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
201	Method and devices for propulsion	US705160	1996-08-29	US5965836A	1999-10-12	Mikhail A. Rakov
A method provides for shooting a missile-rocket. The missile-rocket has two movable parts and a propellant. The propellant is disposed between the one movable part and the first end of the other movable part. The missile-rocket undergoes three phases of acceleration. During the first phase, the method includes the steps of activating the propellant, moving one of the movable parts in response to the activation of the propellant, and urging the one of the movable parts to engage the other one of the movable parts. During the second phase, the method includes the step of urging the other one of the movable parts in response to the engagement. During the third phase, the method includes the step of releasing gases formed by activating the propellant from the missile-rocket to further urge the missile-rocket. The movable parts are preferably a shell and a core. In one embodiment, the core is moved in response to the activation of the propellant and urged to engage the front end of the shell. The shell is urged in response to the core engaging the front end of the shell. Further urging of the core and the shell is by releasing gases formed by activating the propellant from a chamber formed by the core and the shell. In another embodiment, the shell is moved in response to the activation of the propellant and urged to engage the core. The core is urged in response to this engagement. Further urging of the core and the shell is again by releasing gases formed by activating the propellant from a chamber formed by the core and the shell.
202	System for providing power and roll motion stability in a vehicle	US351821	1994-12-08	US5660356A	1997-08-26	Brian J. Selfors; Vijay M. Gondhalekar
A dual flywheel assembly for use in an airborne vehicle for storing mechanical energy therein prior to flight and for permitting the extraction of electrical energy therefrom during flight, which assembly includes two flywheels which are linked by a suitable linkage structure such that, if roll motion of the vehicle starts to occur during flight, the flywheels tilt in equal and opposite directions out of their normal planes of rotation, which tilting motions act in a passive manner to stabilize the roll motion of the vehicle.
203	Gas gun launched scramjet test projectile	US264207	1994-06-21	US5485787A	1996-01-23	Kevin G. Bowcutt; Harry Shortland
A gas gun-launched, propulsion-assisted scramjet projectile adapted to be fired from a gun, preferably at velocities greater than Mach 5, includes a body with an external compression section, an internal compression section, a combustion section, a nozzle section, and means for channeling ambient fluid to an engine in one of the sections of the body, the channeling means and the body cooperating with the engine to produce thrust greater than drag when the projectile travels at velocities greater than Mach 5. The projectile further includes a plurality of circumferentially spaced stabilization fins located at the nozzle region of the body and a sabot assembly releasably secured to the rear portion of the body, where the sabot assembly includes a plurality of elements joined together about the body rear portion to form a housing for protecting the body rear portion from explosive gases in the barrel of the gun.
204	Integral missile antenna-fuselage assembly	US364905	1994-12-27	US5483894A	1996-01-16	Andrew B. Facciano; Ronald N. Hopkins; Rodney H. Krebs; James L. Neumann; Oscar K. Ohanian
An integral missile antenna-fuselage assembly (50) is provided for integration into an armament missile (12) which carries primary missile loads, houses internal electronic assemblies, provides mounting surface zones for external sensor antennas (71) , and protects sensitive antenna components from supersonic aerodynamic heating. Each end of the fuselage assembly (50) is formed from a fastener ring (52,54) having a circumferential recess (84,86) which receives a filament wound main structure (60) to form the missile fuselage tube. Preferably, a titanium liner (58) is first joined to each fastener ring with a step-lap joint (94,96) along which it is adhesively bonded. The liner (58) and adjacent fastener ring portions (52,57) provide a mandrel on which a graphite/Bismaleimide (BMI) resin pre-preg is filament wound and co-cured to form the integral fuselage (60). A plurality of Graphite/BMI doublers (62,63,64,65) are axisymmetrically positioned on the fuselage external surface to form four antenna cavities (66,67,68,69) which receive antennas (71) therein. Subsequently, antenna spacers (72,73,74,75) encase the antennas (71) about which a radome overwrap (70) is filament wound with a Quartz/BMI pre-preg. The entire structure (70) is then integrally cured to the internal fuselage (60) and antenna spacers (72,73,74,75) afterwhich it is surface treated (76) and overcoated (78).
205	Stand-off weapons	US629105	1990-12-12	US5363767A	1994-11-15	Philip I. Robinson
A guided missile for air to ground deployment having a modular construction which can be readily configured to suit varying deployment roles. The missile comprises a common central fuselage 1, 2, 3 carrying a fuel tank and mounting points for an engine, wings and nose-cone 7. Bolted onto either side of the fuselage are panniers 6a, 6b of variable length and payload capacity. In one embodiment the panniers 6a, 6b carry munitions for lateral ejection through frangile panels. In an alternative embodiment, munitions are mounted in the fuselage and the panniers carry fuel.
206	Antitank weapon for combating a tank from the top	US18567	1987-02-04	US5275355A	1994-01-04	Werner Grosswendt; Gerhard Glotz; Helmut Peller
A projectile for a surface-to-surface weapon to combat a target from the top. The projectile includes a warhead; a propulsion system for accelerating the projectile directly after the projectile is placed in flight; a stabilizing guide assembly; a sensor for detecting a target in a longitudinal and lateral direction; and a pulse generator for turning the projectile about its center of gravity. The projectile additionally includes electronics for activating the warhead and for controlling the propulsion system and the pulse generator. A control unit rotates independently of the shaped charge warhead and houses the sensor, pulse generator and electronics. The pulse generator is arranged offset with respect to the sensor in the circumferential direction of the control unit. The electronics actuates the pulse generator in response to the sensor detecting a target, at a given distance ahead of such target, to produce a measured and radially directed control pulse to pivot the projectile so that it is aimed directly at the top of the target. The propulsion system additionally includes a drive assembly which is fired to accelerate the projectile toward a target, immediately after the projectile has been pivoted toward the target by the pulse generator. A mechanism is provided for preventing a restoring force generated by the ambient air from returning the projectile to the direction of flight existing prior to being pivoted.
207	Multiple stage rocket propelled missile system	US137226	1987-12-23	US4964339A	1990-10-23	Thomas W. Bastian; Charles W. Schertz
A rocket propelled missile assembly comprises an outer casing defining an internal solid rocket propellant chamber, the casing having an opening at its forward end aligned with an internal tube submerged in the rocket propellant chamber, and at least one exhaust nozzle at its rear end for venting exhaust gases from the propellant chamber. Solid propellant is contained within the propellant chamber surrounding the internal tube, and a separate terminal stage missile is partially or fully submerged in the tube with the capacity to separate from the tube forwardly through the front end of the casing. The missile separates from the remainder of the system on booster burn out.
208	Seal for the nozzle opening of a projectile	US362946	1989-06-08	US4930420A	1990-06-05	Wolfgang Meffert; Kalr-Heinz Silligmann; Siegmar Fischer; Ulf Hahn
A projectile includes a propellant charge and a nozzle opening provided in a rear projectile part and serving as an exit for propellant charge gases during flight of the projectile; a resilient rupturnable rubber or plastic sealing disc closing the nozzle opening for protection against environmental influences.
209	Missile equipment section structure	US82777	1987-07-31	US4798141A	1989-01-17	Daniel Cunha; Wayne M. Brown; James E. Pool; Thomas M. Sheperd
A plurality of pan-shaped beams and supports of graphite/epoxy laminate mrial are mounted on a circular graphite/epoxy aft panel to form a symmetrical structure which is attached to the missile shell. Four main stiffening beams intersect at right angles to form a central square structure with the intersecting walls extending outward beyond the central square to the missile shell. Four diagonal stiffening beams are disposed across the corners within the central square to form a central hexagonal structure. Additional stiffness is provided by strut support beams oriented parallel to the main support beams and support ribs oriented perpendicular to the main support beams.
210	Gun launched kinetic energy penetrator	US52507	1987-05-07	USH403H	1988-01-05	Alan Glasser
A kinetic energy penetrator assembly includes a motor casing having an aftpening. A nozzle with a nozzle opening is seated in the aft opening of the casing and confines expanding gases produced by burning propellant in the casing to a configuration for applying a thrust to the casing. An aft pusher plate is connected to a plug which plugs the nozzle opening and which has an aft space for receiving expanding gases. A penetrator rod is connected to the forward end of the motor casing and includes a bore riding sabot having substantially the same diameter as the diameter of the pusher plate and an aft portion of the motor casing. The penetrator assembly is meant to be launched from a gun with expanding gases in the gun barrel pushing against the pusher plate and ejecting the penetrator at some velocity from the barrel bore. An initiator carried in the pusher plate and nozzle plug begins to burn when it is exposed to the expanding gases in the gun barrel and, after a selected period of time, ignites propellant in the motor casing which first boosts the velocity of the penetrator assembly and thereafter sustains its velocity. The sabot is designed to peel away from the rod after the penetrator leaves the barrel for producing an aerodynamically advantageous configuration for the penetrator assembly.
211	Guided missile	US932227	1986-11-18	US4715283A	1987-12-29	William C. Yengst
A guided missile is directed to railroad tracks, is buried a particular distance, such as five (5) feet, below the tracks upon reaching the tracks and is covered by rocks in the railroad bed as it moves the particular distance below the tracks. The guided missile detonates when the train approaches on the tracks within a particular distance from the guided missile on the tracks. The train then becomes derailed. The guided missile has a housing which is made from a strong metal and which is relatively thick. Preferably the metal is steel and has a thickness of about 0.2". A nose cone having a blunt configuration is disposed on the housing at the front end of the housing and is made from a material which passes signals into and out of the housing. The material is compressible (e.g. fiberglass, a ceramic or a glass) to become flattened when the missile strikes the ground. A bulkhead preferably having a greater thickness than the housing is disposed in the housing at an intermediate position along the housing length. The bulkhead may be made from the same material as the housing. A seeker including an antenna is disposed in the housing between the nose cone and the bulkhead to transmit signals to the tracks and receive information from the tracks. A warhead is disposed within the housing on the opposite side of the bulkhead from the nose cone. A fuse is disposed within the housing at the rear of the housing to detonate the warhead when the train approaches the missile on the tracks.
212	Integral rocket motor-warhead	US695499	1985-01-28	USH203H	1987-02-03	William B. Thomas; Robert E. Betts
A rocket motor is disclosed which employs a Class 1.1 detonatable composition which is both a propellant and explosive. One grain design is configured to give a high boost acceleration during the burning phase of a perforated portion of the grain. The internally burning grain subsequently changes to an end-burning grain which provides a sustaining thrust burning period. The rocket motor flies to target with the burning surface progressing towards the head end. The rocket burns to target, but the design always provides some remaining propellant which serves as the warhead explosive on impact with the target. Detonator means cause the remaining unburned propellant to denonate at target impact or prior to target impact. This rocket motor design does not provide for separation between the warhead and the motor case. Therefore, the complete rocket motor travels to the target area. The rocket motor case may be serrated to give a controlled shrapnel effect upon detonation at target area which allows all the motor case to act as controlled warhead shrapnel. The rocket motor propellant grain is shaped in one design at the front end with a detonator located within the propellant to ensure that the explosive force acts in the desired direction to produce a desired shrapnel effect after detonation.
213	Reentry vehicle having active control and passive design modifications	US664634	1984-10-25	US4623106A	1986-11-18	Donald A. Price, Jr.; William E. Brandt; Jan Verheul
A modular improved forward section and improved aft section containing an tive-control package are disclosed which can be retrofitted to existing sphere-cone geometry reentry bodies (RBs) and which will provide improved aerodynamic performance and deployment accuracy of the RBs independent of missile error sources and drop sequence. An aft section containing control electronics, a propulsion system and steering jets permits the improve RB to actively correct for attitude and velocity dispersions occurring throughout the flight profile.
214	Plug nozzle kinetic energy penetrator rocket	US604772	1984-04-27	US4573412A	1986-03-04	Donald E. Lovelace; Michael C. Schexnayder; George W. Snyder
A kinetic energy penetrator having a penetrator rod which is placed inside rocket propelled motor casing to become the major load carrying member of the airframe structure.
215	Line throwing device	US404546	1982-08-02	US4505179A	1985-03-19	Steve Nelson; Frank Reynolds; George E. Roos; John Ball
A line throwing device adapted to be launched from a riot gun or similar tubular launching device comprises an elongated projectile that fits in the tubular launching device, a fin assembly slidably mounted on the body of the projectile such that the fin assembly slides forwardly to permit the rear end of the projectile to be positioned in the launching device for launching and slides rearwardly to a flight stabilizing position at the rear of the projectile as the projectile is launched from the tubular launching device. A rocket engine is mounted in the rear of the projectile for propelling the projectile. An ignition mechanism comprising a conventional shotgun primer cap mounted in a plastic casing fits on the end of the rocket and is ignited by the trigger and firing pin of the gun. A line is coiled in a canister removably attached to the gun, with one end of the line being attached to a harness mounted on the projectile so that the line can be carried to the desired target.
216	Combined rocket motor warhead	US434775	1982-10-18	US4459915A	1984-07-17	Robert A. Lynch
A solid fuel rocket in which the rocket casing acts as a warhead. Solid propellant rocket motors require relatively heavy cases to contain the 1000-2000 psi combustion pressure needed for efficient performance. This casing can be used as a fragmentation warhead by forming longitudinal grooves in the elongated rocket casing, causing the casing to fracture along the grooves and allowing the pressure within the casing to disperse the fragments. The resulting strip-like fragments are particularly useful against "soft" equipment targets, such as anti-vehicle and anti-radar applications. Several different methods for rupturing the case along spaced, parallel longitudinal lines are disclosed. This system eliminates the need for a separate warhead including case and explosive at the cost of a slight increase in propellant case thickness and weight.
217	Gun-launched variable thrust ramjet projectile	US217970	1980-12-19	US4428293A	1984-01-31	Leo Botwin; John A. Simpson
A gun-launched ramjet projectile follows a classical vacuum ballistic trajectory by maintaining a thrust-drag balance. The thrust of the ramjet is varied by an air door which bleeds air from the duct that leads from the supersonic diffuser at the front of the projectile to the combustion chamber. The control system for the air door includes an actuator and a pair of accelerometers, the output of which is integrated to provide an indication of velocity. The first accelerometer operates during the launching of the projectile in the gun to measure the launch velocity. A second, and more sensitive, accelerometer measures in-flight velocity changes due to atmospheric conditions. Both of the measured velocities are compared with prerecorded standards and error signals are derived representing any velocity deviations. These error signals are combined and then used to drive the air doors which varies the thrust of the ramjet so that it follows the classical vacuum ballistic trajectory.
218	Rocket assisted projectile and cartridge with time delay ignition and sealing arrangement	US168948	1980-07-11	US4397240A	1983-08-09	Mark M. Rottenberg; William O. Davis
A cartridge arrangement having a rocket assisted projectile for firing therefrom by ignition of propellant in the cartridge case and for subsequent ignition of a rocket grain within the projectile, in which the projectile has a sealed tubular chamber cavity encompassing a tubular or ring shaped end burning rocket grain, the rear end of which chamber is formed by a combined nozzle block and rear penetrator support which has nozzle openings sealed by ignitable time delay igniter plugs, and the outer, inner, and forward extremities of which are bounded by a thin-walled projectile case, a cylindrical penetrator, and a forward penetrator support, and which ignitable time delay igniter plugs are externally ignitable by the burning of the propellant to enable subsequent ignition of the adjacent end of the rocket grain.
219	Projectile for underwater firearm	US203313	1980-11-03	US4357888A	1982-11-09	John C. Phillips; Michael D. Nobel
An underwater firearm for discharging self-propelled projectiles incorporates a swing arm for simultaneously loading a projectile from a magazine into the firing chamber and cocking the firing pin. Guide means in the firing chamber automatically engages a fracturable flange on loading of the projectile to retain the projectile until discharge of the firearm.
220	Missile adaptation kit assembly	US423643	1964-12-28	US4051414A	1977-09-27	Albert S. Will; Robert R. Wilson; Samuel J. Black
A high density component assembly package for a missile including a pluray of circular bulkheads axially supported by rigid spacing members to form a cylindrical adaption kit. Electronic components are mounted on and/or between the bulkheads with the electrical interconnections therebetween accomplished by the use of flat printed cables wrapped around the periphery of the assembly.

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