting the relative responsiveness of the two systems in accordance with the pressurization state of the JRC system pressure chamber. In one embodiment, the pivoting action of a joystick which actuates the gas flow control pintles of the JRC system is permitted only under sufficient pressurization of the pressure chamber. In a second embodiment, the extent to which the pintles protrude from their controllable housings is adjusted according to the pressure in the pressure chamber. In this manner, when JRC is undesirable or is unavailable, the missile aerofins are permitted their full range of motion without being constrained by the pintles.
摘要翻译：使用喷气反应控制（JRC）和机翼控制系统的导弹转向综合系统设有可变联接机构，用于根据JRC系统压力室的加压状态调节两个系统的相对响应性。在一个实施例中，仅在压力室的足够的加压下允许致动JRC系统的气体流量控制枢栓的操纵杆的枢转动作。在第二实施例中，根据压力室中的压力来调节枢轴从其可控制壳体突出的程度。以这种方式，当JRC是不希望的或不可用的时候，导弹飞行器可以被允许其全范围的运动，而不受枢轴的约束。

3. 发明授权

US4779821A Small vehicle roll control and steering 失效
标题翻译：小型车辆滚动控制和转向
公开(公告)号：US4779821A
公开(公告)日：1988-10-25
申请号：US9102
申请日：1987-01-28
申请人： Trevor G. Sutton
发明人： Trevor G. Sutton
IPC分类号： F02K9/88 , B64C15/00
CPC分类号： F02K9/88 , F42B10/663 , F42B10/666
摘要： An automotive vehicle is subject to attitude control input impulses effective only with respect to a roll axis and a selected one of a pitch and yaw axis. A selected and controlled sequencing of roll attitude control allows attitude control also of both the selected one axis and the other of the pitch and yaw axis for the vehicle.
摘要翻译：机动车辆经受仅对于侧倾轴线和俯仰和偏转轴线中所选择的一个有效的姿态控制输入脉冲。滚动姿势控制的选择和控制顺序允许对于车辆的所选择的一个轴线和另一个俯仰角和偏航轴线的姿态控制。

4. 发明授权

US4163534A Steering of an aerodynamic vehicle 失效
标题翻译：空气动力学车辆的转向
公开(公告)号：US4163534A
公开(公告)日：1979-08-07
申请号：US905237
申请日：1978-05-12
申请人： Hans-Jochen Seeger
发明人： Hans-Jochen Seeger
IPC分类号： F42B10/64 , F42B15/16 , B64C15/12 , B64C19/02 , F42B15/18
CPC分类号： F42B10/666 , F42B10/64
摘要： A vehicle has two pairs of transversely oriented rudders and duplex nozzles; three motors pivot the rudders and nozzles for yaw, pitch and roll steering whereby each motor drives the requisite rudder(s) and pivots one or two nozzles so that thrust vector and aerodynamic steering is provided always in unison.
摘要翻译：车辆有两对横向取向的舵和双面喷嘴; 三个电动机使方向舵和喷嘴枢转以进行偏航，俯仰和侧倾转向，由此每个电动机驱动所需的舵并枢转一个或两个喷嘴，使得总是一致地提供推力矢量和空气动力学转向。

5. 发明授权

US3237890A Integrated thrust vector control system 失效
标题翻译：综合推力矢量控制系统
公开(公告)号：US3237890A
公开(公告)日：1966-03-01
申请号：US9458861
申请日：1961-03-09
申请人： TRW INC
发明人： THIELMAN RUSSELL F
IPC分类号： B64C9/38 , F02K9/84
CPC分类号： F42B10/666 , B64C9/38 , F02K9/84 , F42B10/663 , Y02T50/44

6. 发明授权

US3200587A Rocket vehicle attitude control 失效
标题翻译：火箭车姿态控制
公开(公告)号：US3200587A
公开(公告)日：1965-08-17
申请号：US13848161
申请日：1961-09-15
申请人： GEN MOTORS CORP
发明人： JOSEPH TOLSON WILLIAM
IPC分类号： F02K9/84
CPC分类号： F02K9/84 , F42B10/666

7. 发明授权

US3195462A Pull rocket shroud 失效
标题翻译：拉火箭罩
公开(公告)号：US3195462A
公开(公告)日：1965-07-20
申请号：US11075461
申请日：1961-05-17
申请人： AEROJET GENERAL CO
发明人： PETRE PHILIP C
CPC分类号： F42B10/666

8. 发明授权

US3070329A Directional control for rockets 失效
标题翻译：火箭定向控制
公开(公告)号：US3070329A
公开(公告)日：1962-12-25
申请号：US896760
申请日：1960-02-16
申请人： UNITED AIRCRAFT CORP
发明人： AUGUSTUS HASBROUCK
IPC分类号： F02K9/84 , F02K9/88
CPC分类号： F02K9/84 , F02K9/88 , F42B10/666

9. 发明授权

US07800033B1 Separation activated missile spiraling mechanism—FA 有权
标题翻译：分离激活导弹螺旋机构FA
公开(公告)号：US07800033B1
公开(公告)日：2010-09-21
申请号：US12654126
申请日：2009-12-11
申请人： Tom Kusic
发明人： Tom Kusic
IPC分类号： F42B15/01
CPC分类号： F42B10/666
摘要： An aircraft in the form of multi-stage missile 1 with a spiral inducing assembly 2 which is capable of inducing the missile to travel in a continuous spiraling motion without the missile rolling. A fin 6a is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The fin 6a is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing the pitch relative to the longitudinal axis of the rotate-able tube 3. Fin 6a is rotated to a greater than another fin on the right side of the tube 3. The difference in degree of rotation between the fins makes the fin 6a exert a greater force on the rotate-able tube 3 than the fin on the right side when the fins are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the fins would exert a lateral force on the rotate-able tube 3. Thus, as well as forcing the rotate-able tube 3 to rotate, the fins would also push the rotate-able tube sideways. But as the rotate-able tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiraling motion of the missile when in flight. Rotation of the fins is activated automatically by separation of sections of the main body.
摘要翻译：具有多级导弹1形式的飞机，具有螺旋诱导组件2，其能够引导导弹以连续的螺旋运动而无导弹滚动。翅片6a附接到能够围绕机身的环绕部分旋转的管3。翅片6a能够以可旋转的管3相对于可旋转管3以可枢转的方式旋转，从而相对于可旋转管3的纵向轴线改变间距。翅片6a旋转到在管3的右侧大于另一个翅片。翅片之间的旋转差异使得翅片6a在翅片旋转时在可旋转管3上施加比在右侧的翅片更大的力在同一个方向因此，旋转力之间的不平衡使得可旋转管3旋转。当旋转时，翅片将在可旋转管3上施加横向力。因此，以及迫使可旋转管3旋转，翅片也将侧向推动可旋转管。但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向不断旋转，导致在飞行中导弹的螺旋运动。通过分离主体部分自动激活翅片的旋转。

10. 发明申请

US20060284006A1 MISSILE CONTROL SYSTEM AND METHOD 有权
标题翻译： MISSILE控制系统和方法
公开(公告)号：US20060284006A1
公开(公告)日：2006-12-21
申请号：US11113511
申请日：2005-04-25
申请人： Daniel Chasman , Michael Leal , Stephen Haight
发明人： Daniel Chasman , Michael Leal , Stephen Haight
IPC分类号： B64B1/36
CPC分类号： F42B10/666 , F02K9/30 , F02K9/805 , F02K9/86 , F05D2240/128 , F05D2250/323 , F05D2250/324 , F05D2250/41 , F05D2260/60 , F16K3/085 , F42B10/663
摘要： A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.
摘要翻译：导弹包括具有转向和姿态控制系统推进器的控制系统，其具有控制阀。每个控制阀具有在其中具有多个小喷嘴的喷嘴板。喷嘴板包括一对部分，其中一个部分可相对于另一个部分旋转。通过喷嘴板的流动的控制可以通过喷嘴板的部分的相对定位来实现。喷嘴板的上游收敛部分可以相对于导弹固定，喷嘴板的下游喉部和/或发散部分可移动。可以通过使用在导弹体外部的致动器来实现喷嘴板的可移动部分的移动。控制阀提供了一种控制来自转向推进器的流量的简单，轻便和紧凑的方式。

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