An ordnance for air-borne delivery to a target under remotely controlled in-flight navigation. In one embodiment, self-powered aerial ordnance includes upper and lower cases. A plurality of co-axial, deployable blades is powered by a motor positioned in the upper case. When deployed, the blades are rotatable about the upper case to impart thrust and bring the vehicle to a first altitude above a target position. An explosive material and a camera are positioned in a lower case which is attached to the upper case. The camera generates a view along the ground plane and above the target when the ordinance is in flight. When the vehicle is deployed it is remotely controllable to deliver the vehicle to the target to detonate the explosive at the target. The ordnance may drop directly on a target as a bomb does.

A flight vehicle engine includes an isolator with a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

A flight vehicle engine includes an isolator with a swept-back wedge to improve flow mixing. The wedge includes forward shock-anchoring locations, such as edges or rapidly-curved portions, that anchor oblique shocks in situations where the isolator has sufficient back pressure. The swept-back wedge may also create swept oblique shocks along its length. Boundary layer flow streamlines are diverted running parallel to or parallel but moving outward conically to the swept-wedge leading edge moving outboard and upward. The non-viscous flow outside the boundary layer is processed through the swept-back ramp shock and diverted outboard and upward as well. The outboard aft portion of the wedge at the sidewall intersection may also induce shocks and divert flow near the walls closer toward the walls and upward, and/or improve flow mixing.

A projectile launching system can include a projectile launcher and a projectile. The projectile launcher can include at least one barrel, a projectile, a firing pin mechanism, an activator, and a power system. The barrel can extend along a longitudinal axis between first and second ends, with an exit port at the second end. The projectile can be positioned in the barrel and include primer, propellant, and a sub-projectile. The firing pin mechanism can be selectively project into the barrel to engage the primer, whereby the propellant is ignited and the projectile is launched out of the barrel. The activator can be engaged with the firing pin mechanism and engageable by a user to control the firing pin mechanism. The power system can rotate the barrel or the projectile as the firing pin mechanism is projecting into the barrel and engaging the primer of the projectile.

A uniform projectile casing which is utilized for projectiles with different ranges. A projectile of relatively short range can in this case be optimized with regard to payload, whereas a projectile with the relatively long range is subjected to a range optimization, with a reduction in payload. The payload of a projectile of relatively long range is generally lower in relation to a projectile with relatively short range. The artillery projectiles have a projectile casing of equal size for the projectiles of different range. To create an artillery projectile, for example 155 mm, a uniform payload-optimized 30 km projectile casing) is used, from which 40 km projectiles can be generated (produced, assembled) by means of a reduction in payload. The range is selected and defined by mutually different projectile bases. The artillery projectile has multiple modular parts which are assembled in order to create the artillery projectile.

In one embodiment, a less lethal munition including a ring airfoil projectile. The flight trajectory of the projectile has increased accuracy resulting from the aerodynamic stabilization of the projectile. In some embodiments, the projectile is both aerodynamically stabilized and spin stabilized.

In one embodiment, a less lethal munition including a ring airfoil projectile. The flight trajectory of the projectile has increased accuracy resulting from the aerodynamic stabilization of the projectile. In some embodiments, the projectile is both aerodynamically stabilized and spin stabilized.

Projectile launch apparatus (20) for use in a fluid environment. The apparatus (20) comprises a launch tube (21) having a supercavitating projectile (24) with cavitator (29) received within the launch tube (21). A means for generating expulsion gas (not visible) is arranged to provide expulsion gas to propel the projectile (24) from the launch tube (21), with means for bleeding expulsion gas (31, 32) being provided to bleed a portion of expulsion gas around the projectile (24). This allows expulsion gases to contribute to the formation of the gas cavity around the supercavitating projectile (24) as the projectile (24) is launched from the launch tube (21). Particularly suited to the deployment of supercavitating projectiles underwater, such as in underwater mine disposal applications.

Projectile launch apparatus (20) for use in a fluid environment. The apparatus (20) comprises a launch tube (21) having a supercavitating projectile (24) with cavitator (29) received within the launch tube (21). A means for generating expulsion gas (not visible) is arranged to provide expulsion gas to propel the projectile (24) from the launch tube (21), with means for bleeding expulsion gas (31, 32) being provided to bleed a portion of expulsion gas around the projectile (24). This allows expulsion gases to contribute to the formation of the gas cavity around the supercavitating projectile (24) as the projectile (24) is launched from the launch tube (21). Particularly suited to the deployment of supercavitating projectiles underwater, such as in underwater mine disposal applications.

A projectile (10) for firing from a barrel (12) of a firearm has an elongated tubular body (14) with a leading end (16), a trailing end (18) and a passage (100) extending through the body (14) and opening onto the leading end (16). An insert (102) is disposed in the passage (100). A cavity (20) is formed in the body (14) between the insert (102) and the trailing end (18) for holding a volume of propellant. A seal arrangement (22) is formed on the body (14) and located between and in-board of the leading end (16) and the trailing end (18). The seal arrangement (22) extends circumferentially about body to form a substantial seal against an inner circumferential surface of the barrel (12). A driving band (28) is supported on the body (14) between the seal arrangement (22) and the trailing end (18) and arranged to maintain substantial coaxial alignment of the body (14) of the projectile and the barrel (12) of the firearm while the projectile travels along the barrel (12). The driving band (28) has one or more flow paths (38) that enable fluid communication between opposite axial ends of the driving band (28).