8results about "Missile propulsion" patented technology

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).

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.

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.

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.

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.