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91. 发明申请

US20110297031A1 Surface Ship, Deck-Launched Anti-Torpedo Projectile 有权
标题翻译：地面船，甲板上发射的反鱼雷弹
公开(公告)号：US20110297031A1
公开(公告)日：2011-12-08
申请号：US12057123
申请日：2008-03-27
申请人： Jyun-Horng Fu , Lance Hamilton Benedict , Antonio Paulic , Robert M. Krass
发明人： Jyun-Horng Fu , Lance Hamilton Benedict , Antonio Paulic , Robert M. Krass
IPC分类号： F42B15/22 , F42B10/02
CPC分类号： F42B15/22 , F42B10/06 , F42B10/46
摘要： A surface ship, deck-launched anti-torpedo projectile is disclosed. The projectile has a blunt-end nose to create a cavitating running mode. The nose has a gradual, stepped, right-circular cylindrical or conic geometry. In some embodiments, the projectile includes a plurality of tail fins that are dimensioned and arranged to be within the generalized elliptical cavity that shrouds the projectile in the cavitating running mode.
摘要翻译：公开了一种水面船，甲板式发射的反鱼雷弹。射弹有一个钝的鼻子，创造一个气蚀运行模式。鼻子有一个渐进的，阶梯式的，右圆的圆柱形或圆锥形几何。在一些实施例中，抛射体包括多个尾翼，其尺寸和布置成在通气化运行模式中围绕弹丸的广义椭圆形腔内。

92. 发明申请

US20100192797A1 WARHEAD 失效
标题翻译：弹头
公开(公告)号：US20100192797A1
公开(公告)日：2010-08-05
申请号：US12602460
申请日：2008-05-15
申请人： Wolfgang Seidel , Michael Schwenzer
发明人： Wolfgang Seidel , Michael Schwenzer
IPC分类号： F42B12/24 , F42B10/02 , F42C13/00
CPC分类号： F42B12/24 , F42B10/02 , F42C13/006
摘要： The invention relates to a warhead (10) for attacking particularly half-hard and/or soft targets, wherein the warhead comprises a splinter-forming casing (1) and an explosive material positioned in the casing (1). The warhead (10) further has a front plate (2) having a splinter formation, into which a distance sensor (3) is integrated. An igniter (5) for the explosive material and a stabilizing strap for adjusting perpendicular flight characteristics on the way to the target are located in the rear part of the warhead (10), wherein the initiation of the igniter (5) is determined by a property of the target to be attacked, namely, the parameter of a defined height from the target.
摘要翻译：本发明涉及一种用于攻击特别是半硬和/或软目标的弹头（10），其中弹头包括分裂成形壳体（1）和定位在壳体（1）中的爆炸材料。弹头（10）还具有一个具有分段形成的前板（2），一个距离传感器（3）被集成在其中。用于爆炸材料的点火器（5）和用于在到达目标的路上调整垂直飞行特性的稳定带位于弹头（10）的后部，其中点火器（5）的启动由要攻击的目标的属性，即从目标定义的高度的参数。

93. 发明授权

US06981672B2 Fixed canard 2-D guidance of artillery projectiles 有权
标题翻译：固定炮弹2-D引导炮弹
公开(公告)号：US06981672B2
公开(公告)日：2006-01-03
申请号：US10664223
申请日：2003-09-17
申请人： John A. Clancy , Thomas D. Bybee , William A. Friedrich
发明人： John A. Clancy , Thomas D. Bybee , William A. Friedrich
IPC分类号： F42B10/02 , F41G7/00 , F41G9/00
CPC分类号： F42B10/04 , F42B10/64
摘要： Applicants have invented a guidance system for guiding a projectile, the projectile having a body portion capable of being spun in a first direction and a nose portion connected to the body portion by a spin control coupling, the nose portion being capable of being spun in a second direction. The nose portion including first and second aerodynamic surfaces fixedly attached to the nose portion and configured and arranged to cause the nose portion to spin in a second direction during projectile flight. The nose portion including third and fourth aerodynamic surfaces fixedly attached to the nose portion, which are configured and arranged such that when the nose portion is spinning the third and fourth aerodynamic surfaces have no net effect on projectile flight, but when the nose portion is despun using the spin control coupling, the third and fourth aerodynamic surfaces induce both a moment and a lateral force to the nose, causing the projectile flight path to change.
摘要翻译：申请人已经发明了一种用于引导射弹的引导系统，所述射弹具有能够沿着第一方向旋转的主体部分和通过旋转控制联接件连接到主体部分的鼻部，所述鼻部能够以第二个方向鼻部包括固定地附接到鼻部部分的第一和第二空气动力学表面，并且被构造和布置成使得在射弹飞行期间鼻部部分沿第二方向旋转。鼻部包括固定在鼻部上的第三和第四空气动力学表面，其被构造和布置成使得当鼻部旋转时，第三和第四空气动力学表面对抛射体飞行没有净效应，但是当鼻部部分被去除时使用旋转控制联轴器，第三和第四空气动力学表面引起了鼻子的瞬间和横向力，导致射弹飞行路径改变。

94. 发明授权

US5929370A Aerodynamically stabilized projectile system for use against underwater objects 失效
标题翻译：用于水下物体的空气动力学稳定的射弹系统
公开(公告)号：US5929370A
公开(公告)日：1999-07-27
申请号：US993544
申请日：1997-12-18
申请人： Jeffrey A. Brown , Reed Copsey , Marshall Tulin , Roy Kline
发明人： Jeffrey A. Brown , Reed Copsey , Marshall Tulin , Roy Kline
IPC分类号： F42B10/02 , F42B10/46 , F42B15/22 , F42B15/20 , F42B5/24
CPC分类号： F42B10/46 , F42B10/02 , F42B15/22
摘要： A projectile is propelled from a location in air, through an air/water interface, and toward a submerged underwater object. The projectile includes a forward end that forms a cavitation void around the projectile in water, avoiding water drag on the remainder of the projectile. The projectile further includes an outwardly flared or finned rearward end that aerodynamically stabilizes the projectile in air and flare stabilizes it in water, in each case against yaw.
摘要翻译：射弹从空气中通过空气/水界面向潜水的水下物体推进。射弹包括一个前端，在水中在射弹周围形成一个空穴空穴，避免了在其余的射弹上的水分阻力。抛射体还包括一个向外扩张或翅片的后端，使空气动力学稳定射弹在空气中，并且火炬将其稳定在水中，在每种情况下都能抵挡偏航。

95. 发明授权

US5902952A Anti tip-off device 失效
标题翻译：防拆装置
公开(公告)号：US5902952A
公开(公告)日：1999-05-11
申请号：US941930
申请日：1997-09-30
申请人： Thomas A. DelGuidice , Fred W. Watson, Jr.
发明人： Thomas A. DelGuidice , Fred W. Watson, Jr.
IPC分类号： F42B10/02 , F42B10/04 , F42B14/02 , F41F5/00 , F41F3/04
CPC分类号： F42B10/04 , F42B10/02 , F42B14/02
摘要： An anti tip-off device for rocket rockets adapted for collapsible tube-inbe launchers is provided. The dual-diameter launch tube requires stabilization of the rocket within the larger diameter tube. The anti tip-off device has two segments which together form a hollow cylinder which fits over the nose section of a standard high explosive anti-armor rocket. A sliding surface is located around the circumference of the cylinder to provide support for the rocket during transit of the larger launch tube. The surface contact prevents the rocket from wobbling or tipping during the rocket's transit of the launch tube. Alternately, permanently-bonded stabilizer legs or a bonded ring may be attached to the rocket to match the diameter of the larger launch tube. The anti tip-off device may be fabricated using any material suited to the launcher and rocket combination, including lexan, teflon, nylon, wood, or aluminum.
摘要翻译：提供了适用于可折叠的管内发射器的用于火箭弹的反倾销装置。双直径发射管需要在较大直径的管内稳定火箭。反倾销装置具有两个部分，它们一起形成一个中空圆筒，该中空圆筒装配在标准的高爆炸性防甲架火箭的鼻部上。滑动表面位于圆柱体的圆周周围，以便在较大的发射管运送期间为火箭提供支撑。表面接触防止了火箭在发射管过境期间摆动或倾倒。或者，永久粘合的稳定器腿或接合环可以附接到火箭以匹配较大发射管的直径。防脱落装置可以使用适合于发射器和火箭组合的任何材料制造，包括lexan，特氟隆，尼龙，木材或铝。

96. 发明授权

US5564651A Yaw angle free projectile 失效
标题翻译：无角自由射弹
公开(公告)号：US5564651A
公开(公告)日：1996-10-15
申请号：US391834
申请日：1989-08-04
申请人： Peter Wiemer , Werner Grosswendt
发明人： Peter Wiemer , Werner Grosswendt
IPC分类号： F41G7/00 , F42B10/02 , F42B10/28 , F42B10/62 , F42B12/04 , F42B15/00 , F42B15/01
CPC分类号： F42B10/661
摘要： A fin stabilized projectile for combatting a tank from above of the type including a rotating control unit disposed at the front of the projectile and containing a sensor for scanning the area to detect a target, and wherein the final phase of flying into the target is initiated by a force which acts on the tip of the projectile, particularly on the control unit. Since the control unit rotates relative to the warhead of the projectile to enable its sensor to detect the target, the gyro effect of this rotary movement generates pendulum movements in the projectile and thus causes deviations from the target at different target distances. To avoid yaw angles and lateral displacements of the projectile during the rotating-descending phase, a drive arrangement is provided within the projectile between the control unit and the warhead to impart an angular momentum to the warhead corresponding to the angular momentum of the control unit but directed in the opposite direction. Preferably this drive arrangement simultaneously serves as the drive for producing the rotation of the control unit.
摘要翻译：一种用于与上述类型相撞的坦克的稳定的弹丸，包括设置在射弹前部的旋转控制单元，并且包含用于扫描该区域以检测目标的传感器，并且其中启动飞入目标的最后阶段通过作用于射弹尖端的力，特别是在控制单元上。由于控制单元相对于弹丸的弹头旋转以使其传感器能够检测到目标，因此该旋转运动的陀螺效应在弹丸中产生摆动运动，从而在不同目标距离处产生与目标的偏差。为了避免在旋转下降阶段期间弹丸的偏航角度和侧向位移，在控制单元和弹头之间的射弹内提供驱动装置，以向对应于控制单元的角动量的弹头赋予角动量，但是指向相反的方向。优选地，该驱动装置同时用作用于产生控制单元的旋转的驱动器。

97. 发明授权

US5452864A Electro-mechanical roll control apparatus and method 失效
标题翻译：机电辊控制装置及方法
公开(公告)号：US5452864A
公开(公告)日：1995-09-26
申请号：US221358
申请日：1994-03-31
申请人： Robert L. Alford , John G. Rupert
发明人： Robert L. Alford , John G. Rupert
IPC分类号： F42B10/26 , F42B10/02 , F42B10/14 , F42B10/24
CPC分类号： F42B10/26
摘要： An apparatus and method for controlling roll of a projectile is disclosed. The projectile includes two sections decoupled about a roll axis. The front section includes a stator and the rear section includes a rotor and a static spin imparting member. The spin rate of the projectile is controlled by utilizing the rotor and stator in combination as a generator to brake the spin or as a motor to establish spin.
摘要翻译：公开了一种用于控制弹丸滚动的装置和方法。抛射体包括关于辊轴线解耦的两个部分。前部包括定子，后部包括转子和静电自旋赋予构件。通过将转子和定子组合用作发电机来控制抛射体的旋转速度来制动旋转或作为电动机来建立旋转。

98. 发明授权

US5375792A Method for reducing dispersion in gun launched projectiles 失效
标题翻译：减少喷射射弹分散的方法
公开(公告)号：US5375792A
公开(公告)日：1994-12-27
申请号：US221127
申请日：1994-03-31
申请人： John C. Grau
发明人： John C. Grau
IPC分类号： F42B10/02 , F42B10/00
CPC分类号： F42B10/02
摘要： Disclosed is a method for reducing dispersion in gun launched projectiles.n axial thrust is applied to the projectile at a specific time in the yaw cycle to cancel the effect of aerodynamic jump which arises from the effect of yawing motion disturbance created by an initial disturbance.
摘要翻译：公开了一种减少炮弹发射弹丸分散的方法。在偏航周期的特定时间，向射弹施加轴向推力，以抵消由初始扰动产生的偏航运动障碍的影响产生的气动跳跃的影响。

99. 发明授权

US5207397A Rotatable nose and nose boom strakes and methods for aircraft stability and control 失效
标题翻译：可旋转的鼻梁和鼻梁吊架和飞机稳定和控制的方法
公开(公告)号：US5207397A
公开(公告)日：1993-05-04
申请号：US535736
申请日：1990-06-08
申请人： Tsun-Ming T. Ng , Bert F. Ayers
发明人： Tsun-Ming T. Ng , Bert F. Ayers
IPC分类号： B64C19/00 , B64C23/00 , F42B10/02
CPC分类号： F42B10/02 , B64C19/00 , B64C23/00
摘要： Methods and apparatus for stability and maneuver control using rotatable nose strakes to control forebody vortices at medium to high angles of attack are disclosed. In one form, small left and right nose strakes are supported on a member or members forming the forward most contours of the forebody. Supporting of the two strakes on a single member allows rotation of the two in unison, the angular position thereof controlling the asymmetry of the forebody vortices at higher angles of attack, while support of each strake on a separate forebody nose member allows individual strake control for the same purpose. In another embodiment, the strakes may be mounted on a nose boom for rotation about the axis of the nose boom, whereby rotation of the strakes about the nose boom axis affects the development of the forebody vortices and the asymmetry thereof. Various embodiments and methods of operation thereof are disclosed.
摘要翻译：公开了使用可旋转的鼻梁进行稳定和机动控制的方法和装置，以控制中等至高的迎角的涡流。在一种形式中，小的左右鼻梁支撑在形成前体最前方轮廓的构件上。在单个构件上支撑两个斜槽允许两个旋转一致，其角度位置控制在更大的迎角处的前体旋涡的不对称性，同时每个肩带在单独的前身鼻部构件上的支撑允许单独的行程控制同样的目的在另一个实施例中，可以将吊架安装在起重臂上以围绕鼻梁的轴线旋转，由此，绕着起重臂轴线的斜面的旋转影响前体旋涡的形成及其不对称性。公开了各种实施例及其操作方法。

100. 发明授权

US3374969A Stabilized projectile 失效
标题翻译：稳定弹丸
公开(公告)号：US3374969A
公开(公告)日：1968-03-26
申请号：US56868166
申请日：1966-07-28
申请人： ARMY USA
发明人： RHODES RICHARD R
IPC分类号： F42B10/02
CPC分类号： F42B10/02

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