29results about "Missile propulsion" patented technology

A ram accelerator for accelerating a projectile is provided. The ram accelerator includes a baffle section configured to start the projectile in the ram accelerator without an obturator. The ram accelerator generally includes a tube having a projectile bore; and a baffle section operably coupled to a proximal end of the tube. The baffle section has an annular baffle wall defining a central bore axially aligned with the projectile bore; and a propellant chamber arranged adjacent to the annular baffle wall, wherein the propellant chamber is configured to enclose a propellant. The propellant can be ignited as the projectile passes through the baffle section by pressure created by the projectile, by an ignition source, or by a flame carried by the projectile to start the ram acceleration of the projectile.

The present invention belongs to the field of power launch experiments, and specifically relates to a gas ejection experimental device. It comprises a pressure chamber, a rear flange, a gas-sealing sleeve, a launch tube, a front head, a sensor fixing base, a barrel ferrule, and a dummy projectile, which are arranged in sequence. The pressure chamber is connected to the rear flange via a flange, the gas-sealing sleeve is placed in the launch barrel in the manner of a piston, and the rear flange and the launch tube, as well as the launch tube and the front head, are connected via threads. The present invention can experimentally measure the ejection internal ballistics by installing different charge gas generators in the pressure chamber. By varying the length of the engine growth tube, the internal ballistic characteristics under different low-pressure chamber initial volumes can be obtained. The front head of the present invention is equipped with a sealing tray recovery device, which can effectively improve the pressure release process after ejection, prevent the rapid escape of high-temperature gas, and enhance the concealment of the launch site.

The invention relates to development of an advanced 360-degree projectile launch helmet system, which can launch projectiles (which may be selected from bullets, pellets, tasers, lasers, etc.) from within the helmet without any collateral damage either to helmet or to the person wearing the same. The system can be voice or remote activated and cross counters any recoils that are generated because of the launch of the projectiles.

The present invention relates to a modular launcher (1) for a projectile (100) launched with a propellant charge (10), the projectile (100) being arranged so that a detonator (20) is disposed in a projectile body (50) disposed in the launcher (1) and assembled with at least one propellant charge (10) in the launcher (1). Furthermore, the present invention relates to a method for assembling a projectile in a launcher by using modules.

The invention relates to the weapons industry, in particular to firearms. The firearm comprises a barrel (1) with a muzzle cut (2) and is provided with an external jet engine (9) configured to generate a jet of gases (10) coaxial with the barrel axis beyond the muzzle cut (2) in the direction of firing. The invention also concerns a projectile (6) for a firearm, comprising a cavity (18) containing a flowable substance (19) and one or more channels (20) communicating with the cavity (18) and having outlet openings (22) on an outer surface of the projectile (6). The cavity (18) is provided with a piston (23) capable of rectilinear movement and adapted to receive the impact of gases of the propellant charge (5). According to the invention, the projectile (6) has two alternative configurations. In the first configuration, a surface of the cavity (18) has one or a plurality of spiral -shaped protrusions (24) made along the axis of rotation of the projectile (6) and adapted to interact with the piston (23). In the second configuration, the piston (23) is made as a stepped piston consisting of several cylindrical surfaces of different diameters corresponding to the cylindrical surfaces of the cavity (18).

A cartridge (20) has a cartridge case (22) extending along an axis (500) from a base (104) to a mouth (102) and having an interior. A projectile (24) is mounted in the case. A propellant (26) is contained within the case. The propellant has an annular grain encircling the axis.

An artillery configured to propel a projectile, the artillery comprising a firing mechanism, a barrel, and a helical electromagnetic recoil mechanism. The firing mechanism fires the projectile in a first direction toward a target. The barrel has an open-ended bore that guides the projectile in the first direction. The helical electromagnetic counter recoil mechanism includes an electrical energy source, a stator, and a helical electromagnetic armature. The electrical energy source provides electrical energy when the firing mechanism fires the projectile. The stator and armature generate an electromagnetic force via the electrical energy. The helical electromagnetic armature moves in a second direction opposite the first direction via the electromagnetic force when the firing mechanism fires the projectile in the first direction to minimize recoil of the artillery.

A disruptor barrel assembly 1 comprises a barrel 2 and a compensator 3 for eliminating recoil. The compensator 3 is arranged concentrically around the barrel 2, with the compensator 3 taking the form

A ram accelerator for accelerating a projectile is provided. The ram accelerator includes a first tube body having a first projectile bore, a second tube body having a second projectile bore axially aligned with the first projectile bore, and a baffle positioned between and operably coupling the first and second tube bodies. The baffle can have an annular baffle wall defining a central bore that is axially aligned with the first and second projectile bores, and a chamber arranged adjacent to the annular baffle wall. The chamber can extend radially outward from the central bore and the annular baffle wall can be configured to sweep a combustion wave relative to the projectile to prevent the combustion wave from traveling ahead of the projectile, leading to an unstart mechanism of the projectile in the ram accelerator.

A toy projectile launcher having a housing, a projectile container, a cocking slide, an air piston assembly, a barrel interface section, and a detachable launch barrel is disclosed. The projectile container is adapted to hold projectiles, such as foam darts. The cocking slide can be moved for-ward and backward. When the cocking slide is moved backward the air piston barrel moves backward, and a projectile is moved in front of the air piston assembly. When the cocking slide is moved forward, the projectile is pushed into the barrel interface section by an air nozzle disposed on the front of the air piston assembly. A first airtight seal is formed between the air piston assembly and the rear of the foam dart, and a second airtight seal is formed between the barrel interface section and the detachable launch barrel.

The invention relates to a recoilless apparatus for firing cartridge-based ammunitions comprising a gun barrel (1) and a compensating mass launch tube (2) wherein a projectile is accelerated in one direction inside said gun barrel counterbalanced by a compensating mass accelerated in the opposite direction inside said launch tube thereby minimizing recoil and further providing means of automatic ammunition handling.

The present invention relates to a cartridge for a premix of flammable gas or inert gas with or without propellant powder, making it possible to propel a mobile at speeds of interest, and reusable. More particularly, a case (10) of the cartridge is designed with an optimized geometry integrating two chambers, an upstream chamber (11) and a downstream chamber (12) forming a longitudinal duct with variable section, and in which said duct has a convergent nozzle shape at an outlet of the upstream chamber (11) opening into the downstream chamber (12), and a flared shape at an inlet of the downstream chamber (12) and relative to the outlet of the upstream chamber, said flared shape being capable of generating a turbulent flow of a fluid propelled through the upstream chamber (11) and entering the downstream chamber (12). Advantageously, this geometry will make it possible to increase the combustion speed in the ballistic phase. Figure for the abstract: Fig. 1.

The present invention discloses a composite baffle for recoilless gun rear-jet ammunition and a preparation method thereof. Prepreg layer: a plain square carbon fiber prepreg is thinly coated with modified epoxy resin to obtain a first fiber layer; a unidirectional carbon fiber prepreg tape and a glass fiber prepreg are layered and thinly coated with modified epoxy resin to obtain a second fiber layer; a unidirectional carbon fiber prepreg tape and a carbon fiber prepreg are layered and thinly coated with modified epoxy resin to obtain a third fiber layer; the first fiber layer, the second fiber layer and the third fiber layer are sequentially stacked together from top to bottom to obtain a composite layer; the composite layer is molded and cooled to obtain a composite baffle. The composite baffle prepared by the present invention is dispersed into a plurality of 0.1-0.2 mm fiber sheets under the action of gunpowder gas. The sheets fall when encountering wind resistance during flight and will not pose a threat to the rear personnel.

To obtain a flying object capable of improving propulsion performance and improving guidance accuracy to targets moving at high speeds.SOLUTION: A flying object 1, which corresponds to ground-to-air, ship-to-air, or air-to-air, comprises: a rotary detonation engine 5 with a thrust deflector 6 that controls a thrust deflection angle to change a thrust axis; a pulse detonation engine 7 with a plurality of nozzles; a seeker 2 that obtains tracking information of a target; an inertial device 3 that obtains inertial information of the flying object 1; and an autopilot 4 that calculates a thrust command and a thrust deflection angle command of the rotary detonation engine 5, which are necessary to correct an error to an expected meeting point with a target on the basis of the tracking information and the inertial information, and a nozzle thrust command of the pulse detonation engine 7, and outputs the commands to the rotary detonation engine 5 and the pulse detonation engine 7.SELECTED DRAWING: Figure 10

The present invention relates to a disruptor barrel assembly comprising a barrel (2) and a compensator (3). The compensator is arranged concentrically around the barrel, with the compensator taking the form of an annular chamber fluidly connected to the interior of the barrel by way of one or more holes (7).

The present invention relates to a disruptor barrel assembly comprising a barrel (2) and a compensator (3). The compensator is arranged concentrically around the barrel, with the compensator taking the form of an annular chamber fluidly connected to the interior of the barrel by way of one or more holes (7).

Techniques are disclosed for automatic detection and analysis of firearm discharge. An apparatus includes at least one processing device configured to obtain first sensor data from a first set of sensors associated with a firearm and to obtain second sensor data from a second set of sensors associated with a subject. The processing device is also configured to detect, based on a first portion of the first and second sensor data, potential discharge events for the firearm. The processing device is further configured to identify, based on a second portion of the first and second sensor data, whether respective ones of the potential discharge events represent actual discharge events. The second portion of the first and second sensor data comprises, for a given potential discharge event, sensor data for a given time period before, during and / or after a given time at which the given potential discharge event is detected.

An automatic recoilless firearm includes a barrel (100, 600) and a compensating mass launch tube (102, 616) in which a projectile is accelerated in one direction within the barrel (100, 600) and is counteracted by a compensating mass accelerated in the opposite direction within the compensating mass launch tube (102, 616) to minimize recoil and further provide for automatic ammunition handling. The firearm also includes one or more bolts (604, 620) and a barrel configured to reduce or eliminate the transfer of momentum and mechanical energy to the barrel and / or the firearm body (610) during operation of the firearm.

The present disclosure relates to a launch system and method. The launch system and method can include at least a preliminary accelerator tube system (PAT) that can be combined with one or more of a main accelerator tube system (MAT), a flight test tube, or a soft catch. The PAT alone or combined with the MAT can be used for launch of a vehicle for testing and / or for delivery of a payload.

Dynamic ram accelerator operation permits operation with lower acceleration, permitting launch of acceleration sensitive payloads such as crewed vehicles. Operational cost is reduced, and reliability improved, by reducing or eliminating internal consumable parts. Relative motion between a projectile and propellant at entry to the ram accelerator enables initial ram combustion at relatively lower velocity. Valves may maintain separation between sections within the ram accelerator that contain different propellant compositions. Timing of valve opening and closing is coordinated to provide conditions suitable for ram combustion. Control over propagation speed of propellant within the system may be obtained using one or more of baffle shape, baffle spacing, propellant temperature, propellant pressure, propellant mixture, temperature of components such as baffles, and so forth. Before the projectile is launched, internal separators between sections are removed, providing an open path to the ram accelerator exit.

This method involves reacting a mixture of hydrazine hydrate and hydroxyethylhydrazine with a nitrate to produce a product mixture containing hydrazine hydrate, hydrazinium nitrate, hydroxyethylhydrazine, and hydroxyethylhydrazinium nitrate, and then distilling the product mixture to produce a final mixture containing hydrazine, hydroxyethylhydrazinium nitrate, and hydrazinium nitrate.

A projectile has a rounded or conical front, a cylindrical body and a base, the base meeting a wall of the cylindrical body at an angle of between 10 and 80 degrees, the base being rounded or conical.

A system which adjusts the muzzle energy of an adjustable velocity accelerator in response to signals from a connected rangefinder or imaging device. Embodiments of the invention may be used to enhance the safety of a less-lethal weapon system by automatically adjusting its muzzle energy to compensate for a target moving closer or further away, or preventing injury to an unintended third party who crosses into the line of fire at close range. The preferred embodiment relates to a portion of an active control system for a coilgun or railgun. Other embodiments may be applicable to precision targeting for defense / military applications, or integrating an identification friend-or-foe (IFF) system in combination with a rangefinder to reduce the risk of friendly fire incidents.

The present invention relates to a magnetic recoil buffer system for a firearm, comprising: a buffer tube ( 1) made of a conductive, non-ferromagnetic material; a magnet (3); a compression spring (9); and a ring made of a magnetic material, preferably a nut (2). The buffer tube (1) has an open end (1A) and a closed end (IB) and comprises an external threaded portion (23) extending from the open end (1A) and is connectable to a firearm frame by means of the external threaded portion (23) at its open end (1A). The magnet (3) is slidably arranged inside the buffer tube (1) between the open and closed ends (1A, IB) to create eddy currents in the buffer tube (1) when the magnet (3) moves inside the buffer tube (1) and to dampen the movement of a bolt and a bolt carrier of the firearm. A compression spring (9) is arranged inside the buffer tube (1) and secured between the closed end (IB) and the magnet (3) to dampen the movement of the magnet (3). The ring is arranged on the outer circumference of the buffer tube (1) to further dampen the movement of the magnet (3) and to magnetically lock the bolt and the bolt carrier or a dynamic breech of the firearm. The present invention relates to a magnetic recoil buffer system for a firearm, comprising: a firearm frame (51), a bolt carrier (52) with a magnet (53), a guide rod (54) with a compression spring (55), a static stopper (56) and a cocking lever with a guide element made of a magnetic material.

A method includes reacting a mixture of hydrazine hydrate and hydroxyethylhydrazine with a nitrate to produce a product mixture that includes hydrazine hydrate, hydrazinium nitrate, hydroxyethylhydrazine, and hydroxyethylhydrazinium nitrate, and distilling the product mixture to produce a final mixture that includes hydrazine, hydroxyethylhydrazinium nitrate, and hydrazinium nitrate.

A paintball marker is provided, comprising: a housing; a combustion chamber defined within the housing; a piston movable within the housing; a bolt driven by combustion within the combustion chamber; a fuel system in fluid communication with the combustion chamber; an oxidizing system in fluid communication with the combustion chamber; and an ignition system configured to ignite a mixture of fuel and oxidizing agent in the combustion chamber, wherein combustion of the mixture drives the piston to actuate the bolt.

A fuel powered paint marker having a first stage and a second stage comprising: a housing; a combustion chamber; a piston; a compression chamber; a fuel system; an oxidizing system; an oxidizing agent; a fuel assembly included in the fuel system; a separation assembly included in the fuel system and separating the oxidizing agent from the fuel assembly in the first stage; a bolt drive system; a fuel nozzle included in the fuel system for injecting fuel into the combustion chamber during the second stage; and, an ignition for igniting the fuel and oxidating agent in the combustion chamber driving the piston forward and compressing a gas in the compression chamber thereby ejecting a projectile wherein the fuel and oxidizing agent are separated during the first stage and mixed in the combustion chamber.

An ejection module for ejecting a projectile includes a module forward end and a module aft end. The module forward end includes a central axis, and a module interface configured for selectively affixing the module to the projectile in a load-bearing manner, and for enabling selective disconnection between the module and the projectile. The module aft end includes a module propulsion system having a plurality of rocket motors and rocket propellant source. Each rocket motor: is laterally spaced with respect to the central axis; has a respective fixed thrust vector non-parallel with respect to the central axis; and is configured for generating a controllable level of respective thrust along the respective thrust vector, independently of the respective level of thrust generated by the other rocket motors along their respective thrust vectors. The module propulsion system is configured for enabling independently controlling the respective level of thrust of each rocket motor.