According to an aspect of the invention, there is provided a mortar bomb, comprising: a main body; a nose; a tail extending from the main body, away from the nose; an obturating ring groove for accommodating, in use, an obturating ring, the ring groove being located in the main body; wherein a maximum diameter of the main body is upstream of the ring groove, toward the nose.

The disclosure of the present invention relates to an archery broadhead air flow interrupter or an attachment for a broadhead point configured to create a turbulent low pressure zone around the cutting blades, prevent broadhead planing, and improve the accuracy of a broadhead archery point.

An assembly (2) for attachment to a projectile comprises a first part (4) and a second part (6) mounted for rotation relative to the first part (4) about an axis (A). There is an axial gap (G) between the first and second parts (4, 6). At least one plastically deformable element (34) is arranged within the gap (G) between the first and second parts (4, 6), the plastically deformable element (34) being such as to deform due to the closing of the axial gap (G) between the first and second parts (4, 6) during launch of the projectile.

The present invention relates to a projectile including a body having a longitudinal axis and an intermediate portion comprising a wing or fin deployment device including at least a number N, at least equal to three, of wings or fins able to be deployed, the deployment method comprising at least two phases, a first deployment phase in which each wing or fin switches from a position tangential to the body of the projectile and parallel to the longitudinal axis to a semi-deployed position, and a second deployment phase with the switching of each wing from the semi-deployed position to a deployed position in which it is perpendicular to the body of the projectile, said wing deployment device is configured to synchronize the deployment of wings or fins in the second phase.

An assembly and method for assembling a projectile with a compact low friction high temperature shaft seal is provided. The assembly includes an outer shell, a rotating shaft inside the outer shell, and a seal attached to the rotating shaft. The rotating shaft can rotate independently of the outer shell. The seal can seal a gap between the outer shell and the rotating shaft.

An assembly and method for assembling a projectile with a compact low friction high temperature shaft seal is provided. The assembly includes an outer shell, a rotating shaft inside the outer shell, and a seal attached to the rotating shaft. The rotating shaft can rotate independently of the outer shell. The seal can seal a gap between the outer shell and the rotating shaft.

A system can include a spinning structure configured to spin in operation, and at least one mass operatively connected to spinning structure to rotate about a spin axis with the spinning structure. The at least one mass can be configured to be moved relative to the spinning structure during a spin of the spinning structure. The system can include an actuation system configured to move the at least one mass relative to the spinning structure. The actuation system can be configured to move the at least one mass while the spinning structure is spinning to use the spin of the spinning structure to induce a precession torque on the spinning structure. The actuation system can be configured to synchronize actuation motion of the at least one mass to the spin of the spinning structure such that the induced precession torque is in a desired direction.

Launch vehicles with ring-shaped external elements, and associated systems and methods. An aerospace system in accordance with a particular embodiment includes a launch vehicle having a first end and a second end generally opposite the first end, with the launch vehicle being elongated along a vehicle axis extending between the first and second ends, and having an external, outwardly facing surface. The system can further include an annular element carried by the launch vehicle, the annular element having an external, inwardly-facing surface radially spaced apart from, and extending at least partially circumferentially around, the vehicle axis. The annular element can have a first edge surface facing a first direction along the vehicle axis, and a second edge surface facing a second direction along the vehicle axis, the second direction being opposite the first direction. A propulsion system can be carried by the launch vehicle, and can have at least one nozzle positioned toward the first end of the vehicle to launch the vehicle. A controller can be in communication with the launch vehicle and programmed to direct the vehicle in the first direction during vehicle ascent, and in the second direction during vehicle descent.

A projectile includes a body having rotationally axial symmetry; and a meplat at a tip end of the body. The meplat includes a flat portion defined by a plane that intersects the projectile perpendicularly with respect to a central axis through a lengthwise direction of extension of the projectile, and a chamfered portion defined by a chamfer cut extending from an outer perimeter of the flat portion toward an outer surface of the body.

A projectile includes a body having rotationally axial symmetry; and a meplat at a tip end of the body. The meplat includes a flat portion defined by a plane that intersects the projectile perpendicularly with respect to a central axis through a lengthwise direction of extension of the projectile, and a chamfered portion defined by a chamfer cut extending from an outer perimeter of the flat portion toward an outer surface of the body.