专利检索_ 自推进弹或发射物例如火箭;导弹专利检索_ 自推进弹或发射物例如火箭;导弹专利检索查询

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序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
181	EXPLOSIVE CUTTING	US13825490	2011-09-22	US20130233194A1	2013-09-12	Erik Peter Carton
A method for explosive cutting using converging shockwaves, and an explosive cutting device are disclosed. The method includes providing a projectile with an explosive charge, positioning the projectile over the object so it extends along an intended line of cut, and detonating the explosive charge so that the projectile is accelerated toward the object, wherein the projectile either impacts on the object and the projectile includes a wave-shaping element which is shaped such that the impact generates converging shockwaves in the underlying object to be cut causing a crack to be propagated through the object along the intended line of cut; or impacts on a wave-shaping element in contact with the object, the wave-shaping element being shaped such that the impact generates converging shockwaves in the underlying object causing a crack to be propagated through the object along the intended line of cut.
182	Aircraft, missile, projectile, or underwater vehicle with reconfigurable control surfaces	US12977519	2010-12-23	US08367992B1	2013-02-05	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.
183	Device for reducing aerodynamic drag of a vehicale	US12745022	2008-11-21	US08226044B2	2012-07-24	Gerald Raymond; Philippe Bourdieu
A device for reducing the aerodynamic drag of a vehicle includes at least one masking element for at least one part of a nozzle of the vehicle's engine, the masking element having a resorbable material designed to be eliminated in the nozzle's flow once the engine is ignited. A space craft includes the nozzle attached to the fuselage of the space craft.
184	Plasma jet guard	US12586378	2009-09-22	US20110068690A1	2011-03-24	Bereli M. Lazar
The system includes a method and means of technological defense against violent atmospheric cyclones: tornadoes, hurricanes, others. The controlled meteorological missiles equipped with rocket servo-motors and magneto-gas-dynamic ionizers are used.The running out hot exhaust gases of rocket motors are converted into electro-conductive dashed plasma jets, which initiate and trigger multiple electro-shorting dischargers between contrary charged zones through ionized plasma jet segments of said dischargers.This disorders and de-energizes the cyclonic electrically saturated zones by multiple triple diverse and combined actions. The rotations slow down and end, and the cyclones get dispersed by own winds.The Guard can be used for preventing violent sky cyclones and severe lightning storms by preemptive operating into monitored over-saturated atmospheric electrostatic fields.
185	MINIATURE MISSILE	US12377604	2007-08-16	US20100320312A1	2010-12-23	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.
186	PYROPHORIC ARROWS	US12867052	2009-02-17	US20100307364A1	2010-12-09	Nahum Orlev; Amir Weitz
An arrow-type warhead (100,200,300,400,500,600,700) comprises an envelope (102,202), a filling (108), a hardened head section (104) to promote penetration of the target and a stabilizing mechanism (106,210,302,402,502,602) to stabilize the warhead in flight, hi some embodiments the filling (108) is pyrophoric and undergoes an exothermic reaction with the envelope upon impact. In other embodiments the filling is incendiary and undergoes reaction with the envelope upon impact in an oxygen rich-environment. In yet other embodiments, the filling is explosive. In all embodiments, the warhead may be equipped with a mini-rocket propulsion mechanism (802) for propelling the warhead to the target.
187	Explosive material sensitivity control	US11812362	2007-06-18	US07845279B2	2010-12-07	Benjamin Keren; Yael Cohen-Arazi; Samuel Friling; Erez Hanina
An armor module and an explosive material therefore, which explosive material is normally retained at a less sensitive position, and upon demand it is modified into a more sensitive position, where its initiation ability is upgraded and wherein the modification is carried out by heating the explosive material.
188	System and method for the measurement of the unambiguous roll angle of a projectile	US11335678	2006-01-20	US07589663B1	2009-09-15	Geoffrey H. Goldman; William O. Coburn; Thomas J. Pizzillo
A system for the measurement of an angle of roll of a projectile is disclosed. The projectile has a casing with a rear end, a front end, and a side wall extending therebetween. The system includes a radar configured to transmit a polarized electromagnetic signal toward the projectile and a groove disposed on the side wall of the casing. The groove has a width, a depth, and a length, the width extending along a longitudinal axis of the projectile, the depth extending inwardly from an outer surface of the casing toward the longitudinal axis, and the length extending along the outside of the casing. The radar is further configured to receive a return signal from the projectile, wherein the return signal from the groove is modulated as a function of the angle of roll of the projectile. Amplitude or phase modulation of the return signal from the groove can be used to uniquely determine the roll angle of the projectile.
189	Release mechanism in missile	US10009281	2000-06-02	US06928931B1	2005-08-16	Hans B. Biserød
A release mechanism between a projectile and a rocket motor in a missile. The projectile releases from the rocket motor during flight of the missile when the rocket motor burns out and aerodynamic retardation commences. The front end of the rocket motor comprises a forward closure, a lock retainer received and movable within the forward closure, at least one lock, at least one spring that biases the lock against the lock retainer in a direction opposite the to the direction of motion of the missile. The rear end of the projectile has a central boss surrounded by the forward closure of the rocket motor, wherein the boss comprises recesses or a circumferential groove in which the at least one lock lies and keeps the forward closure and the boss axially together.
190	Rocket accuracy improvement device	US10457695	2003-05-19	US06761330B1	2004-07-13	David A. Bittle; Donald E. Davis; Robert C. Glover; Roswell W. Nourse
Rocket Accuracy Improvement Device, when coupled between the warhead and motor of a typical free flight rocket, isolates the warhead from the rocket motor in the axis using a plurality of ball bearings and thereby enables the warhead to spin independently of the motor. The separation of the warhead from the motor allows the angular momentum of the warhead, which has reached its maximum spin rate by the time the motor burns out, to act gyroscopically to maintain the trajectory of the rocket even when the motor reverses its spin, thus achieving a much more predictable flight path for the rocket.
191	Survivable and reusable launch vehicle	US10309828	2002-12-04	US06749153B1	2004-06-15	Henry August
A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.
192	SURVIVABLE AND REUSABLE LAUNCH VEHICLE	US10453777	2003-06-03	US20040108411A1	2004-06-10	Henry August
A reusable, mach-velocity mobile platform delivers a weapons payload via vertical launch, powerless glide, weapons release, and landing operation phases. The platform includes a generally tubular shaped body having an aft and forward end, and a payload section. An arch wing is supported by the body aft end. The arch wing has an upper and a lower wing joined at distal ends by two curved end plates. A nose assembly is connected at the forward end having an upward directed fixed angle-of-attack to generate forward end lift. Thermal tiles attached under the body and the lower wing under-side radiate/dissipate heat generated during a high angle-of-attack platform reentry. Radar absorptive or radar translucent material is used. The platform preferably discharges payload from the aft end for safe separation. A landing gear is extended for the landing phase of operation.
193	Retarding and lock apparatus and method for retardation and interlocking of elements	US09980948	2002-03-29	US06659393B1	2003-12-09	Hans B. Biserød
A retarding and locking mechanism for use between two mutually translatable bodies. A first body can be induced into motion and guided into a second body and, after a predetermined movement of the first body, the first body is subject to retardation and interlocked to the second body, such that the first and second bodies together form a unitary, integrated body. The first body has a radially outwardly directed shoulder and the second body has a radially inwardly directed shoulder corresponding to the radially outwardly directed shoulder of the first body. A compressible element is provided between the shoulders of the first and second bodies.
194	ROCKET MOTORS WITH INSENSITIVE MUNITIONS SYSTEMS	US10016697	2001-11-01	US20030079464A1	2003-05-01	Mark A. Solberg; Robert E. Black
An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive munitions charge. In a preferred embodiment, the rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.
195	Method and apparatus for testing engines	US10164718	2002-06-10	US20030051536A1	2003-03-20	Jason S. Tyll; Robert J. Bakos; Florin Girlea; Ralph Woelfel; Dean Modroukas; John I. Endos
A scramjet has a cowl, a center structure, and a plurality of wide pylons connecting the cowl to the center structure, with scramjet engines positioned between adjacent pylons. Leading surfaces of adjacent pylons converge to one another to provide side wall compression to air entering the engines. The center structure includes a fore body, a center body and an aft body that, with the pylons, define a basic structure either formed entirely from one piece or several securely connected pieces. A method of testing the scramjet projectile comprises using a gun to accelerate the scramjet projectile to the takeover velocity of the engines.
196	Self-propelled rocket and collapsible rocket launch stand for use in providing the controlled occurence of an avalanche or a mud slide	US09892114	2001-06-26	US20020000174A1	2002-01-03	Reginald Paul Seller
A self-propelled and constant-acceleration rocket for use in triggering an avalanche includes a hollow cylindrical body member having an interior volume, an open top end, and an open bottom end whose exterior surface includes a plurality of flight guidance fins. A partition wall divides the interior volume into an upper volume and a lower volume. An explosive payload is mounted within the upper volume, and a nose cone having a circular and planar tip closes the open top end of the body member. A rocket motor is mounted within the lower volume. The rocket has a center of gravity and a center of pressure that are both located on the rocket's central axis and within the lower volume. The center of gravity is located closer to the open top end than is the center of pressure. A collapsible launch stand holds the rocket in a launch tube for launching of the rocket. Adjustment of a pair of launch tube support members provides for adjustment of the rocket's launch angle.
197	Device for controlling bird strike hazards	US09202327	1999-04-13	US06289815B1	2001-09-18	Raymond Tougeron; Daniel Casenave
A device for dispersing birds in airport areas, including a self-propelled projectile with a delayed firing element (15, 18, 27, 29) and a sound-effect charge (9) designed to scare birds away and housed in said projectile.
198	Universal warhead adapter, and missile and method incorporating same	US09337925	1999-06-22	US06227096B1	2001-05-08	Larry James Thomas
A universal warhead adapter comprises a tubular sleeve configured to contain any of various warheads of different configurations, and an aft bulkhead designed to replicate the aft end of a standard warhead with which existing tail assemblies are compatible. A universal missile is made by disposing a selected warhead within the sleeve and fixing the warhead therein with fastening mechanisms, and attaching a tail assembly to the aft bulkhead and a nose assembly to the forward end of the sleeve. Control surfaces, rocket motors, and/or turbine engines can be attached directly to the sleeve. An umbilical can be routed internally from a tail assembly through the sleeve and can be connected to an aircraft electrical system via an integral connector attached to the sleeve.
199	Vehicle refueling system	US231368	1999-01-13	US6142421A	2000-11-07	Miles R. Palmer
A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.
200	Rocket launching system employing thermal-acoustic detection for rocket ignition	US902893	1997-07-30	US6000340A	1999-12-14	James G. Small
A rocket launching system employing ignition apparatus that is used with a small rocket to launch the rocket from a gun. The rocket is equipped with acoustic (pressure) and optical (thermal) sensors that detect a pressure pulse and light flash of a primer charge used to fire the gun. The simultaneous detection of the pressure pulse and the light flash by the sensors generates output signals that are used to complete an electrical circuit in an electronic ignition circuit that activates an igniter that ignites a rocket motor.

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