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31. 发明授权

US5505408A Differential yoke-aerofin thrust vector control system 失效
标题翻译：差速轭翼型推力矢量控制系统
公开(公告)号：US5505408A
公开(公告)日：1996-04-09
申请号：US139939
申请日：1993-10-19
申请人： John M. Speicher , Allan A. Voigt , Che-Ram S. Voigt
发明人： John M. Speicher , Allan A. Voigt , Che-Ram S. Voigt
IPC分类号： B64C15/02 , F02K9/84 , F42B10/64 , F41G7/00
CPC分类号： F42B10/663 , B64C15/02 , F02K9/84 , F42B10/64 , F42B10/666 , Y10T74/18816
摘要： An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.
摘要翻译：用于控制导弹或类似车辆的可转向喷嘴的致动系统与机翼控制系统组合，两者都由相关联的驱动马达和齿轮组件一致地驱动，一个用于每个机翼。喷嘴转向系统包括两个基本上相同的轭板，其沿着大致横向于导弹轴线的平面安装，并且围绕导弹轴线相对于彼此正交地定向，用于使喷嘴通过相互正交的轴线枢转，由此实现全方向转向。轭板在相对的端部联接到小齿轮上，小齿轮由相同的齿轮组件驱动，驱动相关联的机翼。当翼翼旋转到导弹控制模式时，该布置允许可操纵的喷嘴和机翼的共同的方向控制，同时将喷嘴保持在中性方向。

32. 发明授权

US4844380A Detachable thrust vector mechanism for an aeronautical vehicle 失效
标题翻译：航空器的可分离推力矢量机制
公开(公告)号：US4844380A
公开(公告)日：1989-07-04
申请号：US5714
申请日：1987-01-21
申请人： John R. Peoples , Billy R. Phillips
发明人： John R. Peoples , Billy R. Phillips
IPC分类号： B64G1/00 , B64G1/26 , B64G1/64 , F42B15/36
CPC分类号： B64G1/002 , B64G1/26 , F42B10/666 , F42B15/36 , B64G1/641 , B64G1/645
摘要： A relatively inexpensive, high efficiency, detachable thrust vector mechanism is provided for addressing the current shortcomings in the art. In the illustrative embodiment, the invention is used in conjunction with a nautical or aeronautical vehicle having primary propulsion means and at least one fin movable, to provide maneuverability, in response to a conventional control system. The invention is a detachable thrust vector mechanism comprising auxiliary propulsion means pivotally attached to the missile through connecting means. Contact means are provided for transferring bi-directional motion of the fin to the auxiliary propulsion means. The mechanism is operable to provide auxiliary thrust for the missile along a thrust vector determined by the control system. The invention is effective to provide missile steerage at low speeds, particularly during initial launch and pitchover. The mechanism of the present invention falls away during flight to fully exploit the original optimized aerodynamic or hydrodynamic design of the missile.The thrust vector mechanism of the present invention conserves the main motor fuel, reduces the initial missile launch signature and effectively increases its range. The invention also provides a low cost, disposable mechanism for converting a missile designed for high speed (air-to-air) launches to one adapted for low speed (surface) launches. That is, under the teachings of the present invention, existing missiles may be inexpensively retrofit to provide thrust vector control.
摘要翻译：提供了一种相对便宜，高效率，可拆卸的推力向量机制，用于解决本领域当前的缺点。在说明性实施例中，本发明与具有主要推进装置和至少一个翼片可移动的航海或航空车辆结合使用，以响应于常规控制系统来提供机动性。本发明是一种可拆卸的推力矢量机构，包括通过连接装置枢转地连接到导弹的辅助推进装置。提供接触装置用于将翅片的双向运动传递到辅助推进装置。该机构可操作地沿着由控制系统确定的推力向量为导弹提供辅助推力。本发明有效地在低速下提供导弹转向，特别是在初始发射和俯仰时。本发明的机理在飞行中脱落，以充分利用原始的优化的空气动力学或流体动力学设计的导弹。本发明的推力矢量机构节省了主要的发动机燃料，减少了初始导弹发射特征，有效提高了其发射距离。本发明还提供了一种低成本的一次性机构，用于将设计用于高速（空对空）发射的导弹转换成适于低速（表面）发射的导弹。也就是说，在本发明的教导下，现有的导弹可以被廉价地改造以提供推力矢量控制。

33. 发明授权

US4648567A Directional control of rockets using elastic deformation of structural members 失效
标题翻译：结构构件弹性变形对火箭的定向控制
公开(公告)号：US4648567A
公开(公告)日：1987-03-10
申请号：US634620
申请日：1984-07-26
申请人： Inge Maudal , John F. Moss
发明人： Inge Maudal , John F. Moss
IPC分类号： F42B10/64 , F42B15/02
CPC分类号： F42B10/64 , F42B10/666
摘要： A missile is disclosed which utilizes elastic deformation of structural members in order to control missile flight. The elastic deformation may be in the mounting of the rocket nozzle, the provision of deformable control surfaces, or provision of deformable sections of rocket body, all of which are controlled by independent actuating means.
摘要翻译：公开了一种导弹，其利用结构构件的弹性变形来控制导弹飞行。弹性变形可以是火箭喷嘴的安装，提供可变形的控制表面，或提供火箭体的变形部分，所有这些都由独立的致动装置控制。

34. 发明授权

US3460349A Reaction engine with intermittent thrust and direction control 失效
标题翻译：具有间歇力和方向控制的反应发动机
公开(公告)号：US3460349A
公开(公告)日：1969-08-12
申请号：US3460349D
申请日：1967-04-07
申请人： CURTISS WRIGHT CORP
发明人： BIEHL RICHARD E
IPC分类号： F02K9/94 , F02K1/24 , F02K9/04
CPC分类号： F42B10/663 , F02K9/94 , F42B10/666

35. 发明授权

US3048010A Swiveling nozzle for solid rocket 失效
标题翻译：用于固体火箭的旋转喷嘴
公开(公告)号：US3048010A
公开(公告)日：1962-08-07
申请号：US29960
申请日：1960-01-04
申请人： UNITED AIRCRAFT CORP
发明人： LEDWITH WALTER A
IPC分类号： F02K9/84 , F42B10/66
CPC分类号： F02K9/84 , F42B10/66 , F42B10/666

36. 发明授权

US2621871A Steering control device for jetpropelled flying machines 失效
标题翻译：喷射飞行器的转向控制装置
公开(公告)号：US2621871A
公开(公告)日：1952-12-16
申请号：US3764048
申请日：1948-07-08
申请人： AIME ROBERT ROGER
发明人： AIME ROBERT ROGER
IPC分类号： B64C15/12 , B64D39/00 , F42B10/64 , F42B10/66
CPC分类号： F42B10/666 , B64C15/12 , F42B10/64

37. 发明申请

US20160123711A1 DRAG REDUCTION SYSTEM 审中-公开
标题翻译： DRAG减少系统
公开(公告)号：US20160123711A1
公开(公告)日：2016-05-05
申请号：US14895829
申请日：2014-05-30
申请人： BAE SYSTEMS PLC
发明人： DENNIS JOSEPH FLYNN , PAUL MARTIN LOCKING , MARTIN JOHNSON
IPC分类号： F42B10/40 , F42B10/66
CPC分类号： F42B10/40 , F42B10/66 , F42B10/666 , F42B10/668
摘要： The invention relates to a drag reduction system, more specifically a forward mounted drag reduction system for use on extended range artillery.There is provided a long range artillery projectile having forward end comprising a fuze, an aft located base unit and located therebetween a projectile body defining cavity which comprises a payload, a forwardly located gas generator capable of generating a gas flow, and an ignition device to ignite the gas generator; preferably at a predetermined time after the projectile is launched.
摘要翻译：减阻系统技术领域本发明涉及一种减阻系统，更具体地说，涉及一种用于扩展射程火炮的前挂式减阻系统。提供了一种远距离炮弹，其前端包括引信，位于后方的基座单元，并且位于其间，具有限定空腔的射弹体，其包括有效载荷，能够产生气流的向前定位的气体发生器，以及点火装置点燃气体发生器; 优选在发射弹丸之后的预定时间。

38. 发明授权

US09157714B1 Tail thruster control for projectiles 有权
标题翻译：飞弹尾部推进器控制
公开(公告)号：US09157714B1
公开(公告)日：2015-10-13
申请号：US14080845
申请日：2013-11-15
申请人： BAE Systems Information And Electronic Systems Integration Inc.
发明人： Robert D. Frey, Jr.
IPC分类号： F42B10/66 , F41G7/22 , F42B10/00
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 method for guiding a projectile includes storing a gas in a chamber that is attached to the projectile. The projectile has an explosive front end and a rear guidance kit consisting of a body extension and a tail boom. The chamber is located in the body extension with the control electronics. Two or more fins that are configured to stabilize the projectile while the projectile is in flight. Pulses of gas are released out of the chamber through a nozzle at the end of the tail boom to control an angle of attack to control the lift of the projectile to guide the projectile to a target while the projectile is in flight.
摘要翻译：介绍了一种引导弹丸的系统和方法。用于引导射弹的方法包括将气体存储在附接到射弹的腔室中。抛射体具有爆炸性的前端和后部引导套件，其包括主体延伸部和尾部吊杆。该腔室与控制电子设备位于车身延伸部分。两个或更多个鳍被配置为在弹丸飞行期间稳定射弹。气体的脉冲通过尾部末端的喷嘴从室内释放出来，以控制攻角，以控制射弹的升力，以便在弹丸飞行时将射弹引导到目标。

39. 发明授权

US08624171B2 Tail thruster control for projectiles 有权
标题翻译：飞弹尾部推进器控制
公开(公告)号：US08624171B2
公开(公告)日：2014-01-07
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： F42B10/60 , F42B10/66 , F42B10/00
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。

40. 发明授权

US07812294B2 Aircraft spiraling mechanism with jet assistance-f 失效
标题翻译：飞机援助飞机螺旋机构f
公开(公告)号：US07812294B2
公开(公告)日：2010-10-12
申请号：US12458659
申请日：2009-07-20
申请人： Tom Kusic
发明人： Tom Kusic
IPC分类号： F41G7/00
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 ramjet 6b is attached to a tube 3 that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3 with respect to the rotate-able tube 3, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3. Ramjet 6b is rotated to a greater than another ramjet on the right side of the tube 3. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3 than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3 to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3. Thus, as well as forcing the rotate-able tube 3 to rotate, the ramjets 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.
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。冲压喷枪6b连接到能够围绕机身的环绕部分旋转的管3。冲压喷枪6b能够相对于可旋转管3以可枢转的方式旋转在可旋转管3上，从而相对于可旋转管3的纵向轴线改变它们的间距。将冲压喷嘴6b旋转至在管3的右侧大于另一冲头喷枪。冲击喷嘴之间的旋转差异使得冲压喷嘴6b在可旋转管3上施加比在冲击器旋转时右侧的冲压式喷射器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，冲击器将在可旋转管3上施加横向力。因此，以及迫使可旋转管3旋转，冲击器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。

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