摘要:
A multi-step separator for a fuze (10) is configured to be mated to an explosive device in a military munition (20), either at a production facility during manufacture of the munition or during use in the field. The fuze (10) includes a detonator with a booster or spit-back element for initiating an energetic sequence resulting in a high-order detonation of the explosive device (20). The multi-step separator includes: (a) a fuze-munition interface device for retaining the fuze (10) in a confined, close relationship with the explosive device (20) and for releasing the fuze (10) when and if it is subjected to an external stimulus that may cause it to detonate the explosive device (20); and (b) a separating device (18) for physically distancing the fuze (10) from the explosive device (20) when and if the fuze (10) is released.
摘要:
The invention relates to a hollow charge which includes: a confinement casing (1); an explosive charge (2) placed in the confinement casing (1) and having a V-shaped surface (2A); a detonator (3) placed behind the explosive charge (2); and a spraying material layer (4) placed in front of the V-shaped surface (2A) of the explosive charge (2). A pyrogenic material layer (10) is used to heat the spray coating (4). Said pyrogenic material can also be mixed with the explosive charge (2). The invention is useful for separating two floors of an aeronautical vehicle or for neutralizing the latter.
摘要:
The invention relates to a submunition (1), in particular luminous munition, that can be discharged from a spin-stabilized carrier projectile and has a submunition body (2) and a parachute housing (3) arranged on the rear side of the submunition body (2) with a main parachute located therein. To achieve the effect that the main parachute is activated when there is a predeterminable spin of the submunition (1), the invention proposes connecting the submunition body (2) and the parachute housing (3) releasably to one another by way of a centrifugal coupling (4) in such a way that the submunition body (2) and the parachute housing (3) are non-positively and/or positively connected to one another by the centrifugal coupling (4) as a result of the centrifugal force occurring when the carrier projectile is fired, and in such a way that the centrifugal coupling (4) releases the connection between the submunition body (2) and the parachute housing (3) after the centrifugal force has subsided to a predeterminable value.
摘要:
- Le missile (1) comprend au moins un étage propulsif (5) séparable et un véhicule terminal (6) qui est agencé à l'avant de l'étage propulsif (5) séparable, ledit missile (1) étant pourvu à l'avant d'une coiffe de protection (2) séparable comprenant au moins deux coques individuelles (3, 4), et d'une pièce de liaison (10A) liée au missile (1), vers l'arrière au-delà de la position (P1) de l'extrémité arrière (11) du véhicule terminal (6), ladite coiffe de protection (2) étant configurée pour, lorsqu'elle est montée sur le missile (1), entourer tout ledit véhicule terminal (6) et étant liée par une extrémité arrière à la pièce de liaison (10A) par l'intermédiaire d'éléments de liaison articulés (7).
摘要:
A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple stage ordnance control system and controlling initiation of an energetic material are also disclosed.