专利检索_ .弹道在水面下结束的导弹专利检索_ .弹道在水面下结束的导弹专利检索查询

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	System and method for airborne deployment of object designed for waterborne task	US13965311	2013-08-13	US09056679B1	2015-06-16	Tye A. Langston; Rodolfo T. Arrieta; Ted R. Clem
An airborne deployment system and method for deploying an object designed. for a waterborne task. An unmanned aerial vehicle (UAV) has an object such as an unmanned underwater vehicle (UUV) releasably coupled thereto. The UAV is guided to a target site on a body of water in accordance with navigation. rules predicated on navigation capability of the UAV. The UUV Is released from the UAV at a location that is one of in the air and on the water in accordance with release rules predicated on the navigation capability of UAV.
22	Systems, devices, and/or methods for managing targeted payload descent	US13836320	2013-03-15	US08939056B1	2015-01-27	David Anthony Neal, III; Kevin Marlan Ehlmann; William Thomas Gressick; Alec Jacob Devine Bateman; Kenneth Richard Horneman
Certain exemplary embodiments can provide a system, machine, device, manufacture, circuit, composition of matter, and/or user interface adapted for and/or resulting from, and/or a method and/or machine-readable medium comprising machine-implementable instructions for, activities that can comprise and/or relate to, providing a guided descent from a release zone and toward an entry zone.
23	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.
24	Surface ship, deck-launched anti-torpedo projectile	US12057123	2008-03-27	US08151710B2	2012-04-10	Jyun-Horng Fu; Lance Hamilton Benedict; Antonio Paulic; Robert M. Krass
A surface ship, deck-launched anti-torpedo projectile is disclosed. The projectile has a blunt-end nose to create a cavitating running mode. The nose has a gradual, stepped, right-circular cylindrical or conic geometry. In some embodiments, the projectile includes a plurality of tail fins that are dimensioned and arranged to be within the generalized elliptical cavity that shrouds the projectile in the cavitating running mode.
25	Cavitating core	US12298536	2007-02-12	US08082851B2	2011-12-27	Andrey Albertovich Polovnev; Vladimir Shaymukhametovich Khasiakhmetov
The invention relates to ammunition for missile weapon and firearm. The cavitating core of the invention comprises a head part conjugated with a secant nose surface along the cavitating edge, a central part, and an aft part with a gliding surface, wherein the caliber of the core is defined by the maximum diameter of the circle describing the core cross-section. The contour line enveloping the cross-sections from the cavitating edge to the core caliber in the plane of the core axial longitudinal section is limited by the dependence: Dx=d×[1+(1x/d)×(2×sin φ/π)1/N]N, where Dx—is the current diameter of the core enveloping contour R, mm; d—is the cavitating edge diameter, mm; Lx—is the current distance from the cavitating edge to the core caliber, mm; φ=60° . . . 270°— is the apex angle of the tangents to the secant nose surface at the points of its conjugation with the cavitating edge measured from the side of the head part; N=(2π/φ)0.4 . . . (2π/φ)0.2— is the core volume factor, wherein the core caliber is equal to the current diameter of the core enveloping contour Dx. As a result the invention makes it possible to increase the effective distance for hitting underwater targets when shooting from the air to the water and/or during underwater shooting using arbalests, harpoon guns, artillery, small and sporting-and-hunting weapons.
26	Surface Ship, Deck-Launched Anti-Torpedo Projectile	US12057123	2008-03-27	US20110297031A1	2011-12-08	Jyun-Horng Fu; Lance Hamilton Benedict; Antonio Paulic; Robert M. Krass
A surface ship, deck-launched anti-torpedo projectile is disclosed. The projectile has a blunt-end nose to create a cavitating running mode. The nose has a gradual, stepped, right-circular cylindrical or conic geometry. In some embodiments, the projectile includes a plurality of tail fins that are dimensioned and arranged to be within the generalized elliptical cavity that shrouds the projectile in the cavitating running mode.
27	Supercavitating Projectile and Operation Thereof	US12327550	2008-12-03	US20090173248A1	2009-07-09	Jyun-Horng Fu
A method for operating a supercavitating projectile is disclosed.
28	Vapor explosion weapon	US11398735	2006-04-03	US07282634B2	2007-10-16	Robert Kuklinski
The apparatus of the present invention utilizes the heat energy of a weapon propulsion system to produce a vapor explosion. It includes an outer shell with a nozzle port and a body being made from a metal. The body surrounds a propulsion device and captures its waste heat to heat metal within the body. An explosive device is embedded in the body and can explode on transmission of a signal whereby the heated metal within the body produces a vapor explosion that significantly enhances the effectiveness and lethality of the weapon. The apparatus also discloses a second metal in the body and a heat shield for further enhancing effectiveness.
29	Expendable sonobuoy flight kit with aerodynamically assisted sonobuoy separation	US10848131	2004-05-19	US20050258310A1	2005-11-24	Derek Bilyk; Patrick Zdunich; Marc MacMaster
The invention is a flight kit that can be retrofitted to existing navy sonobuoys. The invention gives sonobuoys the capability of self-deployment, allowing them to be sent to a location remotely without the use of manned aircraft or recoverable unmanned air vehicles. This capability is advantageous in instances where it is desired to place a sonobuoy in an area hostile or hazardous to manned aircraft. The invention is an attachment of a GPS navigation and control system, wings, control surfaces, and a propulsion system, onto a naval size-A sonobuoy, using the sonobuoy as the central structural load-bearing component of the assembly. The invention navigates from a launch point on a ship to a designated position, where the sonobuoy separates from the invention, using the wings' aerodynamic forces to mechanically assist in separating the sonobuoy from the flight kit. The sonobuoy and the flight kit enter the water separately to ensure no interference with the sonobuoy.
30	Sonotube compatible unmanned aerial vehicle and system	US882368	1997-06-25	US6056237A	2000-05-02	Richard L. K. Woodland
The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus. The launch canister comprises retractable launch stabilizing legs, turbine engine exhaust orifices, and various antennas. The launch canister apparatus alternatively comprises a modified type "A", "B", or "C" sonotube launch canister. The system of the invention also comprises a portable Command, Control, Communications, Computer, and Intelligence (C4I) control and sensing analysis console. The console is preferably ruggedized, waterproof, shockproof, and comprises necessary control and analysis computers, input/output devices, antennas, and related hardware and software for vehicle and mission control. A C4I console and/or launch canisters may be transported by means of a backpack adapted for man portability.
31	Method and arrangement for combating a submerged target object	US907152	1992-07-01	US5214618A	1993-05-25	Georg Bugiel
A method for combating a submerged target object through the intermediary of an active body which is deployable in an airborne mode, and which picks up a sonar contact with the target object from a helically descending searching trajectory below the water level. Also disclosed is an arrangement for combating a submerged target object, especially a double-hulled submarine, through the intermediary of an active body deployable in an airborne mode which is equipped with a sonar installation and with guidance media for the traversing of a helical gliding search trajectory. Upon contacting a target through the intermediary of a searching sonar which is more simply constructed in comparison with a homing sonar, the active body launches an effector which is equipped with an extremely rapid drive into linear attacking trajectory tangentially to the searching trajectory, and wherein the effector will detonate a warhead upon impact against a target.
32	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.
33	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.
34	Rocket-thrown weapon	US3613617D	1960-03-17	US3613617A	1971-10-19	HAMILTON MILES H
1. A missile for use against a target submarine, comprising, in combination: A FORWARD SECTION INCLUDING A PAYLOAD APPARATUS FOR DELIVERY TO A SUSPECT WATER AREA; A ROCKET MOTOR STATIONED REARWARDLY OF SAID FORWARD SECTION AND IN AXIAL ALIGNMENT THEREWITH, TO PROVIDE A THRUST PHASE OF MISSILE FLIGHT; SAID ROCKET MOTOR COMPRISING A NOZZLE STRUCTURE AT ITS AFT EXTREMITY TO DIRECT ROCKET MOTOR PRESSURIZED PROPELLANT GASES REARWARDLY, AND FURTHER HAVING A PORT AT ITS FORWARD EXTREMITY; A BULKHEAD STRUCTURE STATIONED IMMEDIATELY FORWARD OF SAID ROCKET MOTOR AND IN OBTURATING RELATIONSHIP TO SAID PORT; RELEASABLE FASTENING MEANS SECURING SAID ROCKET MOTOR TO SAID FORWARD SECTION AND MAINTAINING SAID PORT-OBTURATING RELATIONSHIP; SAID PORT HAVING AN ORIFICE AREA GREATER THAN THE EFFECTIVE ORIFICE AREA OF SAID NOZZLE STRUCTURE; SAID ROCKET MOTOR THEREBY BEING CONTINUOUSLY SUBJECTED, DURING GENERATION OF PRESSURIZED PROPELLANT GASES, TO A NET FORCE TENDING TO SEPARATE IT FROM SAID AIRFRAME AND BULKHEAD STRUCTURE; SAID ROCKET MOTOR HAVING A CHARACTERISTIC MAXIMUM PERIOD OF THRUST GENERATION; AND MEANS FOR RELEASING SAID FASTENING MEANS, WHEREBY TO SEPARATE AND JETTISON SAID ROCKET MOTOR AND CORRESPONDINGLY TERMINATE SAID THRUST PHASE OF MISSILE FLIGHT, PREDETERMINATELY DURING MISSILE FLIGHT AND PRIOR TO EXPIRATION OF SAID CHARACTERISTIC MAXIMUM PERIOD.
35	Autopilot	US26697852	1952-01-17	US3011738A	1961-12-05	SKRAMSTAD HAROLD K; HART JOHN A

36	Aerial bomb	US36169040	1940-10-18	US2489610A	1949-11-29	BARKER MAURICE E

37	Projectile.	US17733217	1917-06-27	US1302167A	1919-04-29	HUBBARD ALEXANDER

38	Explosive.	US1907372686	1907-05-09	US908149A	1908-12-29	SCHROETTER OTTO VON

39	Projectile	US603466D		US603466A	1898-05-03

40	Pilot-shell and centering-ring for submarine projectiles	US425616D		US425616A	1890-04-15

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