| 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 | 无人水下航行器的远距离输送 | CN201580010769.4 | 2015-01-15 | CN106068438A | 2016-11-02 | 凯勒·斯托尔斯 |
| 一种射弹(100)包括引导飞行中的射弹的引导组件(102、103)。射弹进一步包括壳体和中空的鼻锥体(106)。壳体与引导组件配合并且鼻锥体与壳体耦合。鼻锥体包括被配置为容纳UUV(202)的内表面。射弹进一步包括控制器(108)，其识别用于部署飞行中的UUV的条件并且响应于确定条件满足使鼻锥体从壳体脱离。 | ||||||
| 2 | 光纤制导鱼雷中的放线机构及所构成的制导鱼雷 | CN201610201309.6 | 2016-04-01 | CN105758260A | 2016-07-13 | 方庆文 |
| 本发明公开了一种光纤制导鱼雷中的放线机构及所构成的制导鱼雷，放线机构包括两个相互平行的挡板，两个挡板并排设置且两个挡板之间形成线圈空间，线圈空间内安装有线圈，线圈两端面分别与两个挡板通过粘接剂对应粘接而成；所述线圈由若干层光缆环单元通过粘接剂以层叠方式依次粘接而成，所述光缆环单元由光缆绕成具有两个端部的未闭合圆环形，所述线圈的光缆放线端位于放线机构外部；制导鱼雷包括鱼雷弹体和放线机构，鱼雷弹体具有飞行控制器和鱼雷尾部。本发明可解决侧面出线问题，又能适用于弹体内部有限空间使用。 | ||||||
| 3 | Storage cover separation device of flying object | JP26163797 | 1997-09-26 | JPH1194500A | 1999-04-09 | MATSUI TOSHIHIKO |
| PROBLEM TO BE SOLVED: To positively achieve separation without any risk of touching a mounted object by providing at least one steering wing that normally performing a flight control operation and at the same time is separated and operated according to a command signal at each storage cover. SOLUTION: Steering wings 3a and 3b are provided at the left and right of the front part of each storage cover 1 being divided into two portions vertically, a command signal is sent to a thruster 2a for separation and the steering wings 3a and 3b from an auto-pilot device 8 when a specific target location is reached, the connection of the storage cover 1 is untied, and at the same time the steering wings 3a and 3b are operated by the same command signal, thus achieving a steering angle so that an air force is generated and performing travel and separation in a direction away from an underwater cruising body 5. Therefore, since the size of the air force and the scattering in an operation direction are small, the separation operation of the storage cover 1 is made positive and the estimation accuracy of the trace of the storage cover 1 after separation increases, thus preventing collision against a mounted object. | ||||||
| 4 | SCHWERGEWICHTSTORPEDO ZUM ABSETZEN IN EIN GEWÄSSER AUßERHALB EINER SICHTWEITE EINES ZIELS SOWIE TRANSPORTSCHLITTEN UND FLUGZEUG | EP16707616.5 | 2016-01-05 | EP3247972A1 | 2017-11-29 | LÄMMLE, Knud |
| The invention relates to a heavyweight torpedo for dropping into a body of water outside of a visibility range of a target, comprising a parachute, a parachute-releasing element, and a water-ingress detection element, wherein the parachute-releasing element and the water-ingress detection element are designed in such a way that the parachute-releasing elements are activated at a defined height of the heavyweight torpedo above a water level, upon water contact of the heavyweight torpedo, upon partial immersion of the heavyweight torpedo, or upon immersion of the heavyweight torpedo. | ||||||
| 5 | STAND-OFF DELIVERY OF UNMANNED UNDERWATER VEHICLES | EP15703353.1 | 2015-01-15 | EP3123102A1 | 2017-02-01 | STOWERS, Kyle |
| Embodiments described herein provide apparatus and method for stand-off deployment of UUVs utilizing self-directed projectiles that include guidance kits. One embodiment is a projectile that includes a guidance kit that directs the projectile in flight. The projectile further includes a shell and a hollow nose cone. The shell mates with the guidance kit and the nose cone couples with the shell. The nose cone includes an interior surface configured to house a UUV. The projectile further includes a controller that identifies a condition for deploying the UUV in flight, and detaches the nose cone from the shell in response to determining that the condition is satisfied. | ||||||
| 6 | Underwater vehicle guided by a Lidar imaging system | EP92118653.2 | 1992-10-31 | EP0534496B1 | 1996-06-26 | Keeler, Norris R.; Kaman, Charles H.; Ulich, Bobby Lee; Cardero, Silvio A.; Manthy, Robert S. |
| 7 | Method and apparatus for removing navigational hazards in water | EP92104957.3 | 1992-03-23 | EP0494092A2 | 1992-07-08 | Manthy, Robert S.; Daniels, Kirk; Wells, Anthony R.; Keeler, Norris R.; Renehan, Patrick L. |
An underwater maneuverable vehicle (10) is presented which carries an explosive charge and can be used for immediate removal or destruction of various menaces to navigation and other underwater hazards (58). The battery powered vehicle (10) is air dropped from a platform (12) which carries an imaging lidar system (36) for detection and is operated and navigationally controlled in conjunction with an imaging lidar system. |
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| 8 | Method of producing missile nose cones | US12491953 | 2009-06-25 | US08256086B2 | 2012-09-04 | Robert A. Shutler; Margaret Rose Manning; Paul A. Leitch; Paul E. Liggett |
| A method for producing a missile nose cone is disclosed. The method consists of manufacturing a first missile nose cone from a first lot of polymeric material and determining a first rupture value. The method further consists of manufacturing a second missile nose cone from a second lot of polymeric material and determining a second rupture value of the second missile nose cone. Both first and second lots of material are mixed into a test batch with one another based on their associated rupture values. An evaluation missile nose cone is then manufactured from the test batch and a determination is made as to whether the evaluation missile nose cone has a desired rupture value. If a desired rupture value is not obtained, then the mixing and evaluation steps are repeated. | ||||||
| 9 | Air-to-subsurface missile system | US402060 | 1964-09-29 | US5012717A | 1991-05-07 | Morton L. Metersky; James R. Howard |
| The invention is an air-to-subsurface missile system which has an acousticoming torpedo and a directional sonobuoy held in the missile behind the torpedo by a cowling means which includes fins for aerodynamic stability. When the missile reaches the desired location in a body of water, the torpedo and sonobuoy are released. The sonobuoy has the ability to search for targets and to communicate both with the homing torpedo and with a tactical command station. Thus the torpedo can be guided to a target by the sonobuoy and command station, even at ranges at which the torpedo could not locate a target with its own homing system. | ||||||
| 10 | Missile nosepiece | US153110 | 1988-02-08 | US4788914A | 1988-12-06 | James T. Frater |
| A nosepiece for the forward end of a missile that is launched into the atmosphere for a ballistic trajectory and a water entry impact comprises a frangible base and a separable nosecap, the base having multiple segments of rigid foam defining an axial bore into the base and a volume of soft cellular foam within the bore to protect the forward end of the missile. The nosecap is in seated relationship within the bore opening on the tip end of the base during airborne flight and separates therefrom to expose the axial bore opening prior to water entry impact such that upon impact the base is fractured by the force of water entering the exposed bore and thus separated from the missile. | ||||||
| 11 | Mercury button switch | US39814564 | 1964-09-02 | US3327084A | 1967-06-20 | COOK LEONARD W; COUTANT EDWARD R; GILMORE ARVILLE W |
| 12 | Parachute release mechanism | US85120359 | 1959-11-05 | US3066632A | 1962-12-04 | BEMIS WALDO E |
| 13 | Autopilot | US26697852 | 1952-01-17 | US3011738A | 1961-12-05 | SKRAMSTAD HAROLD K; HART JOHN A |
| 14 | Breakaway suspension band | US32416152 | 1952-12-04 | US2786392A | 1957-03-26 | JOSEPH NIEDLING HERMAN |
| 15 | Propulsion assembly for torpedoes | US71142046 | 1946-11-21 | US2568433A | 1951-09-18 | DALY THOMAS A; HOGUE PAUL M |
| 16 | Apparatus for decelerating torpedoes | US66802746 | 1946-05-08 | US2539643A | 1951-01-30 | SMYTHE WILLIAM R |
| 17 | Torpedo | US17013817 | 1917-05-22 | US1382166A | 1921-06-21 | CHARLES BLUM |
| 18 | Torpedo. | US19763217 | 1917-10-20 | US1290829A | 1919-01-07 | CARPENTER GEORGES J N |
| 19 | STAND-OFF DELIVERY OF UNMANNED UNDERWATER VEHICLES | US14228686 | 2014-03-28 | US20150375840A1 | 2015-12-31 | Kyle Stowers |
| Embodiments described herein provide apparatus and method for stand-off deployment of UUVs utilizing self-directed projectiles that include guidance kits. One embodiment is a projectile that includes a guidance kit that directs the projectile in flight. The projectile further includes a shell and a hollow nose cone. The shell mates with the guidance kit and the nose cone couples with the shell. The nose cone includes an interior surface configured to house a UUV. The projectile further includes a controller that identifies a condition for deploying the UUV in flight, and detaches the nose cone from the shell in response to determining that the condition is satisfied. | ||||||
| 20 | METHOD OF PRODUCING MISSILE NOSE CONES | US12491953 | 2009-06-25 | US20100326182A1 | 2010-12-30 | Robert A. Shulter; Margaret Rose Manning; Paul A. Leitch; Paul E. Liggett |
| A method for producing a missile nose cone is disclosed. The method consists of manufacturing a first missile nose cone from a first lot of polymeric material and determining a first rupture value. The method further consists of manufacturing a second missile nose cone from a second lot of polymeric material and determining a second rupture value of the second missile nose cone. Both first and second lots of material are mixed into a test batch with one another based on their associated rupture values. An evaluation missile nose cone is then manufactured from the test batch and a determination is made as to whether the evaluation missile nose cone has a desired rupture value. If a desired rupture value is not obtained, then the mixing and evaluation steps are repeated. | ||||||
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