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公开(公告)号：US11885601B1
公开(公告)日：2024-01-30
申请号：US17373824
申请日：2021-07-13
发明人： Christopher Hoppe , Andrew Ehler , Matthew Snyder
摘要： A missile comprises a generally cylindrical body having a distal end and a proximal end; a nosecone having a pointed distal end and a proximal end, wherein the proximal ends of the body and nosecone are oriented toward each other; a forward angled section rotatably attached to the proximal end of the nosecone at its forward edge, the opposite end of the forward angled section having an angled edge perpendicular to the longitudinal axis except for the angle defined by the edge; a rear angled section rotatably attached to the proximal end of the body at its rear edge, the opposite end of the forward angled section having an angled edge matching the angled edge of the forward angled section, the angled edges of the forward angled section and the rear angled section being rotatably attached.
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公开(公告)号：US20220196366A1
公开(公告)日：2022-06-23
申请号：US17689945
申请日：2022-03-08
摘要： New systems, devices and methods for extremely precise aiming and shooting of firearms are provided. In some embodiments, predicted projectile impacts may be selected and adjusted, prior to execution. In some embodiments, a device including specialized computer hardware and software aids a user in planning a shot(s), evaluating the accuracy of the planned shot(s), adjusting the location of the planned shot(s), and executing the planned shots. In some embodiments, smart bullets with on-board electronics, active aerodynamics, and wireless communications capabilities adjust a flight path of the smart bullet in-flight, to match a selected target location and/or flight path. In some embodiments, an active firearm barrel may counteract and/or otherwise adjust for any other relevant ballistic and other accuracy-impacting factors with a position-actuable firing mechanism to maintain a projected flight path of such a point of impact.
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公开(公告)号：US10597154B1
公开(公告)日：2020-03-24
申请号：US16178236
申请日：2018-11-01
申请人： Steven M. Hoffberg
发明人： Steven M. Hoffberg
摘要： A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.
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公开(公告)号：US10458764B2
公开(公告)日：2019-10-29
申请号：US15332425
申请日：2016-10-24
摘要： A canard deployment mechanism includes a canard connected to a shaft that is hingedly attached to a rotatable hub that is moveable between a stowed and deployed position. The mechanism further includes a locking feature on the canard for restraining the canard in the stowed position. In an embodiment the mechanism further includes a pawl rotatably mounted on a drive gear to contact and restrain the canard in the stowed position.
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公开(公告)号：US09121680B2
公开(公告)日：2015-09-01
申请号：US13743829
申请日：2013-01-17
申请人： Raytheon Company
发明人： Robert W Morgan , James P Normoyle , Kurt J Wuest , David Drake
摘要： An air vehicle, such as a missile, for example an interceptor, includes control surfaces and a vectored thrust system, both used for steering the missile. A controller is operatively coupled to both steering mechanisms, and is configured to operate in a low dynamic pressure mode, which uses the vectored thrust system for at least part of the steering, only when the dynamic pressure is low, such as when the missile is at high altitude. At higher dynamic pressure, such as at lower altitude, the controller is configured to operate in a high dynamic pressure mode that uses only the control surfaces for steering. This allows the interceptor to operate at higher altitudes than interceptors that use only control surfaces for steering during flight. During flight for a high altitude interception the missile shifts from the high dynamic pressure mode to the low dynamic pressure mode.
摘要翻译： 诸如导弹的空中飞行器，例如拦截器，包括用于导向导弹的控制表面和向量推力系统。 控制器可操作地联接到两个转向机构，并且被配置为在低动态压力模式下操作，其仅在动压低时使用向量推力系统用于至少一部分转向，例如当导弹是 在高空。 在较高的动态压力下，例如在较低的高度，控制器被配置为在仅使用控制表面进行转向的高动态压力模式下操作。 这允许拦截器在高于高度的情况下操作，而不是在飞行中仅使用控制面进行转向的拦截器。 在高空拦截飞行期间，导弹从高动态压力模式转变为低动态压力模式。
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公开(公告)号：US20140326824A1
公开(公告)日：2014-11-06
申请号：US14345752
申请日：2012-09-13
申请人： Mats Larsson
发明人： Mats Larsson
IPC分类号： F42B10/62
CPC分类号： F42B10/62 , F42B10/60 , F42B10/64 , F42B15/01 , G01P13/025
摘要： The invention relates to a method for determining angle of incidence for a projectile in the path of the projectile from launcher to target, which projectile is guidable and substantially or partially roll-stable and comprises a control system and at least two actuators with associated control members, in which the following steps are included: determination of applied force for pitch control by evaluation of the moment upon the actuators of the projectile, determination of applied force for yaw control by evaluation of the moment upon the actuators of the projectile, calculation of the pitch component α of the angle of incidence and of the yaw component β of the angle of incidence, based on comparison between the evaluated moments and reference data for moments. The invention also relates to a GNC system.
摘要翻译： 本发明涉及一种用于确定射弹在从发射器到目标的路径中的入射角的方法，该射弹是可引导的并且基本上或部分地滚动稳定，并且包括控制系统和至少两个具有相关联的控制构件的致动器 ，其中包括以下步骤：通过评估射弹致动器上的力矩来确定用于俯仰控制的施加力，通过评估射弹致动器上的力矩来确定用于偏航控制的施加力，计算 入射角和偏航分量bgr的俯仰分量α; 的入射角，基于评估的力矩和力矩的参考数据之间的比较。 本发明还涉及一种GNC系统。
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公开(公告)号：US08674277B2
公开(公告)日：2014-03-18
申请号：US13508633
申请日：2010-11-11
摘要： There is disclosed a collar (100) which may be attached to a munition in order to control the trajectory of the munition. The collar (100) has a collar body (10); a surface (12) for capturing the projectile as it leaves the barrel; a sill (14) for supporting the surface (12) at the muzzle of the barrel; and a guidance means (20a, 20b, 21a, 21b) for altering the flow of air around the collar (100). The collar (100) supports itself at the muzzle and may attach to the projectile at the surface (12) to integrate with the projectile as the projectile is fired. The collar (100) is particularly suited for attachment to mortar rounds. Such a collar (100) gives a weapon operator the option of increasing the precision of a munition without having to carry a plurality of munition types.
摘要翻译： 公开了一种衣领（100），其可附接到弹药以控制弹药的轨迹。 衣领（100）具有衣领（10）; 用于当抛射体离开桶时捕获射弹的表面（12）; 用于在所述枪管的枪口处支撑所述表面（12）的基台（14）; 以及用于改变所述轴环（100）周围的空气流的引导装置（20a，20b，21a，21b）。 衣领（100）在枪口处支撑自身，并且可以在射弹被射击时附着在表面（12）处的射弹与射弹结合。 套环（100）特别适合于附着在迫击炮弹的周围。 这样的衣领（100）使武器操作者能够提高弹药的精度，而不必携带多种弹药。
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公开(公告)号：US06845937B2
公开(公告)日：2005-01-25
申请号：US10453777
申请日：2003-06-03
申请人： Henry August
发明人： Henry August
IPC分类号： B64C5/12 , B64C39/02 , B64C39/06 , B64C39/12 , B64D1/06 , F42B10/16 , F42B10/62 , F42B12/58 , F42B12/62 , F42B15/00 , B64C37/02
CPC分类号： B64C39/024 , B64C2201/021 , B64C2201/046 , B64C2201/104 , B64C2201/121 , F42B10/16 , F42B10/62 , F42B12/58 , F42B12/62 , F42B15/00
摘要： A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.
摘要翻译： 可重复使用的马赫速度移动平台通过垂直发射，无力滑翔，武器释放和着陆操作阶段提供武器有效载荷。 平台包括具有尾部和前端的大致管状的主体和有效载荷部分。 一个弓翼由身体后端支撑。 拱翼具有通过两个弯曲端板在远端连接的上翼和下翼。 前端组件在前端连接，具有向上定向的固定迎角，以产生前端提升。 安装在车体下方的散热瓦片和下部翼片下侧辐射/消散在高角度攻角平台折返期间产生的热量。 使用雷达吸收或雷达半透明材料。 该平台优选地从尾端排出有效载荷以进行安全分离。 起落架延伸到着陆阶段。
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公开(公告)号：US5423497A
公开(公告)日：1995-06-13
申请号：US512826
申请日：1965-12-03
申请人： Richard S. Ransom
发明人： Richard S. Ransom
CPC分类号： F42B10/62
摘要： A missile or other moving body comprising a rotatable portion arranged for rotation relative to another portion of the missile or body and control means for rotating said rotatable portion to bring it to any one of a plurality of preselected positions in relation to a datum and for exerting a thrust thereon having a lateral component with respect to the axis of rotation of said rotatable portion to produce a steering effect on the missile or body, said control means including a variable-incidence control surface mounted on the rotatable portion for rotation about a rotary axis transverse to the rotary axis of the rotatable portion, and actuator means responsive to control signals applied thereto for turning said control surface about its rotary axis to a first disposition in which it produces a component thrust causing rotation of said rotatable portion, and a second disposition in which it produces a lateral steering force on the missile.
摘要翻译： 导弹或其他移动体，其包括相对于导弹或身体的另一部分旋转的可旋转部分和用于使所述可旋转部分旋转以使其相对于基准的多个预选位置中的任何一个并用于施加的控制装置 其上具有相对于所述可旋转部分的旋转轴线的横向分量的推力以在导弹或身体上产生转向效应，所述控制装置包括安装在可旋转部分上的可变入射控制表面，用于围绕旋转轴线旋转 横向于可旋转部分的旋转轴线的致动器装置，以及响应于施加到其上的控制信号以将所述控制表面围绕其旋转轴线转动到第一配置的致动器装置，在第一配置中，其产生使所述可旋转部分旋转的分量推力，以及第二配置 其中它在导弹上产生横向转向力。
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公开(公告)号：US4966078A
公开(公告)日：1990-10-30
申请号：US456145
申请日：1989-12-27
摘要： Projectile steering apparatus and method employing the autogiro principle. Two rotatable blades are swung out from a longitudinal slot in a flying projectile. The blades are shaped to rotate as a result of the air stream rushing past the projectile. Steering is effected by altering the orientation of the blades with respect to the projectile in synchronism with rotation of the projectile. By varying the autogiro pattern produced by the pair of blades, it is possible to impart a force for correcting the projectile trajectory.
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