专利检索_ ..被用于平衡后坐的反向射弹专利检索_ ..被用于平衡后坐的反向射弹专利检索查询

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
61	Countermass for recoilless weapons	US916088	1992-07-29	US5285713A	1994-02-15	Anders N. Brage
A countermass for recoilless weapons which is intended to be placed behind the projectile propelling charge (3) of the weapon and which is also intended to depart together with the propellant gases exiting rearwardly from the weapon when the projectile is propelled forwards. The countermass includes a countermass body (5) which is deformable at the pressure and the temperature prevailing in the barrel during firing of the projectile and which has at least one gas through flow passage (6) which widens rearwardly in nozzle form.
62	Recoilless launching device	US749002	1985-06-26	US4643071A	1987-02-17	Theodor Baechler; Josef Amann
The countermass of a recoilless launching device is composed of a combustible material and has a firing connection with the working space in which the propellant charge burns up.
63	Propellant charge for recoilless weapons	US423086	1973-12-10	US4172420A	1979-10-30	Alfred Voss; Heinz Kroschel; Manfred Strunk
Propellant charge device for recoilless weapons of the type having a barrel open at both ends with the propellant charge device being positioned behind a projectile and insertable into the front end of the barrel. The propellant charge device includes an elongated casing having a powder charge portion, a cavity portion and a tamp portion axially sequentially arranged within the casing and extending from the front to the rear thereof. The casing has a length such that it extends within the barrel of the weapon from the position thereof behind the projectile substantially over the entire length of the barrel.
64	Expellable reaction mass for recoilless projectile launchers	US809677	1977-06-24	US4132148A	1979-01-02	Rolf Meistring; Karl Rudolf; Werner Schmid; Fritz Zeyher
A reaction mass for a launching tube having a centrally positioned propellant charge for propelling a missile at its forward end and a reaction mass located rearwardly of the propellant charge which is propelled at the rear end, comprises an inert, readily fragmentizing, expellable reaction mass comprising a glass material which is internally prestressed and which disintegrates at the launch. The reaction mass is advantageously in the form of a glass cylinder which is either connected to a metallic pusher member arranged rearwardly of the propellant charge which is pushed by the ignition of the charge in a rearward direction, or it may comprise a glass cylinder which includes its own pusher head formation. The pusher itself is arrested by a brake positioned at the rear exit. In addition, the rear exit is closed by a diaphragm which may shatter after ignition of the propellant charge. The reaction mass may also comprise a front pusher face which is engaged with a rear brake positioned at the rear opening or it may comprise a plurality of layers of glass held to a pusher head which is arrested at the rear opening. In still another embodiment, the glass may comprise a plurality of flat discs held together in an assembly to a pusher member.
65	Assembly for launching a projectile	US683001	1976-05-04	US4050351A	1977-09-27	Emile J. Stauff
An assembly for launching a projectile comprises a launch tube having a smooth or rifled bore, a charge of gunpowder located in the tube for firing a projectile which is placed in the tube in front of the charge, a braking propellant located in the tube behind the gunpowder charge and carrying a ballast material, and means ensuring that the gunpowder charge is ignited before the braking propellant. The braking propellant may be connected to a projectile by means of a sleeve to form a rigid unit which is loadable in the launch tube, the sleeve containing the gunpowder charge.
66	Dual combustion missile system	US610027	1975-09-03	US4012987A	1977-03-22	John E. Burkhalter; Richard H. Sforzini
A missile system with an ogival projectile for operation in a trajectory m a tubular launch tube includes a housing and a slug respectively slidable in the projectile and the housing with the projectile and housing respectively including combustion chambers and pistons enclosing propellant grains therein. The projectile and slug are respectively launched forwardly in the trajectory and rearwardly and the housing is ejected from the projectile responsive to simultaneous ignition of the propellant grains. The piston is ejected from the projectile responsive to continued ignition of the corresponding propellant grain.
67	Recoilless discharge device	US3796128D	1972-05-03	US3796128A	1974-03-12	ZEYHER F
A recoilless discharge device for projectiles includes a discharge tube which is open at both ends and which carries an inert mass which is directed toward one end when a projectile is fired out of the other end. The inert mass advantageously comprises four separate circular sector stacks arranged around the tube and guided longitudinally by radially extending supporting ledges. Each stack comprises relatively thin foil material having a very large surface per unit of mass. The stacks are held together by strings and the stacks are divided easily when they are ejected from the rear tube opening.
68	Reactionless flare-launching apparatus	US3633509D	1969-09-30	US3633509A	1972-01-11	GRANDY ANDREW J; GOLDSTEIN SIDNEY
A reactionless flare-launching apparatus having two spacedapart, frangibly secured together pistons located within an openended elongated tube, is mounted transversely to an aircraft longitudinal axis. Two flares, positioned within the tube outwardly of the pistons, are urged out of the tube away from the aircraft after a predetermined gas pressure, applied in the tube between the pistons, breaks the frangible securing element and permits the pistons and flares to be ejected laterally from the aircraft.
69	Floatable rocket launcher	US37659964	1964-06-19	US3279319A	1966-10-18	SEMONIAN JOSEPH W; PURSEL GARY T

70	Nonrecoil gun	US74444334	1934-09-17	US2156605A	1939-05-02	LYMAN PRETTYMAN GEORGE WILLIAM

71	Fixed ammunition for non-recoil guns.	US23656818	1918-05-25	US1311021A	1919-07-22	SPEAR LAWRENCE Y; DAVISON GREGORY C

72	Non-recoil ordnance.	US18317517	1917-07-27	US1280579A	1918-10-01	SHUKER WILLIAM

73	Apparatus for firing projectiles from air-craft.	US1913777763	1913-07-07	US1108716A	1914-08-25	DAVIS CLELAND

74	COUNTERMASS LIQUID FOR A SHOULDER LAUNCHED MUNITION PROPULSION SYSTEM	US15507476	2017-02-27	US20180347923A1	2018-12-06	Dominic Jezierski; Jerry Lambert; Harry Blomquist; Stephen Joseph Early; Bill Goodwin
A countermass liquid for a shoulder launched propulsion system that has low corrosivity, high density, low viscosity, and a constant viscosity as a function of temperature. Upon function of the shoulder launched propulsion system, the countermass liquid may be expelled through the breach end of the shoulder launched propulsion system by expanding propellant gas. The countermass liquid may be an organic salt selected from the group consisting of at least one or more of cesium formate and potassium formate.
75	HIGH ALTITUDE SPACE LAUNCHER	US15869334	2018-01-12	US20180134414A1	2018-05-17	ABBAS ALIKOUHI
Disclosed is a high altitude space launcher system for transferring payloads from surface to orbit at a significantly lower cost than conventional rockets. It comprises a aerostat lifted one stage light gas gun operating in stratosphere that shoots rocket assisted projectiles containing payload at near orbital velocities to a low angle trajectory. Alternatively, to launch acceleration sensitive payloads such as astronauts the light gas gun is replaced with a muzzle loaded conventional gun that shoots a single stage rocket at a much lower velocity. The system is mostly static structure, attached to a tether-elevator that moors it to land or a ship and provided it with electricity and lifts the projectiles to the gun.
76	Method and device for improving countermass-based recoil control in projectile launchers	US14059002	2013-10-21	US09631882B2	2017-04-25	Kevin Paul Grant
A recoil controller is disclosed whose body 1 incorporates a strategically designed inner surface or surfaces 2. A moving countermass 6 impacts one or more times against one or more inner surfaces 2. During this process momentum is transferred from the countermass 6, to the inner surfaces 2, and then to the body 1 of the recoil controller, and then to anything to which it is attached or against which it is braced. The distributions, over time, of the momenta resulting from this transfer of momentum will depend on various factors including the composition, geometry and placement of the inner surfaces 2. A given recoil controller is designed such that the distributions, over time, of the momenta resulting from its use, are preferable to the distributions, over time, of the original momenta. The countermass 6′ shown in FIG. 1 is the countermass 6 shown after one impact.
77	Gas powered fluid gun with recoil mitigation	US15004666	2016-01-22	US09534879B1	2017-01-03	Mark C. Grubelich; Gerold Yonas
A gas powered fluid gun for propelling a stream or slug of a fluid at high velocity toward a target. Recoil mitigation is provided by a cavitating venturi that reduces or eliminates the associated recoil forces, with minimal or no backwash. By launching a quantity of water in the opposite direction, net momentum forces are reduced or eliminated.
78	Gas compensated recoilless liquid disrupter	US14831953	2015-08-21	US09534864B2	2017-01-03	Rudra Kinkar Dey
The method of controlling recoil in a disrupter comprises: providing liquid in a liquid chamber of the disrupter, the liquid chamber having a front nozzle for expelling the liquid therethrough; providing combustible propellant in a propellant chamber of the disrupter that communicates with the liquid chamber and that has a rear nozzle for expelling combustion gases therethrough; providing a bather between the liquid and the propellant to avoid admixing both; and igniting the propellant to generate expanding combustion gases that will expel the liquid out of the disrupter through the front nozzle in a first direction, either rupturing or propelling the barrier in the process, the combustion gases exhausting out of the disrupter at least partly through the rear nozzle in a second direction, with the first and second directions being at least partly opposite one another to control the recoil of the disrupter.
79	Bleeding mechanism for use in a propulsion system of a recoilless, insensitive munition	US14276240	2014-05-13	US09441894B1	2016-09-13	Leon Moy
A bleeding mechanism for use in the propulsion system of a recoilless, insensitive munition utilizing a utilizing a fluidic countermass. The present bleeding mechanism utilizes a firing pin or a similar puncture or tear device. A heat sensitive material blocks the movement of the firing pin. A mechanical locking mechanism locks the firing pin in position until it is unlocked by the melting of the heat sensitive material. When the insensitive munition is exposed to heat, the reaction of the heat sensitive material within the bleeding mechanism allows the firing pin to be released and to rupture a cartridge seal. The cartridge may be filled with a compressed compound, which releases gas under pressure to the countermass container, causing a countermass cover to rupture, thereby emptying the countermass fluid.
80	GAS COMPENSATED RECOILLESS LIQUID DISRUPTER	US14831953	2015-08-21	US20160169614A1	2016-06-16	Rudra Kinkar Dey
The method of controlling recoil in a disrupter comprises: providing liquid in a liquid chamber of the disrupter, the liquid chamber having a front nozzle for expelling the liquid therethrough; providing combustible propellant in a propellant chamber of the disrupter that communicates with the liquid chamber and that has a rear nozzle for expelling combustion gases therethrough; providing a bather between the liquid and the propellant to avoid admixing both; and igniting the propellant to generate expanding combustion gases that will expel the liquid out of the disrupter through the front nozzle in a first direction, either rupturing or propelling the barrier in the process, the combustion gases exhausting out of the disrupter at least partly through the rear nozzle in a second direction, with the first and second directions being at least partly opposite one another to control the recoil of the disrupter.

1 2 3 4 5 6 7 8 9

该功能需要专业版企业版VIP权限，您可以：