| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 一种可旋转电磁轨道炮炮弹 | CN201610055049.6 | 2016-01-27 | CN105651123A | 2016-06-08 | 袁晓明; 陈晓阳; 关继红; 张立杰 |
| 一种可旋转电磁轨道炮炮弹，引信后部外表面设螺纹，弹体前端设凹槽，凹槽内设内螺纹，引信和弹体通过螺纹相连，弹体外壁上设T型槽，弹体外壁T型槽内插接T型板，T型板固定在旋转动力壳的内板内壁上，旋转动力壳套接在弹体的外部，旋转动力壳内板和外板为两端开口的圆柱形壳体，内板置于外板的内部，内板和外板之间设叶片，弹体后端设螺纹孔，弹体后端与绝缘层一侧相邻，绝缘层中部设通孔，绝缘层另一侧与电枢一端相邻，螺钉从右依次穿过电枢中部的通孔和绝缘层中部的通孔，螺钉的一端设螺纹，螺钉一端插接在弹体后端的螺纹孔内，螺钉与弹体螺纹连接。本发明炮弹运动方向稳定，射击准确率高，射程较远，适用于电磁轨道炮的远距离和精确作战。 | ||||||
| 2 | 超低空高超音速巡航导弹 | CN201610306404.2 | 2016-05-11 | CN106017236A | 2016-10-12 | 鲁正祥 |
| 本发明涉及一种超低空高超音速巡航导弹，其特征在于在一仿弹体巡航导弹的头部设有高速旋转的“金刚钻头”，在该导弹的弹体外层设有“高速旋转外壳”；在该导弹的弹体内层设有“不旋转内舱”；借“流弹线形”无轮无翼；借“金刚钻头”化解风阻；借“旋转外壳”消除抖动；借“尾喷角度”控制方向；本发明能压缩反导系统反应时间及空间，甚至突破现有反导系统(尤其能确保核弹发射颗颗致命)。 | ||||||
| 3 | 発射体およびそのような発射体を収容するように意図された砲身 | JP2015230295 | 2015-11-26 | JP2016109416A | 2016-06-20 | ステファン・ベザン; カロル・ビヨー; ディディエ・スタネック; ヤニク・ボダス |
| 【課題】発射体およびそのような発射体を収容するように意図された砲身を提供する。 【解決手段】2つの端部12、13の間で軸Xに沿って延在する発射体11であって、軸Xの実質的に円筒状の砲身18内に配置されるように意図された発射体11に関する。発射体11は、発射体11の2つの端部12、13の第1端部12に開口し、および圧縮流体を受け入れるように意図された、その中心の中空部分14と、軸Xに対して実質的に垂直に中空部分14から発射体11を貫いて延在し、および発射体11の実質的に接線方向に圧縮流体を放出するように意図された実質的に半径方向の出口を有する複数の排気口15とを含む。発射体11と砲身18とを含む発射装置に関するものである。 【選択図】図1 |
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| 4 | PROJECTILE ET CANON DESTINÉ À RECEVOIR UN TEL PROJECTILE | EP15195553.1 | 2015-11-20 | EP3029412B1 | 2017-03-22 | VÉZAIN, Stéphane; BILLOT, Carole; STANEK, Didier; BAUDASSÉ, Yannick |
| 5 | Spinning Projectile | US15984791 | 2018-05-21 | US20180335285A1 | 2018-11-22 | Frederick Scott Gizowski |
| 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. | ||||||
| 6 | Exhaust assembly for mass ejection drive system | US11549223 | 2006-10-13 | US20070152097A1 | 2007-07-05 | Edgar Melkers; Rudy Eisentraut; Doron Strassman |
| 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. | ||||||
| 7 | Spherical missile and launching means therefor | US3554078D | 1969-02-10 | US3554078A | 1971-01-12 | HORVATH JOSEPH S |
| A spherical jet-propelled missile and launching device adapted to securely retain and support the spherical missile oriented for stable rotation about a spin axis at a small angle of elevation relative to the straight line path of flight of the missile for a short period of time following ignition and during which time the launching device utilizes means such as a motor or a turbine operated by the hot exhaust gases of the missile to spin the missile about the spin axis and preferably also utilizes the gases to cause release of the missile by thermal activation or melting of a thermally degradable bond by which the missile is initially retained to the launching device.
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| 8 | Slug for shotgun | US85226959 | 1959-11-12 | US3063376A | 1962-11-13 | BADEN POWELL EDWARD |
| 9 | EXHAUST ASSEMBLY FOR MASS EJECTION DRIVE SYSTEM | EP06826075 | 2006-10-13 | EP1934547A4 | 2011-11-30 | MELKERS EDGAR R; EISENTRAUT RUDY; STRASSMAN DORON |
| 10 | EXHAUST ASSEMBLY FOR MASS EJECTION DRIVE SYSTEM | EP06826075.1 | 2006-10-13 | EP1934547A2 | 2008-06-25 | MELKERS, Edgar, R.; EISENTRAUT, Rudy; STRASSMAN, Doron |
| 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. | ||||||
| 11 | PROJECTILE ET CANON DESTINÉ À RECEVOIR UN TEL PROJECTILE | EP15195553.1 | 2015-11-20 | EP3029412A1 | 2016-06-08 | VÉZAIN, Stéphane; BILLOT, Carole; STANEK, Didier; BAUDASSÉ, Yannick |
La présente invention concerne un projectile (11) s'étendant selon un axe X entre deux extrémités (12, 13), le projectile étant destiné à être positionné dans un canon (18) de forme sensiblement cylindrique d'axe X. Selon l'invention, le projectile (11) comprend : L'invention concerne aussi le canon (18) et un dispositif de lancement comprenant un projectile (11) et un canon (18) selon l'invention.
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| 12 | EXHAUST ASSEMBLY FOR MASS EJECTION DRIVE SYSTEM | EP06826075.1 | 2006-10-13 | EP1934547B1 | 2012-12-12 | MELKERS, Edgar, R.; EISENTRAUT, Rudy; STRASSMAN, Doron |
| 13 | High Spin Projectile Apparatus Comprising Components Made by Additive Manufacture | US15852968 | 2017-12-22 | US20180154446A1 | 2018-06-07 | James F. Brown; Thomas Ott |
| A method of making a projectile apparatus is provided that includes making one or components of the apparatus using an additive manufacture technique such as 3-D printing or laser-aided additive manufacture. The projectile apparatus can have a projectile, a propellant, and one or more optional components such as a wading, a sabot, and an intermediary device. The projectile can be fired through a barrel having a smooth bore. Additive manufacture methods can be used that involve forming components from superalloys having nanoparticles incorporated therein. The projectile apparatus can convert gas pressure or gas velocity into a high rate of projectile spin. The projectile has long-range accuracy due to a high or sustainable velocity and high rate of spin. | ||||||
| 14 | PROJECTILE AND BARREL INTENDED TO ACCOMMODATE SUCH A PROJECTILE | US14957392 | 2015-12-02 | US20160161230A1 | 2016-06-09 | Stéphane VÉZAIN; Carole BILLOT; Didier STANEK; Yannick BAUDASSÉ |
| A projectile extending along an axis X between two ends, the projectile being positioned in a barrel of substantially cylindrical shape of axis X is provided. The projectile comprises: a hollow part at its centre, opening onto a first of the two ends of the projectile to receive a compressed fluid, a plurality of vents passing through the projectile from the hollow part substantially perpendicular to the axis X and with a substantially radial outlet to expel the compressed fluid substantially at a tangent to the projectile. The invention also relates to the barrel and to a launch device comprising a projectile and a barrel. | ||||||
| 15 | Exhaust assembly for missile system, and method | US11549223 | 2006-10-13 | US07728266B2 | 2010-06-01 | Edgar R. Melkers; Rudy Eisentraut; Doron Strassman |
| A system, device and method provide 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 tail fin 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. | ||||||
| 16 | Short duration, high-torque rocket nozzle | US10292948 | 2002-11-13 | US06676072B1 | 2004-01-13 | Steven S. Kim; Eric Hawley |
| 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. | ||||||
| 17 | Warhead decoupling bearing | US10292949 | 2002-11-13 | US06666144B1 | 2003-12-23 | Steven S. Kim; Eric J. Hawley |
| 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. | ||||||
| 18 | Anti-personnel bomb | US47128265 | 1965-07-12 | US3264985A | 1966-08-09 | REED EDWIN G |
| 19 | SELF-SPINNING BULLET AND RELATED METHODS OF USE | US15424626 | 2017-02-03 | US20180051967A1 | 2018-02-22 | Todd Ronald Schwark |
| 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. | ||||||
| 20 | SELF CONTAINED INTERNAL CHAMBER FOR A PROJECTILE | US15583536 | 2017-05-01 | US20170322001A1 | 2017-11-09 | Dimosthenis Panousakis |
| The present disclosure provides a projectile with a self-contained internal chamber. Reaction of propellant inside the internal chamber can generate high pressure and the resultant exhaust gases can be used for projectile linear acceleration, rotational acceleration or other purposes. Torque can be produced by exhausting the pressure via radially placed, tangential nozzles or other outlets and can be configured to induce sufficient projectile spin to stabilize the projectile without the need for barrel rifling. The internal chamber may be separate or integral to the projectile itself. The projectile may include two or more chambers or compartments internal to the chambers. The disclosed projectile allows for higher pressures in the internal chamber than in the barrel and greater flexibility on pressure manipulation in the barrel and the projectile, allowing for a more efficient propellant combustion and manipulation of projectile characteristics such as muzzle and rotational speeds. | ||||||
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