公开(公告)号：US06676072B1

公开(公告)日：2004-01-13

申请号：US10292948

申请日：2002-11-13

Applicant: Steven S. Kim ,  Eric Hawley

Inventor： Steven S. Kim ,  Eric Hawley

IPC: F42B1000

CPC classification number: F42B10/28

Abstract: A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned torque ring inside of the nozzle that is anchored with erodible tabs. The tabs erode as the rocket exits the launcher. With the erosion of the tabs, the torque ring is free to rotationally move, which eliminates any torque imparted onto the rocket while retaining the torque ring with the rocket. This increases the reliability of rocket precision.

Abstract translation: 用于管发射火箭的火箭旋转控制系统在火箭上具有固定位置喷嘴，并且在喷嘴内部设置一组内部定位的扭矩环，其被可蚀刻的突片锚定。 当火箭退出发射器时，选项卡被侵蚀。 随着突片的侵蚀，扭矩环自由旋转移动，消除了在火箭上保持扭矩环时施加在火箭上的扭矩。 这增加了火箭精度的可靠性。

公开(公告)号：US20180051967A1

公开(公告)日：2018-02-22

申请号：US15424626

申请日：2017-02-03

Applicant: Todd Ronald Schwark

Inventor： Todd Ronald Schwark

IPC: F42B10/26

CPC classification number: F42B10/26 ,  F41A21/18 ,  F42B10/06 ,  F42B10/28 ,  F42B30/02

Abstract: A bullet may have its base shaped such that explosive from the cartridge or chamber causes the bullet to spin. A bullet may have any shape to the base that causes spinning that closely or exactly matches the rifling of a particular rifle. The base may be structured to achieve an impellor or turbine action to angularly accelerate the bullet while the bullet is being acted upon by an axial force from a propellant explosion during free travel within the gun or while travelling along the rifling.

公开(公告)号：US20100237185A1

公开(公告)日：2010-09-23

申请号：US12405310

申请日：2009-03-17

Applicant: Richard Dryer

Inventor： Richard Dryer

IPC: F42B10/66

CPC classification number: F42B10/668 ,  F42B10/26 ,  F42B10/28

Abstract: A spin-stabilized projectile is steered by taking air from an air intake at the front of the projectile, and expelling the air along an outer surface of the projectile to alter its trajectory toward the desired impact location. Air taken in through the air intake is directed toward a rotor that is able to rotate relative to the rest of the projectile. The rotor has an outlet that may direct the air taken in at the air inlet out in a direction having both radial and circumferential components. The force produced in the radial direction provides a steering force substantially normal to the projectile axis, used to steer the projectile. The force produced in the circumferential direction is used to provide impetus to spin the rotor. A brake is used to control the rotational speed of the rotor, to control the direction that the air is expelled from the projectile.

Abstract translation: 通过从射弹前部的进气口吸入空气，沿着射弹的外表面排出空气，改变其轨迹，朝向所需的冲击位置，引导旋转稳定的射弹。 通过进气口吸入的空气被引向能够相对于其余射弹旋转的转子。 转子具有出口，该出口可引导在空气入口处吸入的空气沿具有径向和周向分量的方向。 在径向方向上产生的力提供了基本上垂直于射弹轴线的转向力，用于引导射弹。 在圆周方向上产生的力用于提供旋转转子的动力。 制动器用于控制转子的转速，以控制空气从射弹排出的方向。

公开(公告)号：US20240183642A1

公开(公告)日：2024-06-06

申请号：US18406585

申请日：2024-01-08

Applicant: FSG Enterprises

Inventor： Frederick Scott Gizowski

IPC: F42B10/28 ,  F42B10/26 ,  F42B12/02 ,  F42B30/02

CPC classification number: F42B10/28 ,  F42B10/26 ,  F42B12/02 ,  F42B30/02

Abstract: A projectile, includes a head having a forward tip and a rear end, a stem extending from the rear end of the head and formed integrally with the head, and a sleeve positioned adjacent to the head and being collinear with the head and coaxial with the stem. The sleeve is hollow and substantially cylindrical and has an inner diameter and an outer diameter. A base is formed integrally with the stem by pressing a rearward end of the stem and expanding a rear dimension of the stem to capture the sleeve between the base and the head. The head and the base are rotatably dependent upon each other by connection with the stem, and the head, stem, and base are rotationally independent of the sleeve.

公开(公告)号：US11867487B1

公开(公告)日：2024-01-09

申请号：US17686354

申请日：2022-03-03

Applicant: Wach LLC

Inventor： Michael L. Wach ,  Michael L. Wach, Jr.

IPC: F42B12/62 ,  F42B10/28 ,  F42B10/02 ,  F42B14/06 ,  F42B14/02

CPC classification number: F42B14/06 ,  F42B10/025 ,  F42B10/28 ,  F42B12/625 ,  F42B14/02

Abstract: Launching an aeronautical system can comprise applying force or energy to the system in connection with accelerating the system. Responsive to the force or energy, an element of the system can move along a defined path within the system. The system can comprise a drive that converts motion along the defined path into rotational motion. The drive can rotate a mass within the system, which can be supported by a gas bearing. The rotating mass can comprise the moving element, a different system element, or the entire system. The rotating mass can produce angular momentum and can support gyroscopic stabilization of the aeronautical system. Rotational energy can be selectively imparted to and transferred between system elements in connection with stabilization management. System elements can moderate the system's response to impulsive stimuli associated with rotation and acceleration. A gas bearing can support an external surface of the system during launch.

公开(公告)号：US4886223A

公开(公告)日：1989-12-12

申请号：US200228

申请日：1988-05-31

Applicant: Robert F. Gartner

Inventor： Robert F. Gartner

IPC: F42B10/28

CPC classification number: F42B10/28

Abstract: The boat tail (28) of a fin-stabilized projectile (10) for firing from a smooth bore gun tube (14) is provided with a plurality of transversely extending spin chambers (34 a,b,c,d). Each chamber communicates with a converging-diverging nozzle (36 a,b,c,d) which extends through the outer surface of the boat tail (28) to provide free access to the surrounding atmosphere when the nozzles (36 a,b,c,d) are clear of the gun tube (14). When the propulsive charge in the rear of the gun tube (14) is ignited, a portion of the propellant gas produced by the charge enters the spin chambers (34 a,b,c,d) through the nozzles (36 a,b,c,d) and is stored in the chambers (34 a,b,c,d) until the converging-diverging nozzles (36 a,b,c,d) clear the gun tube (14), at which point the propellant gas exits through the nozzles (36 a,b,c,d) in the form of high speed tangentially directed jets which cause the projectile to spin at a predetermined rate which reduces dispersion due to fin misalignment.

Abstract translation: 用于从光滑钻枪管（14）射出的翅片稳定的射弹（10）的船尾（28）设置有多个横向延伸的旋转室（34a，b，c，d）。 每个室与会聚发散的喷嘴（36a，b，c，d）连通，其延伸穿过船尾（28）的外表面，以便当喷嘴（36a，b，c） ，d）没有枪管（14）。 当枪管（14）后部的推进装料被点燃时，由电荷产生的推进剂气体的一部分通过喷嘴（36a，b，c，d）进入旋转室（34a， c），并且存储在腔室（34a，b，c，d）中，直到会聚发散喷嘴（36a，b，c，d）清除枪管（14），此时推进剂气体 通过喷嘴（36a，b，c，d）以高速切向喷射的形式排出，这导致射弹以预定的速率旋转，这降低了由于翅片不对准引起的色散。

公开(公告)号：US3264985A

公开(公告)日：1966-08-09

申请号：US47128265

申请日：1965-07-12

Applicant: REED EDWIN G

Inventor： REED EDWIN G

IPC: F42B10/28 ,  F42B12/58

CPC classification number: F42B12/58 ,  F42B10/28

公开(公告)号：US20230160672A1

公开(公告)日：2023-05-25

申请号：US17893566

申请日：2022-08-23

Applicant: FSG Enterprises

Inventor： Frederick Scott Gizowski

IPC: F42B10/28 ,  F42B30/02 ,  F42B12/02 ,  F42B10/26

CPC classification number: F42B10/28 ,  F42B30/02 ,  F42B12/02 ,  F42B10/26

Abstract: A projectile fired from a weapon which has a bore with inner rifling, having a point and a base which are disposed within a sleeve such that the point and base of the projectile rotate independently of the sleeve when fired from a gun or similar weapon designed to discharge projectiles or similar material.

公开(公告)号：US20070152097A1

公开(公告)日：2007-07-05

申请号：US11549223

申请日：2006-10-13

Applicant: Edgar Melkers ,  Rudy Eisentraut ,  Doron Strassman

Inventor： Edgar Melkers ,  Rudy Eisentraut ,  Doron Strassman

IPC: F42B10/14 ,  F42B15/01

CPC classification number: F02K1/78 ,  F02K9/97 ,  F05D2250/31 ,  F42B10/16 ,  F42B10/28 ,  F42B10/665

Abstract: The present invention discloses a system, device and method for providing an exhaust assembly adapted for use with a mass ejection drive system to produce rotational torque about the principle axis of the drive system. Representative features generally include a vane suitably configured to at least partially engage a mass ejecta stream to apply a net rotational torque about the principal axis of the drive system, and a tailfin coupled to the at least one vane. The tailfin is configured to selectively deploy from an at least partially stowed position in order to decrease the application of net rotational torque about the principal axis of the drive system.

Abstract translation: 本发明公开了一种用于提供排气组件的系统，装置和方法，所述排气组件适于与质量喷射驱动系统一起使用以产生围绕驱动系统的主轴的旋转扭矩。 代表性特征通常包括适当地构造成至少部分地接合质量流出物流以围绕驱动系统的主轴施加净旋转扭矩的叶片，以及联接到至少一个叶片的尾鳍。 尾翼构造成从至少部分收起的位置选择性地展开，以便减小围绕驱动系统的主轴的净旋转扭矩的应用。

公开(公告)号：US06666144B1

公开(公告)日：2003-12-23

申请号：US10292949

申请日：2002-11-13

Applicant: Steven S. Kim ,  Eric J. Hawley

Inventor： Steven S. Kim ,  Eric J. Hawley

IPC: F42B1536

CPC classification number: F42B10/28 ,  F42B15/36

Abstract: The invention comprises an improved precision rocket motor and warhead system by increasing the spin rate of the rocket motor. The system comprises an outer housing segment attached to the end of a rocket motor tube and an annular sleeve placed within the end of the outer housing segment so that the end of the sleeve is aligned with the end of the segment. At least two annular bearings are placed around the outer surface of the sleeve. Normally the annular bearings will be made of a plastic type material that can be “stretched” around the outside of the sleeve prior to placing it within the outer housing segment. The inner surface of the sleeve will include a warhead attachment mechanism to secure the warhead to the inner surface. Finally, the invention includes a locking mechanism that locks the sleeve in place within the outer housing segment while attaching the warhead to the sleeve and unlocks to allow the sleeve to rotate independently of the rocket motor.

Abstract translation: 本发明通过提高火箭发动机的旋转速度，包括改进的精密火箭发动机和弹头系统。 该系统包括附接到火箭发动机管的端部的外部壳体段和设置在外部壳体段的端部内的环形套筒，使得套筒的端部与段的端部对准。 至少两个环形轴承围绕套筒的外表面放置。 通常，环形轴承将由塑料型材料制成，其可以在将其放置在外部壳体段内之前围绕套筒的外部“拉伸”。 套筒的内表面将包括用于将弹头固定到内表面的弹头附接机构。 最后，本发明包括锁定机构，该锁定机构将套管连接到套筒并将其解锁以使套筒独立于火箭发动机旋转，将套筒锁定在外部壳体段内的适当位置。