Cannon recoil inhibitor and impulse noise attenuator
Openings in a muzzle brake provide recoil inhibition and impulse noise attenuation by redirecting the propellant gases to the external environment. A turning vane aggressively turns and redirects the propellant gases in a rearward direction to counter the recoil of the weapon system. An angled baffle provides a physical barrier to redirect propellant gases rearward to provide additional force to counteract the recoil force. Attenuation slits mitigate blast overpressure by producing a fluid barrier of high velocity propellant gases directed radially away from the muzzle brake. The fluid barrier from the attenuation slits interacts with the redirected propellant gas from the turning vane and the angled baffle and redirects the counter recoil gases away from the crew.
1. A muzzle brake for providing blast attenuation and recoil reduction on an artillery cannon, the muzzle brake comprising:
a body defining a supersonic flow passage;
a blast overpressure attenuation flow stage for redirecting propellant gas from the interior of the muzzle brake to the exterior of the muzzle brake substantially normal to the muzzle brake to produce a fluid barrier and further comprising a first attenuation slit and a second attenuation slit defined by the body and extending from an interior surface of the body to an exterior surface of the body and wherein the first attenuation slit and the second attenuation slit are diametrically opposed to each other and confined to a right side of the muzzle brake and a left side of the muzzle brake and wherein the fluid barrier normal to the muzzle brake is produced through deceleration and turning of the propellant gas via formation of a shock within the first attenuation slit and the second attenuation slit;
a gas redirection flow stage axially forward of the blast overpressure attenuation stage and further comprising a first turning vane and a second turning vane defined by the body and extending from an interior surface of the body to an exterior surface of the body, the first turning vane and the second turning vane being diametrically opposed to each other and axially aligned with the first attenuation slit and the second attenuation slit and confined to a right side of the muzzle break and a left side of the muzzle brake, wherein each of the first turning vane and second vane redirects propellant gas from the interior of the muzzle brake to the exterior of the muzzle brake in a direction opposing a recoil force on the cannon through deceleration, turning and reacceleration of the propellant gas via formation of a shock within the first turning vane and the second turning vane; and
an angled baffle stage axially forward of the gas redirection flow stage and comprising an angled baffle defined by the body and extending from an interior surface of the body to an exterior surface of the body which redirects propellant gas from the interior of the muzzle brake to the exterior of the muzzle brake in a direction opposing a recoil force on the cannon by presenting a physical impediment to the propellant gas; and
wherein the fluid barrier interferes with the propellant gas redirected by the gas redirection flow stage and the angled baffle stage thereby minimizing blast overpressure.
2. The muzzle brake of claim 1 wherein the first attenuation slit and the second attenuation slit extend from the interior surface to the exterior surface at an obtuse angle with respect to a central longitudinal axis of the muzzle brake such that propellant gas from the interior of the muzzle brake is redirected to the exterior of the muzzle brake substantially normal to the muzzle brake to produce a fluid barrier.
3. The muzzle brake of claim 1 wherein the first attenuation slit and second attenuation slit each extend along the circumference of the muzzle brake body at a radial angle at least equal to a radial angle of the first turning vane and the second turning vane.
4. The muzzle brake of claim 1 wherein an output of the gas redirection flow stage is approximately one caliber axially forward of an output of the blast overpressure attenuation flow stage.