System for maintaining multiple warheads placed in a missile rotating on its longitudinal axis

• US 4,920,887 A
• Filed: 06/03/1988
• Issued: 05/01/1990
• Est. Priority Date: 06/02/1987
• Status: Expired due to Term

• Current Assignee: Thomson-Brandt Armements
• Original Assignee: Thomson-Brandt Armements
• Inventors: Magnaudet, Eric, Frehaut, Jean-Pierre, Pineau, Jean-Pierre
• Primary Examiner(s): TUDOR, HAROLD JAY
• Application Number:
  US07/201,853
• Time in Patent Office: 697 Days
• Field of Search: 102/340, 102/342, 102/351, 102/357, 102/377, 102/378, 102/393, 102/473, 102/489, 102/505
• US Class Current: 102/489
• CPC Class Codes: F42B 12/62 the submissiles being ejected parallel to the longitudinal axis of the projectile
• CPC Class Codes: F42B 14/06 Sub-calibre projectiles having sabots; Sabots therefor
• CPC Class Codes: F42B 14/065 Sabots carrying several projectiles

Abstract

Disclosed is a system for the holding of multiple warheads, placed in a missile rotating on its longitudinal axis and dropped in trajectory through an end of the missile. Each stage of the warhead includes at least two distinct parts which have to be separated laterally at the moment of dropping, the missile including a casing inside which the warhead is placed. For each stage, mechanisms to fix the parts at the said stage are arranged so that each stage forms a compact unit so as not to cause major radial stresses against the casing due to the centrifugal force created by the rotating missile. The fixing mechanisms are retractable at the moment when the parts are dropped, by means of inertia blocks that are subjected to the centrifugal force. The invention can be applied to sub-munitions and mortar shells.

Claims

1. A system for holding a payload consisting of multiple warheads, placed in a missile, that rotates on its longitudinal axis, and dropped, in trajectory, through an end of said missile, said payload comprising:

at least one stage, which includes at least two distinct parts which have to be separated at the moment of dropping,

said missile comprising a casing within which the said payload is placed, said system comprising, for each stage, means for fixing the parts of said stage so that each stage forms a compact unit so as to make longitudinal translation in said casing of said payload easier and with lower stress, said fixing means being retractable at the moment when the parts are dropped; and

means connected to said fixing means for ejecting said fixing means.

2. A system according to claim 1 wherein said fixing means comprises a plurality of U-shaped sections each of which comprise U-brackets, placed around each stage for forming a compact unit, and comprising at least two fixing sides, each of said sides entering a peripheral hollow corresponding to one of the said parts, said U-brackets including means for holding parts of one and the same stage before dropping operation.

3. A system according to claim 2 wherein said U-brackets are held by the casing before the dropping operation and are spread out during the dropping operation by the centrifugal force so as to detach the U-brackets from said parts of one and the same stage.

4. A system according to claim 3 wherein the means for the ejection of said U-brackets comprise, for each U-bracket, an inertia block which is rigidly fixed to a corresponding U-bracket, at an end portion of said U-bracket for being removed from the casing after a corresponding U-bracket, and then being subject it to centrifugal force due to its mass.

5. A system according to claim 3 wherein the means for the ejection of said U-brackets comprise, for each U-bracket, an inertia block having a ring shaped groove which is deep enough to enable a projecting ring-shaped part of said U-bracket to penetrate said groove so as to be removed from the casing after removal of its a corresponding U-bracket, so as to store kinetic energy due to rotation during outward travel, and to then separate the U-bracket from parts held thereby before the dropping operation.

6. A system according to claim 2 wherein the U-brackets have fixed sides joined to each other by a central part which has a dovetail shape.

7. A system according to claim 1 wherein each stage consists of a central sub-munition, placed coaxially along the longitudinal axis of the missile, and of a plurality of ties that surround said sub-munition and are held in place by the U-brackets.

8. A system according to claim 7 wherein, in each stage, the sub-munition is only partially surrounded along its length by the ties of its corresponding stage and is partially surrounded by the ties of the adjacent stage.

9. A system according to claim 4 wherein said inertia blocks of the U-brackets have a continuous circular ring shape.

10. A system according to any of the claim 1 wherein the parts constituting said stage are placed in bundles inside the casing.

11. A system according to claim 4 wherein the inertia blocks form a support for the sub-munition.

12. A system according to claim 11 wherein on the last sub-munition, the section of the inertia block forming the support of the sub-munition has its extension on the casing enabling a reduction in stresses on the casing upon firing.