子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | Slug assembly for shotgun shotshell | US109267 | 1987-10-16 | US4779535A | 1988-10-25 | Nagatoshi Maki |
| A slug assembly for a shotgun shotshell having a case in which the slug assembly is incorporated, comprising a metal slug having a center axial cavity, an elastically deformable stabilizer which is fitted in the cavity, and a filler which is charged in the cavity. The stabilizer has a plunger having a diameter larger than a diameter of the opening of the cavity of the slug and an annular flange having a diameter substantially identical to a diameter of a barrel bore of a shotgun in which the slug assembly is to be used. The plunger and annular flange are coaxial to each other. The plunger cooperates with the cavity of the slug to maintain a distance between a rear end face of the slug and a front end face of the annular flange of the stabilizer at a predetermined value. | ||||||
| 162 | Projectile for round bore electromagnetic launchers with spin produced or prevented by electromagnetic means | US915607 | 1986-10-06 | US4741271A | 1988-05-03 | Robert M. Delvecchio; Emmanuel Aivaliotis |
| A projectile for use in an electromagnetic projectile launcher is provided with a conductive open loop which is mechanically attached to the body of the projectile. Means are provided for electrically connecting the open loop between a pair of generally parallel projectile launching rails when the open loop is in a predetermined angular orientation with respect to the rails. Current flowing in the loop then interacts with magnetic flux produced by current flowing within the rails to place a torque on the loop which can be used to spin-stabilize the projectile or to prevent rotation of the projectile depending upon the particular application. | ||||||
| 163 | Adapter assembly for flat trajectory flight | US649615 | 1976-01-14 | US4374577A | 1983-02-22 | Michael A. Brown; Chris A. Kalivretenos |
| An aerodynamic lift-generating adapter assembly secures to the nose of an guided projectile to provide a capability for flat-trajectory flight. The adapter assembly comprises a rotatably-supported, roll-stabilized lift-generating section coupled to an actuator section containing inertia means to initiate gyroscope rotor spinning. The control gyroscope is directly linked to the lift-generating device to maintain fixed orientation of the lift. | ||||||
| 164 | Glide projectile having jettisonable keel fin | US793508 | 1977-05-04 | US4145017A | 1979-03-20 | Lothar Stiklorus |
| A non-spinning glide projectile, comprises a body which includes a forward portion having one or more lift-producing devices or outwardly projecting air foil-like surfaces. A keel fin is detachably secured to the body intermediate its length, and means, such as a time fuse device, carried on the body, is employed for detaching the fin and jettisoning it after a predetermined flight path has been completed. | ||||||
| 165 | Non-lethal projectile and launcher therefor | US3782286D | 1972-11-20 | US3782286A | 1974-01-01 | RICHIE E |
| A non-lethal projector and launcher therefor for riot control and the like comprising a body formed from a relatively soft, pliant latex material compressed to projectile form and mounted within a restraining cup which in turn is mounted in a firing shell. The body at its rearward end includes retracted guidance structure that extends on the projectile being fired, a chamber at its forward end to receive a marking fluid for marking the target, and internal subdivisions in its mid portion designed to permit the body to expand laterally on impacting into a soft textured mass that flattens on impact to avoid injury to the target. The projectile launcher is in the form of a barrel assembly including a bell shaped muzzle which permits the projectile to be fired without jamming even when held against the target and braking slots for discharging the propelling gases rearwardly of the launcher to reduce recoil.
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| 166 | Stabilized projectile | US56868166 | 1966-07-28 | US3374969A | 1968-03-26 | RHODES RICHARD R |
| 167 | Projectile | US58534345 | 1945-03-28 | US2494026A | 1950-01-10 | NELSON ANDERSON |
| 168 | Bomb stabilizing means | US38996941 | 1941-04-23 | US2364197A | 1944-12-05 | DEE DOROTHY L |
| 169 | Explosive bomb for aerial work. | US17514717 | 1917-06-16 | US1291685A | 1919-01-14 | RAPP JOSEPH |
| 170 | 개선된 화살용 깃 | KR2020160003058 | 2016-06-03 | KR2020170004172U | 2017-12-13 | 김연 |
| 본고안은개선된화살용깃에관한것으로더욱상세하게는화살에부착되는복수개의화살깃을단면이곡면을갖도록형성함과더불어일면에곡면을갖는보조면을화살깃과일체로형성하여화살의비행중발생하는와류에의한비행의불안정을방지하여안정적인비행을보장할수 있는개선된형태의화살깃에관한것이다. | ||||||
| 171 | 드래그 효과 궤도가 향상된 발사체 | KR1020157029365 | 2011-03-11 | KR1020150129331A | 2015-11-19 | 막스피제이 |
| 발사체는카트리지와공동의총알을포함한다. 추진제는발사될때 총알의속도를증가시키기위해카트리지와공동의총알을충전한다. 공동의총알은편평해진선두단부를가지고, 환형링은편평해진선두단부에중심맞춤되어고정된다. 총알이비행중에있을때, 압력중심이총알의무게중심의전방에있도록, 편평해진선두단부와환형링은압력중심을전방으로이동시킨다. 제 2 실시형태에서, 복수의원주방향으로이격된슬릿들은공동의총알의후미단부에형성되어, 소프트타깃과의충돌시에방사상외측으로벌어지는복수의원주방향으로이격된핀들이만들어진다. | ||||||
| 172 | 포탄 | KR1020140196015 | 2014-12-31 | KR101522212B1 | 2015-05-21 | 배주현; 김완주 |
| 포탄몸체; 구동축을구비하여, 상기포탄몸체의외주면에회전가능하게장착되는조종날개; 상기구동축의내부에축방향으로이동가능하게결합되는축연결부를구비하고, 상기조종날개의내부에인입및 인출가능하게설치되는보조날개; 상기구동축의회전각도에따라상기축연결부와체결또는체결해제되도록상기축연결부와교차되는방향으로고정배치된고정돌기를구비하여, 상기보조날개를선택적으로고정하는보조날개고정유닛; 및상기구동축의내부에설치되고, 상기축연결부와상기고정돌기의체결해제시 상기보조날개를상기조종날개의외부로전개시키기위한동력을제공하는보조날개전개유닛을포함하는것을특징으로하는포탄이개시된다. | ||||||
| 173 | 감소된 마찰 발사체 | KR1020127030524 | 2011-03-01 | KR1020130080438A | 2013-07-12 | 막스피제이 |
| 발사체는 팁에 의해 형성되는 선두 부분, 팁 베이스, 및 선두 로드를 포함한다. 후미 부분은 주 베이스, 절단 베이스, 및 후미 로드를 포함한다. 원통형 인터페이스의 선두 단부는 팁이 팁 베이스와 만나는 환형 숄더에 인접하고, 후미 단부는 주 베이스가 절단 베이스와 만나는 환형 숄더에 인접하다. 팁 베이스와 절단 베이스 각각은 원통형 인터페이스의 선두 단부 및 후미 단부를 지지한다. 원통형 인터페이스의 중간 부분은 선두 로드와 후미 로드에 의해 지지되지 않고, 발사체가 발사될 때, 배럴의 랜드에 의해 방사상 내측으로 변형된다. 원통형 인터페이스의 선두 단부 및 후미 단부는 랜드와 접촉을 유지하고, 중간 부분은 랜드와 접촉을 유지하지 않아서, 발사체의 회전을 희생없이 발사체와 배럴 사이의 마찰을 감소시킨다. | ||||||
| 174 | 포탄 탄저부 홈과 비행중 공기 유입에 의한 포탄의 안정화 | KR1020110010419 | 2011-02-07 | KR1020120090165A | 2012-08-17 | 남호찬 |
| PURPOSE: A groove in a shell base and a device for stabilizing shells are provided to increase the stability of shell while the shells fire by flowing air into a vacuum zone generated at the back of the shell base. CONSTITUTION: A groove in a shell base and a device for stabilizing shells comprise a conical groove(4). The conical groove is formed in the shell base(3). The shell base is the bottom part of the shell. The conical groove is dug around a vertical center shaft(11). The stability of the shell is improved while the pressure of combustion gas generated when propelling charges are burned is focused on the conical groove. | ||||||
| 175 | 포탄의 비행 중 탄미부에 외부 공기 유입에 의한 비행 중 안정화 장치 | KR1020090126526 | 2009-12-18 | KR1020110069930A | 2011-06-24 | 남호찬 |
| PURPOSE: A stabilization device for flying against external air flowing into a rear portion of a shell is provided to demoralized a thin air area, improved a stability by the external air is rotated, emitted rearward of breech portion of shell. CONSTITUTION: A stabilization device for flying against external air flowing into a rear portion of a shell comprises : a shell(1), a shell body(3), an explosive(4) and an external air inlet(9). The explosive fill shell body, the shell body is connected to a shell rear portion. The external air inlet of the shell rear portion is connected to an inner chamber of the shell rear portion. During the shell is fly, the external air flows in the external air inlet, emits rearward of the shell rear portion. | ||||||
| 176 | 스파이크 노우즈 및 이를 구비한 비행체 | KR1020090011582 | 2009-02-12 | KR1020100092286A | 2010-08-20 | 윤상용; 권순길; 김진석; 이종철 |
| PURPOSE: A spike nose enhancing the flight stability in hypersonic and transonic domain and a flying object including the same are provided to simplify manufacturing processes by securing high flying stability in transonic velocity and supersonic velocity domain by preventing the using of a trip ring. CONSTITUTION: A spike nose enhancing the flight stability comprises a joint(102) and a nose part(104). The joint is combined in the body part of a vehicle. The nose part is projected from an adapter. The diameter of the tip-end part of the nose part is 25% or greater of the diameter of the body part of vehicle. | ||||||
| 177 | TACTICAL MISSILE AND BALANCE WEIGHT FOR SAID MISSILE | PCT/FR2013000073 | 2013-03-18 | WO2013144460A1 | 2013-10-03 | BARTHELEMY PATRICK; DUBOIS PHILIPPE; CARTON LAURENTA; SIBILLAUD NICOLAS; FERRAT MARC; PAINTENDRE FREDERIC |
| According to the invention, the balance weights of the missile are made from pellets (15) whereof the particle size is at most equal to 1mm and which is enclosed in a closed package (16). | ||||||
| 178 | TIPPED PROJECTILES | PCT/US2008074581 | 2008-08-28 | WO2009061545A2 | 2009-05-14 | DENNISON GREGORY A |
| A projectile is provided with a projectile tip having enhanced aerodynamic properties to improve accuracy of the projectile. The tip has a body having a base or lower end, an upper end and a curved, side wall between its upper and lower ends that defines an ogive tip length. The tip is received with a projectile jacket and also can have a series of aerodynamic features formed in its body to modify air flow about the body of the projectile in flight. | ||||||
| 179 | Launch vehicles with ring-shaped external elements, and associated systems and methods | EP14160015.5 | 2014-03-14 | EP2778074A3 | 2018-05-02 | Featherstone, Mark; Sanders, John Michael; Ramsey, Roger E.; Wetzel, Eric David |
Launch vehicles (1400) with ring-shaped external elements (1480), and associated systems and methods are disclosed. An aerospace system in accordance with a particular embodiment includes a launch vehicle (1400) having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis (V) extending between the first and second ends, and having an external, outwardly facing surface. The system further includes an annular element (1480) carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element has a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system is carried by the launch vehicle, and has at least one nozzle (1411) positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent.
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| 180 | CERAMIC-ENCAPSULATED THERMOPOLYMER PATTERN OR SUPPORT WITH METALLIC PLATING | EP14822183 | 2014-07-09 | EP3019313A4 | 2017-04-05 | MIARECKI MICHAEL S; PARKOS JOSEPH; LOMASNEY GARY M; WATSON CHARLES R |
| A method for fabricating a ceramic component is disclosed. The method may comprise: 1) forming a polymer template having a shape that is an inverse of a shape of the ceramic component, 2) placing the polymer template in a mold; 3) injecting the polymer template with a ceramic slurry, 4) firing the ceramic slurry at a temperature to produce a green body, and 5) sintering the green body at an elevated temperature to provide the ceramic component. | ||||||
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