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
221	Dual side-mounted inlet-vehicle orientation	US492073	1974-07-26	US3976088A	1976-08-24	Arthur J. Karanian; Robert L. O'Brien
A dual, side-mounted inlet for air-launched ramjet missiles that require h angle-of-attack capability. The inlets are located symetrically on both sides of the vehicle pitch plane at an optimum angular displacement around the vehicle's lower surface from windward side meridian, lying in the pitch plane. The inlet pressure recovery and relative weight flow reach maximum values at angular displacements between 45.degree. and 60.degree. at positive angles of attack. The inlet is attached to the vehicle with a conventional boundary layer diverter of minimum height.
222	Penetrating spear	US325716	1973-01-22	US3935817A	1976-02-03	Carlo Riparbelli
Disclosed is a spear having an elongated rod to penetrate hard targets. The spear is delivered either from the air or the ground and is accelerated by a rocket motor to achieve the required impact velocity, for penetration.
223	Penetrating spear with suspended warhead	US37212673	1973-06-21	US3897730A	1975-08-05	RIPARBELLI CARLO
Disclosed is a spear having an elongated rod or stem to penetrate hard targets. A warhead is suspended directly behind the stem.
224	Rocket catapult aircraft escape arrangement	US44191574	1974-02-12	US3885452A	1975-05-27	WEINSTOCK MANUEL; PISANO FRANK T
A rocket catapult emergency aircraft escape arrangement which is simple in construction and has a maximum of functional reliability. A booster tube of the rocket catapult assembly is secured to a pedestal attached to the aircraft frame and has in one end thereof a cartridge ignited by an electric ignition element in the pedestal. A launch tube of the rocket motor assembly is slidably mounted on the booster tube, secured to a rearwardly exhausting nozzle unit, and carries at its forward end a delay rocket motor igniter unit that ignites the cylinder of rocket propellant grain carried by the rocket tube forwardly of its securement to the nozzle unit. A pair of apertured ears on a rearward portion of the nozzle unit afford connection to a pendant line of a seat occupant''s shoulder harness. Upon an emergency escape operation, the actuated rocket catapult lifts the occupant escapee from the disabled craft as soon as his shoulder harness pendant line becomes taut.
225	Zero volume rocket ignition system	US39324073	1973-08-30	US3861310A	1975-01-21	MERTENS ROBERT C; HARPER DONALD W
A rocket ignition system for artillery fired projectiles has a fixed nozzle design which permits maximum propellant loading by interposing a high density, low residue, heat buring paper intermediate a nozzle end plate and a solid propellant. An initiating squib prior to launch temporarily closes off the nozzle orifice from the hot breech gases. After launch the squib initiates a mild detonating fuze which burns the heat paper and ignites the propellant causing generation of gases whose pressure causes expulsion of the nozzle-squib plug from the nozzle orifice. In a movable nozzle embodiment an initiating train is fixedly held, prior to launch, in a slidable nozzle member adjacent to an igniter pellet charge which activates the propellant. Interposed between the movable nozzle and the propellant grain is an integrally cast liner which excludes all air from the propellant grain surface thus preventing premature ignition of the propellant by gun breech compressed gases.
226	Penetrator projectile	US3754507D	1972-05-30	US3754507A	1973-08-28	DILLINGER R; PAYNE H
A projectile in which a combination of interior elements, including a penetrator, a pyrotechnic delay column and an ignition charge are utilized to ignite a viscous uncured propellant after the projectile has been fired. The thus ignited propellant increases the velocity and effectiveness of the projectile.
227	Rocket propelled target	US3735985D	1970-10-15	US3735985A	1973-05-29	LAYER G E; KREUZER J A; YATES J S
A rocket vehicle suitable for use as an airborne training target is disclosed. The vehicle frame is manufactured of aluminum or other lightweight material having high structural strength and includes a longitudinally extending elongated center member to which are attached a nose cone, fin sections and one or more rocket motors. Attached to the rear of the vehicle are a series of lightweight banners. By varying the length of the banners and the number of rocket motors, visual cross-section as well as the performance characteristics of the vehicle may be varied. The rocket vehicle may be adapted for firing of the rocket motors in sequence with the time of firing controlled in order to obtain sustained high velocity flight over an extended range or to vary the performance of the vehicle during flight.
228	Temperature discriminating dual igniter rocket ignition system	US3731629D	1971-01-27	US3731629A	1973-05-08	LOMBARDI C
An igniter system for solid propellant type rockets and is designed to ignite the propellant over a wide range of temperature conditions. The system consists of a pair of igniters in circuitry with a power source. A thermostatic switch in the firing circuit acts upon a low temperature condition to permit firing of both igniters and upon high temperature, only one igniter.
229	Arrangement in rockets	US3722413D	1970-09-11	US3722413A	1973-03-27	NARVESEN B; TROEN E
A rocket comprises a head and a firing mechanism including a rod to which a nozzle is secured, a plurality of propellant sticks surrounding the rod and anchored to the head, and the nozzle consisting of a ring and a central hub joined to the ring by a web which defines a number of circumferentially spaced bores, the ring having an rearwardly elongated portion forming at the back of the web an elongated cylindrical space and igniter means mounted in said space.
230	Missile	US3684215D	1970-05-28	US3684215A	1972-08-15	JACOBSON GUNNAR; OLSSON OLOF BERTIL
The invention concerns a missile, in particular a guided missile, having stabilizing wings and a solid fuel propulsion motor. The fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile. The portion of the interior of the missile between the two fuel charges consists of an empty space, into which the fuel charges deliver their combustion gases and which is surrounded by an annular member forming the external shell of the missile between the two fuel charges and comprising the jet nozzles for the propulsion motor. The two fuel charges have such relative sizes and locations in the missile that their common gravity center coincides substantially with the total gravity center of the missile. The stabilizing wings are attached to the annular member comprising the jet nozzles and are located circumferentially between said jet nozzles.
231	Ablative structures	US3633631D	1967-09-27	US3633631A	1972-01-11	HATCH DONALD MONROE; WOOD WALTER W
Ablative structures are prepared by laying up panels of at least two dissimilar high-temperature resistant materials impregnated with a thermally curable resin so that the panels are at least partially interleaved and curing the resin and densifying the structure under increased temperature and pressure conditions.
232	Rocket-assisted projectile or gun-boosted rocket with supported propellant grain	US3628457D	1968-12-24	US3628457A	1971-12-21	MAGNUSSON INGEMAR ARNOLD; MARKLUND PER TAGE; BRODDNER SVEN MALTE; AX LARS; ANDERSSON ROBERT BERT
A rocket-assisted projectile having a central supporting tube surrounded by an annular propellant charge, with an annular space between the tube and propellant decreasing in width towards the rear of the projectile. The axial length of the propellant charge is less than that of the chamber containing the propellant to permit elastic deformation of the propellant in the axial direction.
233	Rocket projectile cartridge	US3601056D	1969-10-03	US3601056A	1971-08-24	NICHOLSON MORRIS ROGER
A rocket projectile cartridge in which an ejector groove is provided on the rear of the cartridge for ejecting a faulty round. All of the propellant, the firing pin and primer are contained within the cartridge and move outwardly therewith as the cartridge is fired. The firing of the cartridge is accomplished by (a) the closing of the breach bolt in an open bolt weapon, (b) striking by a hammer contained in the breach block, or (c) the rearward movement of a barrel assembly against a stationary or semifloating breach block.
234	Armor piercing rocket	US3566793D	1968-09-27	US3566793A	1971-03-02	KRUZELL GEORGE R
An armor piercing rocket-type projectile having a drill-type penetrator embedded within the forward nose portion thereof so that upon impact the penetrator is driven forward from the projectile, into the target and displaces material as it moves therethrough.
235	Armor-piercing ammunition	US3561363D	1968-07-09	US3561363A	1971-02-09	BIRKIGT LOUIS
The ammunition comprises an armour-piercing shell whose body is constituted of a material which is basically a metal that oxidizes easily and that burns by heating. An axial passage is provided, in the body of the shell thus constituted, extending from the front end of the shell to a nozzle formed in the rear end of the shell. Ignition means are provided for causing, in the initial phase of the flight of the shell, the inflammation of the inner wall of the axial passage which, from that moment, behaves like a ramjet playing the role of an auxiliary propeller for the shell.
236	Small arms weapon	US3546997D	1965-02-11	US3546997A	1970-12-15	GOULD BERT B; BIEHL ARTHUR T; MAINHARDT ROBERT; BARTON WILLIAM D

237	Method of making a rocket nozzle	US3490121D	1967-07-13	US3490121A	1970-01-20	BIEHL ARTHUR T; MAINHARDT ROBERT

238	Visual target for retrofire attitude control	US3439886D	1968-09-26	US3439886A	1969-04-22	JOHNSON CALDWELL C

239	Self-propelled hollow charge having concave liner with propellant contained therein	US3439613D	1965-03-08	US3439613A	1969-04-22	THOMANEK FRANZ RUDOLF

240	Miniature rocket nozzle	US3437289D	1967-07-13	US3437289A	1969-04-08	BIEHL ARTHUR T; MAINHARDT ROBERT

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