| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Wad and slug for a shotgun cartridge | US555150 | 1983-11-25 | US4587905A | 1986-05-13 | Nagatoshi Maki |
| An assembly of a wad and a slug for a shotgun cartridge, the wad and the slug being coaxially connected to each other by means of male and female connectors provided on the wad and the slug without play between the connectors, the assembly comprising peripheral projections spaced from one another in the axial direction of the assembly. | ||||||
| 122 | Overflying munitions device and system | US92898 | 1979-11-09 | US4356770A | 1982-11-02 | John V. Atanasoff; W. Kenneth Clark; David Henderson; Kenneth W. Wreghitt |
| In a munitions system, a cylindrical canister is fired over a target. The canister carries a target sensing infrared device and, when a target is detected, a projectile is fired downward from the bottom of the overflying missile. A spinning motion is imparted to the missile to stabilize its flight, and a wobbling motion is imparted to the missile to provide a larger target area. The projectile forms a concave lower end to the missile and is fired by an explosive charge. | ||||||
| 123 | Projectile with spin-producing flow passages | US21606 | 1979-03-08 | US4296893A | 1981-10-27 | Josef Ballmann |
| A projectile for shooting from a gun barrel in response to the force of a propellant gas emanating from the aperture of a propellant container, comprising a projectile body having a plurality of spin-producing propellant gas flow passages associated therewith, said passages annularly surrounding, and having their respective axes extending obliquely to, the longitudinal axis of the projectile body, wherein each passage has an inlet portion converging to an adjoining constricted portion, and a diverging portion extending downstream from the constricted portion, the axis of each passage being curved over the entire length of its converging inlet portion and substantially rectilinear over its diverging portion, and the walls of the diverging portion of each passage having a substantially rectilinear form, as viewed in the direction of propellant gas flow. | ||||||
| 124 | Fluid stabilizing insert for projectiles | US638724 | 1975-12-08 | US4094246A | 1978-06-13 | Bruce W. Travor |
| A spin stabilized projectile containing an annulus of incendiary liquid sounding a burster tube, in which the liquid is compartmentalized to minimize rotational spin loss of the projectile due to centrifugal force effect on or anti-spin inertia by the liquid. | ||||||
| 125 | Autorotor launching system | US578958 | 1966-09-01 | US4052927A | 1977-10-11 | Abraham Flatau |
| An airborne launcher and method of delivering a munition system comprisingn combination (a) means to rotate the autorotor to a predetermined angular velocity prior to release from the launcher (b) means which direct the rotation of the autorotor in a clockwise or counterclockwise direction resulting in the desired angle of glide of the munition to a preselected area without the aid of the forward speed of the airborne vehicle. | ||||||
| 126 | Radio controlled wing rotor bomblet | US568682 | 1966-07-28 | US3954057A | 1976-05-04 | Abraham Flatau |
| The invention is directed to controlling the flight of an autorotating wingotor comprising an elongated wing rotor, actuating means remotely controlled, plates coaxially secured to each end of the said rotor, flight control means, said actuating means driving said flight control means axial movement along means mounted adjacent each end of said rotor and thereby effecting the trajectory of the autorotating wing rotor. | ||||||
| 127 | Spherical shaped body with aerodynamic torque ribs | US3611930D | 1966-06-27 | US3611930A | 1971-10-12 | KENSINGER ROBERT S |
| 1. A generally spherically shaped member having a plane of symmetry and an axis passing substantially through the geometric center of said member normal to said plane of symmetry, said member further having external aerodynamic features which will cause it, when placed into an airstream, to spin about said axis regardless of the orientation of said member relative to the airstream, said aerodynamic features including a plurality of torque ribs, each of said ribs having: AN AERODYNAMIC FORCE CENTERED ON SAID PLANE OF SYMMETRY AND EXTENDING A SHORT DISTANCE TO EITHER SIDE OF IT; A FRONT FACE HAVING A FIRST PART EXTENDING FROM ONE SIDE OF SAID AERODYNAMIC FENCE FOR A SHORT DISTANCE SUBSTANTIALLY PARALLEL TO SAID PLANE OF SYMMETRY, THEN CURVING IN A CIRCULAR RADIUS AWAY FROM SAID PLANE OF SYMMETRY INTO A SEGMENT AT AN ANGLE TO SAID PLANE OF SYMMETRY, SAID FACE FURTHER HAVING A SECOND PART EXTENDING FROM THE OTHER SIDE OF SAID AERODYNAMIC FENCE, SAID SECOND PART BEING SUBSTANTIALLY SYMMETRICAL TO SAID FIRST PART WITH REFERENCE TO SAID PLANE OF SYMMETRY; AND A REAR FACE PROVIDING A SMOOTH STREAMLINED SURFACE EXTENDING TOWARDS THE REAR AND DOWNWARD FROM THE UPPER EDGE OF SAID FRONT FACE AND MERGING WITH THE SPHERICAL SURFACE OF THE MEMBER.
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| 128 | Apparatus for launching projectiles | US3500714D | 1967-12-14 | US3500714A | 1970-03-17 | CULLINANE JAMES F |
| 129 | Projectile for firearms | US85482259 | 1959-11-23 | US3065696A | 1962-11-27 | KLEINGUENTHER ROBERT A |
| 130 | Projectile | US71237246 | 1946-11-26 | US2559955A | 1951-07-10 | HARTWELL HARLOW H |
| 131 | Drop bomb | US57174331 | 1931-10-29 | US1986034A | 1935-01-01 | OTTO UTTER ERNST WILHELM |
| 132 | Projectile | US19226417 | 1917-09-20 | US1341844A | 1920-06-01 | KENNEDY DOUGAN |
| 133 | Philip g | US463922D | US463922A | 1891-11-24 | ||
| 134 | 一种带螺旋翼的弩箭 | CN201220041568.4 | 2012-02-09 | CN202494384U | 2012-10-17 | 支海波; 田波; 蒋万; 焦恒刚 |
| 一种带螺旋翼的弩箭，包括箭杆、设置在箭杆一端的箭头和连接在箭杆另一端的带有螺旋翼的尾翼，箭杆与箭头整体成型并且从箭头向箭杆方向成流线型，尾翼与箭杆之间采用活动连接。本实用新型解决的技术问题在于弩箭射击飞行轨迹的方向性和平衡性。本实用新型公开的带螺旋翼的弩箭，通过在箭杆尾端设置螺旋形的尾翼，在提高飞行稳定性的同时，赋予了弩箭绕轴旋转的能力，提高了弩箭的侵切能力。 | ||||||
| 135 | 로켓 제트류 분산의 감소 | KR1020167002380 | 2014-07-01 | KR101889496B1 | 2018-08-17 | |
| 현재개시되는주제사항은제트류오정렬에의해발생되는로켓의분산을감소시키는방법, 장치및 컴퓨터저장디바이스를포함하고, 이로켓은로켓엔진을포함한다. 로켓엔진의총 작동시간의제1 기간및 제2 기간으로의분할을나타내는정보가획득되고; 제1 기간동안생성된임펄스와제2 기간동안생성된임펄스사이의차가사전정의된값보다더 작으며; 로켓엔진의활성화시간으로부터시작하는제1 기간과동일한기간이측정되고; 기간이종료되면로켓의세로축둘레로로켓이회전되고; 회전각도가측정되며; 180° 회전이완료되면회전이중단된다. | ||||||
| 136 | 보조센서를 이용한 회전분리형 유도신관 및 자세추정 방법 | KR20160096583 | 2016-07-29 | KR20180013211A | 2018-02-07 | 정균명 |
| 본발명은탄체와신관부가상호회전운동하는회전분리형유도신관에있어서, 상기탄체의항법정보를제공하는자세측정부, 상기탄체와상기신관부의상호회전운동으로발생하는신호를측정하는신호측정부, 상기신호측정부에서측정한신호를물리량으로변환하는신호처리부; 를포함하는탄체와, 상기탄체와상기신관부의상호회전운동에의한측정신호를생성하는신호생성부; 를포함하는신관부로구성된것을특징으로하는회전분리형유도신관이다. | ||||||
| 137 | 이탈피를 가지는 탄두 조립체를 포함하는 지능형 탄두 | KR1020150033426 | 2015-03-10 | KR1020160109295A | 2016-09-21 | 최우천; 김윤건; 이효근; 송호인; 김인근; 장쾌현 |
| 본발명은지능형탄두에대한것으로, 표적을탐지하기위한센서를포함하는탄두및, 상기탄두와적어도하나의이탈피의결합체로구성되는탄두조립체와, 상기표적을탐지하여거리및 방위각을결정하고, 상기탐지된방위각및, 기설정된방출각에따라상기탄두조립체를회전시켜방출하는플랫폼조립체와, 상기방출된상기탄두조립체가목표방출거리로의비행에필요한추진력및 상기탄두조립체의회전에필요한회전력을제공하는방출장치조립체를포함하며, 상기탄두조립체는, 상기탄두가, 상기적어도하나의이탈피에의해기 설정된일정각도만큼기울어진상태로상기탄두조립체에고정되는것을특징으로한다. | ||||||
| 138 | 발사체를 위한 저렴한 유도 장치 및 작동 방법 | KR1020157020602 | 2013-10-27 | KR1020150108849A | 2015-09-30 | 버젤길; 마룰아사프 |
| 유도 어셈블리는 발사체에 연결되도록 되어 있고, 발사체의 전방 단부에 연결되는 후방 주 유닛, 및 후방 단부에서 후방 주 유닛의 전방 단부에 회전가능하게 연결되는 전방 주 유닛을 포함한다. 전방 주 유닛은 길이 방향 축선 둘레로 회전하도록 되어 있다. 상대 속도 제어 유닛이 후방 주 유닛과 전방 주 유닛 사이에서 작동가능하며, 스핀 제동력을 제공하여 상기 전방 주 유닛의 상대 회전 속도를 느리게 할 수 있다. 적어도 하나의 유도 핀(fin)이 전방 유닛으로부터 반경 방향으로 연장되어 있다. 핀의 피치각은 그 핀에 연결되어 있는 복귀 스프링에 의해 제어가능하며, 그래서 핀에 대한 공기역학적 압력이 낮아짐에 따라 상기 핀의 피치각은 커지고 또한 핀에 대한 상기 공기역학적 압력이 커짐에 따라 더 작아지게 되는, 발사체
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| 139 | 유도무기용 디커플링 베어링모듈 | KR1020110116582 | 2011-11-09 | KR101413498B1 | 2014-07-01 | 최용준; 김형호; 이종수 |
| 본 발명은 발사체의 발사충격을 대부분 흡수하여 파손의 위험성을 최소화시키고, 탄체와 조종체 사이의 간격으로 이물질 등이 유입되는 것을 원천적으로 봉쇄하면서도 탄체와 조종체간의 분리된 스핀운동이 원활하게 이루어질 수 있는 유도무기용 디커플링 베어링모듈에 관한 것이다.
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| 140 | 유도무기용 디커플링 베어링모듈 | KR1020110116582 | 2011-11-09 | KR1020130051308A | 2013-05-20 | 최용준; 김형호; 이종수 |
| PURPOSE: A decoupling bearing module for a guided missile is provided to minimize the risk of damage by absorbing impact of lunching if the lunching impact of a projectile is generated. CONSTITUTION: A decoupling bearing module for a guided missile comprises a rotary shaft, a pair of bearing inner wheels, a pair of bearing outer wheels, a pair of connectors, and a plastic deformation ring(500) in a round shape. The plastic deformation ring in a round shape is protruded to one surface among one end surface of a controller and one end surface of an air frame(2) for preventing contact with each other. The plastic deformation ring absorbs lunching impact of a projectile(1) by plastic deformation if one end surface of the controller and one end surface of the air frame come close through the lunching impact of the projectile. | ||||||
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