| 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 | 带有转动运动的射弹 | CN201480016972.8 | 2014-03-19 | CN105051482B | 2017-10-24 | 弗格斯·威廉·斯威特兹·范·睿瑟玛 |
| 本发明提出了一种射弹(11)和具有中心孔(23)的载弹器(22)，中心孔安装有射弹(11)，中心孔包括在射弹(11)和载弹器(22)之间功能性接合的旋转结构，旋转结构使用时通过射弹沿转动轴线的推进向射弹(11)提供绕转动轴线的旋转运动。旋转结构为射弹后的载弹器内的爆炸能量提供涡旋出口，以形成射弹(11)和载弹器(22)之间的气态轴承并将涡旋转动驱动传递至射弹(11)上以启动爆炸推进。 | ||||||
| 2 | 具有动力和控制装置的导向射弹 | CN200780029615.5 | 2007-07-25 | CN101855511A | 2010-10-06 | 罗伯特·M·莫克; 约翰·马歇尔; 格兰特·斯威尔 |
| 本发明公开一种射弹，所述射弹具有能力以产生和提供动力给位于彼此相对转动的射弹的两部分中的部件。射弹具有给予在两部分中的部件的动力的一对发生器。射弹具有力产生装置用于当射弹沿着射弹的纵轴线移动时改变射弹的方向，并且，力产生装置在射弹上的相对转动位置被发生器控制。 | ||||||
| 3 | 由多段式身管和流体推动自旋弹丸构成的武器系统和方法 | CN201710027172.1 | 2017-01-15 | CN106839868A | 2017-06-13 | 朱锐泷 |
| 一种多段式身管和流体推动自旋弹药，以及由它们构成的武器系统，通过在弹丸后部或尾部设置涡形孔或涡形槽来引导发射药燃气，并将其与多段式身管结合，使得弹丸可以通过流体力学方式形成自旋，而不用依赖于膛线切削。由此尝试在实现滑膛武器的高膛压高初速低阻力的同时，还能获得弹丸自旋，并降低身管和弹丸的成本。 | ||||||
| 4 | 带有转动运动的射弹 | CN201480016972.8 | 2014-03-19 | CN105051482A | 2015-11-11 | 弗格斯·威廉·斯威特兹·范·睿瑟玛 |
| 本发明提出了一种射弹(11)和具有中心孔(23)的载弹器(22)，中心孔安装有射弹(11)，中心孔包括在射弹(11)和载弹器(22)之间功能性接合的旋转结构，旋转结构使用时通过射弹沿转动轴线的推进向射弹(11)提供绕转动轴线的旋转运动。旋转结构为射弹后的载弹器内的爆炸能量提供涡旋出口，以形成射弹(11)和载弹器(22)之间的气态轴承并将涡旋转动驱动传递至射弹(11)上以启动爆炸推进。 | ||||||
| 5 | 磁力加速旋转箭弩 | CN201110270189.2 | 2011-09-03 | CN102313488B | 2015-09-02 | 盖天座 |
| 本发明是一种磁力加速旋转箭弩。属于武器类。其特点是：滑道①上镶嵌有NS极相对的多组磁铁②，推箭滑块⑧的前端镶嵌有磁力线分导块⑦，旋转箭③在前端嵌有磁力线分导块⑦的滑块⑧的推动下，一方面向前运动，同时也在作绕自身的轴芯的转动。当旋转箭③在离开磁铁②时的瞬间，有一个与旋转方向相反的拉力，由于有磁力线分导块⑦后，产生反方向旋转拉力的磁力线⑩，将被分导到磁力线分导块⑦上来，从而使作用在旋转箭③上的反方向旋转拉力减到很小，这样通过多组磁铁②后，在单方向旋转力的作用下，旋转箭③将被加速到很高的转速。从而使旋转箭在飞行中姿态更稳定，有效射程更远。 | ||||||
| 6 | 磁力加速旋转箭弩 | CN201110270189.2 | 2011-09-03 | CN102313488A | 2012-01-11 | 盖天座 |
| 本发明是一种磁力加速旋转箭弩。属于武器类。其特点是：滑道①上镶嵌有NS极相对的多组磁铁②，推箭滑块⑧的前端镶嵌有磁力线分导块⑦，旋转箭③在前端嵌有磁力线分导块⑦的滑块⑧的推动下，一方面向前运动，同时也在作绕自身的轴芯的转动。当旋转箭③在离开磁铁②时的瞬间，有一个与旋转方向相反的拉力，由于有磁力线分导块⑦后，产生反方向旋转拉力的磁力线⑩，将被分导到磁力线分导块⑦上来，从而使作用在旋转箭③上的反方向旋转拉力减到很小，这样通过多组磁铁②后，在单方向旋转力的作用下，旋转箭③将被加速到很高的转速。从而使旋转箭在飞行中姿态更稳定，有效射程更远。 | ||||||
| 7 | Missile | JP2008246684 | 2008-09-25 | JP2010078221A | 2010-04-08 | NASUNO YUSUKE; MATSUZAWA TOYOKI; MIZONOBU KIYOSHI; SUGIMOTO TAKAHISA |
| <P>PROBLEM TO BE SOLVED: To provide a steering airfoil sufficiently enduring acceleration force during shooting and improving controllability in the advancement direction. <P>SOLUTION: The missile includes: the steering airfoil 20 having a body 21 and a shaft 22; and an airframe 30 having an insertion part 32 to which the shaft 22 is rotatably inserted via a rolling bearing 33. A belleville spring 24 is provided between the body 21 of the steering airfoil 20 and the rolling bearing 33. By contraction of the belleville spring 24, the insertion part 32 of the airframe 30 and the body 21 of the steering airfoil 20 are made to abut on each other. <P>COPYRIGHT: (C)2010,JPO&INPIT | ||||||
| 8 | JPS6136159B2 - | JP50223980 | 1980-09-25 | JPS6136159B2 | 1986-08-16 | ANDAASUSOON KAATO; BAATARUSUSOON NIRUSU; BONDESUSOON SUTEIGU |
| 9 | Flying object | JP2008246684 | 2008-09-25 | JP4882099B2 | 2012-02-22 | 卓久 杉本; 豊樹 松澤; 清志 溝延; 雄介 那須野 |
| 10 | Inductive projectiles having a power and control mechanism | JP2009522947 | 2007-07-25 | JP2010513826A | 2010-04-30 | スイート，グラント; マーシャル，ジョン; モック，エム．ロバート |
| A projectile has the ability to generate and provide power to components located in two sections of the projectile which have relative rotation to each other. The projectile has a pair of generators allowing the powering of components in two sections. The projectile has a force-producing device for altering the direction of the projectile as the projectile moves along the longitudinal axis of the projectile and the relative rotational position of the force-producing device on the projectile is controlled by a generator. | ||||||
| 11 | System for ejecting spin-stabilized space flying body | JP2004239508 | 2004-08-19 | JP2005059850A | 2005-03-10 | BANK CHRISTIAN; KOLLOGE HANS-GEORG |
| PROBLEM TO BE SOLVED: To form an ejecting or releasing system to be inherently safe, to be light-weight, and to have reliability and make a released flying body perform a combined motion predeterminable accurately with the translation motion and rotating motion. SOLUTION: The released flying body 1 is supported by a spherical ball 5 in an ejecting container 2. The spherical body 5 is disposed in at least one groove route (3, 4) formed to rise in a spiral shape in the releasing direction between the outer wall of the released flying body 1 and the ejecting container 2. A drive element 6 is formed as a rotatingly driving element. COPYRIGHT: (C)2005,JPO&NCIPI | ||||||
| 12 | JPS56501257A - | JP50223980 | 1980-09-25 | JPS56501257A | 1981-09-03 | |
| 13 | Steerable spin stabilized projectile and methods | JP2011539533 | 2009-09-18 | JP2012511683A | 2012-05-24 | マックール、ジェームズ・ダブリュ |
| スピン安定発射体は、発射体の前後軸を中心とした内部質量の逆回転により、その進路が制御される。 内部質量は、発射体の外部ボディの空洞内にあるブームであってもよい。 内部質量は、外殻に対して傾斜可能であり、外殻の軸を中心に、外殻に対して逆回転するように構成されていてもよい。 逆回転により、発射体の外側の（スピンしていない）環境に対して、実質的に同じ向きにブームを保つことができる。 したがって、発射体の外殻に迎え角を与えることにより、発射体を操縦するために、発射体内のブームまたは他の重量のポジショニングを使用することができる。 磁気システムを使用して、ブームまたは他の重量を逆回転させてもよい。 発射体は、所望の照準点に向けて発射体を操縦することを支援するレーザ誘導システムを有していてもよい。
【選択図】 図２ |
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| 14 | Inductive projectiles having a power and control mechanism | JP2009522947 | 2007-07-25 | JP4855521B2 | 2012-01-18 | スイート，グラント; マーシャル，ジョン; モック，エム．ロバート |
| A projectile has the ability to generate and provide power to components located in two sections of the projectile which have relative rotation to each other. The projectile has a pair of generators allowing the powering of components in two sections. The projectile has a force-producing device for altering the direction of the projectile as the projectile moves along the longitudinal axis of the projectile and the relative rotational position of the force-producing device on the projectile is controlled by a generator. | ||||||
| 15 | Helical arrow | JP34538395 | 1995-11-27 | JPH09145300A | 1997-06-06 | OSHIBE YOSHIFUMI |
| PROBLEM TO BE SOLVED: To reduce an air resistance to cause an arrow to fly a far distance and to enable a rate of getting target to be increased by a method wherein a rear end part of an arrow shaft of an aluminum alloy pipe is formed to a helical shape. SOLUTION: A pipe made of an aluminum alloy, glass fiber, carbon fiber and synthetic resin or the like is formed into a circular shape so as to make an arrow shaft 1. An extremity end of the arrow shaft 1 is provided with a conical, line-stream shape or bullet-shaped arrow head 3 made of steel, or stainless steel. A rear end of the arrow shaft 1 is provided with an arrow slit 4 made of plastic material having a slit therein. Then, a groove having a helical shape of concave type is formed inside a diameter of the arrow shaft 1 just before the arrow slit 4 of the arrow shaft 1. With such an arrangement as above, it is possible to reduce an air resistance while shooting the helical arrow by a bow, cause the arrow to fly a far distance, rotate it in a helical shape, make a stable flying of the arrow and increase a rate of getting a target. COPYRIGHT: (C)1997,JPO | ||||||
| 16 | JPS5418220B2 - | JP4422573 | 1973-04-20 | JPS5418220B2 | 1979-07-05 | |
| 17 | JPS4921367A - | JP4422573 | 1973-04-20 | JPS4921367A | 1974-02-25 | |
| 18 | 발사체를 위한 저렴한 유도 장치 및 작동 방법 | KR1020157020602 | 2013-10-27 | KR101923664B1 | 2018-11-29 | 버젤길; 마룰아사프 |
| 유도어셈블리는발사체에연결되도록되어있고, 발사체의전방단부에연결되는후방주 유닛, 및후방단부에서후방주 유닛의전방단부에회전가능하게연결되는전방주 유닛을포함한다. 전방주 유닛은길이방향축선둘레로회전하도록되어있다. 상대속도제어유닛이후방주 유닛과전방주 유닛사이에서작동가능하며, 스핀제동력을제공하여상기전방주 유닛의상대회전속도를느리게할 수있다. 적어도하나의유도핀(fin)이전방유닛으로부터반경방향으로연장되어있다. 핀의피치각은그 핀에연결되어있는복귀스프링에의해제어가능하며, 그래서핀에대한공기역학적압력이낮아짐에따라상기핀의피치각은커지고또한핀에대한상기공기역학적압력이커짐에따라더 작아지게되는, 발사체 | ||||||
| 19 | 자체회전하는 탄환 | KR1020100094263 | 2010-09-29 | KR1020120032756A | 2012-04-06 | 정근석 |
| PURPOSE: A self-revolving bullet is provided to reduce friction heat generated between the bullet and a gun barrel and to increase the gunshot range of the bullet. CONSTITUTION: A self-revolving bullet(100) comprises an air inlet(110) and one or more exit holes(120). The air inlet is formed in the front end of the bullet and is extended to a predetermined point of an inner rear part of the bullet. The exit holes are formed on the rear surface of the bullet and discharge air flowing through the air inlet to the outside the bullet. | ||||||
| 20 | SPIN-STABILIZED NON-LETHAL PROJECTILE WITH A SHEAR-THINNING FLUID | US15832320 | 2017-12-05 | US20180164084A1 | 2018-06-14 | Erik K. Carlson; Joshua L. Edel |
| A non-lethal projectile having a shear-thinning fluid within an interior cavity. The shear-thinning fluid having a greater apparent viscosity at low shear rates to spin-stabilize the non-lethal projectile during flight and a lower apparent viscosity at a high shear rate corresponding with the shear-thinning fluid shearing against the frangible cap upon the non-lethal projectile striking the target, with the low viscosity of the shear-thinning fluid allowing proper dispersal upon impact with the target. The shear-thinning fluid can comprise a marking media and be in the form of an emulsion with less than about 50% liquid by volume to effectively disperse upon impact with the target. | ||||||
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