A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

A pivot connection part for a flying machine includes an inner body, an outer body radially surrounding the inner body, and a set of connection elements configured to connect the inner body to the outer body. Breaking the connection elements detaches the inner body from the outer body. A first blocking assembly having a cam and a stop is configured to block relative rotation between the inner and outer bodies in a first rotational direction. A second blocking assembly having a pawl and a resilient stop blade is configured to block relative rotation between the inner and outer bodies in a second rotational direction.

A rocket in one example includes separate chambers for storing two thrust grains: an initial thrust grain and a boost thrust grain. The initial thrust grain is stored in a first chamber and the boost thrust grain is stored in a second chamber. The initial thrust grain is ignited separately from the boost thrust grain, such as in a two-stage process where the initial thrust grain is ignited before, or at the same time as, the boost thrust grain. The initial thrust grain has a large surface area (different burn pattern) relative to the boost thrust grain, which causes the initial thrust grain to have a shorter burn time than the boost thrust grain.

A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.

A cover 10 and method for protecting a missile 15 with stowed wings 20 and connected to a vessel carrying it. The cover 10 includes a spoiler shaped front part 25 for covering a gap between the wings 20 of the missile 15 and the fuselage of the missile 15 for minimizing aerodynamic forces.

A tail portion for a fin-stabilized projectile includes at least two deployable fins, which are inclined. The fins are arranged in at least two sections, which are arranged adjacent to another in the axial direction.

A tail portion for a fin-stabilized projectile includes at least two deployable fins, which are inclined. The fins are arranged in at least two sections, which are arranged adjacent to another in the axial direction.

The present invention is directed to a projectile configured to provide a submunition payload across a wide impact pattern, similar to that of a shotgun, at a range typically beyond the capability of standard shotgun rounds. The additional range is provided in some embodiments of the invention by allowing the tailoring deployment range of the submunition payload based upon a given threat.

The present invention is directed to a projectile configured to provide a submunition payload across a wide impact pattern, similar to that of a shotgun, at a range typically beyond the capability of standard shotgun rounds. The additional range is provided in some embodiments of the invention by allowing the tailoring deployment range of the submunition payload based upon a given threat.

Provided is a non-motorized flying unit. The non-motorized flying unit includes a body part having a head part and a tail part having an accommodation space and a through hole, an image capturing unit installed in the through hole and configured to obtain an image information, a protective window installed in the through hole, a plurality of shock absorbing devices installed at the end portion of the tail part, a weight installed at the end portion of the tail part, and a lighting device installed at an end portion of the plurality of shock absorbing devices. A propulsion unit which is detachably coupled to the tail part storing a propellant which, upon combustion, forms pressure in the propulsion unit to provide thrust to the body part.