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 |
|---|---|---|---|---|---|---|
| 21 | AIR VEHICLE WITH CONTROL SYSTEM MECHANICAL COUPLER | EP15771304.1 | 2015-04-23 | EP3177887A1 | 2017-06-14 | MORGAN, Bruce E.; ALEJANDRO, Stevie; ROBICHAUX, Jerry D.; RAMOS, Alfredo; KLEMM, Heinz D.; NICKEL, Bryan W.; DOUGLAS, Andrew P. |
| An air vehicle, such as a munition like a guided bomb or missile, has a control system that allows control surfaces to be mechanically uncoupled from one or more actuators to allow the control surfaces to freely move (rotate) relative to a fuselage of the vehicle, for example allowing the control surfaces to “weather vane” by assuming an orientation corresponding to the direction of airflow past the air vehicle (direction of airflow relative to the air vehicle). When active positioning of the control surfaces is desired, the control surfaces may be mechanically coupled to one or more actuators that are used to position the control surfaces. The selective coupling of the actuator(s) and the control surfaces may be accomplished by selectively coupling together a sleeve that is mechanically coupled to the control surfaces, and a nut that moves along a shaft of an actuator, for example using a resilient device. | ||||||
| 22 | ÜBUNGSPATRONE | EP13717484.3 | 2013-04-12 | EP2841871B1 | 2016-06-15 | SCHÖTZIG, Frank; HEITMANN, Thomas; KRATZSCH, Klaus-Achim; VAGEDES, Michael |
| 23 | LEITWERKSTABILISIERTES VOLLKALIBER-ÜBUNGSGESCHOSS | EP13709379.5 | 2013-03-05 | EP2828607B1 | 2016-05-18 | HEITMANN, Thomas; VAGEDES, Michael; LENGNICK, Mathias; BAUMANN, Christian; RITZERFELD, Elmar; FREUDENTHAL, Klaus-Dieter |
| 24 | DRAG EFFECT TRAJECTORY ENHANCED PROJECTILE | EP11772385 | 2011-03-11 | EP2561309A4 | 2015-10-21 | MARX PJ |
| 25 | Projectile à vol supersonique pour canon à tube lisse | EP15160232.3 | 2015-03-23 | EP2930460A1 | 2015-10-14 | Cayzac, Roxan; Adam, Jean-Roch |
L'invention a pour objet un projectile (1) à vol supersonique tirable par un canon à tube lisse, projectile comportant un corps (2) au calibre du tube du canon et un moyen de stabilisation aérodynamique (3) disposé en arrière du corps (2). Ce projectile est caractérisé en ce que le moyen de stabilisation aérodynamique (3) est formé par un cône dont le plus grand diamètre (D3) est sensiblement égal au diamètre (D2) du corps (2), le cône (3) étant relié au corps (2) par une portée cylindrique (4), le corps (2) comportant une face arrière (5) annulaire perpendiculaire à l'axe (6) du projectile et sur laquelle se raccorde la portée cylindrique (4).
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| 26 | ÜBUNGSPATRONE | EP13717484.3 | 2013-04-12 | EP2841871A1 | 2015-03-04 | SCHÖTZIG, Frank; HEITMANN, Thomas; KRATZSCH, Klaus-Achim; VAGEDES, Michael |
| Practice cartridge comprising a propellant sleeve (2), which is at least partially filled with a propellant powder (9), and a fin-stabilized full-calibre practice projectile (3), fastened to the front of the propellant sleeve (2), wherein the practice projectile (3) comprises a solid head part (4) and a tubular tail assembly (5) adjoining the head part (4) to the rear. To achieve the effect that, after firing the practice cartridge (1), no appreciable pressure fluctuations occur in the barrel of the corresponding weapon even in the case of relatively small amounts of propellant powder (9), the invention proposes that a container in the form of a bag and containing the propellant powder (9) extends axially from the bottom end region of the propellant sleeve (2) into the inner space (13) of the tubular tail assembly (5). | ||||||
| 27 | PIEZOELECTRIC FIBER, ACTIVE DAMPED, COMPOSITE ELECTRONIC HOUSINGS | EP08874892 | 2008-07-02 | EP2307847A4 | 2013-09-11 | FACCIANO ANDREW B; MOORE ROBERT T; HLAVACEK GREGG J; SEASLY CRAIG D |
| 28 | TELESCOPED PROJECTILE | EP06849815.3 | 2006-08-08 | EP1924817B1 | 2009-03-11 | DRYER, Richard |
| A projectile (10) reconfigures in flight from a launch configuration, in which the center of gravity is aft of the center of pressure, to a flight configuration, in which the center of gravity is forward of the center of pressure. The projectile includes a forward portion (12) and an aft portion (14), and the reconfiguration involves movement of at least part of one of the portions relative to the other portion. The projectile may have an overall substantially conical shape when in the launch configuration. The forward portion may include a substantially conical nose (20), and a cylindrical central body (22) attached to the nose. In the launch configuration, at least part of the central body may be located within a hollow (26) in a base (24) of the aft portion. The base may be slidable relative to the central body. | ||||||
| 29 | A PENETRATOR AND METHOD FOR USING SAME | EP03759375.3 | 2003-09-17 | EP1543289A1 | 2005-06-22 | HUNN, David, L.; BANKS, Johnny, E.; COWAN, Carlton, B. |
| A penetrator (100) includes a fore body (120) having a center of aerodynamic pressure (122) forward of a center of gravity (120) and a stabilizing portion (104) removably attached to the fore body such that, when attached to the fore body, a center of gravity for the penetrator is forward of a center of aerodynamic pressure for the penetrator. A method of using a penetrator includes propelling the penetrator toward a first target, penetrating the first target with a fore body of the penetrator, and detaching a stabilizing portion of the penetrator from the fore body. The method further includes impacting the second target with the fore body. | ||||||
| 30 | PROJECTILES HAVING CONTROLLABLE DENSITY AND MASS DISTRIBUTION | EP96917176.0 | 1996-06-05 | EP0779967A1 | 1997-06-25 | LOWDEN, Richard, A.; McCOIG, Thomas, M.; DOOLEY, Joseph, B.; SMITH, Cyrus, M. |
| A projectile (36) achieves inherent aerodynamic characteristics through differential mass density, which places the center of gravity in a desired location relative to the center of pressure. | ||||||
| 31 | Cartouche à projectile de portée limitée | EP95400452.9 | 1995-03-02 | EP0676613A1 | 1995-10-11 | Denis, Jean-Pierre |
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| 32 | 무게중심이 헤드부에 있는 비행안정 탄두 및 그 제조 방법 | KR1020170049955 | 2017-04-18 | KR101754061B1 | 2017-07-05 | 김준규; 김형세 |
| 본발명은비중이낮은금속재로탄두전장(L)의 1/2이상의길이및 용적을탄미에내장함으로써, 탄두무게중심(cg)이탄두헤드부에있어탄두의편주각이줄고, 이에따라비행간탄두의세차운동이줄어들어비행안정이탁월하다. 종래의탄두는탄두탄미부(C-100)에무게중심이있어서일정거리비행은회전력에의한비행안정을도모하나, 비행속도가줄어드는일정거리부터는점차적으로탄미부가전도되게되어전면의저항력이더욱증가되고, 이로인해사거리가줄어들고더욱더 정확도는낮아진다. 상기와같은문제점을개선하기위해서탄두의중간체를비중이낮은금속재로일정용적을채움으로써헤드부로무게중심을이동시켜편주각을줄이고, 세차회전운동을현저히작게하여비행진행간전면저항력을줄이며목표물에최종접촉되는최소의면적으로파괴력을증대시키며비행간전도되지않아정확도및 파괴력과사거리가연장된다. 본발명의탄두는사거리연장을비롯한정확도향상과파괴력증대및 저지력이우수한탄두이며, 탄심체와중간체, 자켓부로분리하여압입, 단조, 드로잉하여조립하는것만으로도탄두를제조할수 있기때문에제작성이향상되는동시에탄두의성능은더욱증대된다. | ||||||
| 33 | 로켓 제트류 분산의 감소 | KR1020167002380 | 2014-07-01 | KR1020160036042A | 2016-04-01 | 레비,벤자민; 골드버그,슈무엘 |
| 현재개시되는주제사항은제트류오정렬에의해발생되는로켓의분산을감소시키는방법, 장치및 컴퓨터저장디바이스를포함하고, 이로켓은로켓엔진을포함한다. 로켓엔진의총 작동시간의제1 기간및 제2 기간으로의분할을나타내는정보가획득되고; 제1 기간동안생성된임펄스가제2 기간동안생성된임펄스와적어도대략동일하며; 로켓엔진의활성화시간으로부터시작하는제1 기간과동일한기간이측정되고; 기간이종료되면로켓의세로축둘레로로켓이회전되고; 회전각도가측정되며; 180° 회전이완료되면회전이중단된다. | ||||||
| 34 | 드래그 효과 궤도가 향상된 발사체 | KR1020127030680 | 2011-03-11 | KR1020130054284A | 2013-05-24 | 막스피제이 |
| 발사체는 카트리지와 공동의 총알을 포함한다. 추진제는 발사될 때 총알의 속도를 증가시키기 위해 카트리지와 공동의 총알을 충전한다. 공동의 총알은 편평해진 선두 단부를 가지고, 환형 링은 편평해진 선두 단부에 중심 맞춤되어 고정된다. 총알이 비행 중에 있을 때, 압력 중심이 총알의 무게 중심의 전방에 있도록, 편평해진 선두 단부와 환형 링은 압력 중심을 전방으로 이동시킨다. 제 2 실시형태에서, 복수의 원주방향으로 이격된 슬릿들은 공동의 총알의 후미 단부에 형성되어, 소프트 타깃과의 충돌시에 방사상 외측으로 벌어지는 복수의 원주방향으로 이격된 핀들이 만들어진다.
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| 35 | 수중 물체에 사용하기 위한 공기 역학적으로 안정화된 발사체 시스템 | KR1019970700838 | 1996-06-06 | KR100220883B1 | 1999-09-15 | 브라운,제프리,에이.; 콥세이,리드; 툴린,마샬; 클라인,로이 |
| 발사체(50)는 공기 중의 한 위치로부터, 공기/물 경계면을 통해, 그리고 수중물체(24)를 향해 추진된다. 발사체(50)는 발사체(50) 주위에 캐비테이션 공간(30)을 형성하는 전방 단부(52)를 포함하여, 발사체 주위의 물 견인을 피한다. 발사체(50)는 공기중에서 발사체(50)를 공기 역학적으로 안정화시키고 외향의 전개된 또는 핀형 후방 단부(54)와 물속에서 발사체를 안정화시키는 플레어를 더욱 포함하고, 각각의 경우는 요잉에 대항한다. | ||||||
| 36 | Steerable rotating projectile | US15476275 | 2017-03-31 | US10118696B1 | 2018-11-06 | Steven M. Hoffberg |
| A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal. | ||||||
| 37 | Rocket-based inverted parachute deployment system | US15249079 | 2016-08-26 | US10106264B1 | 2018-10-23 | Cameron Robertson; Todd Reichert; Damon Vander Lind |
| A system to deploy a parachute is disclosed. In various embodiments, a plurality of rockets are attached to a perimeter of the parachute. Each of the rockets is configured to fly initially in a first direction substantially in a direction of deployment of the parachute and to fly subsequently along a trajectory that includes a component that is substantially perpendicular to the direction of deployment and extends radially from a center of the parachute. | ||||||
| 38 | Caliber shell with rigid mounting to housing of stabilizing fins | US15321018 | 2014-08-26 | US09958241B2 | 2018-05-01 | Renat Abdulberovich Yusupov |
| The invention relates to ammunition for firearms, as smooth and a rifled barrel. The projectile with rigid attached to the housing stabilizing fletching block, plates of fletching block have a continuation on the housing, centering the projectile in the barrel. In the offered variant, on the friction and heat of the bullet and the barrel takes about 1% of the shot energy, besides low vibration. The rest of energy escapes to destination, and that's good. Erasing minimal of the barrel. Application of the projectile in the shotgun and rifle barrels increases the service life of barrels. Use of such projectiles increases the initial speed, and with the sleeve-nozzle and a second charge, allows to increase the speed and specialization of the projectile. At the expense of the aerodynamic and gyroscopic effects, increases the lethal effect over long distances, due to the greater energy saved, improve the close grouping of shots and flat trajectory. | ||||||
| 39 | Aircraft, missile, projectile or underwater vehicle with reconfigurable control surfaces and method of reconfiguring | US13734368 | 2013-01-04 | US09683820B1 | 2017-06-20 | Mehul Patel; T. Terry Ng; Alan B. Cain; Zak Sowle; Jack DiCocco |
| The present invention relates to an aircraft, missile, projectile, or underwater vehicle with an improved control system and a method for increasing the maneuverability or stability of an aircraft, missile, projectile, or underwater vehicle. More particularly, the present invention relates to a method for increasing the maneuverability or stability of an aircraft, missile, underwater vehicle or projectile through the use of removable control surfaces. The technical advantage of the removable control surface system (or “removable control surface”) over other systems is that the removable control surface system enables the aircraft, missile, underwater vehicle or projectile to have two or more design configurations, each configuration being tailored to the aircraft, missile, projectile, or underwater vehicle's specific stability or maneuverability requirements during a specific portion of the flight. | ||||||
| 40 | Pilum bullet and cartridge | US14095745 | 2013-12-03 | US09644929B1 | 2017-05-09 | Michael Sean Bradbury; Darrel Ray Barnette |
| An improved sub-sonic cartridge for small arms containing a bullet whose Calibers (length/diameter) value is 6.0 or greater, which imparts to the bullet substantially greater kinetic energy than smaller and lighter sub-sonic bullets. The greater kinetic energy of the bullet aids in cycling the action of semi and fully automatic firearms as well as imparts greater kinetic energy to the target upon impact. The bullet incorporates an fin unit on the aft portion of the bullet; the aft fin unit is rotationally independent of the rotational state of the bullet in flight. The fin unit forces the Center of Pressure rearward of the Center of Gravity for added stability and accuracy in flight. Volume vacant of propellant within the cartridge shell may be occupied with a durable and heat resistant material to aid in consistent and reliable propellant burn when fired. | ||||||
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