子分类：
- F42B15/01： .制导或控制装置(航空飞行控制入B64C;并非仅安装在运载工具上的制导系统入F41G7/00,F41G9/00;由无线电或其他波定位的入G01S;一般飞行控制入G05D1/00;计算装置入G06)
- F42B15/08： .运载测量仪器用的;{在弹丸内装配敏感载运的装置}(适用于气象学的入 G01W1/08);{弹丸内用于声敏载运的装置}
- F42B15/10： .仅在大气中有弹道的导弹
- F42B15/20： .弹道在水面下开始的导弹(用于在水中运动具有辅助推进装置的入F42B17/00)
- F42B15/22： .弹道在水面下结束的导弹(用于在水中运动具有辅助推进装置的入F42B17/00)
- F42B15/34： .过热或辐射的防护,例如热屏蔽;附加的冷却装置{(航天飞船的热防护入B64G1/58)}
- F42B15/36： .连接火箭发动机和弹体部分的装置;多级连接器;分离装置
| 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 | 안전한 로켓 점화 시스템을 갖는 미사일 | KR1019997006934 | 1998-11-19 | KR100360627B1 | 2002-11-13 | 엣킨슨,바비지. |
| 본발명은로켓모터(24)를구비한미사일(30)용으로설계된로켓점화시스템(32)에관한것이다. 이시스템(32)은광 펄스를검출하고그에응답하여제1 신호(42)를제공하기위한제1 회로(34)를포함한다. 압력파를검출하고그에응답하여제2 신호를제공하기위해제2 회로가제공된다. 다음에, 제3 회로(22, 40)는제1 신호(42)와제2 신호(44)에응답하여미사일(30)을발사한다. 예시적인실시예에서, 시스템(30)은제1 신호형태의제1 성분과제2 신호형태의제2 성분을갖는발사신호를생성하기위한뇌관을포함한다. 제1 검출기(34)는제1 형태의신호를검출하고제2 검출기(36)는제2 형태의신호를검출한다. 프로세서(38, 40)는제2 검출기(36)에의한제2 성분의수신과제1 검출기(34)에의한제1 성분의수신사이에경과된시간에서소정의유효시간차범위사이의차를계산하여이 차이가소정의휴효시간차범위내에있을경우점화신호를제공한다. 불꽃로켓모터점화기(22)는프로세서(38, 40)로부터의점화신호의수신시에로켓모터(24)를동작시킨다. 특정한실시예에서, 제1 검출기(34)는미사일(30)의로켓모터(24) 근방에배치된광 검출기이며제1 성분은광 신호이다. 제2 검출기(36)는기존의피토우압력검출기이며제2 성분은압력신호이다. 예시적인실시예에서, 프로세서(38, 40)는경과된시간을소정의유효시간차범위와비교하도록프로그래밍된기존의미사일유도제어프로세서(38)이다. 프로세서(38, 40) 상의타이머(46)는경과된시간을측정한다. 소정의유효시간차는제1 검출기(34)와제2 검출기(36) 간의위치차와, 상기제1 성분과상기제2 성분의속도차를기초로하여계산된다. 안전스위치(48)는미사일(30)이사용준비가되지않았을때 점화신호를차단한다. | ||||||
| 162 | 로켓 점화를 위해 열-음향 검출을 이용하는 로켓 발사 시스템 | KR1019997002672 | 1998-07-23 | KR1020000068654A | 2000-11-25 | 스몰,제임스,지. |
| 포(30)으로부터로켓을발사시키기위해소형로켓(10)과더불어사용되는점화장치(12, 13, 14, 18)을이용하는로켓발사시스템(40)이제공된다. 이로켓에는포를발사하는데사용되는뇌관차지(35)의압력펄스및 섬광을검출하는음향 (압력) 센서및 광학 (열) 센서가장착된다. 이센서들에의한압력펄스및 섬광의동시검출은로켓모터(16)을점화하는점화기(18)을구동하는전자점화회로(12) 내의전자회로를완성하는데사용되는출력신호를발생시킨다. | ||||||
| 163 | 경량 대전차 무기 | KR1019900700434 | 1989-06-28 | KR100152968B1 | 1998-10-15 | 돈쉬릭커 |
| 내용 없음 | ||||||
| 164 | MINIATURE MISSILE | PCT/IL2007001028 | 2007-08-16 | WO2008020448A3 | 2009-04-30 | BRIL YARIV; HETZ YAKOV; YEHEZKELI ODED; CHISHINSKY EHUD |
| A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation. | ||||||
| 165 | HANGER ASSEMBLY FOR AIRCRAFT | PCT/US2004006795 | 2004-03-05 | WO2004108529A8 | 2005-04-14 | MOATES JAMES BENJAMIN |
| A hanger assembly for suspending an external store from an aircraft includes left and right side panels in hinged connection to a center panel, where the panels, in combination, form a band for substantially circumferentially surrounding the external store. The center panel includes an interface for engagement with an attachment pod on an aircraft, and the side panels are fastened in tension to each other diametrically opposite the interface. The length, thickness and material strength of the band are selected to minimize the bending moment, which is induced in the hanger assembly based on loading experienced during operational use, at a region of the band at which an interface is established with the aircraft. | ||||||
| 166 | MISSILE WITH SAFE ROCKET IGNITION SYSTEM | PCT/US9824720 | 1998-11-19 | WO9932780B1 | 1999-11-11 | ATKINSON BOBBY G |
| A rocket ignition system (32) adapted for use with a missile (30) having a rocket motor (24). The system (32) includes detectors (34, 36) and circuitry (22, 34, 36, 38, 40) for detecting an optical impulse and a pressure wave, both of them being components of a launch signal. In the illustrative embodiment, the system (30) includes a primer for generating the launch signal having. A processor (38, 40) computes the difference between the time elapsed between the receipt of both of the signal components and provides an ignition signal to the pyrotechnic rocket motor igniter (22) if the difference is within a predetermined valid time range. The predetermined valid time difference is computed based on the difference in position between both if the detectors, and the difference in velocities of said signal components. A safety switch (48) blocks the ignition signal when the missile (30) is not ready for use. | ||||||
| 167 | CASE ASSEMBLY INCLUDING ADHESIVE BOND THAT IS INSENSITIVE TO HIGH OPERATING PRESSURES AND EXHIBITS INHERENT HIGH TEMPERATURE RELIEF CAPABILITY, AND MOTOR ASSEMBLY AND ROCKET ASSEMBLY INCLUDING THE SAME | PCT/US9803703 | 1998-02-27 | WO9846960A3 | 1999-02-18 | WRIGHT ROGER D; KLIGER JOSEPH J; CROOK RUSSELL A |
| An embodiment is described for the field of rocket assemblies. A case assembly including a case sleeve structure (102) and an end closure structure (104) having a mating portion (120) bonded to an inner receptacle surface region (108) of the case sleeve structure (102) with an adhesive material. The mating portion (120) is constructed and arranged to transfer longitudinal and radial operating loads from the adhesive material to the end closure structure (104), thereby making the adhesive bond insensitive to high internal operating pressures without the need for supplemental mechanical fasteners. The case assembly may be provided with Insensitive Munitions (IM) capability by selecting as the adhesive material a material having a glass transition temperature below the auto-ignition temperature of the propellant, and excluding from the case assembly any mechanical fasteners that prevent the sleeve-to-closure joint from structurally failing at a temperature below the auto-ignition temperature. | ||||||
| 168 | Solid-fuel ramjet ammunition | US15250538 | 2016-08-29 | US09823053B1 | 2017-11-21 | Lawrence E. Fink |
| A ramjet projectile comprising: an outer assembly that is tubular and comprises first, second and third portions; solid ramjet fuel attached to and disposed inside the first portion of the outer assembly; an inner assembly disposed inside the outer assembly and comprising a first portion threadably coupled to the second portion of the outer assembly and a second portion surrounded by the third portion of the outer assembly to form an annular air passageway having an air inlet. The first portion of the inner assembly comprising a plurality of openings spatially distributed about a circumference. The inner assembly is rotatable relative to the outer assembly between first and second locations displaced by a distance from each other during travel along the gun barrel. The openings are not in flow communication with the annular air passageway when the inner assembly is at the first location and are in flow communication with the annular air passageway when the inner assembly is at the second location. Preferably the solid ramjet fuel comprises boron and a binder. | ||||||
| 169 | METHOD AND SYSTEM FOR PROTECTING FOLDING WINGS ON A MISSILE WHILE IN THEIR STOWED STATE | US15525225 | 2014-11-07 | US20170328692A1 | 2017-11-16 | Arnstein SOLBERG; Jens A. GJESTVANG; Trond Henning SLEVELAND; Kristian JENSRUD; Ivar Thomle HOELSÆTER |
| A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces. | ||||||
| 170 | 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. | ||||||
| 171 | Caseless Projectile and Launching System | US15355984 | 2016-11-18 | US20170067704A1 | 2017-03-09 | Jeffrey M. WIDDER; Christopher A. PERHALA; James R. RASCOE |
| A launcher system includes a launcher having a sealed breech and a barrel adapted to receive a projectile with a charge of propellant and a mechanism to vary the launch velocity by selectively controlling the propellant gases vented out of the projectile and into the barrel. A collar can be repositioned through rotation or sliding movement to selectively allow propellant gases to vent out of the barrel or stop propellant gases from venting out of the barrel. When the collar is in a closed or non-venting configuration, propellant gasses build-up pressure behind the projectile, resulting in a relatively high launch velocity and, when the collar is in the open or venting configuration, a relatively low launch velocity is produced. A sliding breech face and energy-absorbing plug can also be provided to further decrease launch velocity. | ||||||
| 172 | LAUNCH SYSTEM FOR A GUIDED MISSILE AND A GUIDED MISSILE FOR SUCH A LAUNCH SYSTEM | US15152261 | 2016-05-11 | US20160377375A1 | 2016-12-29 | Stefan LEHMANN; Jörg LUTZENBERGER |
| The present embodiment relates to a guided missile launch system comprising a launch tube with a guided missile space for receiving a guided missile and with a cartridge space for receiving a blank cartridge, further comprising a handle piece mountable on the launch tube and separable from the launch tube, the handle piece having a striking pin system for firing the blank cartridge. | ||||||
| 173 | TURBINE ASSEMBLY HAVING A ROTOR SYSTEM LOCK | US15016813 | 2016-02-05 | US20160230587A1 | 2016-08-11 | Oran A. Watts, III; Larry A. Junod |
| A rotor system lock for a gas turbine engine is described which blocks movement of rotating wheel assemblies relative to static vane assemblies in a gas turbine engine in order to block unintended rotation (or windmilling) of the gas turbine engine when it is exposed to high winds while at rest or to ram air during pre-launch flight and thereby avoid damage to components of the engine. | ||||||
| 174 | Munition with Unexploded Ordnance Limiting | US14878355 | 2015-10-08 | US20160102954A1 | 2016-04-14 | John Hultman |
| A munition includes a projectile and a propellant unit. A propellant insert in the propellant unit has at least two propellant chambers each receiving a respective propellant charge. A primer mechanism is actuatable to ignite all of the propellant charges in the propellant insert. The combustion products of a selected one of the propellant charges are directed to the projectile and the combustion products of the non-selected propellant charges are vented. | ||||||
| 175 | Multifunction aerodynamic housing for ballistic launch of a payload | US14190607 | 2014-02-26 | US09273943B1 | 2016-03-01 | Peter D. Poulsen |
| A projectile comprises a payload and an aerodynamic outer housing. The outer housing is arranged, in launch and flight configurations, to surround the payload. The outer housing is further arranged, in the launch configuration, to be launched from a barrel of a launching gun or cannon. The outer housing is further arranged, in the flight configuration, to have a bi-tapered shape that is elongated along a fore-and-aft direction and has a longitudinal profile that tapers in both fore and aft directions. The outer housing is arranged to assume an exoatmospheric configuration upon reaching a target distance-from-launch, a target time-from-launch, a target altitude, or a target velocity. In the exoatmospheric configuration, either (i) the outer housing is arranged to release the payload or (ii) the outer housing and payload are arranged in a propulsion configuration. The projectile can include various additional components or adaptations to enable or achieve specific launch objectives. | ||||||
| 176 | GAS GUN LAUNCHER | US14642720 | 2015-03-09 | US20150175278A1 | 2015-06-25 | John William HUNTER; Harry E. CARTLAND; Philip James SLUDER; Richard Edward TWOGOOD |
| A gas gun launcher has a pump tube and a launch tube with a first end of the launch tube slidably inserted into a second end of the pump tube. The pump tube may hold a heat exchanger to heat a light gas used to launch a vehicle. A sliding seal can be employed to manage recoil and to retain the gas within the launch tube and the pump tube. A fast-closing muffler at the second end of the launch tube can conserve the light gas utilized for launching a vehicle, enabling the light gas to be recycled. A launch tube alignment system is preferably automatic, ensuring the survival of the launch vehicle. | ||||||
| 177 | Fragmentation bodies, warheads including fragmentation bodies, and related ordnance | US13550705 | 2012-07-17 | US08973503B2 | 2015-03-10 | James D. Dunaway; John E. Bott |
| A fragmentation body comprising a substantially monolithic structure comprising a metal material and comprising a major surface having an indentation pattern therein, and an opposing major surface having an opposing indentation pattern therein, the opposing indentation pattern being substantially aligned with the indentation pattern. A warhead and an article of ordnance are also described. | ||||||
| 178 | Projectile-Deployed Countermeasure System | US13682256 | 2012-11-20 | US20140216290A1 | 2014-08-07 | Dennis Yee; Timothy L. Williams |
| Systems and methods described herein provide for the protection of personnel within vehicles and structures from rocket-propelled grenades and other incoming threats. According to one aspect of the disclosure provided herein, a countermeasure system includes an interceptor vehicle configured to stow and launch an expandable countermeasure. The countermeasure may have a flexible body with attached deployment mechanisms that expand the flexible body into the path of an incoming threat to capture the threat. | ||||||
| 179 | Miniature missile | US12377604 | 2007-08-16 | US08664575B2 | 2014-03-04 | Yariv Bril; Yakov Hetz; Oded Yehezkeli; Ehud Chishinsky |
| A miniature lightweight high-maneuverability missile (10) has a missile body (12) with three sets of at least two aerodynamic control surfaces (14, 16, 18) for independent control of roll, pitch and yaw of the missile. Each set of control surfaces (14, 16, 18) is independently controlled by a corresponding actuator (20) deployed within the missile body (12). Other preferred features include selection of an elevation angle of incidence at a target, and switching between explosive and kinetic modes of operation. | ||||||
| 180 | Multi-purpose mounting devices for mounting electrical packages to airborne objects | US12643390 | 2009-12-21 | US08559191B2 | 2013-10-15 | James L. Porter; Matthew Glenn Murphy; Jesse H. Blake |
| Embodiments of a multi-purpose mounting device for mounting an electrical device to a structure coupled to an airborne object are provided. In one embodiment, the multi-purpose mounting device includes an adapter member and a slide member coupled to the adapter member. The slide member is radially spaced apart from the adapter member to form an open slot, which is configured to receive a portion of the external structural therein to secure the multi-purpose mounting device to the airborne object. A first mounting surface is provided on one of the adapter member and the slide member and configured to support the electrical device. | ||||||
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